US3048107A - Air frame center support - Google Patents

Description

Aug. 7, 1962 A. SAMMS AIR FRAME CENTER SUPPORT 3 Sheets-Sheet 1 Filed Sept. 27, 1961 Add BY INVENTOR hus Sam ms 2 48045401- a; BMW

Aug. 7, 1962 A. SAMMS 3,048,107

AIR FRAME CENTER SUPPORT Filed Sept. 27, 1961 5 Sheets-Sheet 2 j i-flyzaac 9 4. a Q41 Aug. 7, 1962 I A. SAMMS 3,048,107

AIR FRAME CENTER SUPPORT Filed Sept. 27, 1961 3 Sheets-Sheet 3 INVENTOR. Adml ahus Ex arm-ms:

jigfbzaou w a. a @MMZL 3,48,1ll7 Patented Aug. 7, 1962 The invention described herein may be manufactured and used by or for the government for governmental purposes without the payment to me of any royalty thereon.

This invention relates to an air frame center support for a missile and more particularly to a multiple stage missile having expendable fuel tanks and frame structure and employing a single thrust chamber in order to provide a missile which becomes lighter in weight as its flight progresses.

When a multiple stage missile blasts off or is accelerating in flight, it must lift not only the weight of its structure but also the weight of its fuel as well. Lifting of the fuel is therefore dead loss and the burning rate must he stepped up to its limit in order to lessen this loss. Engineers are greatly concerned with the ratio of fuel load to total mass. The higher this ratio, the poorer the missiles ability to carry freight (pay load) because a larger portion of the weight must be in fuel. Hence, gigantic missiles are required to lift small pay loads.

It is customary for multiple stage missiles to be operated by first, second and third stage rocket motors and each stage carries in addition to its own rocket motor, a fuel tank, a supporting frame and accessories.

It is evident, therefore, that the missile needs a light weight air frame to be able to carry a larger pay load. The effect of this is to leave behind by dropping on the ground as much dead weight as possible. Discouraging weight penalty can be expressed as follows: For every pound of weight added to the missile, an acceleration of 80 feet per second must be paid in its speed.

It is, therefore, a primary object of this invention to provide a multi-stage missile powered by a single power plant through all stages.

It is another object to provide a missile having a progressively expendable air frame as well as fuel tanks.

It is still another object to provide a means for a single rocket motor to slide, under its own power, up against the next stage upon jettison of the preceding stage.

A further object is to provide a missile having an air frame that is light in weight and possess great strength.

A final object of the invention is to provide an air frame which is economical and simple in construction.

The specific nature of the invention as well as other objects and advantages thereof, will clearly appear from a description of a preferred embodiment as shown in the accompanying drawings in which:

FIG. 1 is a perspective view of a multiple stage missile showing the first stage fuel tanks as jettisoning aft and the rocket motor shown in dotted lines, contacting the second stage;

FIG. 2 is an enlarged side view, partly in section, showing the first stage and rear portion of the missile and the refueling system in section, the first stage fuel tanks being shown as attached and in refueling position;

FIG. 3 is a section taken along line 3-3 of FIG. 1;

FIG. 4 is a schematic plan view of a missile showing the air frame supporting structure;

FIG. 5 is an exploded perspective view of one of the air frame shafts;

FIG. 6 is a detail showing the ratchet and pawl arrangement on the air frame for preventing the rocket motor from rearward movement along the frame;

FIG. 7 is a cross section, on a greatly enlarged scale, showing the release means for unlatching the semicircular tanks;

FIG. 8 is a somewhat schematic detail showing the connection between two air frame shafts;

FIG. 9 is a fragmentary view showing the rocket motor advancing towards an adjacent stage; and

FIG. 10 is a perspective view of a heavy type missile in which the first stage is provided with separate rocket motors, the first stage tanks being shown as jettisoned off the frame.

Referring more particularly to FIG. 1 of the drawing, a missile is shown in flight and is indicated generally by 1. The missile includes a rocket motor, indicated generally by 2, a pair of air frame shafts, indicated generally by 3, semicircular fuel tanks, indicated generally by 4, and a warhead, indicated generally by 5.

