US2776622A - Device for attaching auxiliary rockets to a flying machine - Google Patents

Description

Jan. 8, 1957 R. A. ROBERT 5 DEVICE FOR ATTACHING AUXILIARY ROCKETS TO A FLYING MACHINE Filed May 27. 1948 s Sheets-Shet 1 INVENTOR ROGER A. ROBERT Ir AGENTS Jan. 8, 1957 R. A. ROBERT 7 DEVICE FOR ATTACHING AUXILIARY ROCKETS TO A FLYING MACHINE Filed May 27, 1948 3 Sheets-Sheet 2 Jan. 8, 1957 R. A. ROBERT 2,775,622

DEVICE FOR ATTACHING AUXILIARY ROCKETS TO A FLYING MACHINE Filed May 27, 1948 s Sheets-Shelet s Fia. 6

INVENTOR ROGER A. ROBERT AGENTS United States Patent DEVICE FOR ATTACHING AUXILIARY ROCKETS TO A FLYING MACHINE Roger Aime Robert, Boulogne-sur-Seine, France Application May 27, 1948, Serial No. 29,564

Claims priority, application France May 27, 1947 13 Claims. 01. 102-49 It is known that in flying machines, guided missiles and the like, auxiliary propulsive means are sometimes used with the purpose of imparting to the machine, at the start thereof, a high rate of acceleration in order very rapidly to bring it to its normal speed, which is thereafter maintained by means of the main propulsive or drive unit of the machine.

The auxiliary propulsive or drive means ordinarily used are rockets, which are adapted to be automatically cast off or released so soon as they no longer develop any thrust. Now, the time during which such rockets are actually operative may vary as from one rocket to another, so that they are not as a rule cast off simultaneously. As a result, towards the .end of the period of auxiliary drive, dissymmetrical effects occur which are liable to alter in an unpredictable manner the path of flight of the missile, and this is detrimental to the accuracy in firing.

It has been suggested to direct the propulsive actions of each of said rockets towards the center of gravity of the missile as a whole, so that the termination of the propulsive action of one or more of the auxiliary rockets should not introduce any disturbing torque.

Such a palliative remedy however is not sufficient, since it does not do away with the aerodynamical dissymmetry which occurs whenever the rockets are not cast off simultaneously.

The invention has for its object to provide a device for attaching and casting off auxiliary propulsive units to and from a flying machine, in particular a guided missile designed to convey an explosive charge towards a target, which will eliminate the above drawbacks.

It is an object of the invention to provide an attaching means for auxiliary drive units, of the rocket type, enabling all of the auxiliary rockets to be simultaneously cast off, after they have developed their full propulsive effect and regardless of the actual duration of the effective propulsive period supplied by each of them.

It is another object of the invention that throughout the full period in which the rockets are connected with the machine, including the casting-off stage, the rockets should remain symmetrically positioned with respect to the machine, thus allowing the predetermined trajectory thereof to be faithfully followed.

Another object of the invention is to provide for a safe and simple release of all of the auxiliary rockets after the explosive charge thereof has been burnt up.

It is a further object of the invention to positively avoid that the rockets, both during and after the release thereof, might contact the main body of the machine, thereby modifying its path of light.

It is yet another object of the invention to provide a flying machine (such as a guided missile) which, after the auxiliary drive rockets have been released therefrom, will not present any projection liable to increase its drag, and one in which the liftdrag ratio will be as high as in a similar machine free of any auxiliary drive units.

In the ensuing description given merely by way of 2,776,622 Patented Jan. 8, 1957 example reference is made to the accompanying drawings wherein:

Fig. 1 is a general view in elevation, partly in cross section, of an embodiment of my invention;

Fig. 2 is an enlarged view in elevation and partly in section of the latching device;

Fig. 3 is a cross-section on a still further enlarged scale on the line 33 of Fig. 2;

Fig. 4 is a cross-section on line 44 of Fig. 2, but on a larger scale;

Fig. 5 is a sectional view on an enlarged scale of the rear end of the machine;

Fig. 6 is a front view on a smaller scale of the rear outlet of the machine;

Fig. 7 is an electric wiring diagram.

