US3598345A - Rocket with folding fins and braking device - Google Patents

Abstract

Rocket having a nozzle body with a unit of folding fins arranged around the body. Means are provided for swinging the fins out of a normal position into an operating position. A braking device varies the flight path of said rocket and has swiveling flaps which in the normal position of the fins are located between the fins and the nozzle body in an inactive position. When the rocket is launched the forces that come into action swing the flaps into a braking position. Latch members cooperate with the flaps and are displaced by the fins to release the flaps.

Description

Uni

tied States @atenfi:

ROCKET WITH E OLDENG HNS ANDBRAKING DEWCE 6 Claims, 8 Drawing ll-igs.

US. Cl 244/327, 244/328, 244/329 lat. Cl. i E42B 13/32 Field at earelh 244/327, 3.28, 3.29

Primary Examiner-Verlin R. Pendegrass Arlorney- Wenderoth, Lind and Ponack ABSTRACT: Rocket having a nozzle body with a unit of folding fins arranged around the body. Means are provided for swinging the fins out of a normal position into an operating position. A braking device varies the flight path of said rocket and has swiveling flaps which in the normal position of the fins are located between the fins and the nozzle body in an inactive position. When the rocket is launched the forces that come into action swing the flaps into a braking position. Latch members cooperate with the flaps and are displaced by the fins to release the flaps.

PATENIEDAUBIOIQH 3,598,345

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ATTO RN E Y S ROCKET WITH FOLDING FINS AND BRAKING DEVICE The invention relates to a rocket with a nozzle body around which a unit of folding fins is arranged, of which the fins can be swiveled from a normal position into an operating position having a braking device for changing the flight path of the rocket. A rocket of this type is known in which the brake device for changing the flight path of the rocket consists of a conical brake plate which must be put on to the launcher tube before the rocket is launched. This device has the disadvantage that it cannot be used with automatic rocket launchers in which several rockets are launched in succession, since it is impossible to put the brake plate on the launcher tube at the same rate at which the rockets are launched.

The object of the present invention is to overcome this drawback. The rocket according to the invention is characterized in this that the brake device has swiveling flaps which in the normal position of the folding fins are between the latter and the nozzle body in an inactive position and that forces acting when the rocket is launched swivel the flaps into a braking position. In the case of missiles stabilized by spin it is well known to arrange flaps on swivel axles transversal to the longitudinal axis of the projectile in order to change the flight path of the latter.

Two examples of embodiments of the rocket will now be described with reference to the appended drawings in which:

FIG. 1 shows a longitudinal cross section taken through the center of two flaps according to the first example, wherein the right-hand half shows a folding fin in the normal position and a flap in the inactive position and the left-hand half shows fins and flaps in the swung-up position;

FIG. 2 shows a cross section along line 11- in FIG. 1 which is turned 90 with respect to the latter;

FIG. 3 shows a section along line III-III of FIG. 2 with the fins in the normal position;

FIG. 4 shows a cross section through a flap and the associated holding cams;

FIG. 5 shows an axial longitudinal section according to the second example, wherein in the right-hand half the section is made through the axle of a closed fin and a flap in the inactive position, while in the left half the section is made through the center of a flap and the fin and flap are in the swung-up positron;

FIG. 6 shows a section along line VI-VI of FIG. 5, in which fin and flap are shown on the right in the swung-up position and on the left in the inactive position;

FIG. 7 is a diagram of the hub portion of FIG. 5 in its inactive position and FIG. 8 is a diagram of the hub of FIG. 5 in its active position.

In accordance with FIG. 1 there is a propellent 2 in a housing 1 of a rocket. At the rear end of housing 1 a nozzle body 3 is fixed on which is screwed aconical extension 4 extending backwards. At the front end oftheextension 4 is aflange 5 arranged in front of the narrowest cross section of the nozzle body 3 and in one piece with theextension 4. The external diameter offlange 5 is substantially equal to the external diameter of the rocket housing 1. Thepart 6 ofextension 4 attached to saidflange 5 at the back has an external cylindrical surface area. Therear portion 7 ofextension 4 has a backward-extending, conical external surface area. Theextension 4 is extended in front of its rear end to form aflange 8, thefront part 9 of which is offset with respect to the rear part and provided with a projection 81 extending conically backwards, the said projection ending in afront surface 55. In therear flange 8 there are arranged at regular angular distances fourboreholes 10 parallel to the axis of the rocket, (one of said holes being shown in FIG. 3) and their axes are at a radial distance from the axis of the rocket which substantially agrees with the middle radius Rm of the conical projection 81 (FIG. 3).Boreholes 12 are arranged in thefront flange 5, and these are coaxial with theboreholes 10. Fouraxles 11 are fixed with one end in each borehole l0 and the other end in each borehole l2.

