US3198072A

US3198072A - Portable missile carrier and launcher

Info

Publication number: US3198072A
Application number: US150061A
Authority: US
Inventors: Bengelmann Robert
Original assignee: Boelkow Entwicklungen KG
Current assignee: Boelkow Entwicklungen KG
Priority date: 1959-09-24
Filing date: 1961-11-03
Publication date: 1965-08-03
Anticipated expiration: 1982-08-03
Also published as: DE1156682B; GB925029A; CH388138A

Description

Aug. 3, 1965 R. BENGELMANN 3,198,072

PORTABLE MISSILE CARRIER AND LAUNCHER Filed Nov. 3, 1961 5 Sheets-Sheet 1 Jnvenzor:

2055/? T BENC- EL MANN 71 %a and 7 m ATTORNEYS Aug. 3, 1965 R. BENGELMANN PORTABLE MISSILE CARRIER AND LAUNCHER 5 Sheets-Sheet 2 Filed Nov. 3, 1961 Jn van for: 205521 BENE MWMTM IITTORNEYS Aug. 3, 1965 R. BENGELMANN PORTABLE MISSILE CARRIER AND LAUNCHER 5 Sheets-Sheet 3 Filed Nov. 3, 1961 Jn venlor: ROBERT BENC'ELMAN V WWW 6a ATTORNE Y5 Aug. 3, 1965 R. BENGELMANN PORTABLE MISSILE CARRIER AND LAUNCHER 5 Sheets-Sheet 4 Filed Nov. 5, 1961 Jn van/0r:

[Q0/5527 BEA/GELMANN flwwd 7% Aug. 3, 1965 R. BENGELMANN 3,198,072

PORTABLE MISSILE CARRIER AND LAUNCHER Filed Nov. 5, 1961 5 Sheets-Sheet 5 Jnven for:

HOfiERT BENC-EL MANN 7% W and M te,

A TTORNEYS United States Patent Claims The present application is a continuation-in-part of the pending application Serial No. 57,421, filed September 21, 1960, now abandoned by the present inventor, for a Portable Launching Device.

This invention relates in general to weapon launchers and carriers and associated equipment, and in particular to a new and useful personnel weapon carrier including a missile launching frame adapted to be strapped to the back of a person, including means for supporting and releasing a missile therefrom, means for swinging the missile outwardly from the carrying pad, means for sighting the targets for directing the missile, means for adjustably supporting the frame on the ground, and means for firmg and controlling the missile.

The present invention is an improvement over prior art constructions in the provision of a portable launching device which includes a harness which is adapted to be strapped to the back of a wearer having a frame which supports a protecting plate or launching pad which extends from the shoulders of the wearer to a location below the spine. The reinforcing or supporting frame is advantageously made triangular in construction and includes connecting pieces which extend through the protective pad and which carry a flying body launching platform or carrier. A flying body such as a missile is adapted to be supported at its upper end on the upper end of the 1aunchmg platform with its lower end locked by a locking lever which fits into a slot defined at the lower end of the platform. When the rocket is launched the expelled gases deflect a plate member which releases the locking device so that the rocket may be successfully launched.

A feature of the invention is the provision of a ground supporting device which may be adjustably extended from the supporting frame of the launching device for anchoring the frame to the ground during firing.

A further feature of the invention is the mounting of a launching platform supporting frame which is guided .by parallel linkages between positions resting against the protective pad worn on the back of a missile man to a position spaced outwardly therefrom for launching purposes.

A further feature of the invention is the provision of a sighting device including a rod mounted in alignment with the launching platform for the missile which carries an adjustably positionable sight which may be positioned for viewing by the wearer of the device and which further includes an adjustable scale for the aiming of the missile in accordance with the sighting of the target.

The device further includes a firing button which is connected to an extension cord and which is advantageously carried on a belt which is secured to the launching device.

Accordingly, it is an object of this invention to provide an improved portable missile launching device.

A further object of the invention is to provide a device for launching and carrying flying bodies such as missiles on the backs of military personnel which includes a missile holding launching platform.

A further object of the invention is to provide a missile launching device which includes a harness adapted to be strapped to the wearer and a protective pad adapted to be positioned adjacent the wearers back and with a missile carrying and launching platform including means for suppoting a missile and for releasing the missile for projection.