As seen in FIG. 1, first stage tanks 4 have just been jettisoned off and away from the frame 3, after which rocket motor 2 will slide up on shafts 3 to assume a position as shown in dotted lines where it becomes connected automatically to the next stage tanks 4.

The fuel system comprises semicircular tank halves indicated by 6 and 7 which are identical in all three stages.

As shown in FIG. 2, rocket motor 2 is provided with a tank 8 of its own which is divided into two equal compartments 9 and 19, having outlet conduits 11 and 12 respectively for furnishing a fuel and an oxidizer to the rocket motors 13 and 14.

The rocket motor 2 may be of the same construction as that shown in my co-pending application Serial No. 859,076, filed December 11, 1959. However, other types of rocket motors are readily adaptable to the device of the invention.

As shown in FIG. 2, the first stage 4 is connected to the tank 8 of the rocket motor.

Each stage 4 consists of a pair of semi-circular compartments 15 and 16 for containing fuel and oxidizer and are provided with planar inner faces 17 and 18. Each face is provided with a pair of longitudinal, spaced, semicircular grooves 19 and 20 and a semiconical recess 21 at the rearward end thereof, for a purpose to be later described.

The air frame consists of a pair of parallel sectional shafts indicated generally by 22 which are fixed at their forward ends to war head 5 and rocket motor 2 is slidably mounted thereon for movement towards the warhead only.

Means are provided to prevent rearward movement of the rocket motor 2 and consists (see FIGS. 4 and 6) of a rack 23 integrally provided on the inner sides of shafts 22.

Spring biased pawls 24 are mounted in motor tank 8 for engagement with racks 23, permitting motor 2 to slide in a forward direction only. (See FIG. 6.)

Each shaft 22 is composed of sections 25, representing first, second and third zones for the corresponding stages.

Each section 25 is provided with a threaded reduced extension 26 at its rearward end, except the section 25 which represent the first zone. The last named section permits sliding of rocket motor 2 thereon and is conneeted only at its forward end to the next section.

All of the sections 25 are provided with an internally threaded bore at their forward ends receiving a corresponding threaded extension therein in order to connect the sections in a continuous shaft.

Refueling means are provided to continuously feed fuel to rocket motor 2 consisting of a refueling head 28 (see FIGS. 2 and 6). This head is conical in shape and extends forwardly of tank 8 of the rocket motor and is integral therewith. Extending from head 28 is a divided inwardly extending tube 29 which forms two ports 30 and 31 communicating with a pair of inlet ports 32 and 33 which are provided with spring biased valves 34 anc 35 adjacent their outer ends.

Head 28 is normally received in a stage tank when in assembled relation within the semiconical recesses 21. (FIG. 2.)

Each tank half 4 is provided with an outlet valve which consists of a strap 37 fixed to the inner wall of the semiconical recess 21. A valve rod 38 extends into the recess 21 and has a beveled head 39 carrying a closure member 40. Valve rod 38 is normally biased into recess 21 by a spring 41 so that closure 40 will seat on opening 42 and keep the tank half 4 closed when not in use.

Normally, when the missile is in assembled relation,

tank halves 4 are secured on shafts 22, with the shafts 22 being received in the semicircular grooves 20.

Releasable means are provided for the securement of tank halves in the aforesaid assembled relation and consist of (see FIG. 7) a pair of pins 43 secured to the tank half 4 and arranged two each in spaced relation in a semicircular groove 20 (see FIG. 1).

Each pin 43 (see FIG. 7) is provided with a notch 44. Pins 43 extend into slots 45 provided in shaft ections 25.

A forked arm 46 engages notches 44. Arm 46 is integral with solenoid armature rod 47 which slides in a winding 48.

Means for jettisoning the tank halves from the missile after they are spent and to blow off sections 25, as the missile progresses in flight, are provided and are operated electrically from the command center 49 in warhead 5.