Eachfin 13 carries twohubs 14 and 15. The outer part of the fin is cylindrically bent, while the thicker inside part 13' is straight. As may be seen from the right-hand half of FIG. 1, and from FIG. 2, assuming the left-hand fin 13 to be folded, in the normal position offin 13 the bent part of such a fin will always overlap the straight part 13' of an adjacent fin. The overlappingfin 13 in the normal position does not then project over the profile of the rocket. In accordance with FIG. 3 thefront hub 14 is adapted to slide on asleeve 20 and is pivoted. Saidsleeve 20 and therear hub 15 are slidably supported on theaxle 11. Close to the rear end of eachfin 13 said fin has aborehole 57 to take one end ofa holding wire. Theextension 4 is provided with fourequal boreholes 82, each of which takes the other end of a holding wire. The holding wires have thickened portions at their ends and those thickened portions which are inside theextension 4 are adapted to melt under the action of the hot propellent gases.

According to FIG. 3, thehub 15 has at its rear end anabutting surface 17 which is bounded at the back by astopface 18 at right angles to the axis of the hub. Thesurface 17 forms the same angle with the axis of the hub as the generating line of the conical projection 81 forms with the rocket axis; consequently in the swung-out position offin 13, shown on the left in FIG. 1, theabutting surface 17 can come to rest upon the conical surface 81 as will be described in detail hereinafter. 1

Aspiral spring 19 surrounding theaxle 11 on the one hand presses thesleeve 20 against the rear end surface of theflange 5 ofextension 4 and on the other hand presses thestop face 18 ofhub 15 in the folded position of thefin 13 against thefront surface 55 of the conical projection 81. Oneend 21 of thespring 19 is supported, according to FIG. 2, on theextension 4 and theother end 22 rests on the inside offin 13. Thespring 19 strives to turn the fin 13 anticlockwise around theaxle 11, looking in the forward direction.

Thehub 15 has twocams 25, which extend in the peripheral direction of theextension 4 and in the normal position of thefin 13 each of these engages on one of twoadjacent flaps 30, as shown on the right in FIG. 1.

In accordance with FIG. 2, fourgrooves 27 are arranged at equal distances on the periphery of thefront flange 5. The planes of symmetry of saidgrooves 27 are in the middle between every twoadjacent axles 11 of thefin 13. The bottom of the groove is a part of a cylindrical surface of which the axis coincides with the rocket axis and its diameter with the diameter of the generatedsurface 28 of the nozzle body 3.Axles 29 are arranged inflange 5 and these axles pass transversely through thegrooves 27 and theflaps 30 are pivoted thereon by means of ahub portion 26. Theflaps 30 in their inactive position extend backwards betweenextension 4 and thefins 13.

Theseflaps 30, according to FIG. 4, have a U-shaped cross section, thelegs 23 being provided withplane sidewalls 31, having their edges parallel to the rocket axis. Theflaps 30 are supported by these edges on theextension 4. Theback 32 of theflaps 30, facing thefin 13 the front edge of which back passes into thehub portion 26, is cylindrically curved and hasextensions 33, which are offset from .the two legs in the peripheral direction, and haveslots 34 near the rear ends.

As shown on the right of FIG. 1, in the inactive position of theflaps 30, thecams 25 of thehubs 15 resting on theaxles 11 offins 13 are in front of theslots 34. As shown in FIG. 4, acam 25 engages over eachextension 33 of eachflap 30 and holds the flap in the inactive position.

The nozzle body 3 has two cylindrical generated surfaces 28 and 35 of different diameters. Asleeve 36 is slidably supported on these two surfaces. Thesleeve 36 has aflange 37 and fourtongues 39 projecting downwards from its rear end surface 38. Each of thetongues 39 projects between the front ends of twolegs 23 of aflap 30, which are guided on the lateral surfaces of thegrooves 27 offlange 5. Thetongues 39 have on their outer side grooves 41 crosswise to the axis of the rocket. In each of said grooves 41 there is a radially displaceableprismatic member 42 which is supported on abolt 43 fixed in the ends of the twolegs 23 offlap 30. Agroove 44 is arranged in the sleeve 36 (and extends over its entire periphery) between theflange 37 and the end surface 38.