A further object of the invention is to provide a missile launching device which includes a harness adapted to be strapped to the back of the wearer and adjustable means for extending from the harness which is adapted to be anchored in the ground to provide a support during the launching of the missile.

A further object of the invention is to provide a missile launching device including a main frame member adapted to be worn adjacent the back of the wearer and an adjustable frame movable by parallel linkages between a carrying position adjacent the back of the wearer to a launching position at a spaced location outwardly therefrom.

A further object of the invention is to provide a missile launching device including a harness adapted to be worn on the back of a military person upon which the missile is carried and launched and including sighting means carried by the harness including a member arranged for alignment with the path of flight of the missile and a sight which may be adjusted for viewing by the wearer for aiming purposes.

A further object of the invention is to provide a portable missile launching device including a harness adapted to be strapped to the wearer for carrying and launching a missile and with a firing device capable of being supported by the harness and disassociated therefrom for firing purposes.

A further object of the invention is to provide a missile launching device including a strapped harness with a triangular metallic frame secured to a protector pad and with a missile launching and carrier platform secured and by connections extending through the protector pad.

A further object of the invention is to provide a personnel missile launching device which is simple in design, rugged in construction and economical to manufacture.

The various features of novelty which characterize the invention are pointed out with particularity in the claims annexed to and forming a part of this specification. For a better understanding of the invention, its operating advantages and specific objects attained by its use, reference should be had to the accompanying drawings and descriptive matter in which there are illustrated and de scribed preferred embodiments of the invention.

In the drawings:

FIG. 1 is a front perspective view of a portable missile launching device constructed in accordance with the invention;

FIG. 2 is a rear perspective view of the missile launching device indicated in FIG. 1 shown in position strapped to the back of a military person;

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

FIG. 4 is a rear perspective view of another embodiment of the invention;

FIG. 5 is a fragmentary front plan of a portion of the device indicated in FIG. 4 showing the locking mechanism for the parallelogram guide;

FIG. 6 is a top plan of a portable launching device carried by a missile man in a prone position and having a sighting device constructed in accordance with the invention;

FIG. 7 is a side elevation of the device with the missile man in an upright position and the si hting device swung in position out of use;

F1 3. 8 is a fragmentary side elevation indicating a modified sighting device inciuding means for distance adjustment of the ballistic aiming of the flying body;

FIG. 9 is a section taken on the line 9-9 of FIG. 8;

FIG. 10 is a side elevation of a missile man carrying a complete rocket launching device and including an adjustable ground supporting member;

FIG. 11 is a longitudinal section through one of the ground supporting members with the parts in a retracted position;

FIG. 12 is an elevation with a missile man shown in a prone position carrying a complete rocket launching device with the ground support member adjusted for such position, with the firing device arranged in a position for firing and with the sighting device arranged in a position for sighting; and

FIG. 13 is a perspective View of a firing and signal or command giving device for the flying body arranged in position on a belt portion of the harness.

Referring to the drawings in particular, the invention embodied therein, as indicated particularly in FIGS. 1 to 3, includes a portable missile launching and carrying device which comprises a structural frame generally designated 1 which is formed as an endless or closed tube frame in the form of a triangle and which advantageously includes equal side legs Ia and 1b, and horizontal leg 1g. The size of the tube frame is chosen in such a manner that the corner which has been formed by legs in and lb of equal length lie between the shoulders of the operator while a cross pipe or leg lg will normally fall at the height of the hip of the wearer.

The upper portion of the frame 1 at the intersection of the legs in and 1b is embraced or enclosed by a triangular reinforcement 2 advantageously made of leather, canvas or similar material. Tube carrier or

harness belts

3 and 4 are looped around the respective pipe legs in and 1b and are secured within the reinforcement 2. The harness or

carrier belts

3 and 4 are adapted to extend over the shoulder of a missile man 100 and carry, at their lower ends,

ears'or rings

3a and 4a, respectively, for the reception of a closing member. The two lower corners of the triangle which are situated about the level of the hip of the missile man carry

reinforcements

5 and 6 of a nature similar to that indicated at 2. A belt 11 extends through the

reinforcements

5 and 6 and carries

strap pieces

8 and 9 which are sewn onto the reinforcement and which include an adjustable buckle portion for varying the lengths thereof. The free ends of the

strap pieces

8 and 9 carry a carbine or

spring safety hook

3a and 9a, respectively, which engage into the rings or

ears

3a and 4a, respectively.

