US3768254A

US3768254A - Rocket propulsion method and means

Info

Publication number: US3768254A
Application number: US00208416A
Authority: US
Inventors: D Stuart
Original assignee: Boeing Co
Current assignee: Boeing Co
Priority date: 1962-07-09
Filing date: 1962-07-09
Publication date: 1973-10-30
Anticipated expiration: 1990-10-30

Abstract

15. A rocket comprising, in combination, a housing having an open inlet end portion and an outlet end portion, engine means mounted in said housing and having burner nozzles in a combustion chamber therein and an exhaust portion at said outlet end portion of said housing operable to discharge gases from said combustion chamber therethrough, a liquid hydrogen fuel storage tank positioned within said housing, a liquid air storage tank positioned within said housing, a heat exchanger mounted at said inlet portion of said housing and having an air inlet diffuser portion opening into a relatively narrow air desuperheater portion which in turn opens into an enlarged condenser portion, a plurality of tubes in said condenser portion and said air desuperheater portion of said heat exchanger, inlet headers with the inlet end of said tubes and outlet headers with the outlet end of said tubes, conduit means connected to said hydrogen fuel storage tank and connected to said inlet headers to pass liquid hydrogen fuel therethrough, control means with said last-named conduit means having pressure and temperature pickup means in said air desuperheater portion and said condenser portion of said heat exchanger to regulate flow of said fuel thereto to control pressure and temperature conditions in said air desuperheater portion and said condenser portion of said heater exchanger, conduit means positioned to receive fuel from said outlet headers of said air desuperheater portion and supply said fuel to said burner nozzles in said rocket engine, hydrogen fuel recirculating conduit means connecting said outlet headers of said tubes with the inlet of said hydrogen fuel storage tank, air condensate well means with said condenser portion of said heat exchanger, conduit means connecting said air condensate well with said liquid air storage tank and with said burner nozzles of said rocket engine, means with said liquid air storage tank to separate oxygen from the liquid air and make the same available to said burner nozzles to support combustion of the fuel, conduit means connecting said liquid air storage tank with said last-named means to provide liquid air from said liquid air storage tank thereto, and means in said rocket constructed and adapted to be initially fueled with liquid hydrogen and in flight to receive air from the atmosphere and condense same and separate the nitrogen therefrom to be used as the oxidizer for said hydrogen fuel for burning in said combustion chamber of said rocket engine.

Description

i 1 ROCKET PROPULSION METHOD AND MEANS [75] Inventor: David 0. Stuart, Wichita, Kans.

[73] Assignee: The Boeing Company, Wichita,

Kans.

[22] Filed: July 9, 1962 [21] Appl. No.: 208,416

Primary Examiner-Samuel Feinberg Attorney-1ohn H. Widdowson EXEMPLARY CLAIM 15. A rocket comprising, in combination, a housing having an open inlet end portion and an outlet end portion, engine means mounted in said housing and having burner nozzles in a combustion chamber therein and an exhaust portion at said outlet end portion of said housing operable to discharge gases from said combustion chamber therethrough, a liquid hydrogen fuel storage tank positioned within said housing, a liquid air storage tank positioned within said housing, a heat exchanger mounted at said inlet portion of said housing and having an air inlet diffuser portion opening into a relatively narrow air desuperheater portion which in turn opens into an enlarged condenser portion, a plurality of tubes in said coridenser portion and said air desuperheater portion of said heat exchanger, inlet headers with the inlet end of said tubes and outlet headers with the outlet end of said tubes, conduit means connected to said hydrogen fuel storage tank and connected tosaid inlet headers to pass liquid hydrogen fuel therethrough, control means with said last-named conduit means having pressure and temperature pickup means in said air desuperheater portion and said condenser portion of 7 said heat exchanger to regulate flow of said fuel thereto to control pressure and temperature conditions in said air desuperheater portidn and said condenser portion of said heater exchanger, conduit means positioned to receive fuel from said outlet headers of said air desuperheater portion and supply said fuel to saidburner nozzles in said rocket engine, hydrogen fuel recirculating conduit means connecting said outlet headers of said tubes with the inlet of said hydrogen fuel storage tank, air condensate well means with said condenser portion of said heat exchanger, conduit means connecting said air condensate well with said liquid air storage tank and with said burner nozzles of said rocket engine, means with said liquid air storage tank to separate oxygen from the liquid air and make the same available to said burner nozzles to support combustion of the fuel, conduit means connecting said liquid air storage tank with said lastnamed means to provide liquid air from said liquid air storage tank thereto, and means in said rocket constructed and adapted to be initially fueled with liquid hydrogen and in flight to receive: air from the atmosphere and condense same and separate the nitrogen therefrom to be used as the oxidizer for said hydrogen fuel for burning in said combustion chamber of said rocket engine.

15 Claims, 5 Drawing Figures United States Patent Stuart Oct. 30, 1973 PAIENIEUUCIBO 1913 1,768,254 sum 1 OF 3 v INVENTOR. DAVID O. STUART /#A/' FIG. I

ATTORNEY PATENTEDumao 1915 3 768,254

SHEET- 2 OF 3 INVENTOR. DAVID O. STUART ATTORNEY PATENTEDnmao Tera 3,768,254 SHEET 3 CF 3 I 200* I g F g I '6 3 CH0 lso 8 if 2 l- S 5 AIR DESUPERHEATER I 5 I00 HEAT LOAD I CONDENSER HEAT LOAD o 7 so TIME- sec F G 4 HEAT LOADS AND TEMPERATURE OF COOLANT LEAVING CONDENSER VS TIME COOLANT FLOW RATE WITHOUT RECYCLING LB/HR PER LB/HR FUEL BURNED l-IJ m g 5 ..l COOLANT FLOW RATE WITH RECYCLING 0 5- lo l5 2o 25 TIME-SEC I l l I F g 0 IO 20 5060 ELEVATION I000 FT I COOLANT FLOW RATE vs TIME INYENTOR' F G DAVID o. STUART M ATTQRNEY ROCKET PROPULSION METHOD AND MEANS This invention relates to propulsion. In a more spe cific aspect it relates to method and means for propelling a vehicle, such as a rocket or the like. In still a more specific aspect the invention relates to a rocket or the like vehicle, and to method and means for propelling same, where the oxidizer for the fuel is taken on board and stored during movement of the rocket or the like through the atmosphere. In a still more specific aspect the invention relates to a rocket vehicle, and to method and means for propelling same which includes the production of liquid air and separation of same into fractional components to substantially eliminate the nitrogen portion of the liquid air and provide substantially pure liquid oxygen to engine means for combustion therein with a fuel.

Various types of propulsion method and means are known to the art. The known gas turbine and jet engines are inefiicient in that they require a relatively large expenditure of work to compress air during operation of the engine; Also, propulsion method and means for rockets, space vehicles and the like are also known, however they require the initial storage of a large volume and weight of oxidizer material, usually in the form of a super-cooled liquid such as liquid oxygen or the like, and such increases the lift-off weight of the vehicle to such an extent that greatly increased size and power requirements result for the entire vehicle. No satisfactory method or means are known for propelling a rocket or the like wherein the oxidizer is obtained from the atmosphere during flight and is condensed within the rocket means and subsequently fractionized to remove the relatively large quantities of nitrogen present in the atmospheric air so that liquid air component supplied to the engine means as the oxidizer is substantial-1y free of elements other than oxygen.

In accordance with the vehicle and propulsion means therefor of the present invention, engine means are provided and are cooperatively mountable in rocket means or the like and are operable when mounted therein to drive same. Fuel storage means are mountable in the rocket means and are constructed to receive and store therein a fuel. Condenser means are mountable in the rocket means and operable when mounted therein to receive air from the atmosphere during flight of the rocket means therethrough and to condense the air. Other means are mountable in the rocket means and constructed and operable to fractionate the liquid air from the condenser means into a liquid oxygen fraction and a gaseous nitrogen fraction. Conduit means are connected to the engine means, the fuel storage means and the condenser means to provide fuel and oxygen to burn the fuel in the engine means.

The method of propelling a rocket or the like of the invention includes the steps of receiving atmospheric air during flight, condensing same, and fractionating the resulting liquid air and removing the nitrogen component thereof. The remaining component of the liquid air is transferred to a combustion chamber for oxidation of a fuel therein and the fuel is ignited in the combustion chamber. The resulting exhaust gases are directed from the combustion chamber in one direction to propel the rocket or the like in the opposite direction.

Accordingly, it is an object of this invention to provide new vehicle means.

rocket means.

It is still another object of the invention to provide new method and means for propelling a vehicle such as a rocket or the like.

Another object of the invention is to provide new method and means for propelling a rocket or the like wherein the oxidizer is produced during operation and transferred to a combustion zone for oxidation of the fuel therein and combustion of same.

A further object of the invention is to provide a new method and means for propelling; a rocket or the like wherein air from the atmosphere is condensed during flight of the vehicle and fractionated into a gaseous nitrogen containing fraction and a liquid oxygencontaining fraction with the oxygen-containing fraction being used to oxidize a fuel during burning thereof within a combustion zone.

A further object of the invention is to provide new rocket means or the like wherein the need for storing large volumes and weights of oxidizer in the vehicle at take-off is eleminated.

A further object of the invention is to provide new method and means for propelling a rocket or the like wherein the fuel used for driving the rocket or the like is a low boiling point fuel and which is used for removing heat from atmospheric air during condensation thereof in flight.

Another object of the invention is to provide new rocket means or the like having a relatively low boiling fuel therein for burning in a combustion zone and wherein the fuel is circulated and subsequently recirculated through means for condensing atmospheric air or the like to be used as the oxidizer for the fuel in the combustion zone.

Various other objects, advantages and features of the invention will become apparent to those skilled in the art from the following discussion taken in connection with the accompanying drawings, in which:

FIG. 1 is a longitudinal diagrammatic cross section view through a preferred specific embodiment of the new rocket means of the invention and showing a preferred specific embodiment of propulsion means for rockets or the like of the invention.

FIG. 2 is an isometric view, partially cut away and partially in cross section to show the heat exchanger portion of the propulsion means of the invention as illustrated in FIG. 1.

FIG. 3 is an enlarged partial diagrammatic view illustrating a modified construction of the propulsion means shown in FIGS. 1 and 2.

FIG. 4 is a view illustrating heat loads and temperature of coolant leaving the condenser.

FIG. 5 is a view illustrating the coolant flow rate.

The following is a discussion and description of preferred specific embodiments of the new vehicle means of the invention and method and means of propelling rockets or the like of the invention, such being made with reference to the drawings whereon the same reference numerals are used to indicate the same or similar parts and/or structure. It is to be understood that such discussion and description is not to unduly limit the scope of the invention.

Referring now to the drawings in detail and to FIGS. 1 and 2 in particular a rocket is shown generally at 10 and includes a housing 12 which has a generally cylindrical center portion 14 which is joined at the ends to an integral exhaust end portion 16 having an exhaust opening 17 and an open inlet end portion 18. Preferably a plurality of fins or suitable stabilizing means 20 are secured to the exhaust end portion 16 of the housing 12 and preferably taper from the end portion 16 toward the intermediate portion 14 of the housing 12 with the end portions of the fins 20 nearest the center portion of the housing being in streamlined engagement with the housing 12.

A rocket engine 22 is mounted in housing 12 and is desirably of the type which is constructed to burn a hydrogen or hydrogen-containing fuel therein. The engine 22 has a combustion chamber 24, and a plurality of burner or injector nozzles 26 are positioned to discharge fuel and oxidizing material into the combustion chamber 24. The combustion chamber 24 is preferably generally spherical in shape and opens through a narrow neck portion 28 to an enlarged frusto-conical exhaust portion 30 having the relatively large end portion thereof positioned in spaced relation to the combustion chamber 24 and opening to the atmosphere at the opening 17 of the exhaust end portion 16 of the housing 12. The exhaust portion 30 receives exhaust gases from the combustion chamber 24 and discharges same into the atmosphere, such directing the exhaust gases in one direction to exert an equal and opposite force on the rocket means to cause resultant movement of the rocket means in an opposite direction. The engine means can be of any suitable construction whereby an oxidizer is used.

A liquid hydrogen fuel storage tank 34 is provided and is mountable within the housing 14 in any suitable manner so as to be fixedly positioned therein. Tank 34 has an inlet 36 and an outlet 38 to receive and discharge liquid hydrogen fuel. Tank 34 is preferably constructed to receive and contain the hydrogen fuel when in the liquid state and desirably at a temperature in the neighborhood of 45 R, and preferably the tank 34 is constructed so that little or no heat loss occurs from the tank 34.

A liquid air storage tank 40 is mountable within the housing 14 and is preferably constructed to receive and retain therein liquid air and/or liquid oxygen and maintain same at relatively low temperatures to prevent vaporization thereof. The storage tank 40 preferably has a common inlet and outlet 42 through which the liquid is received and discharged from the tank 40.

A heat exchanger is provided and is shown generally at 44. The heat exchanger is mounted within the housing 12 and includes an air inlet diffuser portion 46 which is preferably frusto-conical in shape as shown and has the relatively large end portion thereof positioned at the open inlet end portion 18 of the housing 12 to receive air from the atmosphere therein during flight of the vehicle and funnel same into a centrally located and preferably elongated air desuperheater portion 48. The desuperheater portion 48 has a throat 50 at the end thereof opposite from the air inlet diffuser portion 46.which opens into an air condenser 52 which is preferably enlarged relative to the air desuperheater portion 48 and can be generally cylindrical in shape as illustrated in FIG. 2.

Means are preferably provided to remove moisture and carbon dioxide from atmospheric air as it passes into the heat exchanger. The means for removing the moisture from the air and the carbon dioxide shown in the drawings includes a plurality of coolant tubes 54 which are positioned across the inlet end of the air desuperheater 48 and desirably extend substantially thereacross as illustrated in FIG. 2. An inlet header 56 is provided and is positioned to be in fluid communication with the inlet end of each of the coolant tubes 54 and a conduit 58 is connected in one end portion to the header 56 and operatively connected in the other end portion to the hydrogen fuel storage tank 34 to provide hydrogen fuel to the tubes 54.

An outlet header 60 is provided and is in fluid communication with the outlet end of each of the tubes 54 and a conduit 62 is connected to the outlet header 60 to receive hydrogen fuel therefrom and discharge same to the engine means. A plurality of fins 64, FIG. 2, are mounted on the tubes 54 and are positioned in spaced relation and provide a relatively large amount of heat transfer surface. The fins 64 are cooled by the passage oflow temperature hydrogen fuel through tubes 54 and water and carbon dioxide in air passing across the fins is frozen on the fins and retained thereon.

