US2952207A - Missile - Google Patents

Description

Sept 13, 1960 M. M. KAMlMoTo 2,952,207

MISSILE Filed June 30, 1952 2 Sheets-Sheet 1 INVENTOR. 34 M|CHAEL M. KAMIMOTO ATTORNEYS Sept. 13, 1960 M. M. KAMlMoTo MISSILE 2 Sheets-Sheet 2 Filed June 30. 1952 m f M A L n E.

INVENTOR.

MICHAEL M. KAMEMOTO ATTORNEYS MISSHJE Michael M. Kamimoto, China Lake, Calif., assignor to the United States of America as represented by the Secretary of the Navy Filed June 30, 1952, Ser. No. 296,508

3 Claims. (Cl. 102-50) (Granted under Title 35, U.S. Code (1952), sec. 266) The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

This invention relates in general to missiles, and more particularly to improvementsl in flight controls for rockets.

One of the objects of the invention is to provide an improved system for controlling the azimuthal and elevational directions of movement of a missile, and controlling roll thereof about its axis of movement.

Another object is to actuate the directional control surfaces of `the missile by the ambient fluid through which the missile moves.

Another object is to actuate the control surfaces of a rocket by ram pressure produced by movement of the missile through air.

Another object is to provide a differential fluid pressure operated diaphragm device for actuating a control surface.

Another object is to provide a plurality of pairs of differential pressure operated diaphragm devices for actuating azimuthal and elevational control surfaces, and a gyroscope for controlling said surfaces to effect roll correction of the missile.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

Fig. l is a fragmentary side elevation of a rocket to which `the subject of the invention is applied;

Fig. 2 is a section taken on line 2 2, Fig. details being omitted;

Fig. 3 is a section taken on line 3 3, Fig. 4, and an enlarged section taken on line 3 3, Fig. 2, portions being broken away;

Fig. 4 is a section taken on line 4-4, Fig. 3;

Fig. 5 is a section taken on line 5 5, Fig. 3;

Figs. 6 and 6A are sections taken on line 6 6, Fig. 3;

Fig. 7 is an enlarged section taken on line 7 7, Fig. l, a portion being broken away;

Fig. 8 is a section taken on line 8 8, Fig. 7;

Fig. 9 diagrammatically illustrates the control system;

Fig. 10 is a section taken on line 11-11, Fig. 11, portions being broken away;

Fig. 1l is -a section taken on line 11 11, Fig. 10;

Fig. 11A is a section taken on line 11A-11A, Fig. 1l, showing another position of parts;

Fig. l2 is a section taken on line 12 12, Fig. l0; and

Fig. 13 is a section through a conduit and valve of Fig. 9;

Referring in detail to the drawing, and particularly Figs. l to 8, rocket 20, movable along its longitudinal axis A, is of any conventional form, which embodies the subject of the invention. The rocket casing or tube 21 is provided with four air scoops 22, 22a, 22h, 22C, spaced equiangularly about its periphery. Fixed fins 23,

l, internal Patented Sept. i3, i950 23a, 23h, 23e yare carried by the rocket rearwardly of the respective scoops and each carries a movable iin. Since the n scoops and lin actuators are all identical the description of one will serve for all. As best shown in Figs. 4 to 8, a sheet of flexible material 19 is clampingly held between the side plates of fixed n 23 and between the side plates of movable n 24, this serving to permit swinging movement of iin 24 about axis 25, as best shown by the dotted positions, Fig. 5. A pair of elongated hollow flexible diaphragrns or bags 26, 27 are secured to the inner wall of tube 21 by a plate 28 and a pin 29 aixed thereto, pin 29 having a flange 30 engaging the bottom wall of la recess 31 and adapted to rock in a transverse plane of the rocket, as bes-t shown in Figs. 6 and 6A The outer end 32 of the pin is convex and seats within a socket 33 carried by the inner edge of fin 24. In Fig. 6, bags 26, 27 have the same internal ram pressure and fin 24 is in the solid line position shown in Fig. 5, that is, in alignment with the direction of ight of the rocket. In Fig. 6A, a differential pressure exists in bags 26, 27, bag 26 being larger in cross section than bag 27, which has tilted plate 28 and its attached pin 29, swinging iin 24 to one of the dotted positions of Fig. 5. It will be apparent that when bag 2'7 expands and bag 26 contracts, iin 24 will be moved to the other dotted line position of Fig. 5. The actual amount of angular movement will depend on the differential pressure in the two bags. The front ends of both bags communicate with air scoop 22, and the rear ends are both closed, as best shown in Figs. 7 and 8. A pipe 34 communicates with the rear end of bag 27 and a similar pipe 35 communicates with the rear end of bag 26. As diagrammatically shown in Fig. 9, similar bags 26a, 27a actuate iin 24a; bags 26b, 27b actuate iin 24h; and bags 26C, 27e actuate iin 24C.