In some instances the belt 11 may comprise three separate sections: A central section Illa, and end section 11b and an end section 110. The end section 110 carries buckle til and the end section 11b is provided with holes to permit the belt to be secured around the waist of the missile man 10%.

Gusset or connecting plates 10, ltd, 1e and 11 are welded to the frame member 1 at the locations indicated and a protective plate generally designated 12 is riveted to each of these plates. The protective plate 12 is of a length to cover the entire back portion of the missile man and includes a lower portion 120 which is curved outwardly for deflecting the exhaust gases of a missile 15. For stiffening purposes, longitudinal reinforcing such as seams or

corrugations

12a and 12b are provided.

The surface of the protective plate 12 which is directed away from the missile man and which has been called for reference purposes the rear of the portable launching device is covered with a heat insulating layer 13. The heat insulating layer advantageously consists of one or several layers of asbestos fabric or similar insulating material, depending upon the requirements. In order to prevent a lateral spreading of the jet from the back of the missile man when the flying body is started, the curved portion 120 carries upturned flanges or guiding plates 12d and He at each side.

A combination launching platform and missile carrier generally designated 14 is provided for a missile or flying body 15 and it is rigidly connected to the frame 1 by supporting pipes 16 which are welded to the pipe lcgs 1a and lb of the carrier and penetrate through the protective plate 12 and the heat insulating layer 13. Side walls or plates 14:; and 1419 are formed at each side of the launching platform and carrier 14. These plates are directly welded to the connecting pipe lg and the lower portion extends through the protective plate 12 and the heat insulating layer 13 for this purpose.

As particularly seen in FIG. 3, there are arranged at the upper portion of the trunk of the flying body 15 two bushings 17 which extend parallel to the flying body longitudinal axis. These bushings are adapted to fit over an upstanding belt or projection 29 which is secured to the upper end of the carrier and launching platform 14-. At the lower end of the flying body 15 there is formed a pin 19 on extension -3 which is adapted to fit into spaced bushing members 2i which also are aligned with the longitudinal axis of the missile. The arrangement advantageously includes bushings 17 on each side of and a bushing 21 at the lower end of the launching platform 14 which support

corresponding pins

19 and 20 on each side of the missile. In the drawing, only one set of the bushings is indicated.

The pin 19 is provided with a transverse groove 1% which aligns with an opening in the bushing 21 provided to accommodate a locking member having a curved locking end 25a. The locking member is pivotal about pivot 26 secured at the lower end of the frame 14. A bafile surface 22a is pivotal about a pivot member 23 held by the carrier and launching platform 14 and is positioned below the discharge 162 of the rocket l5. Deflection of this plate 22a by the rocket exhaust gases causes its rocking about the pivot 23 and articulation of the locking device 25 and rotation about pivot 26. The

pivots

26 and 23 are carried by a bearing block portion 24 of the carrier and launching platform 14. a a

In the locking position, the locking member 25 bears against an end portion 22b of a double armed lever 22 which includes the deflecting platform portion 22a. By the corresponding arrangement of the pivot points 23 and 26 and the pivot point which is formed by the locking nose 25a, there is provided a toggle or knuckle whose abutment in the locking position is directly behind dead center. When the jet exhaust of the rocket 15 starts, the impact displaces the surface 22a to rock the double armed level clockwise as indicated by the arrow, so that the axis of the bolt 26 migrates on a circular rock about the axis of the bolt 23. The resiliently yielding locking nose 25a permits this movement until the dead center is reached wherein the pivot axes 23 and 26 and the rocking axis formed by the locking nose 25a of the toggle joint lie in a single Plane. When this position has been exceeded the release or unlocking is aided by the spring force of the latch 25 caused by spring 164 which extends around the pivot 23. The effect is to produce a very rapid unlocking to draw the locking nose 25a out of the groove 1% to release the pin 19 of the rocket 15.

In FIG. 3 the unlocking of the rocket 15 is shown in the initial stage. As soon as the unlocking has been cornpleted the flying body with the bolt 19 can glide from the bushing 21 and the bolt can move out of the bushing 17 and the missile can leave the launching carrier platform 14. The bushings 17 and 21 and the bolts 2% and 19 are made sufliciently long so that the missile is guided for a portion of its launching time.

