US3738220A

US3738220A - Flexible-fixed launch and aiming shoe/self releasing electrical and/or pyrotechnic connector for rockets

Info

Publication number: US3738220A
Application number: US00130119A
Authority: US
Inventors: R Rogers; L Howard; J Ketechis; K Magnant
Original assignee: US Department of Army
Current assignee: US Department of Army
Priority date: 1971-04-01
Filing date: 1971-04-01
Publication date: 1973-06-12
Anticipated expiration: 1990-06-12

Abstract

A rocket launcher for launching a plurality of rockets from individual launch rails which are mounted on a common platform. Each rocket is provided with a rear shoe assembly including an upper and lower member. The lower member is permanently fixed to the launcher. The upper member is attached to the rocket by a flexible member so that the rocket can move, within limits, and not disturb the shoe. The upper and lower members are permanently secured together and the flexible member is sufficiently rigid so that it can break the restraints between the upper and lower members at launch. Additionally, since the launcher includes a plurality of rails which are mounted on a common platform, aiming may be accomplished by providing a gyro on the aiming surface (the upper member) instead of in the interior of the individual rockets. An electrical/pyrotechnic connector is provided which connects the rocket with an electrical source and which requires no special sequencing of ejection mechanism.

Description

United States Patent 1191 Rogers, Jr. et al.

[ FLEXIBLE-FIXED LAUNCH AND AIMING SHOE/SELF RELEASING ELECTRICAL AND/OR PYROTECHNIC CONNECTOR FOR ROCKETS [75] Inventors: Roy C. Rogers, Jr.; Lawrence W.

Howard; James C. Ketechis; Kenneth K. Magnant, all of Huntsville, Ala.

[73] Assignee: The United States of America as represented by the Secretary of the Army, Washington, DC.

221 Filed: Apr. 1, 1971 211 App]. No.: 130,119

[111 3,738,220 June 12, 1973 3,446,112 5/1969 Planitzer 89/1.806

Primary Examiner--Samuel W. Engle Attorney-Harry M. Saragovitz, Edward J. Kelly, Herbert Berl and Harold W. Hilton [57] ABSTRACT A rocket launcher for launching a plurality of rockets from individual launch rails which are mounted on a common platform. Each rocket is provided with a rear shoe assembly including an upper and lower member. The lower member is permanently fixed to the launcher. The upper member is attached to the rocket by a flexible member so that the rocket can move, within limits, and not disturb the shoe. The upper and lower members are permanently secured together and the flexible member is sufficiently rigid so that it can break the restraints between the upper and lower members at launch. Additionally, since the launcher includes a plurality of rails which are mounted on a common platform, aiming may be accomplished by providing a gyro on the aiming surface (the upper member) instead of in the interior of the individual rockets. An electrical/pyrotechnic connector is provided which connects the rocket with an electrical source and which requires no special sequencing of ejection mechanism.

7 Claims, 11 Drawing Figures I-"ATENIEB 3.738.220

SHEEI 2 0f 3 FIG. 4

e9 66 64 48 I so FIG. 8

Roy C. Rogers Jr. Lawrence W. oword James C. Ketechis Kenneth K. Magnum,

BY 4222,7!NYMEUIZEORS.

PAIENIEUJUNI 2m:

sum 3 If 3 FIG. 9

FIG. IO FIG. ll

Roy C. Roger, Jr. Lawrence W. Howard James C. Kefechis Kenneth K. Magnum,

INVEINyRS,

y 16 My BACKGROUND OF THE INVENTION In the rocket launching system of the present invention, a plurality of rockets are launched from individual launch rails mounted on a common platform. It is necessary to aim all the rockets at a desired target both accurately and quickly.

In existing rockets which use a gyro in some capacity for guidance and/or control, the approach of laying or aiming the rockets at the desired target is accomplished by aiming the gyro either directly or indirectly, since the rocket flies along the gyro axis and not the rocket axis.

In the indirect aimin g method the gyro is mounted to an accurately machined surface within the rocket. At this point there are two approaches which can be taken toward aiming the gyro: '(1) The launcher can be aimed at the target using some optical method, a servo system, or other to position the missile/launcher from a surveyed point to the desired direction; or (2) The missile may be positioned from a known point by either the optical, servo, or other method.