The flying machine shown includes a fair-shaped main body or fuselage 10 (Fig. 1) having a tapered or ogeeshaped front portion or nose 11 and carrying the supporting surface or surfaces (not shown for greater clearness in the drawing). It contains in particular the main drive unit the propulsive jet of which issues from the rear jet outlet 12 of the machine.

Along the body 10 of the machine a number of auxiliary drive units such as rockets 13 are arranged, e. g. four in number, uniformly spaced around the machine, the angular spacing thereof in the example shown being Each of the rockets 13 includes a fair-shaped body 14 with a tapered front portion or nose 15, and a propulsive jet adapted to issue from the rear jet outlet 16.

According tothe invention each of the rockets 13 is so connected with the machine that, in being cast off therefrom, it is first adapted to be released at its front end, so as to pivot about its rear connection with the body of the machine, the final casting off being accomplished only as the center axis of the rocket forms with the center axis of the machine an angle greater than a predetermined value.

The body 14 of the rocket has attached thereto forwardly of its mid-portion and in spaced relationship to each other a pair of collars or rings 17 and 18. Between said collars and rigidly connected thereto within the gap defined between the rocket body 14 and the main body 10 of the missile there is a slideway or slotted member 19. The latter comprises a pair of side flanges 20 and 21 (see Figs. 2 and 3) each of which has a straight slot 22 formed therein, the rigid connection between the slideway and the collars 17 and 18 being effected through a pair of arcuate flanges 23 and 24 formed at the ends of the slideway. Between the side flanges 20 and 21 there is arranged a bar 25 which at the front thereof and projecting from each of its faces mounts a pair of pins 26 each adapted to engage the related slot 22.

The front end of the bar 25 forms a nose 27 with which is adapted to co-operate a complementary nose 28 of a latch member 29 comprising a bell-crank lever 3031 pivotally mounted on a pin 32. A spring 33 hearing at one end against a thrust plate 34 rigid with the body 10 and exerting its action against the bell-crank lever arm 30 continually urges the nose 28 away from the nose 27. Except in the casting-off periods this action is prevented through abutment of the end 35 of the arm 31 against the end 36 of a lever 37 pivotally mounted on a shaft 38. Contact engagement between the planar faces of the noses 27 and 28 is maintained by the resilient action of a small block 39', of rubber or the like, clamped during assembly between the bar 25 and the fuselage 10.

The bar 25 is rearwardly extended beyond the collar 18. It terminates in a head 39 (Figs. 3 and 4) formed with a wide cut-out 40 including a semi-circular portion 41 and two straight portions 42 and 43 parallel or substantially parallel with the side edges of the bar. The head 39 co-operates with a stop-pin 44 having a av'raeaa diameter corresponding with that of the semi-circular portion of the cut-out, so as to allow rotation of the head 39 therein. The pin or rod 44 is secured between the side flanges 45 and 46 of angle sections 47 and 48 rigid with the fuselage 10. A pair of extensible rubber cords 49 and 50 or similar resilient means are interposed between the pins 26 and the related rocket 13.

The rear portion of the rocket 13 has secured thereto a collar 54 formed with a circumferential flange 55. The latter serves as a support for a coil spring 56 surrounding and spaced from the opposite portion of the body 14. This spring is housed within a bushing 57 and its other end bears against a front circumferential flange 58 of said bushing. The bushing 57 is secured to one end of an arm 59 arranged adjacent to the rear portion of the fuselage 10 of the machine and the other or rear end of which is pivotally mounted around a pivot pin 60 on a circular flange 61.

The flange 61 is formed with an angle-shaped cross section having two arms 62 and 63 (Fig. respectively engaging the related arms 64 and 65 of a flange 66 rigid with the body 10. The pivot pins 60 are arranged at the opposite ends of two diameters of the flange 61 extending at right angles to each other, each of said pins being mounted between two side flanges 67 and 68 (Fig. 6).

The face 69 of the arm 59 which lies opposite the body carries towards its rear end a near-rectangular prismatic block 71 or similar projection co-operating with a bead 72 formed on the flange 66.

