US2799987A - Solid fuel ramjet projectiles - Google Patents

Description

July 2,3-

` E. F. CHANDLER 2,799,987 soLxDnlU'ELv RgsMJET PROJECTILBS med Das. 31;'1952 Y' v s sheets-sheer 1 1N VEN TOR.

dward f'.- Chamdkr" Y ATTORNEY y July 23, 1957 E, F, CHANDLER 2,799,987

SOLID FUEL RAMJET PROJECTILES 3 sheets-sheer 2 Filed Deo. 3l, 1952 INVENTOR. giro/ward F. Chnc//cri M, TTRNEY July 23, 1957 E. F. CHANDLER soLID FUELVRAMJET PRoJEcTILEs 3 Sheets-SheetV 3 Filed De. S1, 1952 x GNN JNVENTOR. EYcu/erd E Chandler B Y HTTORNEY United States Patent G SOLID FUEL RAMIET PROJECTLES Edward F. Chandler, Brooklyn, N. Y,

Application December 31, 1952, Serial No. 329,022

3 Claims. (Cl. 60-35.6)

This invention relates to improvements in ramjet type projectiles and missiles.

An object of the invention is to provide a ramjet projectile or missile which employs substantially solid or compacted fuel for producing a reactive thrust to propel the same.

Another object of the invention is to provide a novel and improved ramjet projectile or missile in which there is a substantially solid or compacted fuel, which normally contains insuiiicient oxidizer to afford complete selfcombustion and hence must be supplied in whole or in part by oxygen from an induced airstream on passing through the air.

A further object of the invention is to provide a novel and improved ramjet projectile in which there is an inner chamber for the storage of a charge of solid fuel, powder or the like, which upon actuation and combustion produces high pressure gases to give a reactive thrust in a suitable jet nozzle, the fuel containing insufficient oxidizing material to support self-combustion, the projectile having one or more air intake ports to receive air during forward movement through the air, for affording complete combustion of the fuel under conditions of ramjet pressure-velocity and good etlciency.

Still another object of the invention is to provide a novel and improved ramjet projectile or missile in which air which is entrained by the ramming process during high velocity movement of the projectile through the air, supports the reaction or combustion of the fuel, so that the entire space available may contain fuel and little or no oxidizing material, greatly increasing the effective range over a case where the combustion supporter comprises a portion of the load, such as when using regular self-combustible rocket powder for fuel.

Still a further object of the invention is to provide a novel and improved ramjet projectile or missile in which the ambient air is rammed inside the projectile during movement through the air, and wherein the volume and weight of the products or gases discharged by the power jet nozzle is increased by the nitrogen content of 4the air, thus favoring a jet of high Velocity at lower pressures, because of the increased volume and weight of available gases, and other factors.

Still another object of the invention is to provide a novel and improved solid fuel ramjet projectile which may be pre-loaded like fixed ammunition substantially, and stored, shipped and easily handled in the field, for use against fixed targets or used as an anti-aircraft weapon of the interceptor type.

Another object of the invention is to provide a novel and improved ramjet projectile which is simple in design, inexpensive to manufacture, non-critical in operation, and easily launched into ight.

These and other objects and advantages of the invention will become apparent from the following description of a preferred embodiment thereof, as illustrated 1n the accompanying drawings, forming a part hereof, and in which,

rifice Figure 1 is a longitudinal sectional elevational view of one form of projectile.

Figure 2 is a transverse sectional elevational view taken substantially on plane 2 2 of Figure 1, but enlarged.

Figurel 3 is a itransverse sectional elevational view taken substantially on plane 3 3 of Figure 1, and on the same scale as that of Figure 1.

Figure 4 is a fragmentary longitudinal elevational view of the-projectile of Figure 1, substantially unsectioned.

Figure 5 is a longitudinal sectional elevational View showing another form of projectile according to the invention, portions of the view being shown in fragment.

Figure 6 is a longitudinal sectional elevational View showing a further form of projectile according to the invention, portions of the structure being shown in fragment.