In FIG. 4 another embodiment of the invention is indicated which includes portionswh-ich are identical with the embodiments indicated in FIGS. 1 to 3 and are similarly designated. In this embodiment the carrier and launching platform 14 is mounted on an extensible frame which carries

leg portions

35a, 35b and 35g which compare to the leg portions of the frame 1. The platform includes the side wall portions 14a and 1411 as. previously and the supporting bolt or pins 20 formed at the upper end thereof. The side walls in this embodiment are interconnected by a U-shaped web member 140 arranged intermediate the length thereof. A feature of this construction is that the auxiliary frame 35 is mounted on .a parallelogram rod system which makes it possible to swing the launching carrier 14 away from the protective pad 12 for firing or launching purposes. Thi insures that the flying body is arranged away as far as possible from the missile man in order to make the sighting of a target and the aiming of the missile easier.

The parallelogram linkage includes handle crank levers generally designated 39 which are pivotally carried by blocks 27 which are secured to each side by the leg lg of the frame 1. Another central upper bearing block 23 penetrates the protective member 12 and insulating layer 13 and is secured to an abutment cover (not shown) arranged between the connecting plates 1c and in. A parallelogram linkage member or lever 29 is pivoted in the block 28 and pivoted to a cross frame or connecting member 34 which is secured to the frame 35. Connecting members 1% extend from the cross member 3- and 'hold the platform and carrier 14.

The handle crank arm generally designated 35 includes lever portions 3% and 31 on respective sides which are secured to hearing blocks 32 and 33, respectively, which are mounted on the leg portion 35g. Lever portions 2?, 390 and 31 are of equal length and permit swinging movement of the frame 35 in parallel relationship to the frame 1 from the dotted line position disposed adjacent the protective pad 12. to a solid position indicated in FIG. 4.

The frame 35 is manipulated by means of gripping handles dub, 36b formed at the end of arm portions Eda, a of the crank levers generally designated Two handle portions Sub are provided (FIG. 5) so that the missile man may move the frame to an extended position by grabbing the respective gripping portions 5% in each of his hands to swing the frame 35 outwardly for launching purposes. When the parallelogram rod system is forward the launching carrier lid and the frame 35 will fall in a position adjacent the back of the missile man in the dash-dotted line osition indicated. This position is maintained during carrying or transportation of the flying body and provides a very favorable center of gravity position for the missile man Prior to the launching of the flying body the hand levers 30b are pressed downwardly into an approximately vertical position wherein they are held by spring loaded locking pawls as and 57 arranged to project outwardly from each side of the protective pad 1?. (H65. 4 and 5). This position corresponds to the solid indicated position in FIG. 4 with the launching platform 14 and the frame 35 removed from the back of the missile man so that launching of the flying body according to a jumping start principle will not result in an injury to the missile by the hot jets of the jet engine.

In PEG. 5 the

locking devices

36 and 3? are indicated which are held by covering plates 38 and 3'}, respectively, which are secured to the protective pad 12. The looking

pawls

36 and 37 are pivotable about pivot points 41 and 40, respectively, and include

pins

3 and 42, respectively, which are guided in curved slots 39:: and 35a, respectively, which are formed in the

plates

39 and 38. A tube 44 extends between the

plates

38 and 39 and carries a spring i5 which extends into

bores

36a and 3%, respectively, and are connected to the respective plates and 37. The spring 45 urge the plates 36 and 3'7 to the extended or locking position as indicated in the drawings.

When it is desired to collapse the parallelogram linkage system the locking pawls as and 3," are pressed inwardly against the action of the spring 45 until the limiting

bolts

42 and 46 are situated at the other end of the guide grooves 38a and 39a which permits the parallelogram guide to be lowered by means of the levers 5%.

In FIGS. 6 and 7 there is indicated a sighting device for the aiming and launching of the missile which includes a guiding pipe 46 which extends parallel to the longitudinal axis of the flying body and is secured by plates 47 and 48 to the protecting plate 12 on the missile side of the plate.

A guide rod 3-? is slidable in the guiding pipe 36 and it carries a binocular holding arm or carrier 51 which is provided at one end with a sleeve 51a which extends over the rod 4i and is secured thereto by a clamping nut 51) in a desired adjusted position thereon. For the purposes of anchoring the arm 51 in the adjusted position, a groove 49a is defined along a portion of the length of the rod and the nut 5% is adapted to direct a Wedge memher (not shown) into the groove when the binoculars are to be locked in an adjusted position.