Other means for removing moisture and carbon dioxide from the atmospheric air are shown in the drawings, such including a conduit 66 which is connected in one end portion to the liquid air storage tank 40 and is connected in the other end portion to a header 68 adjacent the air desuperheater portion of the heat exchanger. A plurality of conduits or tubes 70 extend from the header 68 and are positioned at the inlet of the air desuperheater and have a plurality of nozzles 72 which in use spray liquid air or liquid oxygen into the air desuperheater. By spraying the liquid air or liquid oxygen into the air desuperheater water and/or carbon dioxide in atmospheric air passing therethrough is frozen and suspended in the air and the air passing therefrom into the center portion of the air desuperheater is substantially dried and free of moisture and carbon dioxide. The tube wall temperature in the heat exchanger is maintained below the condensing temperature of air by circulation of hydrogen fuel therethrough and it has been found that the resulting ice will not adhere to the walls of these low temperatures. The resulting ice can be collected in a well in the condenser 52 and discharged from the vehicle.

The use of suitable means to remove moisture and carbon dioxide from the air is quite desirable. In the absence of such means ice could form on the tubes in the air desuperheater and/or condenser portions of the heat exchanger and would greatly reduce the heat transfer coefficients and could result in an insufficient amount of heat transfer surface. Also, ice could form in such a manner as to block air flow in the heat exchanger.

Means are provided in the air desuperheater portion 48 of the heat exchanger to cool atmospheric air passing therethrough. Preferably, air cooling means is provided by a plurality of passes of coolant tubes 76 which are preferably positioned with the inlet end thereof at the lower end portion of the air desuperheater of the portion thereof adjacent the condenser 52 and with the outlet end portions of the tubes positioned near the inlet end portion thereof or adjacent the means for drying the air entering same. The coolant tubes 76 preferably have a plurality of spaced plates 78 thereon which provide a large heat conducting surface area and the plates 78 are preferably generally parallel to each other and located in planes parallel to the longitudinal axis of the air desuperheater portion 48.

A coolant inlet header 80 is provided and is positioned in fluid communication with the inlet end of each of the tubes 76 and an outlet header 82 is positioned at the upper portion of the air desuperheater 48 and is in fluid communication with the outlet end of each of the tubes 76. It has been found that by positioning the coolant tubes and headers in the manner shown and described air passing through the air desuperheater 48 will first pass across the relatively warm portions of the plates 78 and then across the cooler portions thereof, the upper portions of the plates 78 and tubes 76 being slightly warmer as a result of heat transfer occuring in the lower portions of the air desuperheater and thus causing warming of the coolant. A conduit 84 connects the outlet header 82 to the burner injectors or nozzles 26 of the engine 22. If desired, the conduit 62 connected to the outlet header 60 of the means to remove moisture and carbon dioxide from the air at the inlet of the air desuperheater portion 48 of the heat exchanger can also be connected to the conduit 84 as illustrated in the drawings.

A plurality of coolant tubes 90 are positioned in the condenser portion 52 of the heat exchanger 44, and preferably each of the tubes 90 is looped and has the inlet end portion thereof at the lower portion of the condenser 52 and has the outlet portion thereof in the upper portion of the condenser portion 52 as illustrated in FIG. 2, so that air entering the condenser portion from the air desuperheater portion passes across the relatively warm portions of the coolant tubes first and then across the relatively cool portions thereof as it moves toward the bottom of the condenser. A coolant inlet header 92 is positioned at the lower portion of the condenserportion of the heat exchanger 44 and is in fluid communication with the inlet end of each of the tubes 90. A conduit 94 connects the inlet header 92 to the outlet 38 of the hydrogen fuel storage tank 34 so that the relatively cold hydrogen fuel can be passed through the tubes 90 and thus remove heat from air within the condenser andcool same.

A diaphragm operated control valve 98 is preferably provided and located in the conduit 94 adjacent the condenser portion 52 of the heat exchanger 44. A bypass conduit 100 is connected to the inlet header 56 of the air desuperheater portion 48 of the heat exchanger 44 and to the conduit 94 between the valve 98 andthe hydrogen fuel storage tank 34. A relay 102 is provided with the valve 98 and pneumatic or

electrical instrument lines

104 and 106 are provided with the relay and extend to the throat 50 of the air desuperheater 48 and to the condenser portion 52 and are operable to sense pressures therein and operate the relay 102 to control the valve 98 and thereby selectively provide liquid hydrogen fuel from tank 34 to the condenser portion 52 of the heat exchanger 44 or to the air desuperheater portion 48 through conduit 100. By regulating the flow of coolant and thus cooling of the air in these two portions of the heat exchanger a pressure drop is maintained between the throat 50 of the air desuperheater portion 48 and the condenser portion 52 of the heat exchanger 44.

A coolant outlet header 110 is provided in the upper portion of the condenser portion 52 of the heat exchanger 44 and is in fluid communication with the outlet end of each of the coolant tubes 90 within the condenser. A conduit 112 connects the outlet header of the condenser portion 52 with the bypass conduit 100 leading to the inlet header of the air desuperheater portion 48. A check valve 114 is positioned in the conduit 112 and is operable to permit coolant flow from the condenser portion 52 and outlet header 110 through conduit to the inlet header 80 of the air desuperheater portion 48 only.

A three-way valve 120, FIG. 1,. is provided and has one outlet thereof operatively connected to the conduit 84 by a conduit 122 to provide hydrogen fuel from the valve to conduit 84 and to the nozzle 26 of the engine 22. A hydrogen fuel booster pump 124 is provided and has the outlet thereof connected to the inlet 36 of the hydrogen fuel storage tank 34 to provide hydrogen fuel thereto under pressure. The inlet of the pump 124 is connected to another outlet of the three-way valve 120 and receives hydrogen fuel therefrom. A conduit 126 is connected in one end portion to the inlet of the three-way valve 120 and is connected in the other end portion to the conduit 122 from the outlet header of the condenser 52 and is preferably positioned between the check valve 114 and the header 110.

Control means are preferably provided with the three-way valve to direct the flow of fuel received by the valve either to the hydrogen fuel storage tank 34 or to the nozzles 26 through conduit 84. Preferably the control means includes a relay 128 which has temperature sensing means 130 and 132 therewith which are connected in their end portions to the outlet 38 and inlet 36 of the hydrogen fuel storage tank 34, respectively, so that when the hydrogen fuel being supplied to tank 34 by pump 124 reaches a predetermined high temperature, the valve 120 closes to the pump 124 and the hydrgen fuel in conduit 126 is directed through conduit 122 and conduit 84 to the engine 22. This prevents recirculation of relatively high temperature hydrogen fuel which may reach a temperature sufficiently high, so that heat removal within the condenser 52 and air desuperheater portion 48 is substantially reduced. On the other hand, when thehydrogen fuel received by conduit 126 is relatively cold the valve 120 operates to recirculate a portion of the hydrogen fuel through pump 124 into tank 34 for subsequent use and additional cooling of air in the heat exchanger 44. Thus, maximum and efficient use of the hydrogen fuel is obtained in operation.

A control valve 140, preferably of the diaphragm operated type is positioned in conduit 126 and has a relay 142 operatively connected thereto. An instrument line 144 is connected to the relay and to a heat sensing element 146 in the throat 50 of the air desuperheater portion 48 of the heat exchanger 44, and the relay 142 is operable in response to the temperature in the throat 50 to control the valve to open same at a relatively low temperature in the throat 50 and close the valve at a relatively high temperature in the throat and thus regulate the flow of hydrogen fuel from header 110 through conduit 112 and check valve 114 into the desuperheater portion 48 of the heat exchanger. A control valve 148 is provided in the bypass conduit 100 leading to the inlet header 80 of the air desuperheater portion and is operatively connected by instrument line 150 to relay 142 so that the valve 148 is opened at relatively high temperatures in the throat 50 of the air desuperheater portion 48 of the heat exchanger and closed at relatively low temperatures therein so that relatively cold hydrogen fuel directly from the tank 34 can be supplied through conduit 94, bypass conduit 100 and valve 148 directly to the inlet header 80 of the air desuperheater portion 48 of the heat exchanger when the temperature of air leaving throat 50 becomes higher than desired.

An air condensate well 160 is provided in the condenser portion 52 of the heat exchanger and is desirably located substantially opposite from the throat 50 of the air desuperheater portion 48. In operation, liquid air condensed in the condenser 52 drains to and is collected in the well 160. A liquid air conduit 162 is connected to the well 160 to remove liquid air therefrom. The other end portion of the liquid air conduit 162 is connected to the burner nozzles 26 to provide liquid air to the engine for oxidation of the hydrogen fuel provided thereto through

conduits

84 and 122.

A bypass conduit 164, FIG. 1, connects the intermediate portion of the liquid air conduit 162 to the inlet 42 of the liquid air storage tank 40 and preferably the tank 40 floats on the conduit 162, that is it either receives liquid air from the conduit 162 or discharges liquid air thereto in response to requirements of the engine means. Preferably a liquid air pump 166 is provided in conduit 162 to transfer the liquid air from the well 160 and desirably the pump 166 is located between well 160 and conduit 164. A valve 168 is provided in conduit 162 between bypass conduit 164 and the burner nozzles 26 of the engine, and the valve preferably has a control line 170 therewith operatively connected to the conduit 84 so that the valve 168 regulates the flow of liquid air to the nozzles 26 in response to the pressure or volume of fluid passing through conduit 84.

Means are preferably provided to fractionate the air condensed by condenser 52 into fractions containing oxygen and nitrogen so that the relatively large volumes of nitrogen which are inert and do not aid in combustion of the hyrogen fuel can be removed. Fractionization of the liquid is preferably obtained by an air rectifying column or packed tower shown generally at 180 which has a housing 182 opening into the upper portion of the liquid oxygen storage tank 40. Housing 182 has a plurality of nozzles 184 therein which are connected to the outlet 42 of the liquid air storage tank 40 by a conduit 186. An air rectifying column recirculating pump 188 is preferably provided to transfer liquid air from tank 40 or directly from conduit 162 to the nozzles 184 which discharge same into the housing 182.

Means are provided to heat the bottom of housing 182 of the air rectifying column to a temperature sufficient to vaporize the liquid air. Since atmospheric air is substantially warmer than the boiling temperatures of liquid oxygen and liquid nitrogen this heating function is preferably provided by a dump conduit 190 which opens in one end portion at the air inlet diffuser portion 46 of the heat exchanger to receive atmospheric air therein and has the other end portion thereof positioned at the exhaust portion 30 of the engine means 22. During flight of the rocket 10, air from the atmosphere passes through conduit 190 due to the pressure differential existing at the end portions thereof. A conduit 192 is secured in its end portions to conduit 190 and is in fluid communication therewith to receive air therefrom at the upstream or inlet end portion thereof. The intermediate portions of conduit 192 are positioned around the bottom of the housing 182 of the air rectifying column or packed tower and passage of atmospheric air through

conduits

190 and 192 provides sufficient warming of the liquid air being discharged into the housing 182 by the nozzles 184 to vaporize the air.

A valve 194 is preferably provided in the inlet end of conduit 192 and has control means therewith operable to open and close same in response to the temperature in the air rectifying column to control the vaporization process. The control means for valve 194 can be provided by a relay 196 which is connected to the valve 194 by a control line 198 and connected by a control line 200 to a heat sensing element 202 positioned within the housing 182 of the air rectifying column or tower with the relay 196 being operable to open and close valve 194 to maintain the temperature within the column within the desired range.

Means are also preferably provided to cool the top or upper portion of the housing 182 of the air rectifying column 180. This can be accomplished in the manner illustrated in the drawings wherein a conduit 203 is provided and is connected in its end portions to the conduit 94 from the hydrogen fuel storage tank 34 and to the conduit 126 leading to the engine means 22. The intermediate portion of the conduit 203 is positioned around the upper portion of the housing 182 and since a pressure differential exists between the

conduit

94 and 126 hydrogen fuel flows through the conduit 203 to cool the upper portion of the tank.

Preferably conduit 203 has a valve 205 therein which can be of the diaphragm operated type and is desirably controlled in response to the temperature within housing 182 to open and close the valve and regulate the flow of hydrogen fuel through conduit 203. The temperature control can be provided by a heat sensing element 207 positioned in the upper portion of the housing 182 with the element 202 and valve 205 each being connected to a relay 209 and in operation the valve 205 opens and closes in response to the temperature of the heat sensing element 207. The cooling means in the upper portion of the housing 182 and the heating means in the lower portion thereof operate to establish and maintain a temperature differential from the lower or bottom portion of the tower to the top or upper portion thereof.

During operation of the rectifying column, liquid air discharged into the housing 182 is vaporized in the warmer or lower portion of the housing and the vapors rise in the tower. A partial condensation of the vapor occurs in the upper portion of the housing or column and the resulting liquid is rich in oxygen and is retumed to the storage tank 40 while the remaining vapor is rich in nitrogen and is exhausted. For this purpose an exhaust conduit 204 is provided and is connected in its end portions to the upper portion of housing 182 and to the dump conduit and desirably has a relief valve 206 therein which is operable to open and discharge the vaporized portion of liquid air containing nitrogen gas to the dump conduit 190 upon reaching a predetermined pressure value.

During operation of the condenser portion 52 of the heat exchanger 44 certain gases present in the atmosphere, for example, neon and helium, which are incondensable will tend to build up or fill the condenser portion 52 and means are provided to discharge the incondensable gases to the atmosphere. For this purpose I same to the atmosphere. Preferably an ejector or gas pump 215 is provided in conduit 214 to deliver these gases to dump conduit 190.

In operating the propulsion means of FIGS. 1 and 2, liquid hydrogen fuel is provided to the hydrogen fuel storage tank 34 and preferably maintained at a pressure sufficient to cover losses and deliver the fuel to the engine, for example, a pressure of approximately 500 pounds per square inch. The hydrogen fuel is initially at a low temperature, for example approximately 45 Rankine. An oxidizer is provided to the engine means during lift off of the vehicle and such can be provided by operation of the heat exchanger means to produce liquid air in the manner described herein and in such instance the vehicle preferably remains stationary until sufficient liquid air is produced and stored to supply the engine requirements for initial portions of the flight. The liquid air produced and stored should be sufficient to supply the engine means during lift-off and during initial period of flight where use of oxidizer may exceed the production rate. As an alternative, the air storage tank 40 can be initially partially filled with an oxidizing material, such as liquid oxygen, with such being provided through

conduits

164 and 162 to the burner nozzles of the engine during lift-off and initial portions of the flight. Liquid hydrogen fuel is provided through the outlet 38 of the tank 34 and through conduit 94 and the conduits leading from the heat exchanger 44 to the engine means and mixed therein with the oxidizer and ignited to lift the vehicle.