VFigure-7 is a longitudinal sectional elevational View showingV still'another form of projectile according to the invention.

Figure 8 is a transverse sectional elevational View taken substantially on plane 8 8 of Figure 7.

Figure 9 is a transverse sectional elevational View taken substantially on plane 9 9 of Figure 7.

Figure 10 is a transverse sectional elevational view taken substantially on plane 10 10, showing the construction at the plane of the section, on Figure 5.

Figure 11` is a transverse sectional elevationalview taken substantially on plane 11-11 of Figure 6, showing the construction at the plane of the section.

`This ,application is copending with my patent application, Serial Number 174,685, tiled July 19, 1950, and entitled Reaction Automotor, which has become abandoned.

In the design and construction of self propelled projectiles or missiles, it is important that the space available in the casing be utilized to the best advantage, so that there is a high pay load capacity in relation to the total weight ofthe projectile itself. For a given range and size of projectile,r the use of a solid Vfuel or compacted powder fuel rocket typey projectile motor necessitates providing a quantity of oxidizing material, with added weight therefor, or corresponding loss in quantity of fuel to make room for the added oxidizing material, sor that the range is shortened considerably. The present` invention discloses a projectile in which solid or compacted powder fuel is used, but with oxidant Vsupplied from the ambient air through which the projectile moves in flight, by the ramjet action, sothat a greater quantity of fuel may be carried in-the projectile itself, and hence a better range and performance may be achieved therefor.

The propellant charge is preferably of a type containing insufficient oxidizer to alord self-combustion, and hence must be supplied in whole or in part by oxygen from the inducedv airstream therethrough from the ambient air through which the projectile passes. Such a projectile may be used as an anti-aircraft weapon of the interceptor type, as well as for other uses against many types of targets. It may be made as a pre-loaded missile well adapted to be stored, shipped and easily handled in the field, and to be fired from a suitable launcher of light mobile design. By taking the usual oxidizingrmaterialout of the rocket powder charge, and employing rammed air for its oxidizing properties in supporting combustion,` a marked and substantial increase in operating characteristics results, with increased ran-ge, and further the volume and weight of the products discharged byk theypower jet nozzle is increasedV by the nitrogen content of the rammed air, with good efhciency;

` The; ramjet missile'of -the kind under discussionV herein, depends upon the ambient air as the reaction support- K the chemical characteristics of which may, Ifor present purposes, be assumed as substantially fixed, or `at least fairly well understood. However, with respect to the fuel or interacting agent, there is considerable latitude for the development and selection of 'a'product or compound, admixture or the like,radapted to react, when ignited or actuated, economically and efficiently to produce ya desired and improved Yend res-ult with respect to reaction rate, gas volume evolved, temperature produced, and the like. V t

Preferably the fuel or reaction compound would be of anrorder permitting the s-ame to lbe molded or otherwise formed, so that when ready for -use it would be in a solid or semi-plastic condition, 'and of a shapeY or design or contour bestsuited for the purpose intended. lIn its simplest form, the fuel might comprise a block or 4a V.perforated tube of carbon or'othersuitable carbonaceous material, charcoal, activated carbon, yor'other materials; Materials of this order may be powdered, mixed, with a petroleum hydrocarbon, tar, or the like, 'and molded to aidesiredV form. YTo accelerate the reaction effect an roxygen-'rich chemical, for example, such as tetra-nitromethane 'may be combined'withrthe fuel. The admixture -may be formed Vto shape under suicient ypressurevto provide a vcohesive mass or, a suitable binder may be employed Isuch as resin, gum, hydrated cellulose, or the like, or the formed mass may be heat treated to a point sufficient to-establish cohesion-within the mass, so that when cool, a substantially rigid or firm ibody is obtained. To increase'the heat release of the reaction, a suitable metal in iinelydivided form, such as aluminum, Ymagnesium, copper, or the like, may be included in 'a fuel compound. Y t

Except to establish by certain examples that the principle disclosed is advantageous and practicable, it is not my purposeherein to limit myself to any particular fuel ,or-reaction agent except possibly with respect tothe launching powder charge which may be a Suitaible type of rocket propellant powder, a double-base smokeless powder or other powder presently known, as for instance in theY so-called bazooka missile, although other known types may also bevused.V Regarding the main powder charge or fuel lfor propelling the ramjet missile subsequent to launching, a projectile according to the invention, would =be ,equipped with la fuel or reactionV compound 'best adapted for the purposes intended, as taught by the principles disclosed herein.