The body 14 of each rocket immediately in front of the portion thereof surrounded by the bushing 57 carries a contact finger 73 adapted to co-operate with a complementary contact element 74 carried by the bushing 57. Two projections 75 connected with the bushing 57 are arranged on both sides of the fingers 73. They carry a shear-pin 76 extending through said finger through a bore 76 of equal diameter.

The pairs of electric contacts 77, 78, 79 and 80 (Fig. 7) each formed by the co-operating contact elements 73 and 74 related to each of the rockets are connected in series in an electric circuit 81 supplied from a suitable source of current 82 such as a storage battery. In said circuit there is interposed the energizing means for an electrically operated jack 83 housed within the body (Fig. 1). The movable part 84 of said jack carries a grooved frame member 85 the groove 86 of which is engaged by rollers 87 each of which forms the termination of an arm 88 of a lever 89 rotatably mounted on a pin 90. The outer end 91 of the opposite arm of said lever is connected through a link 92 with the arm 93 of the lever 37.

The above-described attaching and releasing device operates as follows:

Prior to the starting of the machine or missile, each of the auxiliary rockets is positively maintained in its safety position by means of the pin 76 the shearresistance of which is sufficient to prevent any displacement of the rocket with respect to the machine under the action of its own weight and of the spring 56, thus preventing closure of the contacts 7780. Upon starting, and under the action of the thrust from the auxiliary rockets 13, the shear-pins 76 are sheared and the rockets move slightly forward relatively to the main body 10 of the machine, against the action of the spring 56 already placed under compression. The rockets thus are caused to assume the position shown at the top of Fig. 1.

Throughout the full period they exert their propulsive action the auxiliary rockets retain an unchanged relative position with respect to the main body of the machine. The thrust is transmitted through the bushings 58 and the arms 59. The construction of the rockets is such that in theory the combustion periods therein are the same. In practice however it very often happens that the propulsive actions of the rockets do not terminate simultaneously. When the propulsive action of any one rocket ceases, the effect of the spring 56 relating to that rocket and of the air-drag becomes predominant and the rocket is caused slightly to recede rearwardly with respect to the main body of the machine. This movement is operative to close the corresponding electric contacts comprising elements 73-74. It should be noted that it is after the four pairs of contacts 77 through are closed that the electrically-operated jack 83 is actuated. So long as such is not the case the rockets remain latched with respect to the machine, since pivotal movement of the bar 25 is prevented due to the co-operation of the noses 27 and 28; the thrust exerted by the rocket applies the arm 62 of the circular flange 61 against the arm 64 of flange 66.

As the propulsive action of a rocket ceases, release of the flange 61 rearwardly is prevented through abutment of the prismatic element 71 against the bead 72 as long as the arm 59 has not swung through a predetermined angle. The arm is prevented from thus swinging because of the previous latching of the rocket which remains eflective as long as the rockets have not all terminated their propulsive action.

Only when all of the rockets have stopped exerting their propulsive effect, the circuit 81 is closed and the electric jack 83 is actuated, thereby extending the projecting part of its movable element 84.

The levers 89 then are simultaneously rocked, causing corresponding displacements of the links 92 and levers 93; the ends 36 disengage the levers 29 and the latter, under the urge of the springs 33 retract the noses 28 from their position opposite the noses 27 of the bars 25.

The action of the elastic cords 49 and 50 initiates the rocking movement of the bars 25 about the related pins 44, and the opening-out or flaring movement of the rockets 13 with respect to the main body 10 thereafter mainly proceeds under the effect of the aerodynamic forces, as a result of the pivotal connection still remaining effective between the bars 25 and pins 44. So long as the center axes of the rockets do not form with respect to the axis of the flying machine an angle in excess of a predetermined value, as illustrated by the position shown at the bottom of Fig. 1, the prismatic element 71 (Fig. 5) acts to prevent the flange 61 from slipping backwards with respect to the flange 66. Beyond that position however the prismatic element 71 disengages the bead 72 and the whole assembly comprising the circular flange 61, arms 59, rockets 13, collars 17 and 18, slideways 19 and bars 25 is cast 01f. One or more parachutes, for instance one for each rocket unit, may be provided to allow said units to be ultimately reclaimed. At the time of release the rockets 13 are spaced sufliciently far away from the main body of the machine to avert any risk of their coming into contact with the latter. During the entire casting-off period the rockets remain symmetrically positioned with respect to the axis of the main body 10, so that they do not interfere with the trajectory of the missile.