The rail of guiding rod 49 assumes, during the transportation of the body, the position shown in FIG. 7 with the rod 4-9 fully retracted within the guide tube 46 and the binocular supporting arm 51 swung to the position indicated. When the missile man assumes a prone position as indicated in FIG. 6, the rod 49 is drawn out of the guiding pipe 26 and the binocular carrier 51 is rotated to a position to permit alignment of binoculars 51b carried thereby with the eye of the missile man. If a fine adjustment of the binocular carrier 51 is desired, then, after releasing the clamping nut 5t this can be effected by displacing the carrier on the rail 49.

in the embodiment indicated in FIG. 6, the guide rail advantageously includes an extending pin 52 which rides in an elon ated groove 45a defined on the pipe 46. The rail 4-? may be locked in an extended position by rotating the pin 52 into a side portion of the groove 46a as indicated in FIG. 6.

In FIG. 8 a slightly modified embodiment of a sighting and observation device for the ballistic of the firing body is indicated. This device has, in a manner similar to that indicated in FEGS. 6 and l, a guide pipe 53 which is parallel to the flying body longitudinal axis and is telescopic in a guide pipe (not shown) provided on the protecting plate 12.

The rod 53 forms a reference for the flying body longitudinal axis which is necessary for the ballistic flight of the missile. The ballistic flight is also influenced by the distance to the target upon launching relative to the sighting line of the missile man and means are provided for accounting for such distance.

For the above purpose a rail or scale member 55 is pivotally connected at a bolt 54 to the outer end of the guide rail 53. The scale 55 has markings 55a which are calibrated or gauged corresponding to the target distance, for example, in yards, meters, etc. The indications snow the differential angle between the missile longitudinal axis indicated by the arrow extending from the nose of the missile 15 and the arrow extending outwardly from the monoculars so sighted by the missile man.

The monoculars 56 are held in an arm 57 which is secured to an arm 5') which is pivotal at a belt 58 at one end to the guide rail 55. Pivot 53 is at a predetermined distance from the pivot 54;. The arm 5% carries at its other end a pivotally connected gliding block 61 which is slidable on the scale member 55. A clamping screw 62 (also shown in FIG. 9) is provided to lock the gliding block er in a sighted position. The angle B which has been formed in the triangle by the guide rail 53 and the arm 59 is equal to the an le between the flying bodys starting direction and the sighting line of the missile man and corresponds to the angle of increase or extension necessary for making a ballistic shot of the missile.

When the missile man is not employing the sighting device in a firing position, it is forward so that both the arm 59 and the guide rail 55 lie parallel to the rail 53 and the rail 53 is pushed back into the guide pipe (not shown) carried by the protector plate.

In FTGS. 10 to 12, there is indicated the ground engaging support device for receiving the reaction forces during the launching of the flying body. Ground supporting devices are advantageously connected at either or both of the locations 1e and 1 (FIG. 1) of the launching device. The length of the ground engaging supports is chosen in such a manner that they will project from the ground in substantially a perpendicular direction, whether the missile man is lying in a prone position, as indicated in FIG. 12, or in a kneeling position, as indicated in FIG. 10, so that these supports will take up the reaction forces which result from the deflection of the jet gases against the protecting plate 12 upon the launching of the flying body. These supports are particularly advantageous in connection with flying bodies which lift themselves from the launching pad according to a jumping start or booster process.

As particularly shown in FIG. 11, a ground supporting device generally designated 110 includes three telescopic pipe portions, an outer one 63, an intermediate one 64 and an inner one 65. The intermediate portion 64 is provided with an extension having lug or connecting eyelet 64a. The support device 110 is secured to the platform by a bolt connection (not shown), made to the eyelet 64a and the launching device. This connection is advantageously a pivotal one permitting swinging of the support device 116. The pipe 64 is axially guided in the pipe 63 and rotation of the pipe 63 relative to the pipe 64 is prevented by a longitudinal groove 64b which is engaged by a wedge 66 secured to the pipe 63.