In order to understand Ythe nature of the invention andthe best meansfor carrying it out, reference may now ibe had to the drawings, in which like numerals denote Ysimilar parts throughout the several views.

As seenV in Figure 1, there is a projectile generallyindicated at 20, and having a projectile body '22, suitably contoured on its outer Surface for streamlining as seen, for efficient flight. A suitable warhead 24 may be carried on the Iforward end of the projectile body, and may havesuitable means 26 -such as a fuse or the like, Ifor exploding the head 24 and its exploding charge 28 -upon a direct hit, or when in the vicinity of -a target. Also it is understoodthat the means 26 may ibe provided with homing means to insure a hit, and such means may comprise sonic responsive means subject to vibrations emitted by'an enemy plane or aircraft in Ia manner to steer the projectile tothe target.

t =In the body and aft of the head 24 are a number of air intake ports or openings 30 opening upon the side and' forward portion of the projectile so as to fbe in the path ofVv air through which the projectile is moving, so as to gulp up or entrain the air, which is thus rammed into the air intake ports 30 and compressed in being rammed. The air induction ports 30 communicatethrough ducts 32 with an interior air reception vestibule or chamber 34, so that the air is rammed into the vestibule 34 and tends to be thus forced rearwardly, or leftwardly, in a high degree of compressment, into axialv bore or tube` 36 4which runs through the interior of the mainpowder receiving chamber 38 forming the axial bore of the hous- Iing I22. Such chamber 38 'has a rearward curved combustion 4chamber por-tion '40, and a forward Wall 42.

At the rearward end of the housing 22, it is somewhat constricted or reduced smoothly as at 44, and a main power jet nozzle 46 communicates with the combustion chamber portion `40 as seen best in Figure 1, to receive the lgaseous products of combustion or reaction, and produce a reactive thrust therefrom. In the main charnber 38 is disposed the main solid or compacted fuel charge 50 for propelling the projectile by evolving high pressure gases for jet nozzle 46 upon actuation thereof. This charge 50 of powder -or the like, is preferably propellant rocket powder which is deficient in oxygen, so that it will not 4support complete combustion of charge 50 unless additionalV air is supplied. Charge 50 may have an axial bore 36 extending therethrough, allowing air from air scoops 30 to flow into bore 36.

A charge of self combustible rocket propellantfpowder of `any Well known composition is disposed at 52 in bore 36, which maybe somewhat enlarged as shown, to receive the cylindrical charge 52, and the rearward or leftward end of the charge.52 may be holl'owed out somewhat as -seen at 54, to receive a primer `5'6 which may be percussion ignited vor arranged with wires v53V to connect with a battery to ignite by heat, to set off charge 52, and ultimately charge 50, producing 'high pressure `and temperature gases to .actuate main jet nozzle 46. 'Suitable stabilizing means such `as tail rudders 60 mounted pivotally in vanes or ns 62, so as to control vvflight, would be governed in any well known manner, as by gyro-system, or from a remote control station #by radiant energy, radar, or -other means.