Both these systems make one basic assumption and that is that the axis of the gyro, which we wish to aim at the target, is aligned withthe centerline of the missile or launcher or whatever external surface we choose to relate the gyro axis to for reference and that no change occurs between the gyro and reference. This assumption is valid within certain bounds, but there are manufacturing tolerance build-ups which will change the alignment by unknown amounts. There are such things as droop due to the rockets own weight, or bow from solar radiation, etc., which can and do cause changes in the missile configuration, affecting critical alignments. These changes can occur even up to the time of launching the rocket adding more unknown errors to the aiming of the rocket.

The direct method utilizes some device mounted di-v rectly to the gyro for aiming or laying. This is usually an optical surface wich can be used for collimation of a scope sight thus determining where the gyro is pointing at the time. From this, how far it must be moved to point at the target can be easily obtained. Although this direct method is not subject to the manufacturing toler-- ance build-up to the degree that the indirect method is, it is just as susceptible to' the other problems of rocket droop, solar radiation, etc.

It is obvious, therefore, that problems are encountered when utilizing conventional aiming approaches in a launch system wherein a plurality of rockets are required to be aimed at a target both accurately and quickly.

An additional problem encountered in rocket launching apparatus is the electrical and/or pyrotechnic interface with the launcher. The common procea dure in this area to to provide an electrical and/or pyrotechnic cable attached to the rocket which is ejected just prior to rocket launch. This requires proper sequencing of events to insure the cable is off the rocket before it moves. Also, the open-circuit and/or short circuit uncertainty condition possible during this jetison can cause malfunction ofthe critical internal guidance and control systems and sub-systems.

The launching system of the present invention minimizes both the effects of manufacturing tolerance build-ups and changes in the rocket due to conditions such as droop and solar radiation, providing a very precise knowledge of where the axis of the gyro is pointing, even up to the time of missile launching. It also provides an electrical/pyrotechnic interface between rocket and launcher which requires no sequencing or ejection mechanism and eliminates the disconnect problem.

SUMMARY OF THE INVENTION The apparatus of the present invention is disposed for flexibly securing a plurality of rockets permanently to individual launch rails carried on a common platform. A shoe assembly which includes an upper member secured to the rocket by a flexible attachment and a lower member secured to the launch rail is provided for mounting the rockets on the launch rails. A releaseload joint connects the upper and lower members which are disposed for release therebetween responsive to propulsive forces acting on the rocket. A gyro is mounted on an accurately machined surface of the upper member of the shoe assembly to be carried by the rocket responsive to launching thereof. In this invention, the launch rail aiming surfaces are a permanent part of the launcher and are accurately aligned or bore sighted to the launcher aiming system. Therefore, to aim a full compliment of rockets requires only that the rockets be loaded on the launcher, the gyros mounted on the aiming surfaces and then the launcher slewed to the proper azimuth and elevation for the target.

BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is a pictorial view of the rocket launching system of the present invention.

FIG. 2 is an elevational view of the arrangement of a single rocket on a launch rail of the launcher, showing the shoe assembly, gyro mounting and the electrical/- pyrotechnic connector.

FIG. 3 is an elevational view of the upper section of the shoe assembly.

FIGS. 4 and 5 are opposite end elevational views of the upper shoe section shown in FIG. 3.

FIG. 6 is an elevational view of the lower section of the shoe assembly.

FIGS. 7 and 8 are opposite end elevational views of the lower shoe assembly shown in FIG. 6.

FIG. 9 is an elevational view taken along line 9-9 of FIG. 6.

FIG. 10 is a sectional of the electrical/pyrotechnic connector of the present invention.

FIG. 11 is an elevational view of the electrical/- pyrotechnic connector shown in FIG. 10.

DESCRIPTION OF THE PREFERRED EMBODIMENT As shown in FIG. 1 a plurality of rockets 10 are mounted on a rocket launcher system 12 including a plurality of launch rails 14 mounted on a common platform 16. Platform 16 is disposed for movement to align the rails 14 in the desired elevation and azimuth positions. The rails are supports for the rockets and are permanent fixtures on platform 16.