What I claim is:

1. Auxiliary propulsive device for a flying machine, which comprises a central collar, a plurality of rockets arranged in uniformly spaced relationship about and parallel with the axis of said collar, arms interposed between said collar and said rockets for supporting said rockets, and deformable resilient means deformable in the direction of said axis interposed between each rocket and its supporting arm.

2. In a flying machine, a central faired body, a plurality of auxiliary rockets arranged parallel with and along said body, and connecting means between said central body and said plurality of rockets comprising: a hearing rearwardly of and connected to said body, a collar surrounding said bearing, two cooperating abutment surfaces on said bearing and said collar respectively, and, associated with each rocket: an arm pivotally mounted mam on said collar on a transversely extending pivot axis, a cup member laterally fixed on said arm on the outer side thereof, an aperture in said cup member adapted to allow one of said rockets to slidingly pass therethrough, an annulus secured on said auxiliary rocket, resilient means interposed between said cup member and said annulus, a first ring secured on said rocket forwardly of said annulus, a second ring secured on said rocket between said first ring and said annulus, a longitudinal rib integral with said rings and interposed therebetween, a longitudinal groove formed in said rib, a transversely extending projection integral with said faired body rearwardly of said rib, a bar longitudinally disposed between said faired body and the rocket, a two-timed fork at the end of said bar and cooperating with said projection, a pin integral with said bar at the opposite end thereof cooperating with said groove, resilient traction means interposed between said pin and said rocket and hookingly engaging said rocket at a point rearward of said projection, a nose on said bar, and a hook cooperating with said nose to block said bar, means for controlling retraction of said hooks with respect to said rockets, and comprising an electric motor within said central body, drive transmission means from said motor to said retraction controlling means, an electric feed circuit for said motor, switches in said circuit each comprising a contact element carried on a rocket and an opposite contact element carried on the corresponding annulus relating to said rocket, said contact elements adapted to cooperate together upon the action of said first named resilient means exceeding the opposing action of the propulsion jet of said rocket.

3. A flying machine which comprises a main rocket, a plurality of longitudinally extending auxiliary rockets spaced about said main rocket, connecting means between said main rocket and said auxiliary rockets resiliently deformable in a direction parallel with the common axial direction of said rockets, and frangible means rigidly connecting said main rocket with said auxiliary rockets and adapted to break upon exertion of the propulsive action of the auxiliary rockets.

4. In a flying machine, an elongated fair-shaped main body, a plurality of starting jet rockets arranged about said main body, a common support for said jet rockets removably mounted on the rear end of said body, means pivotally connecting said rockets to said support, latch means on said body and engaged with said jet rockets releasably securing said jet rockets and said support to said body, said jet rockets being supported for slight 1ongitudinal movement relative to said body, resilient means urging said jet rockets longitudinally in a direction opposite to the direction they are moved by their propulsive action, and release means in said main body operated by longitudinal movement of said jet rockets when moved by said resilient means to release said latch means and free said jet rockets and said support to drop clear of said body when the propulsive action of all of said jet rockets has ended.

5. A flying machine according to claim 4, wherein said release means is electrically operated and comprises a member for releasing said latch means, a normally open switch for each of said jet rockets arranged to be closed when said jet rockets are moved by said resilient means, and a circuit connecting said member and said switches in series with a source of electric current to energize said member when all of said switches are closed.

6. In a flying machine, a faired body, a plurality of auxiliary jet rockets positioned about said body, a bearing ring mounted on the rear end of said body, a collar removably supported on said bearing ring, means connecting said jet rockets to said collar, cooperating abutments on said collar and said bearing ring to transmit the propulsive thrust of said jet rockets to said body, latch means on said body engaging said rockets and retaining said collar and rockets against rearward displacement relative to said body, and means on said body for releasing said latch means to free said rockets and collar to drop rearward off said body when all of said jet rockets have expended their propulsive thrust.