The tank halves 6 and 7 of the three stages are jettisoned in the order of first, second, then third stages as they are spent of fuel, each half 4 containing respectively, an oxidizer and a fuel, all stages operating similarly.

Upon burning out of the fuel in a stage, electrical energy from the command center 49 will Withdraw armature 47 with forked arm 46 from notches 44 in pins 43. The tank halves are now unlocked. Switch contacts 50 on arm 46 will then contact switch contacts 51 on a plate 52 which is in electrical contact with small charges 53 situated at the outer perpheral surface of each section 25 and spaced at each end thereof, there being two charges 53 arranged in diametrical relation in each end of a section 25. Upon contact of switch contacts 50 and 51 electrical energy fires charges 53 to blow apart tank halves 4. (Four charges 53 are fired simultaneously).

After the charges 53 separate the spent tank halves 6 and 7 of a stage, rocket motor 2 will run up shafts 22 to the next stage under its own power.

Now the shaft sections 25 are ready for separation.

Electrical energy from command center will supply 1 current to switch points '54 which are arranged, one each,

on a section.

Switch point 54 is connected to a small charge 55 which when energized will blow apart the section 25 behind the rocket motor 2. Suitable means (not shown) may be provided for automatic connection to switch points 54 at the proper time for separation of the sections.

There are four charges 53 and one charge 55 in each shaft section 25.

After the jettison of tank halves 6 and 7 and following separation of the corresponding section, the rocket motor 2 has proceeded up shaft 22 under its own power. Then, the tank 8 of rocket motor 2 will become automatically connected with the next stage tanks 6 and 7. When re fueling head 8 enters semiconical recesses 21, valve head 39 will enter ports 32 and 33 to push open valves 34 and 35 respectively, the valve rod will rise against the bias of spring 41 to uncover the openings 41 and 42 in tank halves and 16 to allow fuel and oxidizer to enter into compartments 9 and 10 in motor 2 and out ports 11 and 12 to the motors 13 and 14.

The same steps are repeated as each stage is burnt out until the rocket motor reaches war head 5, its final position.

Hence, as the missile progresses in flight, it will lose weight and therefore attain a higher rate of speed.

FIGURE 5 shows electrical wiring for the jettisoning charges and the solenoids used in releasing and blasting away the tank halve 6 and 7. However the wiring is standard as in most missiles and the wires may run down the center of the shaft sections or in bores, etc., as desired.

As the rocket motor 2 advances under its own power toward the next stage, it cannot accidentally fall aft rearwardly from the shaft 22 since ratchet teeth 23 engaged by pawl 24 prevent rearward movement of the motor 2.

The air frame of the invention is also equally adaptable to heavier type missiles in which the first stage may have its own rocket motor.

An illustration of such application is shown in FIG. 10 wherein similar parts are labeled with the same reference characters as in the previous figures with the exception that they are followed by letters a, b and c.

The air frame is similar, but tank halves 4a of the first stage are equipped with separate rocket motors and 56. Each motor is provided with housings 58 and 59 which have ports 60 and 61 to admit fuel and oxidizer to main rocket motor 2a. Housings 58 and 59 fit into grooves 62 and 63 in rocket motor tank 8a. Any suitable valve arrangement (not shown) may be used. The second stage may be flared so that the third stage may be smaller, as shown. The stage 1 naturally will have the greatest lifting force due to its larger size.

Other means for sliding the shafts 22 through rocket motor 2 may be provided, and in FIGURE 10, another way of slidable mounting shafts 22 on motor 2 is shown. A tubular member 64 is integral with each side of the motor and permits sliding of motor 2a on the shaft 22.

It is apparent, therefore, that a novel, highly efficient air frame construction is attained by the present invention, affording greater economy as well as being simple and light weight in construction.

Variations and modifications may be effected without departing from the scope of the novel concept of the present invention as set forth in the appended claims.