The nozzle body 3 has anannular extension 45 concentrically surrounding its front end and threaded on the outside. Screwed on to this thread is an adjustingsleeve 46 having an inwardly projectingflange 47 which forms a stop forflange 37 ofsleeve 36. A slotted spring-ring 49, which is pressed by its own tension on thesleeve 36, is arranged in anannular groove 48 cut intoflange 47 from the inside. Apart 50 of the adjustingsleeve 46 is milled or knurled in order to increase its gripping capacity; but it can also have a gear-tooth system. In the inactive position of the flaps 30 ashoulder 52 connecting the two boreholes ofsleeve 36 is at a slight distance from and facing ashoulder 53 of nozzle body 3. Twoboreholes 54 passing through the wall of nozzle body 3 open out into theannular space 56 bounded by these twoshoulders 52 and 53.

Instead ofboreholes 54 axially directed springs can be arranged, which are supported on the one hand on nozzle body 3 and on the other hand onsleeve 36 and exert to slide thesleeve 36 backwards.

The rocket we have described operates in the following manner: Before the rocket is inserted in the launcher tube, according to the desired amount of drag to be generated by theflaps 30, the adjustingsleeve 46 is screwed more or less far backwards from the zero position shown on the right in FIG. I, for example to the position indicated on the left in FIG. 1. Thesleeve 46 is turned by hand on thepart 50 in order to do this. It can also be shifted by the cogwheel of an automatic control (not shown in the drawing) provided that the adjusting sleeve, as stated, has a gear-tooth system, in which the cogwheel engages. The rocket is then pushed into the launcher tube, from which it can be launched.

After the ignition of the propellent 2, while the rocket is passing through the launcher tube (not shown) under the thermal effect of the combustion gases of the propellent, the said holding wires which have hitherto held thefins 13 in the normal position, will melt. However, the fins I3 are still held in the folded position by the launcher tube until they come into the operating position, under the action of the springs [9 en gaging them, after the rocket has left the tube. During this opening movement thesurfaces 18 ofthe rear fin hubs l slide on thefront surface 55 of the flange of theextension 4. Just before the operating position is reached, the hub surfaces 18 slide off thisfront surface 55, so that now thefins 13 are moved back by the axially directed compressive forces of thesprings 19 attacking theirhubs 15, until the abuttingsurfaces 17 rest on the conical surface 38 offlange portion 9, thus preventing further swinging of fin l3 beyond the open position.

In this axial movement of thefins 13 the earns 25 are shifted into the range of theslots 34, cut in theextensions 33 of theflaps 30, so that theseflaps 30 can now swing up around theiraxles 29. This swinging up takes place under the action of a force exerted by gases, branching off from the nozzle and passing through theboreholes 54 into theannular space 56, on theshoulder surface 52 of the sleeve 36 (now acting as piston) and thus on thebolts 43 passed into the grooves 41 of theirtongues 39. Thesleeve 36 can thereupon be moved back until itsflange 37 strikes on the flange 47 (of adjusting sleeve 46) acting as a stop. In this final position thesleeve 36 and also theflap 30 coupled therewith, which have now swung into the braking position shown on the left in FIG. 1, are prevented from moving back by the spring-rings 49 jumping into thegroove 44 ofsleeve 36.

Sleeve 36 can, instead of this, also be moved by the force of said spring loading said sleeve.

In FIGS. 5 to 8 similar parts, or parts exercising the same function as in the first embodiment are designated by the reference numerals used there. Theflaps 30 are pivoted aroundaxles 29 which, contrary to the first example. are arranged in the region of the rear part offin 13. The forked hubparts 58 (of flap 30) supported on theaxles 29 engage ingrooves 59 arranged in aflange 60 of nozzle body 3 situated behind the nozzle throat. The front part a offlange 60 is offset with respect to the rear portion and provided with aprojection 79 extending conically backwards, and ending in afront surface 55 which supportshubs 15 of thefin 13. Between flange 60 and aring 61 screwed on the rear end of nozzle body 3 there is a thread on which adjustingring 62 is screwed and can be shifted by turning in the axial direction. The brake action is at the maximum if theflap 30 lie with the surfaces (FIG. 8) of their hub portions in a plane perpendicular to the longitudinal axis of the rocket (FIG. 5) in which the rear surface offlange 60 rests which also forms the stop for adjustingring 62.