7. A missile, comprising a central body, a plurality of rockets uniformly spaced about the periphery of said body, a bearing ring mounted on said central body, a collar slidably positioned on said bearing ring, each of said rockets being connected to said collar, and cooperating abutments on said collar and said bearing ring for conveying the propulsive thrust of said rockets to said body; the connection of said rockets to said collar being a pivotal connection, and comprising latch means on said body forwardly of said bearing ring and engaged with said rockets holding them against free pivotal movement relative to said collar, and mechanism in said body for releasing said latch means freeing said rockets for pivotal movement relative to said body when the propulsive thrust of all of said rockets is expended.

8. A missile, comprising a central body, a plurality of rockets uniformly spaced about the periphery of said body, a bearing ring mounted on said central body, a collar slidably positioned on said bearing ring, each of said rockets being connected to said collar, and cooperating abutments on said collar and said bearing ring for conveying the propulsive thrust of said rockets to said body; said connection of said rockets to said collar comprising an arm extending from each of said rockets and pivotally connected at their ends remote from said rockets to said collar so that said rockets and arms may pivot radially outward about the pivoted ends of said arms, and a radially inwardly extended projection on each of said arms in abutting engagement with said bearing ring, said projections being of a length to clear said bearing ring as said arms pivot outward from said body to an angular position relative to said body to allow said rockets, arms and collar to drop safely from said body when said rockets have expended their propulsive thrust.

9. In a flying machine, a faired body, a plurality of rockets spaced evenly about said body, latch means on said body releasably engaging said rockets securing them to said body, an electrically operated release mechanism on said body and engaging said latch means for operating said latch means to release said rockets, and a control circuit for said release mechanism including a series connected normally open switch for each of said rockets to energize said release mechanism when said switches are closed, said rockets being supported for slight longitudinal movement in each direction parallel to the flight axis of said body, resilient means acting to move said rockets in a direction to close said switches when said rockets have expended their propulsive thrust.

10. A flying machine according to claim 9, comprising fragile connections between said rockets and their supports holding said rockets against the action of said resilient means preventing said switches from being accidentally closed and arranged to be broken when said rockets are moved against the action of said resilient means by their propulsive force.

11. A flying machine according; to claim 4, comprising resilient means acting between said body and each of said rockets to pivot them radially outward when released by said latch means.

12. A flying machine, comprising a main rocket, a plurality of arms extended longitudinally of and spaced equally about said main rocket, said arms being pivotally attached at their rear ends on said main rocket, an auxiliary starting rocket carried by each of said arms, latch means on said main rocket engaging said starting rockets for releasably holding said arms and starting rockets in pivoted positions against the sides of said main rocket, and means on said main rocket controlled by said starting rockets when they have expended their propulsive thrust to release said latch means, said starting rockets being supported on said arms for slight sliding movement in a direction parallel to the flight axis of said main rocket and resiliently moved in a direction opposite to the direction they are urged by the propulsive thrust of said starting rockets; said release means being electrically operated and comprising a normally open switch for each of said starting rockets arranged to be closed when said rockets are urged by said resilient means, and a circuit connecting in series all of said switches, said release means and a source of current for energizing said release means when all of said switches are closed.

13. A flying machine according to claim 12, wherein said starting rockets are normally held against being resiliently urged to close said switches by a frangible element connected between said starting rockets and said arms and arranged to be broken when said starting rockets are moved by their propulsive thrust.

References Cited in the file of this patent UNITED STATES PATENTS Goddard July 7, 1914 Lepinte Dec. 21, 1926 Dornier Dec. 2, 1930 Myers May 25, 1937 Schuyler et a1. Oct. 31, 1939 Morgan May 14, 1946 Anderson et a1 J an. 21, 1947 Van Dorn Aug. 26, 1947 FOREIGN PATENTS Great Britain June 28, 1937 Germany Oct. 29, 1938

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