During operation, air from the atmosphere is funneled into the air desuperheater portion of the heat exchanger 44 through the air inlet diffuser. The size of the air inlet varies with the size of the vehicle, an area of approximately 30 to 90 square feet being satisfactory for vehicles having a take-off weight of approximately 100,000 pounds. Simultaneously liquid hydrogen fuel at approximately 45 R is provided to the tubes 54 in the air desuperheater or liquid oxygen is provided from tank 40 through conduit 66 to header 68, conduits 70 and spray nozzles 72 and sprayed into the air desuperheater to freeze moisture and carbon dioxide present in the air so that the air entering the intermediate portion of the airdesuper heater is substantially dried. This prevents the formation of ice in the heat exchanger.

The substantially dried atmospheric air then passes across the rows of fins 78 in the air desuperheater 48 at velocities up to approximately Mach one and simultaneously the fins are cooled by passing liquid hydrogen fuel from storage tank 34 through the conduits or tubes 76 and the heat seeking or sensing element 146 in the throat 50 of the air desuperheater portion 46 operates the relay 142 to regulate the flow of liquid hydrogen fuel through the coolant tubes 76 so that the atmospheric air leaves the throat 50 of the air desuperheater at a temperature of approximately 200 Rankine. The air leaves the air desuperheater throat 50 ahd passes into the relatively large condenser portion 52 of the heat exchanger.

The pressure control system, including relay 102 and pressure means associated therewith, operates the valve 98 to control passage of hydrogen fuel into the tubes 90 of the condenser portion 52 of the heat exchanger to cause condensation of air therein and create a pressure drop between the desuperheater portion and the condenser portion of the heat exchanger. By establishing a pressure drop across the throat 50 of the heat exchanger critical flow is obtained at this point and thus the mass flow is a maximum and the physical size of the heat exchanger a minimum for a given pressure and temperature. Also, this permits dividing of the load between the desuperheating and the condensing sections of the heat exchanger.

The air entering the condenser 52 is passed over the coolant tubes therein which are also being supplied with liquid hydrogen fuel at approximately 45 Rankine to thereby cool the air to a low temperature, preferably below Rankine, which results in condensation of the condensable portions of the air therein. The incondensable gases including neon and helium received by the condenser 52 are exhausted to the atmosphere through conduit 214 and dump conduit 190 leading to the exhaust portion 30 of the engine means.

The aircondensed in the condenser portion 52 is collected in the air condensate well and transferred by the liquid airpump 166 to the liquid air storage tank 40 and to the engine nozzles 26. Atleast a portion of the liquid air received by the storage tank 40 is transferred by the pump 188 to the air rectifying column or packed tower and discharged thereinto from the nozzles 184. Simultaneously air from the atmosphere is passed through the dump conduit 190, into the conduit 192 and through valve 194 to warm the lower portion of the housing 182 of the air rectifying column and hydrogen fuel passes through conduit 203 to cool the upper por' tion of housing 182 to thereby fractionate the liquid air into a gaseous portion and a liquid portion, the gaseous portion being rich in nitrogen as a result of heating of the liquid air sprayed into the air rectifying column. The gaseous fraction of the air is transferred through conduit 204 and valve 206 to the dump conduit and exhausted to the atmosphere. The portion of the liquid air rich in liquid oxygen is returned to the liquid air storage tank 40 through the open end of the housing 182 and when supplied to the burner nozzles 26 of the engine is used for oxidizing the hydrogen fuel therein. The fuel is mixed with the liquid air and ignited in the combustion chamber 24 of the engine means 22 and the resulting exhaust gases are directed outwardly through the neck portion 28 of the engine means and exhaust portion 30 thereof to the atmosphere in one direction and-causes an equal and opposite force to be directed on the rocket itself to propel same in the opposite direction.

During operation of the system, the relay 102 and control means associated therewith functions to provide the desired pressure drop between the throat 50 of the air desuperheater 48 and the condenser portion 52. At the same time the relay 142 functions in response to the temperature of the heat sensing element 146 in the throat 50 of the air desuperheater portion 48 to regulate the flow of hydrogen fuel coolant into the air desuperheater portion of the heat exchanger in response to the temperature at the throat so that a substantially constant temperature is obtained for the cooled atmospheric air entering the condenser.

These control means for the heat exchanger are quite desirable, since under various conditions of flight the load of the condenser and air desuperheater will change relative to each other. For example, during initial movement of the rocket and while the velocity thereof is relatively low the condenser load is relatively great and the load of the air desuperheater is relatively small. When the rocket reaches a substantial velocity the mass of air passing through the air desuperheater increases and the desuperheater requires additional liquid hydrogen fuel to cool the air passing therethrough and valve 148 is opened so that additional liquid hydrogen fuel directly from tank 34 is supplied to the tubes 76 across the air desuperheater portion.

Some of the nitrogen containing liquid air is transferred directly by pump 166 to the engine 22, however the large portion thereof is fractionated by operation of the air rectifying column 180 to remove the inert nitrogen portion of the liquid air.

The hydrogen fuel stored in the tank means 34 is at a relatively cold temperature, preferably in the range of 25 to 65 Rankine. it has been found that at these temperatures diatomic molecules of hydrogen have two molecular forms which are related to the nuclear spins. These forms are ortho hydrogen in which the nuclei spin in the same direction and para hydrogen in which the nuclei spin in the. opposite direction. While these two forms of hyrogen have the same physical properties in most instances, there is a difference between the internal energy levels of the ortho and para forms of hydrogen and at a specified constant temperature heat must be added to the para hydrogen form to convert it to the ortho hydrogen form. For this reason the hydrogen stored in tank means 34 is preferably in the para form and the para to ortho heat of conversion and the relatively high specific heat capacity of the hydrogen provides a highly attractive heat sink. The para to ortho hydrogen conversion can be accelerated by the addition of suitable catalysts and, hydrous ferric oxide and Cr O Al O have been found to be satisfactory catalysts for this purpose.

The performance of a rocket or similar vehicle such as shown in the application and described hereinbefore has been determined. This analytical determination is based upon a vehicle having an initial take-off weight of approximately 100,000 pounds and where the engine exerted a substantially constant thrust of approximately 200,000 pounds with the vehicle having a vertical trajectory. For purposes of the calculations the effect of nitrogen stripping and regenerative cooling on the performance of the vehicle was not evaluated and the values given do not include data for the deicing means. Also, it was assumed that ninety per cent conversion of para to ortho hydrogen was obtained. For the calculations the condenser terminal temperature difference, that is the temperature difference between the condensing air temperature and the leaving hydrogen coolant temperature, was taken at 20 Rankine and the temperature of the atmospheric air leaving the throat 50 of the air desuperheater 48 was considered a constant 200 Rankine. The nozzle velocity of the vehicle was considered to be a constant 5,500 feet per second. Computations were made to obtain operation data as the air inlet area varied from 40 to 80 square feet, such being a significant variable since the air inlet size determines the total volume or mass of air received by the heat exchanger and available for condensation and thus determines the total volume of liquid air available as an oxidizer for the fuel in the engine. Under these conditions the acceleration of the vehicle varied from a value of approximately feet per second squared at an altitude of 30,000 feet to approximately 40 feet per second square at an altitude of 100,000 feet for a vehicle having an air inlet area of 80 square feet and varied from approximately 25 feet per second square at 40,000 feet altitude to approximately feet per second square at 150,000 feet altitude for a vehicle having an air inlet of 40 square feet. Under these conditions the vehicle velocity increased to a value of approximately 1,500 feet per second at 100,000 feet altitude for the vehicle having an air inlet area of 80 square feet and for the vehicle having a 40 square feet air inlet area the velocity increased to approximately 3,500 feet per second at an altitude of 150,000 feet.

The flight time determined for the vehicle having 40 square feet of air inlet area was approximately 1 10 seconds during which time the vehicle reached an altitude of approximately 160,000 feet. For the vehicle having the air inlet area of 80 square feet a flight time of approximately seconds and altitude of approximately 100,000 feet was indicated.

Since the rocket or vehicle including the propulsion means of the invention will continue to take on oxygen and store same during flight through the atmosphere and particularly at the relatively low atmospheric levels where the amount of oxygen in the air is relatively high the weight of the vehicle varies with the altitude of flight. For example, considering a vehicle having an air inlet area of 40 square feet and the weight of the vehicle was initially 100,000 pounds, the weight decreased to approximately 92,000 pounds at an altitude of approximately 3,000 to 5,000 feet at which time the weight began to increase as the total volume of oxygen or liquid air stored in the vehicle increased so that the total weight of the vehicle was approximately 105,000 pounds at and altitude of 30,000 to 40,000 feet and the vehicle weight then decreased steadily to a final weight of approximately 50,000 pounds at an altitude of 150,000 feet. The final weight is less than the initial weight, since all fuel and oxidizer are exhausted in flight. For a vehicle having an air inlet area of 80 square feet, the weight decreased from an initial weight of 100,000 pounds to approximately 95,000 pounds at 1,000 feet and then increased to a total weight of approximately l55,000 pounds at 35,000 to 45,000 feet of altitude with the total weight then decreasing to a value of approximately 115,000 pounds at an altitude of 100,000 feet. From this data maximum performance of the heat exchanger as indicated by the total weight on the vehicle occurs at an altitude of between 20,000 and 50,000 feet of altitude where the velocity of the vehicle is relatively high and where the atmosphere is relatively dense in terms of oxygen present in the air.

The amount of air stored on the vehicle during flight of the vehicle is also related to the air inlet area and the altitude of the vehicle and computations indicate that a vehicle having an air inlet area of 40 square feet stores a maximum of approximately 25,000 pounds of air thereon when it reaches an altitude of approximately 40,000 to 50,000 feet and that a vehicle having air inlet area of approximately 80 square feet stores approximately 95,000 pounds of air as it reaches an altitude of 40,000 to 50,000 feet. In both instances the air stored on the vehicle decreases above the altitude of maximum storage indicated, since the vehicle then uses the air stored for combustion in the engine means at a rate greater than the condensing rate of the heat exchanger. Since the weight of the vehicle varies considerably with the air inlet rate and the amount of air stored therein the fuel exhausted during the flight is also variable with the altitude of the vehicle and the amount of fuel exhausted increases relatively rapidly during the first 50,000 feet of flight during which time 20,000 pounds of fuel is exhausted for a vehicle having an air inlet area of 40 square feet and the use of fuel then increases relatively gradually to a maximum of approximately 25,000 pounds at an altitude of approximately 160,000 feet. For a vehicle having an air inlet area of approximately 80 square feet the amount of fuel exhausted increases relatively rapidly to approximately 60,000 feet with the fuel expended to that altitude totaling approximately 47,000 pounds and with the fuel exhausted then decreasing to a total of approximately 52,000 pounds at an altitude of 100,000 feet.

The air flow rate and the fuel flow rate in the heat exchanger are also variable with the altitude of the vehicle under the conditions set forth hereinbefore, and for a vehicle having a 40 square foot inlet area the air flow rate varies from approximately 400 pounds per second at 1,000 feet of altitude to a maximum of approximately 1,700 pounds per second at an altitude of 10,000 to 12,000 feet and then decreases to approximately 1,500 pounds per second at an altitude of 20,000 feet. For a vehicle having an air inlet area of 80 square feet the air flow rate increases from approximately 750 pounds per second at 1,000 feet altitude to approximately 2,800 pounds per second at an altitude of 8,000 to 10,000 feet and then decreases to a rate of approximately 2,300 pounds per second at an altitude of 20,000 feet. Under these same conditions the fuel flow rate varies from approximately 100 pounds per second at an altitude of 1,000 feet to approximately 450 pounds per second at an altitude of 10,000 to 20,000 feet for a vehicle having an air inlet area of 40 square feet. For a vehicle having the air inlet area of approximately 80 square feet the fuel flow rate varies from approximately 200 pounds per second at 1,000 feet to approximately 800 pounds per second at an altitude of approximately 8,000 to 10,000 feet and then decreases slightly to approximately 650 pounds per second man altitude of 20,000 feet.

The heat transfer rate for the heat exchanger also varies with the altitude of the vehicle. For example, assuming an air inlet area of 40 square feet the heat transfer rate in the air desuperheater varies from approximately 25,000 BTU per second at 1,000 feet altitude to a maximum of approximately 120,000 BTU per second at 10,000 to 1 2,000 feet altitude and then decreases to approximately 1 10,000 BTU per second at 20,000 feet. For the same inlet area the condenser heat transfer rate varies from approximately 40,000 BTU per second at 1,000 feet altitude to approximately 185,000 BTU per second at 10,000 to 14,000 feet altitude and then decreases to approximately 175,000 BTU per second at 20,000 feet. For an air inlet area of approximately 80 square feet, the desuperheater heat transfer rate varies from approximately 50,000 BTU per second at 1,000 feet altitude to approximately 185,000 BTU per second at 6,000 to 8,000 feet and decreases from this altitude to approximately 135,000 BTU per second at 20,000 feet altitude. For an inlet area of 80 square feet the condenser heat transfer rate varies from approximately 80,000 BTU per second at 1,000 feet altitude to approximately 310,000 BTU per second at approximately 7,000 to 12,000 feet altitude and then decreases to approximately 250,000 BTU per second at 20,000 feet of altitude.

The condensing pressure of air in condenser 52 is a variable and depends upon the temperature and pressure of the air therein. Since air is a mixture of gases, its condensing temperature for a constant pressure process varies slightly. However, this temperature variation is relatively small and for the: purposes of the calculation, it was assumed to be a constant temperature process. The air cooling in the air desuperheater, on the other hand, is a varying pressure, varying temperature process. With these assumptions the condensing pressures of a typical rocket based upon the given values set forth hereinbefore were computed, and it was found that for a rocket having an air inlet area of 40 square feet the condensing pressure varied from approximately 2,000 pounds per square foot at initial lift off ofthe vehicle to a value of approximately pounds per square foot at an altitude of 150,000 feet, the condensing pressure varying relatively quickly during the first 50,000 to 60,000 feet of altitude and being at approximately 750 pounds per square foot at an altitude of 50,000 feet. For a rocket having an air inlet, of approximately square feet, condensing pressure varies from approximately 2,000 pounds per square foot at lift-off to approximately 10 pounds per square foot at an elevation of 100,000 feet with the rate of change being substantially the same as that described for the 40 square foot inlet area rocket. I l

The inlet total temperature also varies with altitud and for a 40 square foot inlet area the temperature varies from approximately 520 Rankine at lift-off to approximately l,450 Rankine at 150,000 feet. Likewise the inlet total temperature for a rocket having an air inlet of 80 square feet varies from approximately 520 Rankine at liftoff to approximately 600 Rankine at 100,000 feet.