As indicated in FIG. 11, the pipe 65 has at one end a collar 65a which facilitates its axial guidance in the pipe 64 and limits its withdrawal by contacting portion 63a when extended. The cylindrical part of the pipe 65 is axially guided in a guiding part 63a. The outer circumference of the guiding part 63a includes a threaded portion 63]) onto which is screwed a nut 67 having a narrowing grip. Between the nut 67 and the portion 63a is arranged an elastic clamping ring 68 which tightly embraces the cylindrical part of the pipe 65. When the nut 67 is tightened the clamping ring 68 is elastically deformed and is thereby pressed against the pipe 65. By means of this clamping arrangement the positioning of the pipe 65 relative to the pipe 63 may be accomplished. This permits the extension of the pipe 65 out of the pipe 63 to facilitate adjustment in accordance with the distance of the launching device from the ground.

In order to facilitate a good support of the ground engaging support member 110 on the ground, there are provided at the front end of the pipe 65 a pointed portion 65b and a disc 69 which permits penetration into the ground of the ground engaging member.

In addition to the securing device comprising the

parts

63a, 67 and 63 for the pipe 65, there is provided an additional securing device for the pipe 63. The outer circumference of the pipe 64 is provided with a plurality of grooves or cutouts 70 which are spaced in an axial direction and which are engageable by a tooth 71a of a locking pawl generally designated 78 which is rockably mounted on a bolt 73 on a bearing block 72 which is secured to the pipe 63. A spring 112 which is coiled around the pivot 73 includes an end portion 74 which extends into a recess on the sleeve 73 and an opposite end which biases the tube 71a into one of the cutouts 70.

During transportation of the launching device, the

telescopic pipes

63, 64 and 65 are arranged as indicated in FIG. 11 telescoped within each other. A respective clamping device arranged at the bearing blocks (not shown) and cooperating with the securing eye 64a of the pipe 64 prevents the retracted ground engaging members from disturbing the missile man during walking by swinging back and forth. When it is desired to extend the device, sleeve 63 may be extended relative to sleeve 64 by unlocking the pawl 78 and thereafter locking the tooth 71a in any desired grove 7Q defined along the length of the tubes 64. For extending the tube 65 relative to the tube 63 the nut 67 is loosened and thereafter tightened when the support is in an extended position. It should be appreciated that the ground supporting device of this 8 character may be employed wherever telescopic members are required for support, such, as a tent pole, clothes line or other pole constructions.

In FIGS. l0, l2 and 13, there is indicated a firing and signal giving device which comprises essentially a box 75 which is detachably secured to the belt 10 of the launching and carrier device. The box '75 for guided flying bodies includes a depression 75a in which is universally pivoted to a control lever 76. By means of this control lever, the control of the flying body takes place substantially in respect to two main axes. The lever 76 cooperates in a known manner with corresponding potentiometers (not shown). For both guided and ballistic flying bodies there is provided at the box 75 in a depression a starting button 77 for igniting the engine or engines of the flying body 15. The starting button 77 may be secured against unintended actuations by means of a flap 38 which can be locked or swung out of the way.

If the launching device is arranged for more than one flying body then instead of several starting buttons there may be provided at the box 75 a selector switch by means of which the sequence of the flying bodies to be shot is preselected.

To permit the detachable securing of the device to the belt it there is provided a holding frame 78 which is closed at three sides and has a rectangular cutout portion. The box 75 is provided with lateral extensions 75b which slide into the frame from a position above the frame.

In the interior of the box 75 there is arranged a cable drum (not shown) onto which is wound a portion of the control cable 79 to insure that the firing and command giving device, in all possible firing positions, has a suflicient length of cable 79. The cable drum is under the constant influence of a spring (not shown), which spring has a tendency to draw the cable 79 into the box 75 and to wind it onto the drum.

Because of the spring loaded cable drum, it is possible during transportation and during actuation to insure that no disturbing loose cable will hang freely outside of the box 75. The cable is guided through a guide channel 80 which is secured to the belt 10 and is led from there to the back of the protective pad 12. The cable extends either directly to the flying body 15 or to other devices such as, for example, a launching arrangement at the rear of the carrier.

At the side of the carrier at which the launching platform 14 is arranged there is provided a plurality of readily exchangeable batteries 81 and in the case of guided flying bodies additional other required electrical elements. From the batteries 81 and other electrical elements, a firing and control cable 82 leads directly to the ignition device which is provided at the interior of the flying body. The provision of batteries and the additional electrical elements on the protecting plate 12 has the advantage that the firing and signal giving device which is embodied by the box 75 can have the smallest possible dimension, so that it may be easily handled by the missile man in any desired position.