. rThe missile may also have intermediate wings. or vanes 64 also for stabilizing its flight and/or providing some lift where needed. The missile preferably would be tired from a suit-able launcher of light mobile design. When aimed and ready, chargeqS is actuated,vsetting olf charge 52, to evolve hot high pressure gases in chamber Y 40 for energizing the ,nozzle 46, for driving the projectile initially. When the charge 52 `is consumed, a suitable channel or channels 36 Vare opened 'by the absence of this initial powder, thereby letting the air from air intake ducts 30 pass through in the Vdirection of arrows 70, to aidv in the combustion of powder 50, which has vbeen highly heated lby the burning of the launching powder 52. The air thus passes rearwardly throughV the bore or bores 36 in the main charge 50, under ramjet pressurevelocity, and causes the charge 50 to burn forwardly, that is, contra-flow from the ignition surface 53.

By utilizing entrainedrair through air scoops 30 to support the reaction, practically the entire space available, such as in chamber 40 between walls 41 and 42, may

contain fuel, thus greatly increasing the effective range t products discharged by the power jet 45 is increased byV the nitrogen content of the air. This method and construction favors a jet of high velocity with lower pressures, because of the increased volume and Weight of available rammed air and gases entering at 30. The drawing in Figure l is purely substantially schematic, it being understood that modifications andchanges may be made to improve aerodynamic form, stability in ight, and increase operational functions. The air inlet or inlets 30 may be ramjet action. And the bore or bores 36 through the charge 50 may be formed to favor desired reaction effect by insuring contact of the air and/or interacting'agents, so I do not wish to be confined tota single axial bore 36, since other arrangements may be employed.

I Referring now to Figure 5, it is seen that it is another fonn of projectile according to the invention, in which 'there is a projectile body 70 having,r stabilizing wings or vanes 72 at an intermediate location, and reduced "at its rearward end as at 74 to provide a main jet nozzle 76 for producing. a reactive thrust as at 78. Tail stabilizers or vanes are provided as at 80, and they may be equipped with steering apparatus if desired. The projectile body 70 is thus formed with an interior chamber 82 inside its wall 84, and has a war head carried at 86 and extending rearwardly inside the opening 88 thereof, so as to allow for air entry space as at 90vto ram air therein on moving at high velocity through the ambient air while in flight. An annular charge of rocket propellant powder 92 is disposed coaxiallyin chamber 82, and spaced from the wallv 84 of the housing to denne the annular ram air passageway 94 therebetween. Radial ribs or other means may be used to support the charge 92 in axial position as shown, and venturi guide vanes or bulges 98 are also supported in position as shown, by anyv suitable means, to provide increase in velocity of incoming Aair in the direction of arrows 100.V The main charge 92 has an axial bore 102 which is open at its forward or right end, but closed at its rearward or 'leftend as seen. in`r Figure .5, by the launching powdercharge l104 seated therein. Charge 104 may be of` regular rocket powder composition,` so as to be self combustible, containing suitable oxidizing material and hence is not self combustible. unless voxygen from ambient air is added thereto by ramming action through ports S8. A plug 106 .of suitable ignition powder may also be employed to insure that the reaction initiated by heat from charge 104 may be employed.

As seen in Figure 5, upon launching, some ram air entering at openings 8S, passes rearwardly to flow in the direction of arrows 100, to intermix with the reaction products of the launchingv charge 104, increasing the volume and weight of nozzle discharge and reducing the head resistance. The air channel 102 is normally closed by the launching charge 104, positioned within the propellant rocket charge 92, which requires air to support its combustion. A suitable incoming rammed air guide shield collar 110, annular in shape, may be positioned as shown in Figure 5, to aid in guiding theair, and may have openings as at 112 to allow some air to flow therethrough into axialbore. 102 of the main charge. Similarly, a guide cone 120 may be positioned permanently as shown, forwardly of charge 92, for guiding the reaction: products into the throat of the rnain jet nozzle 76...

Figure 6 shows another form of projectile for use in obtaining increased performance characteristics. In this view there is a projectile body 130 having a wall 132 defininga main chamber134, and reduced at its rearward end as at 136 to integrate smoothly with the main jet nozzle 138 which discharges rearwardly as at 140, to produce a reactive thrust. Stabilizing tail iins 142 may be carried at the tail end, and similarly there may be intermediate wings 144 on the body to regulate and guide movement of the projectile as desired. The body is reduced at 146 to receive the war head 148 which is smoothly curved at 150 to define a chamber 152 to receive control or regulating or homing and steering controls as needed, and closed by wall 154.