What is claimed is:

1. An air frame construction for a multiple stage missile comprising, a warhead containing a source of electrical energy, a pair of parallel shafts connected at one of their corresponding ends to said warhead, a rocket motor slidably mounted on said shafts, a series of adjacent propellant tanks releasably secured on said shafts between said rocket motor and said warhead, passage means for feeding propellant from a proximate tank to said rocket motor, explosive means carried by said shafts and fired by electrical energy from said electrical energy from said warhead for sequentially jettisoning said tanks as they become depleted of propellant, Whereby said rocket motor will travel up said shafts under its own power and becomes connected to the succeeding tank for replenishment of propellant to said rocket motor.

2. An air frame construction for a multiple stage missile comprising, a warhead containing an electrical energy source, a rocket motor, a pair of parallel, sectionalized shafts connected at their forward ends to said warhead, said rocket motor slidably mounted on said shafts, a series of axially aligned propellant tanks releasably secured on said shafts between said rocket motor and said head, the proximate of said tanks being connected to said rocket motor for supplying propellant thereto, each tank comprising a pair of semicircular containers having planar inner faces, there being a pair of longitudinal semicircular, spaced grooves in said planar faces for receiving one half the diameter of each of said shafts when said tanks are in assembled position in said air frame, means carried by said rocket motor and the adjacent tank for establishing refueling connection between said rocket motor and said adjacent tank, means for releasably securing each tank half in mating relation with another tank half on said shafts, means carried in said shafts for jettisoning a tank from said air frame whereby said rocket motor will move up, under its own power, and become automatically connected with the adjacent tank to be refueled, means carried by said rocket motor and said shafts to prevent rearward movement of said rocket motor on said shafts and means carried by said shaft sections for separating a section after said rocket motor has run up on said shafts after said rocket motor has established refueling connection with an adjacent tank.

3. An air frame as set forth in claim 2, wherein said sectionalized shaft comprises at least three axially aligned sections, each of said sections having an intern-ally threaded axial bore in its forward end; and an externally threaded reduced extension on the rearward end of the second and third sections and the rearward face of said warhead for threadable engagement with said internally threaded bores in said first, second and said third section respectively.

4. An air frame as set forth in claim 2 wherein the means carried by said rocket motor and an adjacent tank for establishing refueling connection therebetween comprises a diametrically divided receiving tank secured to said rocket motor and being in communication with said rocket motor, a conical refueling head extending axially forward from said tank on said rocket motor, a pair of inlet ports in said head and leading into said receiving tank, a spring biased flap valve disposed in each inlet port, there being a semiconical recess on one end of said planar faces of each tank half, there also being an opening in the wall of said recess and a spring biased valve secured to the inner wall of said recess, said last named valve and the valve in the inlet port in said refueling head opening when said head enters said semiconical recess of a semi-circular tank, whereby passage is established for entry of propellant from said tank to said rocket motor.

5. An air frame as set forth in claim 2 wherein the means for releasably securing each tank half in mating relation with another tank half on said shafts comprises a pin extending from the ceiling of each longitudinal groove near the ends thereof, there being a notch in each pin, there also being a series of diametrical slots in each shaft section corresponding in number to the number of said pins, said pin entering said slot when said tank halves are in assembled relation, a forked arm normallye engaging said notches in said pins and a transversely moving solenoid armature integral with said arm, said armature adapted to withdraw said forked arm from said notches when energized electrically from said warhead to unlock said tank halves.

6. An air frame as set forth in claim 2, wherein the means for jettisoning the tank halves comprises a pair of diametrically opposed explosive charges disposed on the outer surfaces of each section of said shafts and arranged near each end of said section, said explosive charges being fired by electrical energy from the source in said warhead.

7. An air frame as set forth in claim 2 wherein the means for preventing rearward movement of the rocket motor when sliding forward on said shafts comprise a rack integral with the inner side of each shaft and a spring biased pawl carried by said rocket motor and engaging said rack.

8. An air frame as set forth in claim 2 wherein said means for separating a section of said shaft comprises an explosive charge fired electrically from said warhead.

No references cited.

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