As will be seen from the foregoing figures regarding the variables encountered in the heat exchanger operation, the control means regulating the flow of hydrogen fuel through the condenser and air desuperheater portions are quite desirable and provide means for compensating for the changing loads of the condenser and desuperheater in accordance with various conditions encountered. Also, when the trajectory of the missile or vehicle deviates from a vertical mission such control means are especially important in order to continuously condense air during flight.

The foregoing discussion regarding the values and operation of the propulsion means have ,been based upon a constant throat temperature for the air desuperheater of 200 Rankine. This temperature can also be a variable and a change in this temperature affects the heat transfer rate and loads in both the condenser and desuperheater. For example, assuming a total vehicle weight of 100,000 pounds having; an engine thrust of 200,000 pounds with a characteristic nozzle velocity of 5,500 feet per second, and assuming a total air inlet area of 40 square feet with a total terminal temperature difference across the condenser of 20 Rankine, then a change in the throat temperature from 200 Rankine to Rankine will increase the heat transfer rate required in the air desuperheater by approximately 25,000 BTU per second over the altitude range of from 6,000 to 20,000 feet. At the same time the heat transfer rate in the condenser portion of the heat exchanger will be reduced by 25,000 to 30,000 BTU per second over the same altitude range. The temperature at the throat of the air desuperheater can be regulated either by controlling the flow of coolant into the air desuperheater portion of the heat exchanger or by the length of the air desuperheater through which the air must pass during cooling thereof, a longer desuperheater section serving to cool the air to a lower temperature.

The foregoing data is based on a condenser terminal temperature difference of Rankine. The effect of a change in the condenser terminal temperature difference on the performance of the system has been calculated and based on the given data for a 100,000 pound vehicle as set forth hereinbefore, and assuming an air inlet area of 40 square feet at an altitude of 10,000 feet the total fuel flow rate for a condenser terminal temperature of 10 Rankine is approximately 400 pounds per second, for a 20 Rankine condenser terminal temperature difference the fuel flow rate is approximately 425 pounds per second, for a 40 Rankine terminal temperature difference the fuel flow rate is approximately 550 pounds per second and for a 60 Rankine condenser terminal temperature difference the fuel flow rate is approximately 800 pounds per second.

Since the total air received by the vehicle for condensation is directly proportionate to the total air inlet area, the heat rate or heat transfer load is also variable in relation to the inlet area. For the 100,000 pound vehicle described having a condenser terminal temperature difference of 20 Rankine and nozzle velocity of 5,500 feet per second and assuming a temperature of 200 Rankine at the throat of the air desuperheater portion of the heat exchanger, the heat rate varies from approximately 120,000 BTU per second for an inlet area of 40 square feet to approximately 190,000 BTU per second for an air inlet area of approximately 80 square feet.

It has also been determined that for a 200,000 pound thrust vehicle and with a heat exchanger unit weight of 1 pound per square foot of area obtained by design of the heat exchanger that the heat exchanger weight increases as the condenser terminal temperature difference decreases, that is for a condenser terminal temperature difference of 70 Rankine the heat exchanger weight would be approximately 16,000 pounds and for a condenser terminal temperature difference of 20 Rankine the heat exchanger weight would be approximately 26,000 pounds. Using the same basis, the total weight of the heat exchanger, fuel tank and fuel therein is determined in relation to the condenser terminal temperature difference and varies from approximately 52,000 pounds for a difference of 20 R up to approximately 105,000 pounds for a condenser terminal temperature difference of 70 Rankine.

The heat transfer load increases as the vehicle thrust increases, and the additional heat transfer load requires an increase in the heat exchanger weight. In view of this, the propulsion means of the invention is most desirable for vehicles having relatively low thrust to vehicle take-off weight ratios. In addition, since 30 per cent by weight of the air in the atmosphere is beneath 10,000 feet altitude and some 70 per cent by weight of the air is present beneath 30,000 feet of altitude the system is most suitable for either low altitude boost missions or for applications where at least initial portions of the trajectory are in altitudes beneath 30,000

to 40,000 feet where air is stored for subsequent use in TABLE I Heat Exchanger Weight per sq. n. l lb. 0.75 lb. 0.50 lb. 0.25 lb. Take-off Weight, lb. 100,000 100,000 100,000 100,000 Thrust, lb. 200,000 200,000 200,000 200.000 Air Inlet Area, R. 40 40 40 40 Nozzle Velocity, fps 5,500 5,500 5.500 .500 Temperature Leaving Desuper-heater, R 200 200 200 200 Condenser-Terminal- Temp.-Diff., R 30 25 20 10 Bum-out Altitude, ft. 1 10,000 107,500 105,000 100.000 Burn-out Velocity,

2,500 2,450 2,400 2,300 Mission Time, sec. 94 93 92 Bum-out Weight, lb. 73,500 74,750 76,000 78,000

Fuel Required, lb. 26,500 25,250 24,000 22,000 Fuel Tank at 3%, lb. 795 760 720 660 Maximum Air Stored, lb. 25,000 24,500 24,000 22,000 Air Surge Tank at 3%, lb. 750 735 720 660 Power Plant 8:. Pump Weight, lb. 2,670 2,670 2,670 2,670

Connecting Struct. & Misc. lb 2,000 2,000 2,000 2,000 Heat Exchanger Weight, lb. 22,390 18,054 12,875 7,750 Total Weight Empty, lb. 28,605 24,219 18,985 13,740

Payload, lb. 44,895 50,531 57,015 64,260

These figures indicate a significant improvement over payload carried by present chemical rockets.

FIG. 3 of the drawings illustrates a modification or embodiment of the invention wherein means are provided for storage and subsequent recirculation of at least a portion of the hydrogen fuel previously used for cooling prior to transfer of the fuel to the engine means. Such as embodiment or modification is quite desirable where total heat transfer to the liquid hydrogen fuel is relatively low due to the condensing temperature or volume of air being condensed at any specific time and where the recirculated hydrogen fuel can be mixed with the relatively cold hydrogen fuel from the storage tank 34. The embodiment of FIG. 3 is the same as that shown in FIGS. 1 and 2 with the exception of the addition of the surge tank and related apparatus, it being understood that the liquid hydrogen fuel tank, liquid oxygen storage tank and rectifying means or fractionating means of FIGS. 1 and 2 are also utilized with the surge tank and related structure of FIG. 3.

In FIG. 3 a liquid hydrogen fuel surge tank is shownat 220 and has an inlet 222 and an outlet 224. The surge tank 220 is preferably located between the hydrogen fuel storage tank 34 and the heat exchanger means 44. In this embodiment the hydrogen fuel is supplied under pressure to the heat exchanger 44 by operation of a fuel pump 226 in conduit 94 between the valve means 98 and the hydrogen fuel tank 34. Use of the fuel pump 226 is an alternative to the use of the pump 124 illustrated in FIG. 1. A control valve 228 is provided downstream or on the suction side of the pump 226 and valve 228 is normally open during initial portions of the flight of the rocket means and pump 226 then transfers hydrogen fuel directly from tank 34 and supplies same to the heat exchanger 44 and then to the engine as explained hereinbefore. The dump conduit 126 leading from the condenser outlet header has a three-way valve 230 therein and a conduit 232 connects the valve 230 to the inlet 222 of the surge tank 220.

A conduit 234 connects the outlet 224 of surge tank 220 to the fuel pump 226 and has a control valve 236 therein. A relay 238 is provided with the

control valves

236 and 228 and is operatively connected through a relay 240 to pressure sensing means 242 located in the condenser portion 52 of the heat exchanger 44. The relay 238 in connection with the pressure sensing means 242 is operable to open valve 236 at high condenser pressures and close the valve at relatively low condenser pressures. The relay 238 operates to close the valve 228 on high condenser pressures and open same on low condenser pressures. The relay 240 operates control valve 230 to provide hydrogen fuel from conduit 126 to the surge tank on relatively low condenser pressures in the condenser 52 and to bypass the surge tank 220 on high condenser pressures.

During start-up conditions the condenser load or duty is always larger than the air desuperheater load and for some missiles and missile trajectorys this condition is always true. However, if the missile speed becomes large, and thus the kinetic energy associated with the incoming air is large, the air desuperheater load becomes larger than the condenser load. See FIG. 4.

When the condenser load is larger than the desuperheater load, the required coolant flow through the condenser is larger than the required coolant flow through.

the desuperheater. The control valve 140 is opened and part of the coolant flow from the condenser bypasses the air desuperheater. As missile speed increases the load on the desuperheater section of the heat exchanger increases and the load on the condenser decreases by operation of the pressure control system including relay 102 and

control lines

104 and 106; which:

operate valve 98. Thus, as missile speed increases the control valve 140 closes and additional coolant is supplied through conduit 112 to the air desuperheater portion of the heat exchanger.

The temperature curve in FIG. 4 is the temperature of the coolant leaving the condenser and this temperature rises as the missile speed increases. As a result of this the coolant flow used at the first part of the trajectory where the coolant. temperature leaving the condenser is relatively low and can be stored in surge tank 220 and subsequently re-used. Thus, during the first part of the trajectory, the excess of the relatively low temperature coolant leaving the condenser that is not required in the desuperheater passes through valve 140, conduit 126 and three-way valve 230 into the surge tank 220. During this time. valve 140 istopen and valve 228 is open and three-way valve 230 is open to the surge tank 220. Valve 236 from the surge tank 220 is closed. When the missile reaches a relatively high speed and the condensing pressure increases, the relay 240 causes the three-way valve 230 to close to the surge tank 232. Coolant flow then not required. for desuperheating is transferred through conduit 126 to the engine means. At this time the control valve 236 is opened and coolant flows from surge tank 230 intothe pump 226. Preferably, the coolant fromsurge tank 226 is proportioned between the surge tank 220 and the hydrogen fuel storage tank 34. With the pump 226 for transferring the hydrogen fuel, the fuel in the surge tank is at relatively high pressures as a result of operation of pump 226 and the surge tank pressure is high in outlet end of each of said coolant tubes, a conduit concomparison to that in the tank 34. Therefore, the fuel from surge tank 220 is preferably fed into the pump 226 at the last stages of the pump.

The advantages of the surge tank 220 and recirculation system of FIG. 3 is illustrated in FIG. 5. In FIG. 5 a missile flying a vertical trajectory to 60,000 feet with a constant acceleration of 6 g. is illustrated with the savings in coolant flow as a result of recycling the coolant being the difference between the upper and lower curves. The net average coolant flow rate using the systern of FIG. 3 is reduced from approximately 9.7 pounds to approximately 8.4 pounds coolant flow per pound of fuel burned for the given condition.

While the rocket means of the invention has been described in connection with preferred specific embodiments thereof, it will be apparent to those skilled in the art that various modifications or changes can be made therein without departing from the spirit of this disclosure or the scope of the claims.

. I claim:

I. A rocket comprising, in combination, a housing having a generally cylindrical centerportion joined at the ends to an open exhaust end portion and an open inlet end portion, a plurality of fins secured to said exhaust end portion of said housing tapering toward the intermediate portion of said housing with the inner end portion of said fins being in streamlined engagement with said housing, a rocket engine having a combustion chamber with burner nozzles and an enlarged frustoconical exhaust portionhaving the relatively small end portion thereof in communication with said chamber to receive gases therefrom and having the relatively large end portion thereof opening to the atmosphere at said exhaust end portion of said housing, a liquid hydrogen fuel storage tank positioned within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a heat exchanger positioned within said housing and having a hollow air inlet diffuser portion at one end portion thereof opening into a centrally located elongated air desuperheater portion having a throat opening into an enlarged air condenser portion, means positioned at the inlet of said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough, said air inlet diffuser portion of said heat exchanger being frustoconical in shape and having the relatively large end portion thereof positioned at said open inlet portion of said housing to receive air therein, a plurality of passes of coolanttubes in said air desuperheater portion of said heat exchanger, a plurality of spaced plates secured to said tubes with said plates being parallel to each other and to the axis of said air desuperheater portion of said heat-exchanger, a coolant inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header in fluid communication with the necting said last-named header to said burner nozzles of said rocket engine, a plurality of coolant tubes in said condenser portion of said heat exchanger, each having the inlet end thereof at the lower portion of said condenser portion and having the outlet end thereof at v the upper portion of said condenser portion, a coolant inlet headerpositioned at the lower portion of said condenser portion of said heat exchanger and in fluid communication with said inlet end of each of said condenser coolant tubes, a conduit connecting said lastnamed header to said outlet of saidl hydrogen fuel storage tank, a diaphragm operated control valve in said last-named conduit, a by-pass conduit connecting said inlet header of said air desuperheater portion of said heat exchanger to said last-named conduit between said valve and said hydrogen fuel storage tank, a relay with said valve, pneumatic instrument lines with said relay and with said condenser portion and said throat of said air desuperheater portion of said heat exchanger operable to sense pressures therein and operate said relay to control said valve and selectively provide liquid hydrogen to said condenser portion to thereby maintain a pressure drop between said throat of said air desuperheater portion and said condenser portion of said heat exchanger, a coolant outlet header positioned at the upper portion of said condenser portion of said heat exchanger and in fluid communication with said outlet end of each of said condenser coolant tubes, a conduit connecting said outlet header of said condenser portion with said bypass conduit to said inlet header of said air desuperheater portion of said heat exchanger, a check valve in said last-named conduit operable to permit coolant flow from said condenser portion to said air desuperheater portion of said heat exchanger only, a three-way valve having one outlet thereof operatively connected to said conduit connecting said outlet header of said air desuperheater portion of said heat exchanger to said burner nozzles of said engine, a coolant booster pump having the inlet thereof connected to another outlet of said three-way valve with the outlet of said pump being connected to said inlet of said hydrogen fuel storage tank, another conduit having one end portion secured to and in fluid communication with said last-named conduit between said check valve and said outlet header of said condenser portion and having the other end portion thereof connected to the inlet of said three-way valve, a relay with said three-way valve having temperature sensing means therewith operatively connected to said inlet and said outlet of said hydrogen fuel storage tank and operable to close said three-way valve to the passage of hydrogen fuel therethrough to said storage tank when said fuel reaches a predetermined temperature, a diaphragm operated control valve in said last-named conduit, a relay with said last-named control valve, a pneumatic instrument line with said relay and with said throat of said desuperheater portion of said heat exchanger operable in response to the temperature in said throat of said desuperheater of said heat exchanger to operate said relay to open said last-named control valve at a relatively low temperature in said throat and close said last-named valve at a relatively high temperature in said throat, a diaphragm operated control valve in said bypass conduit, said last-named control valve being operatively connected to said last-named relay to be opened at relatively high temperatures in said throat and closed at relatively low temperatures in said throat of said desuperheater portion of said heat exchanger, an air condensate well in said condenser portion of said heat exchanger opposite from said air desuperheater portion thereof, a liquid air conduit connected in one end portion to the outlet of said air condensate well and connected in the other end portion to said burner nozzles of said rocket engine, a bypass conduit connected in one end portion to an intermediate portion of said liquid air conduit and connected in the other end portion to the inlet of said liquid air storage tank, a liquid air pump in said liquid air conduit positioned between said air condensate well and said last-named bypass conduit to provide liquid air to said burner nozzles and to said liquid air storage tank, valve means in said liquid air conduit between said last-named bypass conduit and said burner nozzles with said valve means being controlled by the pressure of fluid passing through said conduit connected to said outlet header of said air desuperheater portion of said heat exchanger and said burner nozzles, a liquid air rectifying column on said liquid air storage tank opening into said liquid air storage tank and having a plurality of nozzles therein, a conduit connected in one end portion to said inlet of said liquid air storage tank and connected in the other end portion to said nozzles in said air rectifying column, an air rectifying column circulating pump in said last-named conduit to provide liquid air from said liquid air storage tank to said nozzle in said air rectifying column, a dump conduit extending from said air inlet diffuser portion of said heat exchanger to said exhaust portion of said rocket engine, a conduit connected in its end portions to said dump conduit and having the intermediate portion thereof surrounding the lower portion of said air rectifying column and operable to pass air from the atmosphere therethrough to provide heat to said air rectifying column and heat the liquid air therein and vaporize same, a valve in said last-named conduit, valve control means with said last-named valve operable to open and close same in response to the temperature in said air rectifying column, a conduit connected in one end portion to said conduit connected to said hydrogen fuel storage tank and to said inlet header of said condenser portion of said heat exchanger, the other end portion of said last-named conduit being connected to said conduit connected to said outlet header of said condenser portion of said heat exchanger with the intermediate portion of said lastnamed conduit being positioned around the upper portion of said air rectifying column to cool same and condense a portion of the vaporized air therein containing oxygen and return same to said liquid air storage tank, a valve in said last-named conduit having valve control means therewith operable to open and close said valve in response to the temperature within said column, an exhaust conduit secured in one end portion to the upper portion of said air rectifying column and secured in the other end portion to said dump conduit to discharge gases from said air rectifying column, a relief valve in said last-named conduit, a conduit secured in one end portion to said dump conduit and connected in the other end portion to the upper portion of said condenser portion of said heat exchanger and operable to receive and discharge to said dump conduit incondensable gases received by said condenser portion, and a gas pump in said last-named conduit, said rocket being constructed and adapted to be initially fueled with liquid hydrogen in said hydrogen fuel storage tank with said hydrogen being circulated through said heat exchanger with air from the atmosphere being received by said heat exchanger through said air inlet diffuser and condensed in said condenser portion and subsequently supplied to said liquid air storage tank and said burner nozzles of said engine by said liquid air pump and with hydrogen being burned in said engine to propel said vehicle.

2. The rocket as defined in claim 1 wherein said means to remove moisture from air includes a plurality of coolant tubes positioned at the inlet end of said air desuperheater and extending thereacross, an inlet header in fluid communication with the inlet end of each of said last-named coolant tubes, a conduit connected in its end portions to said last-named header and to said conduit connected to said outlet of said hydrogen fuel storage tank, an outlet header in fluid communication with the outlet end of said last-named coolant tubes, a conduit connecting said last-named header to said conduit connecting said outlet header of said air desuperheater portion of said heat exchanger to said burner nozzles of said engine, a plurality of fins mounted on said last-named coolant tubes in spaced relation, said fins on said last-named coolant tubes being cooled by the passage of hydrogen fuel therethrough to freeze thereon moisture in atmospheric air received from said air inlet diffuser.

3. A rocket comprising, in combination, ahousing having an open exhaust end portion and an open inlet end portion, fins secured to the outer surface of said housing at said exhaust end portion thereof and tapering toward the intermediate portion thereof with the upper end portion of said fins being in streamlined engagement with said housing, a rocket engine mounted in said housing having a combustion chamber with burner nozzles therein and an enlarged frusto-conical exhaust portion having one end portion thereof in communication with said chamber to receive exhaust gases therefrom and having the other end portion thereof opening to the atmosphere at said exhaust end portion of said housing, a liquid hydrogen fuel storage tank mounted within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a heat exchanger positioned within said housing and having a hollow air inlet diffuser portion in one end portion thereof positioned at said inlet endportion of said housing to receive air from the atmosphere, said heat exchanger having a centrally located air desuperheater portion in fluid communication with said air inlet diffuser portion and having a throat opening into an enlarged air condenser portion, means with the inlet of said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough, a plurality of coolant tubes passing through said air desuperheater portion of said heat exchanger, an inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header in fluid communication with the outlet end of each of said coolant tubes, conduit means connecting said outlet header with said burner nozzles of said engine, aplurality of coolant tubes in said condenser portion of said heat exchanger, a coolant inlet header positioned in the lower portion of said condenser portion of said heat exchanger and in fluid communication with the inlet end of each of said condenser coolant tubes, conduit means connecting said inlet header of said condenser portion and said inlet header of said air desuperheater portion of said heat exchanger to said outlet of said hydrogen fuel storage tank, a valve with said last-named conduit means having pressure sensing control means therewith and with said condenser portion and said air desuperheater portion of said heat exchanger to operate said valve and maintain a pressure drop between said air desuperheater portion of said heat exchangerand said condenser portion thereof, conduit means connecting said outlet header of said condenser portion to said inlet header of said air desuperheater portion of said heat exchanger, check valve means with said lastnamed conduit means operable to permit coolant flow from said condenser portion to said air desuperheater portion of said heat exchanger, hydrogen fuel coolant recirculating conduit means connected in one end portion to said last-named conduit means between said check valve means therein and said outlet header of said condenser portion of said heat exchanger, valve means having the inlet thereof connected to the other end portion of said hydrogen fuel coolant recirculating conduit means, coolant booster pump means having the inlet thereof connected to said last-named valve means to receive liquid hydrogen fuel from said liquid hydrogenfuel coolant recirculating conduit means and having the outlet thereof connected to the inlet of said hydrogen fuel storage tank to provide hydrogen fuel thereto under pressure, hydrogen fuel dump line conduit means connected in one end portion to said lastnamed valve means and connected in the other end tures in said air desuperheater portion of said heat exchanger, other valve means with said conduit means connecting said inlet header of said air desuperheater portion of said heat exchanger to said outlet of said hydrogen fuel storage tank and having control means therewith operable to open said valve means on high temperatures in said air desuperheater portion of said heat exchanger, an air condensate well in said condenser portion of said heat exchanger, conduit means connected to said air condensate well and to said burner nozzles of said rocket engine, pump means in said last-named conduit means, valve means in said last-named conduit means, between said pump means and said burner nozzles and having control means therewith to regulate the passage of liquid air therethrough, other conduit means connected in one end portion to said last-named conduit means between said pump means and said valve means and connectedin the other end portion to the inlet of said liquid air storage tank, an air rectifying column connected to said liquid air storage tank and opening thereinto, conduit means connected to said inlet of said liquid air storage tank and to said air rectifying column to provide liquid air thereto, pump means in said last-named conduit means, means with the lower portion of said air rectifying column to provide heat thereto to vaporize the liquid air supplied thereto, means with the upper portion of said air rectifying column to cool same and liquefy a portion of the vaporized air therein and return same to said liquid air storage tank, conduit means with said air rectifying column operable to receive and discharge to the atmosphere gases from said air rectifying column, said rocket being constructed and adapted to be initially fueled with liquid hydrogen in said liquid hy drogen fuel storage tank with said hydrogen being supplied through said coolant tubes to said condenser portion and said air desuperheater portion of said heat exchanger to condense air received by said heat exchanger and supply same to said liquid air storage tank and to said burner nozzles in combination with said liquid hydrogen for combustion therein to drive said rocket.

4. Rocket means comprising, in combination, a housing, engine means mounted in said housing and having an exhaust portion opening to the atmosphere at one end portion of said housing to discharge gases therefrom to drive said rocket means, liquid fuel storage tank means within said housing to receive and store a liquid fuel at relatively low temperatures, oxidizer storage tank means within said housing operable to receive and store a liquid oxidizer for said rocket engine means, heat exchanger means having an air inlet diffuser portion positioned to receive air from the atmosphere during flight of said rocket means, said air inlet diffuser having a relatively narrow neck portion, said heat exchanger having an air desuperheater portion with the inlet thereof at said neck of said air inlet diffuser portion, said heat exchanger having a condenser portion which is enlarged relative to said air desuperheater portion and positioned to receive air from said desuperheater portion, tube means within said condenser portion and said air desuperheater portion of said heat exchanger to receive and pass therethrough a fluid, conduit means operatively connecting said fuel storage tank means with the inlet and outlet of said tube means in said condenser portion and said air desuperheater portion of said heat exchanger to circulate fuel thereto and return same to said fuel storage tank means, conduit means operatively connected to said engine means and said fuel storage tank means to transfer fuel therefrom to said rocket engine for combustion therein, an air condensate well with said condenser portion of said heat exchanger to collect air condensed therein, conduit means connecting said air condensate well with said liquid oxidizer storage tank means and with said engine means, said rocket means being constructed and adapted to receive air from the atmosphere and condense same during operation and to provide said liquid air and said fuel to said rocket engine means for combustion therein to drive said rocket means.

5. Heat exchanger means for a rocket or the like having a housing with an engine mounted therein and said engine having a combustion chamber and an exhaust portion opening to one end portion of said rocket, an open inlet end at the other end portion of said housing, and hydrogen fuel storage tank means within said housing to receive and store liquid hydrogen, said heat exchanger comprising, in combination, an air inlet diffuser positioned at said other end portion of said housing to receive air from the atmosphere therein, said air inlet diffuser being frusto-conical in shape and having the relatively large end portion thereof positioned at said other end portion of said housing, an air desuperheater positioned at the relatively small end portion of said air inlet diffuser to receive air from said air inlet diffuser, said air desuperheater being elongated and having a throat at the end portion thereof opposite from said air inlet diffuser, a condenser positioned to receive air from said throat of said air desuperheater, a plurality of passes of coolant tubes in said desuperheater, a coolant inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header in fluid communication with the outlet end of each of said coolant tubes, a plurality of passes of coolant tubes in said condenser of said heat exchanger, a coolant inlet header positioned at the lower portion of said condenser and in fluid communication with the inlet end of each of said condenser coolant tubes, a

coolant outlet header positioned at the upper portion to said condenser and in fluid communication with the outlet end of each of said condenser coolant tubes, said inlet header of said air desuperheater and said inlet header of said condenser being operatively connectable to said hydrogen fuel storage tank to receive hydrogen fuel therefrom, said outlet header of said air desuperheater and said outlet header of said condenser being operatively connectable to said rocket engine, a conduit connecting said outlet header of said condenser to said inlet header of said air desuperheater, check valve means in said last-named conduit permitting fluid flow from said condenser to said air desuperheater only, said heat exchanger being constructed and adapted to in operation receive air from the atmosphere in said air diffuser and to condense same to be provided to said engine for combustion therein with said hydrogen fuel.