Air ramming induction openings 156 are formed as shown, so that when the projectile moves rightwardly as seen in Figure 6, air is rammed into the openings 156 at high velocity and in high compression, through air ducts 158, and into the axial tube extension 160, and also through the openings 162 into space 164 and in the direction of arrows 166 into the combustion space 168. A reaction agent or powder 170 is adapted to discharge its reaction products or gases forwardly, having an axial bore or throat passage 164 as shown, through which tube 160 extends. The charge 170 is of a nature which will not support combustion by itself, being deficient or lacking in oxidizing materials or the like, and needs ambient rammed air to supply oxygen thereof and therefor. Such rammed air is supplied by tube 160, to support and enhance the combustion of charge 170. The launching charge v of self-combustible powder may be actuated in any. desired manner, as by electricity or a percussion c ap, andthe burning of this charge 180 may providethe heat for'initiating the reaction of charge 170 and the rammed air, through the fuse 182, or in any suitable manner.` A wall 184Y and another wall at 186, may be forrned` of metal or ceramic material as desired, to provide desired compartmentation, and supported on ribs for centering as shown.

As seen in Figures 5 and 6, the rearward passage of air throughthe outer channels such as 82 and 134 serve to reduce drag or head friction during the brief launching period.Y lt will be noted that while causing air to be passed through a relatively restricted channel within the missilel would normallytend to increase head resistance, due to friction, this tendency is` overcome in the present instancebecauseof the action of the launching powder charge. That is, the ram-air is drawn into the stream of reaction products being discharged from the power jet, thereby accelerating the ow of said air which action tends to aid the initial night velocity, that is, during the launchingperiod andv in preparation for the power drive initiatedV thereby.

The schematic illustrations being shown will be understOQflS showing only some of the proposed airk guide paths, and it will be understood that they may be modied in anyk well Yknown manner to insure cooperation between the, launching reaction and the air initially entering the reaction zoneanother effect being the increase in volume and Weight of the nozzle discharge beyond that of the, powder alone, thusv augmenting theV power Vlaunching thrust.

Referring now to Figure 7, it is seen that there is il# lustrated another form of the projectile according to the invention, in which there is a projectile body 190, provided at an intermediate portion with stabilizing or flight wings or vanes 192, and at its tail end portion with stabilizing vanes or the like 194. The body 190 is thus hollow, with a relatively thin wall 196, which is convergent at the forward end portion 198 to denne. an air ram intake opening199, and convergent at the rearward end portion 202 to terminate in the main jet nozzle. 20.4.,

An isentropic curved diffuser body 206, somewhat sharply conical at its forward end 208 to decrease the shock waves, and smoothlyV rounded at 210, is disposed inside the air inlet passageway 212 in the manner shown, so as to be spaced from wall 196 at all points, being supportedaxially by ribs or other suitable means, carried by wall 196 or otherwise. The main jet nozzle block 214 is shaped as shown, being expanded somewhat to form a combustion chamber at 216, into which the guide nozzle 213 opens. A main propellant charge 220, annular in section, is disposed concentrically in the bore of housing 196, and it has an axial bore 222 to receive at one end the launching powder charge 224. The charge 224 is one which is formed with oxidizing material suiiicient to support its combustion, whereas the charge 220 is formed of powder or the like which has little if any oxygen or oxygen bearing materials, so that it will not support its own combustion, and needs ambient rammed air for this purpose to attain complete combustion. The air enters at 199 at high velocity due to the speed of the launched missile, owing in the direction of arrows 230, through the air passage 212 around the isentropic diffuser 206, and it is seen that at location 232 there is a change in air pressure, due to the shape of the diffuser 206, the air speed being slowed down and then increased in velocity, as it enters the constricted passage at location 234. A closure cap 236 closes the left end of the bore 222 and also the left end of the charges 224 and 220, being supported in any suitable manner. Actuation of charge 224, produces high pressure launching gas in bore 222 to pressurize nozzle 218 and main nozzle 204, launching the projectile, and at the same time being V7 arranged to ignite main charge 220. Air being rammed into Vthe housing, ows'through air channel 230, Vandthe wall orlplate`-2`36 isby then burned away, being formed of burnable' materials,` allowing the rammed air to ow through the bore of the main charge 220, aidingin burning the same, and aiding by injection means in inducing ow of the rammed air also in channel 230, Vwhen the launching charge has been consumed. VGood intermixfture ofV air andV gaseous products takes placein combustion chamber 216, producing a high velocity mainv jet thrust of considerable magnitude. Y