In the normal position ofa flap 30 (FIG. 5) the flap extends substantially along the nozzle body 3, which widens in diameter towards the front. Theflaps 30 in the normal position are masked by thefins 13, since they are arranged between the axles ll of said fins. Similarly to the first example, the contiguous edges 63 (FIG. 6) of twoadjacent flaps 30 are overlapped by thecams 25 of abolt 24 arranged in the front hubportion of afin 13. The ends of aspiral spring 65, arranged in aslot 64 of the hub-part 58 of aflap 30 and surrounding theaxle 29 are supported on the flap and on the nozzle body 3. Thespring 65 is exercising its efforts to turn the flap 30 (FIG. 5) anticlockwise, but the flap is held in the inactive position by the lockingcams 25. The latter are in front of the slots 66 (FIG. 6) cut in theedges 63ofthe flap 30.

A wedge-shapedlatch member 67 indicated in FIG. 5 is represented on an enlarged scale together with the hub-portion 58 of aflap 30 in FIGS. 7 and 8. Anotch 68 is cut out from the front in said wedge-shapedlatch member 67 which tapers from front to back. Theend 70 of anotherspiral spring 69 wound aroundspring 65 is supported on the surface 72 (bordering on the notch 68) of thelatch member 67. Theother end 71 ofspring 69 rests on the surface 73 (on the outside in relation to the rocket) oflatch member 67 and presses same against the bottom 74 ofgroove 59 in the nozzle body 3. Thelatch member 67 is pressed backwards through theend 70 of thepretensioned spring 69 so that it is supported with itssurface 73 on thesurface 75ofthe hub portion 58.

In accordance with FIGS. 7 and 8 the rotary axis 0ofa flap 30 does not coincide with the axis P of thecylindrical surface 76, which forms the rounded end of thehub portion 58. Thesurface 73 of thelatch member 67 touches saidcylinder 76 along a line A. The two parallel axes O and P, which are at a distance from each other, lie in a plane which, in the inactive position of flap 30 (FIG. 7) intersects thecylinder 76 along the line B and forms an angle of 45 with a plane perpendicular to the axis of the rocket. Aplane 77 containing the axis of rotation O intersects thesurface 73 oflatch member 67 to which it is perpendicular, along a line C.

A cylinder 78 (dotted lines in the drawing) whose axis coincides with the axis 0 and whose radius is equal to the distance A0, of the axis 0 from the contact line A, intersects thecylinder 76 along a lineE. Another cylinder 79 of radius OB, placed around 0, intersects theplane 77 along a line D. As also shown in FIG. 7, the distance of that part ofcylinder 76 between A and E from the axis 0 is greater than the distance ofcylinder 78 from the same axis, and the greatest distance between these twocylindrical surfaces 76 and 78 occurs in the plane which contains the axis 0 and the line B. Thecylinder 76 enters theplane area 80 of the hub-portion 58 along a line designated as G. The distance ofcylinder 76 from the axis of rotation 0 decreases steadily from B towards G.

In the position of thehub 58 shown in FIG. 8, where the flap is swung into the active position at to the inactive position, thelatch member 67 touches thecylindrical surface 76 of thehub 58 along a line F.

This second embodiment operates in the following manner: Thefins 13 are opened by thesprings 19. The hub surfaces 17 are supported on thefrontal flange portion 9 of the nozzle body 3, whereby thefin 13 is locked. Since thefins 13 are axially displaced when opening, thecams 25 of the lockingbolts 24 geared thereto slide over theslots 66 of theflaps 30. The

flaps 30 are thereby released and swung by thesprings 65 around theaxles 29 into the operating position in which, as shown in FIG. 5, they are supported on the adjustingring 62.

The entire radius of action of theflaps 30 determined by the limiting positions of the adjustingring 62, is limited by their position, shown on the left in FIG. 5, and also by a position (not shown) fully hinged back at l80 with respect to the inactive position. Contrary to the first example, in this case the radius of action of theflaps 30 is shifted to the rear region offins 13, which is an advantage insofar as the stabilizing effect of the fins cannot be undesirably affected by the stream around the flaps. Another advantage is the fact that the aerodynamic braking forces, which also have a stabilizing effect on the rocket, in this case act upon a greater lever arm with respect to the center of gravity of the rocket.

When aflap 30 is swung out of the inactive position into the operating position shown in FIG. 5, then, according to FIG. 7, the section ofcylinder 76 between lines A and B comes first of all in contact withlatch member 67. Since the line B is at a distance from the axis of rotation O which is greater by the distance between line D and line C than the distance of line C from said axis 0, thelatch member 67 will be thrust forward, against the pressure exerted by theend 70 ofspring 69, along thesurface 74 of the nozzle body 3. If the line B ofcylinder 76 has reached theplane 77, thelatch member 67 has travelled a path a and reached its foremost position. When theflap 30 is swung on beyond the line B towards line G, thelatch member 67 is thrust back, since the distance of the part ofcylinder 76, how passing in front of it, from the axis of rotation O is continuously decreasing, so that it remains in contact with thehub portion 58.