As best shown in Figs. 9 and 13, pipes 34, 35b are connected to a normally closed solenoid operated valve V1, which, when opened, will bleed air from pipes 34, 35b through vent port P1. Pipes 35, 34h are similarly connected to valve V2 land port P2. Pipes 34a, 35C are similarly connected to valve V3 and port P3, and pipes 35a, 34al are similarly connected to valve P4 and port P1.

Assuming that the system -is provided with only the construction so far described, .the operation is as follows: When valve V1 is open and valve V2 closed, air will bleed out through port P1, reducing the pressure in pipes 34, 35b thus etfecting a diiferential pressure -between bags 26, 27 and 2612, 27h, respectively, thus swinging fins 24, 24h in the same direction. As will be apparent, if valve V2 is open and valve V1 closed, these iins will be swung in the opposite direction. Similarly, when one of valves V3, V4 is open and the other closed, fins 24a, 24e will swing in one direction or the other, depending upon which of these valves is open. The solenoids may be controlled by any suitable intelligence which dictates change of direction and signals a corrective control to the valves. As will be apparent, one pair of opposite tins controls azimuthal `direction of flight and the other pair controls elevational direction of flight.

Roll of the rocket about its axis or direction of flight is also controlled by the iins just described by moving opposite pairs thereof in opposite directions. A rotor 37, of a gyroscope, 38, provided with buckets 39, is mounted for rotation by shaft 40 in gimbal 41, the latter being rotatable labout axis 42 on pintles 43 rotatably supported by the rocket. A pipe L1 communicates with pipe 34 and terminates in frame 44, delivering air to jet 45. Pipe L2 communicates with pipe 35 and terminates in frame 44, delivering air to jet 46. Before the gimbal has processed, the ends of pipes L1, L2 are misaligned from the air receiving ends of jets 45, 46, respectively, by the same amount, as best shown in Fig. l2, so that there is equal ow of air to .both jets. When the gimbal precesses, one

of the jets becomes more nearly aligned with its supply pipe and the other less aligned with its supply pipe, thus changing the relative rates of flow through lines L1 and L2. Pipe L3 communicates with pipe 35h, and pipe L4 communicates with pipe 34h, thes'e pipes similarly terminating in frame 44 and supplying air to jets 47, 48, respectively, which latter are misaligned with pipes L2, L4 in the same manner described for jets 45, 46. Assuming that valves V1 and V2 are closed and the gyroscope precesses as shown in Fig. 11A, pipe L1 will become less aligned with jet 45, and pipe L2 will become more nearly aligned with jet 46, and the pressure in pipe L1 will be greater than in pipe L2. Due to the similar misalignment of pipes L3, L4 with jets 47, 48, respectively, the pressure in pipe L4 will be greater than in pipe L3. Bags 27 and 26h will then collapse 4and bags 26 and 27h expand, thus moving fins 24, 24b in opposite directions, As will be apparent, if the gyroscope precesses in the opposite direction, the opposite movement of fins 24, 24b will be opposite to that just described. The opposite direction of movement of opposite pairs of fins will, as will be apparent, apply a corrective force opposing roll of the rocket. The other pair of fins 24a, 24e are similarly co-ntrolled by the gyroscope through pipe L5, terminating in frame 44 above pipe L4, a'nd pipe L3, terminating above pipe L3, at one side of the gimbal, and pipes L7 and L3 terminating, respectively below pipes L2, L1, at the other side of the gimbal. It will be apparent, therefore, that when a roll correction is required, fins 24 and 24b will move in opposite `directions and fins 24a and 24C will also move in opposite directions, the roll correction of the pairs being cumulative.