As shown in FIG. 2, a rocket securing and retaining device includes a shoe assembly- 18 having upper and lower sections and 22, respectively. A member 24 extends upward from section 20 for secured relation with the rocket. Member 24 is made of spring steel to permit flexing" of the rocket within its restraints.

Upper shoe section 20 includes a plate 25 having a plurality of spaced aft-facing hook-

like members

26, 28 and 30. Hook member 26 is positioned adjacent an aft edge 32 of plate 25 and is substantially evenly spaced between the

edges

33 and 34 of plate 25 (FIG. 4). Hook members 28 and are positioned at the forward end 36 of plate 26 and

adjacent sides

33 and 34 of plate 25, respectively.

In each of the forward hooks 28 and 30 (FIG. 4) is a

hole

37 and 38, respectively sufficient for bolt clearance. In the aft hook 26 is a tapped hole 40 for a bolt. A plurality of channels 42 are provided in plate 25, through a portion of its length and out of the top thereof for electrical leads for electrical and pyrotechnic connection between the rocket and ground equipment (FIG. 3).

Lower shoe section 22 is secured to launch rail 14 (FIG. 2) and includes a plate 44 which is formed with three forward facing

hook receptacles

46, 48 and 50 (FIG. 9). A slot 52 is provided which extends from receptacle 48 to the inner edge 53 of a lip 55 extending across the forward edge 54 of plate 44. A

lip

56 and 58 is provided on opposite sides of plate 44. A tapped hole 60 (FIG. 7) is provided in the forward face 62 of receptacle 50 and another tapped hole 64 is provided in thefoward face 66 of receptacle 46. A clearance hole 68 is provided in receptacle 48 (FIG. 8).

Upper and lower shoe sections are assembled so that

hook members

30, 28 and 26 of member 25 interlock with the

hook receptacles

50, 46 and 48, respectively on member 44. Three special bolts which have a designed fail load are assembled, two through

holes

37 and 38 of member 25 into

holes

64 and 60 of member 44, respectively. The third bolt is assembled through hole 40 of member 25 and into hole 68 of member 44. These bolts secure

parts

25 and 44 together. When the two parts are securely mated, an upper surface 69 of member 44 is firmly positioned against a lower surface 70 of member 25. The length of the surface 69 provides the desired guidance length at launch. When assembled, an end surface 72 and lower surface 74 (FIG. 8) are parallel and perpendicular respectively to a forward surface 75 of a-gyro mounting surface 75 of member 76 and the launcher interface at

surfaces

70 and 72 of member 44.

A gyro 78 is mounted on the surface 75 of gyro support member 76 which forms the launcher aiming surface. Thus, to accurately and quickly align the full compliment of rockets with a target it is only necessary to mount the gyros to the aiming surface. The rockets are free, because of the flexible attachment to the launcher, to assume whatever positions they will within the launch restraints. The launch rail aiming surfaces are permanent fixtures of the launcher and are accurately aligned or bore sighted to the launcher aiming system. Thus, when the gyros have been mounted on the gyro mounting or aiming surfaces, it is only necessary to slew the launcher to the proper azimuth and elevation.

A coupling connector 80 (FIGS. 2 and 10) is mounted on a bracket 82 secured to surface 72 of lower shoe section 44. Leads 84 extend from connector 80 to the launcher connector/cable. A second connector 86 is mounted on the upper shoe member 25 adjacent the forward end 36 thereof. Leads 88 extend from connector 86 to the desired locations in the rocket. Leads 84 and 88 are connected by additional leads (not shown) which extend through channels 42 provided in member 25 (FIG. 3).

Connector 80 is more clearly shown in FIGS. 10 and 11 to include connections for mating with a standard electrical or pyrotechnic connector on both ends. The connector provides attachment and completes the circuit through pins 92 and pyrotechnic connector 94 with the connector 86 mounted on the upper shoe and the launcher connector/cable. Bracket 82 is provided for mounting the connector to the upper shoe.

In operation, when the rocket is mounted on the launcher, surface 72 of plate 44 is forced back against a stop on the launch rails (not shown). Lower surface 74 of plate 44 is forced downward against the rail and the shoe is clamped in this position. The launch rail surfaces which mate with

surfaces

72 and 74 are precision machined surfaces and have been previously aligned with the launcher sighting system (optical, servo, etc.). When the rocket is in position, it becomes a matter of pointing only the launcher rail (in particular, the portion of the rail where the shoe is clamped) at the target since the gyro is now essentially a part of the rail and is precisely aligned to the rail. When this rail is pointed at the target the gyro is also very closely pointed at the target. At this time or piror to aiming, the launcher attached electrical and/or pyrotechnic cables are attached to the connector on the aft face of plate 44.