Although I have described my invention in specilic terms, it will be understood that various changes may be made in size, shape, materials and arrangement' without departing from the spirit and scope of the invention. i

YI claim: Y

' 1. A ramjet projectile* comprising a projectile body having a combustion chamber formed therein, a reaction nozzle forming an 'outlet at the rear of said combustion chamber, a cylindrical'main propelling charge disposed in said combustion chamber and spaced from the interior wallslhereof to `define an Yairpassageway therebetween, the forward portion of said projectile body being reduced, permanently 'open air intake openings formed in said body to receive rammed `air through which said projectile t moves, said main charge having an axial bore formed therethrough, said main propelling charge being deficient in oxygen furnishingmaterial, a second charge containing oXYgen furnishing. material'disposed in the rearward end of said bore` to block the same, and means for igniting said second charge, for producing launching gas pressureV for said projectile, and upon being consumed, unblocking said Vbo'reto allow said rammed air to ow through saidr'bore and/through said space between said charge and the interior of said chamber, for supporting combustion thereof upon' 'ignition by said second charge',V for undergoing ramjet action and continuing in ramjet flight,

and wherein there is an air guide casing in said combus-V tion chamber adjacent the forward end ofhsaidimain propelling charge, and having openings to allow rammed air to'enter said bore of .said main propelling charge and for guiding said air.

' 2'. A ramjet projectile comprising a projectile body having a combustion chamber formed therein, a reaction Vnozzle forming an outlet at the rear of said combustion therethrough, said main propelling charge Vbeing' decient in oxygenfurnishing material, a second charge containing oxygen furnishing .material disposed in the "rearward end Yof said bore'to'block the same, and means for igniting guide some of the rammed airinto said main charge bore, Y

Yand'whereinthere is van air and jet guide casing in the rearward portion of said combustion chamber, for guiding air and products of combustion toward said reaction noz- Azle of said projectile-`A 3. A ramjet projectile comprisingra projectile body having a combustion chamber formed therein, af reaction nozzle forming anoutlet at the rear of saidl combustion chamber,'a Vcylindrical main propelling charge disposed in said combustion chamber Vand spaced from the interior walls thereof to define an air passageway therebetween, the forward portion'of said projectile body being reduced,

Vpermanently open air'intake openings formed in said body to'receive rammed air vthrough which said projectile moves, said main'charge having an Vaxial bore formed therethrough, said 'main propelling charge being deficient in oxygen furnishing material, a second charge containingV oxygen furnishing material disposed in the rearward end of said bore kto block theV same, and means for igniting said second charge, for producing launching gaspressure for said projectile, and upon being consumed, unblocking said bore to allow saidV rammed air to oW through said bore and through Ysaid space between said charge and the'interior. oftsaid chamber, for supporting combustionl Y thereof upon ignition by said second charge, for iunder'-v going ramjet action Vand continuingin ramjet Hight, v'and wherein constrictions are disposed in said space between said charge and the interior of said combustion chamber, for enhancing ,the velocity of air ow therethrough.

References Cited inthe file of this patent UNITED STATES PATENTS Y MacDonald Oct. 14, 1952 Great Britain Mar. 26, V1952

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