Assuming again that the pressure in pipes L1, L1 are greater, respectively, than in pipes L2, L3 (which would effect a roll correction) and valve V1 is now opened, the pressure differential between pipes L1 and L3 will then become greater and the pressure differential between pipes L1 and L2 will become less. Fins 24, 24h, instead of being swung in opposite directions in equal angular amounts will now move so that fin 24b is swung a greater amount, and fin 24 a lesser amount, thus retaining substantially the same roll correction as formerly, but now producing an azimuthal steering correction. As will be apparent, opening of valve V2 instead of valve V1 produces an opposite effect. Opening of valve V1 (or V2) does not affect the position to which fins 24a, 24e have been previously moved by the gyroscope control and the net roll corection thus remains substantial as it formerly was with an azimuthal steering correction added to the roll correction. Similarly, if valve V3 or V4 is opened while the fins are moved to a roll correction position, the net roll correction remains substantially as it formerly was with lan elevational correction added to the roll corvrection.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

l. Directional flight control and roll control apparatus for a missile comprising; first and second vertical iins movably carried by the missile at substantially diametrically opposite sides thereof adapted to control azimuthal direction of movement of the missile, third and fourth horizontal fins movably carried by the -missile at substantially diametrically opposite sides thereof adapted to control elevational direction of movement of the missile, a

first pair offiexible expansible chambers operatively connected to the first fin adapted to move same in opposite directions from a normally neutral position in response to gas pressure applied within said chambers, second, third, and fourth pairs of similar chambers similarly connected, respectively, to said second, third and fourth fins adapted to similarly move same, means for applying the same` gas pressure to all of said chambers when said fins are all in their neutral positions, first valve means for reducing the pressure in one chamber of the first pair and one chamber of the second pair to effect differential pressure between the respective pairs and effect movement of the first .and second fins in one direction, second valve means for reducing the pressure in the other chamber of the first pair and the other chamber of the second pair to effect differential pressures in the respective pairs and effect movement of the first `and second fins in the opposite direction, whereby said first and second valves control the azimuthal direction of flight, third and fourth valves similarly Vconnecting the third and fourth pairs of chambers for controlling the elevational direction of movement, `a gyroscope carried by the missile, and valve means operable in response to precession of the gyroscope for reducing the pressure in said one chamber of the first pair of chambers and said other chamber of the second pair, or reducing pressure in saidother chamber of the first pair and said one chamber of said second pair, whereby said first and second fins move in opposite di'- rections and correct roll of the missile about its direction of movement, said last named valve means being adapted to similarly control said third and fourth fins for also correcting roll. v

2. Apparatus in accordance with claim l including means for delivering ambient air under ram pressure to all of said chambers to apply said gas pressure therewithin.

3. Apparatus in accordance with claim 2 wherein said valve means is constructed and arrangedto deliver air from at least some of said chambers to said gyroscope for rotating its rotor.

References Cited in the file of thisl patent UNITED STATES PATENTS 2,183,311 Goddard Dec. l2, 1939 2,322,782 Hemstreet June 29, 1943 2,414,898 Rons Jan. 28, 1947 2,419,443 Eaton Apr. 22, 1947 2,584,127 Harcum et al. Feb. 5, 1952 FOREIGN PATENTS 579,816 Great Britain Aug. 16, 1946

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