Under the action ofspring 65 and under the action of an aerodynamic force increasing as the angle of traverse increases and finally under the action of an inertia force which attacks theflap 30 during the phase of acceleration, theflap 30 strikes the adjustingring 62 at relatively high speed and is rejected by said ring. This rebound movement is powerfully damped by a high frictional force which appears because thelatch member 67 is now clamped between thesurface 74 and the region of thehub 58 situated between line B and line G. The path travelled by theflap 30 when rebounding from the adjustingring 62 is therefore short, so that after a return movement under the action ofspring 65 and the aerodynamic force, it rebounds from adjustingring 62, but now with so little energy that it is immediately stopped and held in the operating position under the action of said frictional force.

By reason of the development of thehub part 58 of aflap 30, thelatch member 67 of course also acts in the same way in any other predetermined operating position of the flap.

In the case of rockets which perform a twisting movement, centrifugal forces act upon theflaps 30. These forces are exerted to turn the flaps, which are in the operating position, in the opposite direction to the aerodynamic forces, i.e. clockwise (see FIG. 8). Thelatch members 67 now prevent theflaps 30 from being turned away from the adjusting ring by the centrifugal forces when the speed of the rocket decreases and therefore the aerodynamic forces become less.

I claim:

1. Rocket comprising a nozzle body, folding find arranged around said body, axles for said fins on said nozzle body parallel to the rocket axis, means for swinging said fins from a folded position alongside said nozzle body into an operating position extended from said body, a braking device on said body to vary the flight path of said rocket comprising swiveling flaps which in said folded position of said fins are located between said fins and said nozzle body in an inactive position and means operative when the rocket is launched swinging said flaps into a braking position extended from said body.

2. Rocket according to claim 1 wherein latch members are provided for said flaps supported on said axles for said fins and said latch members are displaced by said fins to release said fla s.

5 Rocket according to claim 2 wherein said fins are brought by a swiveling movement and a displacement in the axial direction out of said folded position into said operating position and said flaps have slots into which said latch members engage upon axial displacement of said fins to release said flaps.

4. Rocket according to claim 1 wherein axles for said flaps are provided on said nozzle body arranged adjacent the rear ends of said fins in a plane perpendicular to the rocket axis and said flaps in inactive position rest on said nozzle body in front of said axles of said flaps.

5. Rocket according toclaim 4 wherein said flap axles are arranged on said nozzle body adjacent the front ends of said fins in a plane perpendicular to the rocket axis and said flaps in the inactive position lie behind said flap axles on said nozzle body.

6. Rocket according to claim 1 wherein the braking position of said flaps is in a region bounded by the position in which said flaps are in a plane perpendicular to the rocket axis and by the position in which said flaps are pointing backwards approximately parallel to the rocket axis.

Claims (6)

1. Rocket comprising a nozzle body, folding fins arranged around said body, axles for said fins on said nozzle body parallel to the rocket axis, means for swinging said fins from a folded position alongside said nozzle body into an operating position extended from said body, a braking device on said body to vary the flight path of said rocket comprising swiveling flaps which in said folded position of said fins are located between said fins and said nozzle body in an inactive position and means operative when the rocket is launched swinging said flaps into a braking position extended from said body.

2. Rocket according to claim 1 wherein latch members are provided for said flaps supported on said axles for said fins and said latch members are displaced by said fins to release said flaps.

3. Rocket according to claim 2 wherein said fins are brought by a swiveling movement and a displacement in the axial direction out of said folded position into said operating position and said flaps have slots into which said latch members engage upon axial displacement of said fins to release said flaps.

4. Rocket according to claim 1 wherein axles for said flaps are provided on said nozzle body arranged adjacent the rear ends of said fins in a plane perpendicular to the rocket axis and said flaps in inactive position rest on said nozzle body in front of said axles of said flaps.

5. Rocket according to claim 4 wherein said flap axles are arranged on said nozzle body adjacent the front ends of said fins in a plane perpendicular to the rocket axis and said flaps in the inactive position lie behind said flap axles on said nozzle body.

6. Rocket according to claim 1 wherein the braking position of said flaps is in a region bounded by the position in which said flaps are in a plane perpendicular to the rocket axis and by the position in which said flaps are pointing backwards approximately parallel to the rocket axis.

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