When the missile man, as indicated in FIG. 12, goes into a position ready for launching the missile, the necessary or required cable length is automatically reeled out from the box 75 which is taken off the frame 78. This ermits the missile man to always bring the firing and command device into a position which is convenient for operation by him. When the device is to be returned to the belt the cable is automatically wound within the box 75.

Thus, the invention provides a portable launching device Which includes means for sighting and accurately ballistically aiming the missile, for anchoring the launching device to the ground for support purposes and providing means for launching and controlling the fli ht of the missile in those instances Where the missile is of a guided type. It should be appreciated that the different embodiments show means for carrying only a single missile, but the invention is not limited thereto and several flying bodies may be transported provided the weight is not excessive. The principles of the invention for carrying and launch-ing purposes would, of course, apply in each instance.

While specific embodiments of the invention have been shown and described in detail to illustrate the application of the inventive principles, it will be understood that the invention may be embodied otherwise without departing from such principles.

What is claimed is:

1. A missile carrier and launching device comprising a rigid endless frame member including a horizontal leg portion adapted to lie substantially horizontally across the back of the missile man at a location adjacent his waist, strap means connected to said frame member, said strap means including shoulder encircling strap portions and a belt portion for encircling the waist of the missile man, a protective plate secured to said straps and including a lower portion extending in a curved direction outwardly from said frame member for deflecting gases from the missile and adapted to overlie the back of the missile man, a launching platform and carrier secured to said frame, said launching platform and carrier constituting a missile holder and including a pin-receiving socket for a pin borne by the missile, and means locking said pin in said socket.

2. A missile carrier and launching device according to claim 1, wherein said protective plate curved portion includes a side deflecting flange at each side for deflecting gases.

3. A missile carrier and launching device according to claim 1, in which said pin is disposed substantially parallel to the back of the wearer for supporting a missile thereon.

4. A missile carrier and launching device according to claim 1, wherein said endless frame is of triangular shape in which the side leg portions thereof extend upwardly to a point centrally of the back of the missile man.

5. A missile carrier and launching device according to claim 1, including a main frame member of triangular outline connected to said harness means at one side of said protective plate, a second frame member located on the opposite side of said protective plate from said main frame member and carrying said launching platform and carrier, and parallel linkage means for swinging said second frame member between a carrying location adjacent said protective plate and to a launching location at a spaced location outwardly from said protective plate.

6. A missile carrier and launching device according to claim 5, wherein said parallel linkage means includes a crank handle member pivotally connected to said main frame and including a handle portion manipulatable by said missile man to swing said second frame member to a desired location.

7. A missile carrier and launching device according to claim 1, wherein said means for locking said pin of said missile in said socket includes a gas deflecting plate pivotally mounted on said launching platform and carrier at a location adjacent said missile, said plate being deflectable by the exhaust gases of said missile to release said locking means.

8. A missile carrier and launching device according to claim 1, including means pivotally connected to said frame and adapted to extend from said frame to the ground for anchoring said launching platform and carrier during the firing of the missile.

9. A missile carrier and launching device according to claim 1, in which said frame, strap means and belt con- H stitute a harness and, including a rod member connected to said harness and disposed to align with the means for supporting said missile in an upright position in parallel relationship to the longitudinal axis of said missle and sighting means carried by said rod.

10. A missile carrier and launching device according to claim 9, wherein said sighting means includes an adjustable sight holder slidabie and rotatable along said rod.

11. A missile carrier and launching device according to claim 10, wherein said sighting means includes a tubular member adapted to be secured to said protective plate and to lie in the same plane as the longitudinal axis of the missile to be carried thereby, a guide rod slidable in said tubular member and bracket means on said guide rod for supporting a sighting device such as a monocular.

12. A missile carrier and launching device according to claim 11, wherein said carrier means adapted to hold a sighting device such as a monocuiar includes an arm member pivotally connected to said red at a spaced location from the end thereof, a scale member pivotally connected to the end of said rod, said monocular carrying member having a block at the end thereof slidable on said scale member whereby sighting of a target is effected to give the increased angle for firing the missile in accordance with the range of the target.