6. A rocket comprising, in combination, a housing having a generally cylindrical center portion joined at the ends to an open exhaust end portion and an open inlet end portion, a plurality of fins secured to said exhaust end portion of said housing tapering toward the intermediate portion of said housing with the upper end portion of said fins being in streamlined engagement with said housing, a rocket engine having a combustion chamber with burner nozzles and an enlarged frustoconical exhaust portion having the relatively small end portion thereof in communication with said combustion chamber to receive gases therefrom and having the relatively large end portion thereof opening to the atmosphere at said exhaust end portion of said housing, a liquid hydrogen fuel storage tank positioned within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a liquid hydrogen fuel surge tank positioned within said housing and having an inlet and an outlet, a heat exchanger positioned within said housing and having a hollow air inlet diffuser portion at one end portion thereof opening into a centrally located air desuperheater portion having a throat opening into an enlarged air condenser portion, means positioned in said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough, said air inlet diffuser portion of said heat exchanger being frusto-conical in shape and having the relatively large end portion thereof positioned at said open inlet end portion of said housing to receive air therein, a plurality of passes of coolant tubes in said air desuperheater portion of said heat exchanger, a coolant inlet header in fluid communication with the inlet end of each of the coolant tubes, a coolant dump conduit connecting said outlet header to said burner nozzles of said rocket engine, a plurality of coolant tubes in said condenser portion of said heat exchanger, a coolant inlet header positioned at the lower end portion of said condenser portion of said heat exchanger and in fluid communication with the inlet end of each of said condenser coolant tubes, a conduit connecting said last-named header to said outlet of said hydrogen fuel storage tank, a hydrogen fuel pump in said last-named conduit operable to provide hydrogen fuel under pressure from said hydrogen fuel storage tank to said inlet header of said condenser portion of said heat exchanger, a diaphragm operated control valve in said last-named conduit between said pump and said inlet header, a bypass conduit connecting said inlet header of said air desuperheater portion of said heat exchanger to said last-named conduit between said valve and said pump, a relay with said valve, pressure sensing means with said relay and with said condenser portion and said throat of said desuperheater portion of said heat exchanger operable to sense relative pressures therein and operate said relay to control said valve and selectively provide liquid hydrogen to said condenser portion to thereby maintain a pressure drop between said throat of said air desuperheater portion and said condenser portion of said heat exchanger, a coolant outlet header positioned at the upper portion of said condenser portion of said heat exchanger and in fluid communication with the outlet end of each of said coolant tubes therein, a conduit connecting said outlet header of said condenser portion with said bypass conduit to said inlet header to said air desuperheater portion of said heat exchanger, a check valve in said last-named conduit operable to permit coolant flow from said condenser portion to said air desuperheater portion of said heat exchanger only, a three-way valve having one outlet thereof operatively connected to said hydrogen fuel dump conduit, a conduit connecting another outlet of said three-way valve to said inlet of said hydrogen fuel surge tank, another conduit having one end portion secured to and in fluid communication with said conduit connecting said outlet header of said condenser portion with said bypass conduit and connected thereto between said check valve and said outlet header of said condenser portion of said heat exchanger and having the other end portion connected to the other end portion of said threeway valve, a diaphragm operated control valve in said last-named conduit, a relay with said last-named control valve, temperature sensing means with said lastnamed relay and with said throat of said desuperheater portion of said heat exchanger operable in response to the temperature in said throat of said desuperheater of said heat exchanger to operate said relay to open said last-named control valve at a relatively low tempera ture in said throat and close said last-named valve at a relatively high temperature in said throat, a diaphragm control valve in said bypass conduit, said last-named control valve being operatively connected to said lastnamed relay to be opened at relatively, high temperatures in said throat and closed at relatively low temperatures in said throat of said desuperheater portion of said heat exchanger, a conduit connecting said outlet of said hydrogen fuel surge tank to said fuel pump, a control valve in said last-named conduit, a relay with said last-named control valve having pressure sensing means therewith locatedwithin said condenser portion of said heat exchanger and operable to open said valve at high condenser pressures and close said valve at low condenser pressures, relay means with said three-way valve having pressure sensing means therewith operable to open said three-way valve to provide hydrogen fuel to said surge tank on low condenser pressures and operable to provide hydrogen fuel to said fuel dump line on high condenser pressures, a control valve in said conduit from said hydrogen fuel storage tank to said inlet header of said condenser portion of said air desuperheater and located between said hydrogen fuel storage tank and said pump, said last-named control valve being operated by said relay operating said control valve between said surge tank and said fuel pump and operable to close said last-named control valve on high condenser pressures and open said valve on low con denser pressures, an air conensate well in said condenser portion of said heat exchanger opposite from said throat of said air desuperheater portion thereof, a conduit connected in one end portion to the outlet of said air condensate well and connected in the other end portion to said burner nozzles of said rocket engine, a bypass conduit connected in one end portion to an intermediate portion of said last-named conduit and connected in the other end portion to said inlet of said liquid air storage tank, a liquid air pump in said conduit connected to said air condensate well with said pump being positioned between said air condensate well and said last-named bypass conduit to provide liquid air to said burner nozzles and to said liquid air storage tank, valve means in said conduit connecting said air conduit and said burner nozzles positioned between said lastnamed bypass conduit and said burner nozzles with said valve being controlled by the passage of fluid through said dump conduit to said burner nozzles, an air rectifying column on said liquid air storage tank opening into said liquid air storage tank and having a plurality of nozzles therein, a conduit connected in one end portion to said inlet of said liquid air storage tankand connected in the other end portion to said nozzles in said air rectifying column, an air rectifying column circulating pump in said last-named conduit to provide liquid air from said liquid air storage tank to said nozzles in said air rectifying column, a dump conduit extending from said air inlet diffuser portion of said heat exchanger to said exhaust portion of said rocket engine, a conduit connected in its end portions to said lastnamed dump conduit and having the intermediate portion thereof surrounding the lower portion of said air rectifying column and operable to pass air from the atmosphere therethrough to heat the lower portion of said air rectifying column and heat the liquid air discharged from said nozzles therein to thereby vaporize the liquid air, a valve in said last-named conduit, valve control means with said last-named valve operable to open and close same in response to the temperature in said air rectifying column, a conduit connected in one end portion to said conduit connected to said hydrogen fuel storage tank and to said inlet header of said condenser portion of said heat exchanger, the other end portion of said last-named conduit being connected to said outlet header of said condenser portion of said heat exchanger with the intermediate portion of said last-named conduit being positioned around the upper portion of said air rectifying column to cool same and condense a portion of the vaporized air therein containing oxygen and return same to said liquid air storage tank, a valve in said last-named conduit having valve control means therewith operable to open and close said valve in response to the temperature within said column, an exhaust conduit secured in one end portion to the upper portion of said air rectifying tower and secured in the other end portion to said last-named dump conduit to discharge non-combustible gases from said air rectifying column, a relief valve in said lastnamedconduit, a conduit secured in one end portion to said last-named dump conduit and connected in the other end portion to the upper portion of said con denser portion of said heat exchanger and operable to receive and discharge to said last-named dump conduit incondensable gases received by said condenser portion, and a gas pump in said last-named conduit, said rocket being constructed and adapted to be initially fueled with liquid hydrogen in said hydrogen fuel storage tank and with said hydrogen being circulated through said heat exchanger with air from the atmosphere being received by said heat exchanger through said inlet diffuser portion and condensed in said condenser portion thereof and subsequently supplied to said liquid air storage tank and said burner nozzles of said engine by said liquid air pump with a portion of the liquid hydrogen fuel being passed through said heat exchanger being provided to said surge tank during low condenser pressure and subsequently recirculated through said condenser portion and said airdesuperheater portion for subsequent cooling of air therein, and said hydrogen fuel being burned in said engine to propel said vehicle.

7. The rocket as defined in claim 6 wherein said means positioned in said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough includes a plurality of coolant tubes positioned at the inlet end of said air desuperheater and extending thereacross, an inlet header in fluid communication with the inlet end of each of said last-named coolant tubes, a conduit connected in its end portions to said last-named inlet header and operatively connected to said outlet of said hydrogen fuel storage tank, an outlet header in fluid communication with the outlet end of each of said last-named coolant tubes, a conduit connecting said last-named outlet header to said conduit connecting said outlet header of said air desuperheater portion of said heat exchanger to said burner nozzles of said engine, a plurality of fins mounted on said last-named coolant tubes and positioned in spaced relation, said fins on said last-named coolant tubes being cooled by the passage of hydrogen fuel therethrough to freeze thereon moisture in the atmosphere received therein.

8. A rocket comprising, in combination, a housing having an open exhaust end portion and an open inlet end portion, fin means secured to said exhaust end portion of said housing and tapering toward the intermediate portion of said housing with the upper end portion of said fin means being in streamlined engagement with said housing, a rocket engine having a combustion chamber with burner nozzles and an exhaust portion opening to said open exhaust end portion of said housing, a liquid hydrogen fuel storage tank positioned within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a liquid hydrogen fuel surge tank positioned within said housing and having an inlet and an outlet, a heat exchanger mounted within said housing and having an air inlet diffuser portion at one end portion thereof opening into an air desuperheater portion having a throat opening into an enlarged air condenser portion, means positioned in said air desuperheater portion of said heat exchanger to remove moisture from air passing there- -through, coolant tubes positioned in said air desuperheater portion of said heat exchanger, a coolant inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header positioned in fluid communication with the outlet end of each of coolant tubes, a coolant dump conduit connecting said outlet header of said desuperheater portion to said burner nozzles of said rocket engine, a plurality of coolant tubes in said condenser portion of said heat exchanger, a coolant inlet header positioned at the lower end portion of said condenser portion of said heat exchanger and in fluid communication with the inlet end of each of said coolant tubes, a conduit connecting said last-named header to said outlet of said hydrogen fuel storage tank, pump means in said last-named conduit operable to provide hydrogen fuel under pressure to said inlet header of said condenser portion of said heat exchanger, valve means positioned in said last-named conduit between said pump means and said inlet header of said condenser portion of said heat exchanger, control means with said valve means having pressure sensing means therewith located in said air desuperheater portion and said condenser portion of said heat exchanger and being operable to open and close said valve means to maintain a pressure drop between said throat of said air desuperheater portion and said condenser portion of said heat exchanger, bypass conduit means connecting said inlet header of said air desuperheater portion of said heat exchanger to said last-named conduit between said valve means and said pump means, a coolant outlet header positioned at the upper portion of said condenser portion of said heat exchanger and in fluid communication with the outlet end of each of said coolant tubes therein, conduit means connecting said outlet header of said condenser portion with said inlet header of said air desuperheater portion of said heat exchanger, other conduit means connecting said outlet header of said condenser portion of said heat exchanger to said dump conduit to provide hydrogen fuel thereto, valve means with said last-named conduit means and with said bypass conduit means having control means therewith operable to sense the temperature in said throat of said air desuperheater portion of said heat exchanger and open and close said valve means to regulate flow of said hydrogen fuel through said bypass conduit to said air desuperheater portion and from said outlet header of said condenser portion of said heat exchanger, conduit means connecting said hydrogen fuel surge tank and said hydrogen fuel storage tank to said last named conduit means between said valve therein and said dump conduit, conduit means connecting the outlet of said hydrogen fuel surge tank to said fuel pump and having control means therewith operable to sense pressures in said condenser portion of said heat exchanger to permit passage of fluid from said surge tank to said pump at high condenser pressures and prevent passage thereto at low condenser pressures in said condenser portion, an air condensate well in said condenser portion of said heat exchanger, conduit means connecting said air condensate well to said burner nozzles of said rocket engine and to said liquid air storage tank to transfer liquid air condensed in said condenser portion of said heat exchanger to said liquid air storage tank and to said burner nozzles, means with said liquid air storage tank operable to separate the liquid air into a nitrogen containing portion and an oxygen portion and discharge the nitrogen containing portion, said rocket being constructed and adapted to be initially fueled with liquid hydrogen in said hydrogen fuel storage tank and with a liquid oxidizer in said liquid air storage tank with said hydrogen and said oxidizer being supplied to said rocket engine during lift-off of said rocket with air from the atmosphere being received and condensed in said heat exchanger during flight of said rocket means and provided to said liquid air storage tank and to said rocket engine for oxidation of said liquid hydrogen during combustion therein.

9. The rocket as defined in claim 8 wherein said means positioned in said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough includes a pluralityof coolant tubes positioned at the inlet end of said air desuperheater and extending thereacross and being operatively connected in the inlet end thereof to said hydrogen fuel storage tank to receive hydrogen fuel therefrom, means operatively connecting the outlet end of said last-named coolant tubes to said rocket engine, and fin means mounted on said last-named coolant tubes, said fin means being cooled by passage of hydrogen through said last-named tubes to freeze thereonmoisture in the atmosphere passing therethrough.

10. Rocket means comprising, in combination, a housing having an open exhaust end portion and an open inlet end portion, stabilizing means secured to said housing, rocket engine means positioned within said housinghaving a combustion chamber therein and an exhaust portion communicating with the atmosphere at said open exhaust end portion of said housing, liquid hydrogen fuel storage means within said housing having an inlet and an outlet, liquid air storage means positioned within said housing, liquid hydrogen fuel surge tank means positioned within said housing and having an inlet and an outlet, heat exchanger means mounted within said housing and having an air inlet diffuser portion at one end portion thereof opening into an air desuperheater portion having a throat opening into an enlarged air condenser portion, said air inlet diffuser portion of said heat exchanger being positioned to receive air from the atmosphere therein durl ing flight of said rocket means through the atmosphere,

coolant tube means positioned in said condenser portion and said air desuperheater portion of said heat exchanger, conduit means operatively connected to the inlet end of said coolant tube means and to said hydrogen fuel storage means and said hydrogen fuel surge tank means to receive hydrogen fuel therefrom for passage through said tube means, conduit means operatively connected to the outlet end of said coolant tube means and tosaid hydrogen fuel storage means and said hydrogen fuel surge tank means and to said rocket engine means to pass fuel thereto, control means with said conduit means to regulate the passage of hydrogen fuel therethrough, a liquid air condensate well in said condenser portion of said heat exchanger to collect liquid air condensed therein, conduit means connecting said liquid air condensate well with said liquid air storage means and said rocket engine means, and means with said liquid air storage means operable to receive liquid air and remove a portion of the nitrogen therefrom, said rocket means being fueled with liquid hydrogen fuel in said hydrogen fuel storage means with said fuel being provided to said heat exchanger and said rocket engine means with said heat exchanger receiving and condensing therein air from the atmosphere and providing liquid air therefrom to said liquid air storage means and to said rocket engine means for oxidation of said hydrogen fuel during combustion thereof in said combustion chamber of said engine means to drive said rocket means.

11. A method of propelling a rocket or the like comprising the steps of, funneling air from the atmosphere through an air inlet of said rocket having an inlet area of 30 to 90 square feet then into a passageway and across a plurality of plates in said passageway, cooling the plates by placing liquid hydrogen fuel at approximately 45 R in heat conducting relation with the plates and cooling same and freezing and retaining thereon water and carbon dioxide from the atmospheric air, passing the resulting dried atmospheric air across a plurality of rows of fins in the passageway at a velocity of approximately Mach one, cooling the fins by placing liquid hydrogen fuel at approximately 45 R in heat conducting relation therewith and cooling the atmospheric air passing thereacross such leaving the throat of the passageway at a temperature of approximately 200 R, expanding the air leaving the throat of the passageway into a condenser at a pressure of from 10 to 3,000 pounds per square foot thereby further cooling same and simultaneously passing the air over a plurality of tubes containing liquid hydrogen fuel at approximately 45 R cooling the air to a temperature below R and condensing the condensable portions of the air, exhausting to the atmosphere incondensable neon and helium, collecting the resulting liquid air and pumping same to rocket engine means and to storage means floating on the line to the engine means, pumping a portion of the liquid air from said storage means to an air rectifying column and spraying same thereinto while simultaneously heating the lower portion of said column and cooling the upper portion of said column and fractionating the liquid air into a gaseous fraction containing nitrogen and a liquid fraction containing oxygen, exhausting to the atmosphere the resulting gaseous fraction containing nitrogen and returning the liquid fraction containing oxygen to said storage means, providing liquid hydrogen fuel previously used for cooling the air to the engine means and mixing same therein with the liquid air supplied thereto and burning the resultant mixture in a combustion zone, and exhausting the resulting gases to the atmosphere in one direction to thereby exert an equal force on the rocket or the like in the opposite direction.

12. The method as recited in claim 11 additionally comprising the step of recirculating a portion of the liquid hydrogen fuel used for cooling in the condenser through the condenser and the passageway for additional cooling of air passing therethrough.