When the rocket is mounted on the launcher, any movement or misalignment of the rocket to the launcher reference surface, any change of alignment due to solar bow, or any other variation of the rocket with respect to the launcher reference surface is taken up by the flexible member 24 allowing the gyro to remain aligned to the launcher.

When the rocket is fired, the force from the rocket motor thrust is transferred from the rocket to plate 25 by the flexible member 24. When this force reaches the designed fail load of the three bolts, the bolts fail, and the rocket moves forward out of the hooks with the upper portion of the shoe 25 sliding along surfaces 68 of

member

44 and 70 of member 25. Hook 26 rides in the groove 48 to prevent side motion of the rocket during launch. Member 44 remains clamped to the launcher while member 25 travels with the rocket. Gyro 78 which is secured to support member 76 which, in turn, is secured to member 25 travels with the rocket. The gyro may be used to provide guidance during the entire powered flight of the rocket or terminal guidance, as desired. The electrical/pyrotechnic connection has been separated at the forward face of member 25 as the rocket moves forward.

We claim:

1. A rocket launching system comprising:

a. a platform having a plurality of launch rails rigidly secured thereto, each launch rail disposed for support of a rocket thereon;

b. a shoe assembly including an upper portion secured to said rocket and a lower portion secured to said platform, said shoe assembly including releasable attachment means for connecting said upper and lower portions of said shoe assembly and for separation of said upper and lower portions responsive to movement of said rocket as a result of thrust development therein;

c. flexible retaining means for securing said rocket to said upper portion of said shoe assembly to provide for flexing movement of said rockets within predetermined lirnits relative to said launch rails; and,

d. gyro means secured to said upper portions of said shoe assembly whereby aiming of the plurality of rockets is accomplished by placing the launcher rails in the desired azimuth and elevation.

2. A rocket launcher as set forth in claim 1 wherein said flexible retaining means includes a spring steel member secured to each of said rockets and said upper portion of said shoe assembly whereby said rockets are free within predetermined limits to flex relative to said launch rails.

3. A rocket launcher as set forth in claim 2 including a gyro secured to each said upper portion of said shoe assembly whereby aiming of the plurality of rockets is accomplished by slewing the launcher rails to the desired azimuth and elevation.

4. A rocket launcher as set forth in claim 3 including disconnect means for releasably connecting electrical leads to internal rocket components and an external power source, said releasable connecting means including a connector having male and female portions disposed for separation responsive to movement of said rocket during launch thereof.

5. A rocket launcher as set forth in claim 4 wherein said releasable attachment means includes a plurality of arms depending downwardly from said upper portion of said shoe assembly, said lower portion having a plurality of slots therein to receive said arms for engaged relation therebetween.

6. A rocket launcher as set forth in claim 5 including securing means for rigidly securing said upper and lower portions of said shoe assembly in the engaged relation, said securing means disposed for shearing under a predetermined load for release of said upper and lower members to permit launching of said rockets.

7. A rocket launcher as set forth in claim 6 wherein said upper portion of said shoe assembly includes a plurality of channels therein in communication with said disconnect means whereby the electrical leads to said internal components and said disconnect means are routed.

Claims

1. A rocket launching system comprising: a. a platform having a plurality of launch rails rigidly secured thereto, each launch rail disposed for support of a rocket thereon; b. a shoe assembly including an upper portion secured to said rocket and a lower portion secured to said platform, said shoe assembly including releasable attachment means for connecting said upper and lower portions of said shoe assembly and for separation of said upper and lower portions responsive to movement of said rocket as a result of thrust development therein; c. flexible retaining means for securing said rocket to said upper portion of said shoe assembly to provide for flexing movement of said rockets within predetermined limits relative to said launch rails; and, d. gyro means secured to said upper portions of said shoe assembly whereby aiming of the plurality of rockets is accomplished by placing the launcher rails in the desired azimuth and elevation.