13. A missile carrier and launching device according to claim I, in which said frame, strap means and belt constitute a harness and, wherein said harness includes a belt portion for encircling the missile man and firing control means mounted on said belt portion.

M. A missile carrier and launching device according to claim 13, wherein said firing control means includes a control box and cable extending from said box to said missile.

15. A personnel missile carrier and launching device for launching a missile which is propelled by thrust gases off the back of a missile man, comprising a protective plate adapted to overlie the upper portion of the back of a missile man, a missile carrier and launcher platform mounted on one side of said protective plate including means for supporting a missile in a position for firing and launching substantially parallel to said protective plate, said protective plate being curved outwardly and away from said missile carrier and launching platform for deflecting thrust gases from the missile outwardly away from the back of the missile man, a substantially triangular frame secured to said protective plate on the side thereof opposite from said missile carrier and launching platform, and strap means connected to said triangular mounting frame including shoulder encircling strap portions and a belt portion for encircling the waist of the missile man.

16. A personnel missile carrier and launching device for launching a missile which is propelled by thrust gases off the back of a missile man, comprising a protective plate adapted to overlie the upper portion of the back of a missile man, a missile carrier and launching platform mounted on one side of said protective plate including means for supporting a missile in a position for firing and launching substantially parallel to said protective plate, said protective plate being curved outwardly and away from said missile carrier and launching platform for deflecting thrust gases from the missile outwardly away from the back of the missile man, a substantially triangular frame secured to said protective plate on the side thereof opposite from said missile carrier and launching platform, strap means conected to said triangular mounting frame including shoulder encircling strap portions and a belt portion for encircling the waist of the missile man, and a missile recoil force absorbing device pivotally connected to said platform and adapted to depend therefrom and be inserted in the ground for transmitting the reaction forces from the firing of the missile to the ground.

17. A personnel missile carrier and launching device for launching a missile which is propelled by thrust gases off the back of a missile man, comprising a protective plate adapted to overlie the upper portion of the back of a missile man, a missile carrier and launching platform mounting frame, linkage means mounting said frame for positioning said frame directly adjacent said platform and for positioning said frame at a spaced location therefrom, a hand lever member connected to said linkage means for shifting the position of said frame, a missile carrier and launching platform mounted on said frame including means for supporting a missile in a position for firing and launching substantially parallel to said protective plate, means on said plate on the same side thereof as said missile carrier and launching platform for deflecting thrust gases from the missile outwardly away from the missile man, and strap means for strapping the platform onto the back of the missile man connected to said platform and extending outwardly therefrom on the side opposite from said missile carrier said launching platform.

References Cited by the Examiner UNITED STATES PATENTS 1,323,609 12/19 Pratt 421 1,387,308 8/21 Post 891 1,740,080 12/29 Evert 42-1 12 Kroeger et al. 891.7 Gould 891.7 Walker et al 891.7 De Salardi 421 Brandt 89--1.7 X Brandt 89-l.7 Woods 891.7 Buschers 89--1.7 Henig 891.7 Kreske 42-94 Evans et al. 3348 Musser et al. 42-94 Musser et al. 3348 Guthrie et al. 89--l.7 Sarvis 42--l.8 X Piper et a1 89-1.7 Bornhoft 891.7

Examiners.

Claims

1. A MISSILE CARRIER AND LAUNCHING DEVICE COMPRISING A RIGID ENDLESS FRAME MEMBER INCLUDING A HORIZONTAL LEG PORTION ADAPTED TO LIE SUBSTANTIALLY HORIZONTALLY ACROSS THE BACK OF THE MISSILE MAN AT A LOCATION ADJACENT HIS WAIST, STRAP MEANS CONNECTED TO SAID FRAME MEMBER, SAID STRAP MEANS INCLUDING SHOULDER ENCIRCLING STRAP PORTIONS AND A BELT PORTION FOR ENCIRCLING THE WAIST OF THE MISSILE MAN, A PROTECTIVE PLATE SECURED TO SAID STRAPS AND INCLUDING A LOWER PORTION EXTENDING IN A CURVED DIRECTION OUTWARDLY FROM SAID FRAME MEMBER FOR DEFLECTING GASES FROM THE MISSILE AND ADAPTED TO OVERLIE THE BACK OF THE MISSILE