13. A method of propelling a rocket or the like comprising, the steps of, funneling air from the atmosphere into a restricted passageway to increase the velocity thereof, cooling plates positioned across the inlet of the passageway and freezing thereon water and carbon dioxide from the air as it enters the passageway, passing the resulting dried air through the passageway at a velocity of approximately Mach one and simultaneously providing liquid hydrogen fuel at approximately 45 R to the passageway in heat conducting relation with air passing therethrough and cooling the air to its satura tion temperature with the air leaving the passageway in a gaseous state, passing the air into a condenser as it leaves the passageway, providing additional liquid hydrogen fuel at approximately 45 R to said condenser in heat conducting relation with the air in the con denser and cooling of the air therein and condensing the condensable portions of the air, removing the incondensable portions of the air from the condenser and discarding same, collecting the resulting liquid air and moving same to liquid air storage means, removing a portion of the liquid air from the storage means and fractionating the liquid air into a gaseous fraction containing nitrogen and a liquid fraction containing oxy-

Claims

1. A rocket comprising, in combination, a housing having a generally cylindrical center portion joined at the ends to an open exhaust end portion and an open inlet end portion, a plurality of fins secured to said exhaust end portion of said housing tapering toward the intermediate portion of said housing with the inner end portion of said fins being in streamlined engagement with said housing, a rocket engine having a combustion chamber with burner nozzles and an enlarged frusto-conical exhaust portion having the relatively small end portion thereof in communication with said chamber to receive gases therefrom and having the relatively large end portion thereof opening to the atmosphere at said exhaust end portion of said housing, a liquid hydrogen fuel storage tank positioned within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a heat exchanger positioned within said housing and having a hollow air inlet diffuser portion at one end portion thereof opening into a centrally located elongated air desuperheater portion having a throat opening into an enlarged air condenser portion, means positioned at the inlet of said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough, said air inlet diffuser portion of said heat exchanger being frustoconical in shape and having the relatively large end portion thereof positioned at said open inlet portion of said housing to receive air therein, a plurality of passes of coolant tubes in said air desuperheater portion of said heat exchanger, a plurality of spaced plates secured to said tubes with said plates being parallel to each other and to the axis of said air desuperheater portion of said heat exchanger, a coolant inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header in fluid communication with the outlet end of each of said coolant tubes, a conduit connecting said last-named header to said burner nozzles of said rocket engine, a plurality of coolant tubes in said condenser portion of said heat exchanger, each having the inlet end thereof at the lower portion of said condenser portion and having the outlet end thereof at the upper portion of said condenser portion, a coolant inlet header positioned at the lower portion of said condenser portion of said heat exchanger and in fluid communication with said inlet end of each of said condenser coolant tubes, a conduit connecting said last-named header to said outlet of said hydrogen fuel storage tank, a diaphragm operated control valve in said last-named Conduit, a by-pass conduit connecting said inlet header of said air desuperheater portion of said heat exchanger to said last-named conduit between said valve and said hydrogen fuel storage tank, a relay with said valve, pneumatic instrument lines with said relay and with said condenser portion and said throat of said air desuperheater portion of said heat exchanger operable to sense pressures therein and operate said relay to control said valve and selectively provide liquid hydrogen to said condenser portion to thereby maintain a pressure drop between said throat of said air desuperheater portion and said condenser portion of said heat exchanger, a coolant outlet header positioned at the upper portion of said condenser portion of said heat exchanger and in fluid communication with said outlet end of each of said condenser coolant tubes, a conduit connecting said outlet header of said condenser portion with said bypass conduit to said inlet header of said air desuperheater portion of said heat exchanger, a check valve in said last-named conduit operable to permit coolant flow from said condenser portion to said air desuperheater portion of said heat exchanger only, a three-way valve having one outlet thereof operatively connected to said conduit connecting said outlet header of said air desuperheater portion of said heat exchanger to said burner nozzles of said engine, a coolant booster pump having the inlet thereof connected to another outlet of said three-way valve with the outlet of said pump being connected to said inlet of said hydrogen fuel storage tank, another conduit having one end portion secured to and in fluid communication with said last-named conduit between said check valve and said outlet header of said condenser portion and having the other end portion thereof connected to the inlet of said three-way valve, a relay with said three-way valve having temperature sensing means therewith operatively connected to said inlet and said outlet of said hydrogen fuel storage tank and operable to close said three-way valve to the passage of hydrogen fuel therethrough to said storage tank when said fuel reaches a predetermined temperature, a diaphragm operated control valve in said last-named conduit, a relay with said last-named control valve, a pneumatic instrument line with said relay and with said throat of said desuperheater portion of said heat exchanger operable in response to the temperature in said throat of said desuperheater of said heat exchanger to operate said relay to open said last-named control valve at a relatively low temperature in said throat and close said last-named valve at a relatively high temperature in said throat, a diaphragm operated control valve in said bypass conduit, said last-named control valve being operatively connected to said last-named relay to be opened at relatively high temperatures in said throat and closed at relatively low temperatures in said throat of said desuperheater portion of said heat exchanger, an air condensate well in said condenser portion of said heat exchanger opposite from said air desuperheater portion thereof, a liquid air conduit connected in one end portion to the outlet of said air condensate well and connected in the other end portion to said burner nozzles of said rocket engine, a bypass conduit connected in one end portion to an intermediate portion of said liquid air conduit and connected in the other end portion to the inlet of said liquid air storage tank, a liquid air pump in said liquid air conduit positioned between said air condensate well and said last-named bypass conduit to provide liquid air to said burner nozzles and to said liquid air storage tank, valve means in said liquid air conduit between said last-named bypass conduit and said burner nozzles with said valve means being controlled by the pressure of fluid passing through said conduit connected to said outlet header of said air desuperheater portion of said heat exchanger and said burner nozzles, a liquid air rectifying column on said liquid air storage tank opening into said liquid air storage tank and having a plurality of nozzles therein, a conduit connected in one end portion to said inlet of said liquid air storage tank and connected in the other end portion to said nozzles in said air rectifying column, an air rectifying column circulating pump in said last-named conduit to provide liquid air from said liquid air storage tank to said nozzle in said air rectifying column, a dump conduit extending from said air inlet diffuser portion of said heat exchanger to said exhaust portion of said rocket engine, a conduit connected in its end portions to said dump conduit and having the intermediate portion thereof surrounding the lower portion of said air rectifying column and operable to pass air from the atmosphere therethrough to provide heat to said air rectifying column and heat the liquid air therein and vaporize same, a valve in said last-named conduit, valve control means with said last-named valve operable to open and close same in response to the temperature in said air rectifying column, a conduit connected in one end portion to said conduit connected to said hydrogen fuel storage tank and to said inlet header of said condenser portion of said heat exchanger, the other end portion of said

3. A rocket comprising, in combination, a housing having an open exhaust end portion and an open inlet end portion, fIns secured to the outer surface of said housing at said exhaust end portion thereof and tapering toward the intermediate portion thereof with the upper end portion of said fins being in streamlined engagement with said housing, a rocket engine mounted in said housing having a combustion chamber with burner nozzles therein and an enlarged frusto-conical exhaust portion having one end portion thereof in communication with said chamber to receive exhaust gases therefrom and having the other end portion thereof opening to the atmosphere at said exhaust end portion of said housing, a liquid hydrogen fuel storage tank mounted within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a heat exchanger positioned within said housing and having a hollow air inlet diffuser portion in one end portion thereof positioned at said inlet end portion of said housing to receive air from the atmosphere, said heat exchanger having a centrally located air desuperheater portion in fluid communication with said air inlet diffuser portion and having a throat opening into an enlarged air condenser portion, means with the inlet of said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough, a plurality of coolant tubes passing through said air desuperheater portion of said heat exchanger, an inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header in fluid communication with the outlet end of each of said coolant tubes, conduit means connecting said outlet header with said burner nozzles of said engine, a plurality of coolant tubes in said condenser portion of said heat exchanger, a coolant inlet header positioned in the lower portion of said condenser portion of said heat exchanger and in fluid communication with the inlet end of each of said condenser coolant tubes, conduit means connecting said inlet header of said condenser portion and said inlet header of said air desuperheater portion of said heat exchanger to said outlet of said hydrogen fuel storage tank, a valve with said last-named conduit means having pressure sensing control means therewith and with said condenser portion and said air desuperheater portion of said heat exchanger to operate said valve and maintain a pressure drop between said air desuperheater portion of said heat exchanger and said condenser portion thereof, conduit means connecting said outlet header of said condenser portion to said inlet header of said air desuperheater portion of said heat exchanger, check valve means with said last-named conduit means operable to permit coolant flow from said condenser portion to said air desuperheater portion of said heat exchanger, hydrogen fuel coolant recirculating conduit means connected in one end portion to said last-named conduit means between said check valve means therein and said outlet header of said condenser portion of said heat exchanger, valve means having the inlet thereof connected to the other end portion of said hydrogen fuel coolant recirculating conduit means, coolant booster pump means having the inlet thereof connected to said last-named valve means to receive liquid hydrogen fuel from said liquid hydrogen fuel coolant recirculating conduit means and having the outlet thereof connected to the inlet of said hydrogen fuel storage tank to provide hydrogen fuel thereto under pressure, hydrogen fuel dump line conduit means connected in one end portion to said last-named valve means and connected in the other end portion to said conduit means connecting said outlet header of said air desuperheater portion of said heat exchanger to said burner nozzles of said rocket engine, valve means in said liquid hydrogen fuel coolant recirculating conduit means having control means therewith operable to open said valve at relatively low temperatures in said air desuperheater portion of said heat exchanger, other valve means with said conduit means connecting said inlet header of said air desupeRheater portion of said heat exchanger to said outlet of said hydrogen fuel storage tank and having control means therewith operable to open said valve means on high temperatures in said air desuperheater portion of said heat exchanger, an air condensate well in said condenser portion of said heat exchanger, conduit means connected to said air condensate well and to said burner nozzles of said rocket engine, pump means in said last-named conduit means, valve means in said last-named conduit means, between said pump means and said burner nozzles and having control means therewith to regulate the passage of liquid air therethrough, other conduit means connected in one end portion to said last-named conduit means between said pump means and said valve means and connected in the other end portion to the inlet of said liquid air storage tank, an air rectifying column connected to said liquid air storage tank and opening thereinto, conduit means connected to said inlet of said liquid air storage tank and to said air rectifying column to provide liquid air thereto, pump means in said last-named conduit means, means with the lower portion of said air rectifying column to provide heat thereto to vaporize the liquid air supplied thereto, means with the upper portion of said air rectifying column to cool same and liquefy a portion of the vaporized air therein and return same to said liquid air storage tank, conduit means with said air rectifying column operable to receive and discharge to the atmosphere gases from said air rectifying column, said rocket being constructed and adapted to be initially fueled with liquid hydrogen in said liquid hydrogen fuel storage tank with said hydrogen being supplied through said coolant tubes to said condenser portion and said air desuperheater portion of said heat exchanger to condense air received by said heat exchanger and supply same to said liquid air storage tank and to said burner nozzles in combination with said liquid hydrogen for combustion therein to drive said rocket.

5. Heat exchanger means for a rocket or the like having a housing with an engine mounted therein and said engine having a combustion chamber and an exhaust portion opening to one end portion of said rocket, an open inlet end at the other end portion of said housing, and hydrogen fuel storage tank means within said housing to receive and store liquid hydrogen, said heat exchanger comprising, in combination, an air inlet diffuser positioned at said other end portion of said housing to receive air from the atmosphere therein, said air inlet diffuser being frusto-conical in shape and having the relatively large end portion thereof positioned at said other end portion of said housing, an air desuperheater positioned at the relatively small end portion of said air inlet diffuser to receive air from said air inlet diffuser, said air desuperheater being elongated and having a throat at the end portion thereof opposite from said air inlet diffuser, a condenser positioned to receive air from said throat of said air desuperheater, a plurality of passes of coolant tubes in said desuperheater, a coolant inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header in fluid communication with the outlet end of each of said coolant tubes, a plurality of passes of coolant tubes in said condenser of said heat exchanger, a coolant inlet header positioned at the lower portion of said condenser and in fluid communication with the inlet end of each of said condenser coolant tubes, a coolant outlet header positioned at the upper portion to said condenser and in fluid communication with the outlet end of each of said condenser coolant tubes, said inlet header of said air desuperheater and said inlet header of said condenser being operatively connectable to said hydrogen fuel storage tank to receive hydrogen fuel therefrom, said outlet header of said air desuperheater and said outlet header of said condenser being operatively connectable to said rocket engine, a conduit connecting said outlet header of said condenser to said inlet header of said air desuperheater, check valve means in said last-named conduit permitting fluid flow from said condenser to said air desuperheater only, said heat exchanger being constructed and adapted to in operation receive air from the atmosphere in said air diffuser and to condense same to be provided to said engine for combustion therein with said hydrogen fuel.

6. A rocket comprising, in combination, a housing having a generally cylindrical center portion joined at the ends to an open exhaust end portion and an open inlet end portion, a plurality of fins secured to said exhaust end portion of said housing tapering toward the intermediate portion of said housing with the upper end portion of said fins being in streamlined engagement with said housing, a rocket engine having a combustion chamber with burner nozzles and an enlarged frusto-conical exhaust portion having the relatively small end portion thereof in communication with said combustion chamber to receive gases therefrom and having the relatively large end portion thereof opening to the atmosphere at said exhaust end portion of said housing, a liquid hydrogen fuel storage tank positioned within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a liquid hydrogen fuel surge tank positioned within said housing and having an inlet and an outlet, a heat exchanger positioned within said housing and having a hollow air inlet diffuser portion at one end portion thereof opening into a centrally located air desuperheater portion having a throat opening into an enlarged air condenser portion, means positioned in said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough, said air inlet diffuser portion of said heat exchanger being frusto-conical in shape and having the relatively large end portion thereof positioned at said open inlet end portion Of said housing to receive air therein, a plurality of passes of coolant tubes in said air desuperheater portion of said heat exchanger, a coolant inlet header in fluid communication with the inlet end of each of the coolant tubes, a coolant dump conduit connecting said outlet header to said burner nozzles of said rocket engine, a plurality of coolant tubes in said condenser portion of said heat exchanger, a coolant inlet header positioned at the lower end portion of said condenser portion of said heat exchanger and in fluid communication with the inlet end of each of said condenser coolant tubes, a conduit connecting said last-named header to said outlet of said hydrogen fuel storage tank, a hydrogen fuel pump in said last-named conduit operable to provide hydrogen fuel under pressure from said hydrogen fuel storage tank to said inlet header of said condenser portion of said heat exchanger, a diaphragm operated control valve in said last-named conduit between said pump and said inlet header, a bypass conduit connecting said inlet header of said air desuperheater portion of said heat exchanger to said last-named conduit between said valve and said pump, a relay with said valve, pressure sensing means with said relay and with said condenser portion and said throat of said desuperheater portion of said heat exchanger operable to sense relative pressures therein and operate said relay to control said valve and selectively provide liquid hydrogen to said condenser portion to thereby maintain a pressure drop between said throat of said air desuperheater portion and said condenser portion of said heat exchanger, a coolant outlet header positioned at the upper portion of said condenser portion of said heat exchanger and in fluid communication with the outlet end of each of said coolant tubes therein, a conduit connecting said outlet header of said condenser portion with said bypass conduit to said inlet header to said air desuperheater portion of said heat exchanger, a check valve in said last-named conduit operable to permit coolant flow from said condenser portion to said air desuperheater portion of said heat exchanger only, a three-way valve having one outlet thereof operatively connected to said hydrogen fuel dump conduit, a conduit connecting another outlet of said three-way valve to said inlet of said hydrogen fuel surge tank, another conduit having one end portion secured to and in fluid communication with said conduit connecting said outlet header of said condenser portion with said bypass conduit and connected thereto between said check valve and said outlet header of said condenser portion of said heat exchanger and having the other end portion connected to the other end portion of said three-way valve, a diaphragm operated control valve in said last-named conduit, a relay with said last-named control valve, temperature sensing means with said last-named relay and with said throat of said desuperheater portion of said heat exchanger operable in response to the temperature in said throat of said desuperheater of said heat exchanger to operate said relay to open said last-named control valve at a relatively low temperature in said throat and close said last-named valve at a relatively high temperature in said throat, a diaphragm control valve in said bypass conduit, said last-named control valve being operatively connected to said last-named relay to be opened at relatively high temperatures in said throat and closed at relatively low temperatures in said throat of said desuperheater portion of said heat exchanger, a conduit connecting said outlet of said hydrogen fuel surge tank to said fuel pump, a control valve in said last-named conduit, a relay with said last-named control valve having pressure sensing means therewith located within said condenser portion of said heat exchanger and operable to open said valve at high condenser pressures and close said valve at low condenser pressures, relay means with said three-way valve having pressure sensing means therewith operabLe to open said three-way valve to provide hydrogen fuel to said surge tank on low condenser pressures and operable to provide hydrogen fuel to said fuel dump line on high condenser pressures, a control valve in said conduit from said hydrogen fuel storage tank to said inlet header of said condenser portion of said air desuperheater and located between said hydrogen fuel storage tank and said pump, said last-named control valve being operated by said relay operating said control valve between said surge tank and said fuel pump and operable to close said last-named control valve on high condenser pressures and open said valve on low condenser pressures, an air conensate well in said condenser portion of said heat exchanger opposite from said throat of said air desuperheater portion thereof, a conduit connected in one end portion to the outlet of said air condensate well and connected in the other end portion to said burner nozzles of said rocket engine, a bypass conduit connected in one end portion to an intermediate portion of said last-named conduit and connected in the other end portion to said inlet of said liquid air storage tank, a liquid air pump in said conduit connected to said air condensate well with said pump being positioned between said air condensate well and said last-named bypass conduit to provide liquid air to said burner nozzles and to said liquid air storage tank, valve means in said conduit connecting said air conduit and said burner nozzles positioned between said last-named bypass conduit and said burner nozzles with said valve being controlled by the passage of fluid through said dump conduit to said burner nozzles, an air rectifying column on said liquid air storage tank opening into said liquid air storage tank and having a plurality of nozzles therein, a conduit connected in one end portion to said inlet of said liquid air storage tank and connected in the other end portion to said nozzles in said air rectifying column, an air rectifying column circulating pump in said last-named conduit to provide liquid air from said liquid air storage tank to said nozzles in said air rectifying column, a dump conduit extending from said air inlet diffuser portion of said heat exchanger to said exhaust portion of said rocket engine, a conduit connected in its end portions to said last-named dump

8. A rocket comprising, in combination, a housing having an open exhaust end portion and an open inlet end portion, fin means secured to said exhaust end portion of said housing and tapering toward the intermediate portion of said housing with the upper end portion of said fin means being in streamlined engagement with said housing, a rocket engine having a combustion chamber with burner nozzles and an exhaust portion opening to said open exhaust end portion of said housing, a liquid hydrogen fuel storage tank positioned within said housing and having an inlet and an outlet, a liquid air storage tank positioned within said housing, a liquid hydrogen fuel surge tank positioned within said housing and having an inlet and an outlet, a heat exchanger mounted within said housing and having an air inlet diffuser portion at one end portion thereof opening into an air desuperheater portion having a throat opening into an enlarged air condenser portion, means positioned in said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough, coolant tubes positioned in said air desuperheater portion of said heat exchanger, a coolant inlet header in fluid communication with the inlet end of each of said coolant tubes, an outlet header positioned in fluid communication with the outlet end of each of coolant tubes, a coolant dump conduit connecting said outlet header of said desuperheater portion to said burner nozzles of said rocket engine, a plurality of coolant tubes in said condenser portion of said heat exchanger, a coolant inlet header positioned at the lower end portion of said condenser portion of said heat exchanger and in fluid communication with the inlet end of each of said coolant tubes, a conduit connecting said last-named header to said outlet of said hydrogen fuel storage tank, pump means in said last-named conduit operable to provide hydrogen fuel under pressure to said inlet header of said condenser Portion of said heat exchanger, valve means positioned in said last-named conduit between said pump means and said inlet header of said condenser portion of said heat exchanger, control means with said valve means having pressure sensing means therewith located in said air desuperheater portion and said condenser portion of said heat exchanger and being operable to open and close said valve means to maintain a pressure drop between said throat of said air desuperheater portion and said condenser portion of said heat exchanger, bypass conduit means connecting said inlet header of said air desuperheater portion of said heat exchanger to said last-named conduit between said valve means and said pump means, a coolant outlet header positioned at the upper portion of said condenser portion of said heat exchanger and in fluid communication with the outlet end of each of said coolant tubes therein, conduit means connecting said outlet header of said condenser portion with said inlet header of said air desuperheater portion of said heat exchanger, other conduit means connecting said outlet header of said condenser portion of said heat exchanger to said dump conduit to provide hydrogen fuel thereto, valve means with said last-named conduit means and with said bypass conduit means having control means therewith operable to sense the temperature in said throat of said air desuperheater portion of said heat exchanger and open and close said valve means to regulate flow of said hydrogen fuel through said bypass conduit to said air desuperheater portion and from said outlet header of said condenser portion of said heat exchanger, conduit means connecting said hydrogen fuel surge tank and said hydrogen fuel storage tank to said last-named conduit means between said valve therein and said dump conduit, conduit means connecting the outlet of said hydrogen fuel surge tank to said fuel pump and having control means therewith operable to sense pressures in said condenser portion of said heat exchanger to permit passage of fluid from said surge tank to said pump at high condenser pressures and prevent passage thereto at low condenser pressures in said condenser portion, an air condensate well in said condenser portion of said heat exchanger, conduit means connecting said air condensate well to said burner nozzles of said rocket engine and to said liquid air storage tank to transfer liquid air condensed in said condenser portion of said heat exchanger to said liquid air storage tank and to said burner nozzles, means with said liquid air storage tank operable to separate the liquid air into a nitrogen containing portion and an oxygen portion and discharge the nitrogen containing portion, said rocket being constructed and adapted to be initially fueled with liquid hydrogen in said hydrogen fuel storage tank and with a liquid oxidizer in said liquid air storage tank with said hydrogen and said oxidizer being supplied to said rocket engine during lift-off of said rocket with air from the atmosphere being received and condensed in said heat exchanger during flight of said rocket means and provided to said liquid air storage tank and to said rocket engine for oxidation of said liquid hydrogen during combustion therein.

9. The rocket as defined in claim 8 wherein said means positioned in said air desuperheater portion of said heat exchanger to remove moisture from air passing therethrough includes a plurality of coolant tubes positioned at the inlet end of said air desuperheater and extending thereacross and being operatively connected in the inlet end thereof to said hydrogen fuel storage tank to receive hydrogen fuel therefrom, means operatively connecting the outlet end of said last-named coolant tubes to said rocket engine, and fin means mounted on said last-named coolant tubes, said fin means being cooled by passage of hydrogen through said last-named tubes to freeze thereon moisture in the atmosphere passing therethrough.

10. Rocket means comprising, in combination, a housing having an open eXhaust end portion and an open inlet end portion, stabilizing means secured to said housing, rocket engine means positioned within said housing having a combustion chamber therein and an exhaust portion communicating with the atmosphere at said open exhaust end portion of said housing, liquid hydrogen fuel storage means within said housing having an inlet and an outlet, liquid air storage means positioned within said housing, liquid hydrogen fuel surge tank means positioned within said housing and having an inlet and an outlet, heat exchanger means mounted within said housing and having an air inlet diffuser portion at one end portion thereof opening into an air desuperheater portion having a throat opening into an enlarged air condenser portion, said air inlet diffuser portion of said heat exchanger being positioned to receive air from the atmosphere therein during flight of said rocket means through the atmosphere, coolant tube means positioned in said condenser portion and said air desuperheater portion of said heat exchanger, conduit means operatively connected to the inlet end of said coolant tube means and to said hydrogen fuel storage means and said hydrogen fuel surge tank means to receive hydrogen fuel therefrom for passage through said tube means, conduit means operatively connected to the outlet end of said coolant tube means and to said hydrogen fuel storage means and said hydrogen fuel surge tank means and to said rocket engine means to pass fuel thereto, control means with said conduit means to regulate the passage of hydrogen fuel therethrough, a liquid air condensate well in said condenser portion of said heat exchanger to collect liquid air condensed therein, conduit means connecting said liquid air condensate well with said liquid air storage means and said rocket engine means, and means with said liquid air storage means operable to receive liquid air and remove a portion of the nitrogen therefrom, said rocket means being fueled with liquid hydrogen fuel in said hydrogen fuel storage means with said fuel being provided to said heat exchanger and said rocket engine means with said heat exchanger receiving and condensing therein air from the atmosphere and providing liquid air therefrom to said liquid air storage means and to said rocket engine means for oxidation of said hydrogen fuel during combustion thereof in said combustion chamber of said engine means to drive said rocket means.

11. A method of propelling a rocket or the like comprising the steps of, funneling air from the atmosphere through an air inlet of said rocket having an inlet area of 30 to 90 square feet then into a passageway and across a plurality of plates in said passageway, cooling the plates by placing liquid hydrogen fuel at approximately 45* R in heat conducting relation with the plates and cooling same and freezing and retaining thereon water and carbon dioxide from the atmospheric air, passing the resulting dried atmospheric air across a plurality of rows of fins in the passageway at a velocity of approximately Mach one, cooling the fins by placing liquid hydrogen fuel at approximately 45* R in heat conducting relation therewith and cooling the atmospheric air passing thereacross such leaving the throat of the passageway at a temperature of approximately 200* R, expanding the air leaving the throat of the passageway into a condenser at a pressure of from 10 to 3,000 pounds per square foot thereby further cooling same and simultaneously passing the air over a plurality of tubes containing liquid hydrogen fuel at approximately 45* R cooling the air to a temperature below 140* R and condensing the condensable portions of the air, exhausting to the atmosphere incondensable neon and helium, collecting the resulting liquid air and pumping same to rocket engine means and to storage means floating on the line to the engine means, pumping a portion of the liquid air from said storage means to an air rectifYing column and spraying same thereinto while simultaneously heating the lower portion of said column and cooling the upper portion of said column and fractionating the liquid air into a gaseous fraction containing nitrogen and a liquid fraction containing oxygen, exhausting to the atmosphere the resulting gaseous fraction containing nitrogen and returning the liquid fraction containing oxygen to said storage means, providing liquid hydrogen fuel previously used for cooling the air to the engine means and mixing same therein with the liquid air supplied thereto and burning the resultant mixture in a combustion zone, and exhausting the resulting gases to the atmosphere in one direction to thereby exert an equal force on the rocket or the like in the opposite direction.

13. A method of propelling a rocket or the like comprising, the steps of, funneling air from the atmosphere into a restricted passageway to increase the velocity thereof, cooling plates positioned across the inlet of the passageway and freezing thereon water and carbon dioxide from the air as it enters the passageway, passing the resulting dried air through the passageway at a velocity of approximately Mach one and simultaneously providing liquid hydrogen fuel at approximately 45* R to the passageway in heat conducting relation with air passing therethrough and cooling the air to its saturation temperature with the air leaving the passageway in a gaseous state, passing the air into a condenser as it leaves the passageway, providing additional liquid hydrogen fuel at approximately 45* R to said condenser in heat conducting relation with the air in the condenser and cooling of the air therein and condensing the condensable portions of the air, removing the incondensable portions of the air from the condenser and discarding same, collecting the resulting liquid air and moving same to liquid air storage means, removing a portion of the liquid air from the storage means and fractionating the liquid air into a gaseous fraction containing nitrogen and a liquid fraction containing oxygen, exhausting the resulting gaseous fraction containing nitrogen to the atmosphere and returning the liquid fraction containing oxygen to the storage means, continuously transferring a portion of the liquid fraction containing oxygen to a combustion chamber of engine means, and simultaneously transferring to the combustion chamber a portion of the liquid hydrogen fuel used for cooling the air and mixing the fuel with the liquid fraction containing oxygen and burning the resulting mixture therein, the resulting gases being exhausted to the atmosphere in one direction and exerting an equal force on a rocket or the like in the opposite direction.

14. A method of propelling a rocket or the like comprising, the steps of, funneling air from the atmosphere into a restricted passageway and increasing the velocity thereof, removing water and carbon dioxide from the air as it enters the passageway, passing the resulting dried air through the passageway and simultaneously providing low temperature liquid hydrogen fuel to the passageway in heat conducting relation with air passing therethrough and cooling the air with the air leaving the passageway in a gaseous state, passing the air into a condenser, providing additional low temperature liquid hydrogen fuel to the condenser in heat conducting relation with the air therein and cooling of the air therein and thereby condensing the air, collecting the resulting liquid air and moving same to liquid air storage means, removing a portion of the liquid air from the storage means and fractionating same into a gaseous fraction containing nitrogen and a liquid fraction containing oxygen, exhausting the gaseous fraction containing nitrogen and returning the liquid fraction containing oxygen to the storage means, continually transferring a portion of the liquid fraction containing oxygen to a combustion chamber of engine means, and simultaneously transferring to the combustion chamber a portion of the liquid hydrogen fuel used for cooling the air, mixing the fuel with the liquid fraction containing oxygen and burning same in said combustion chamber, the resulting gases being exhausted to the atmosphere in one direction and thereby exerting an equal force on a rocket or the like in the opposite direction.