US3368775A

US3368775A - Separable connector

Info

Publication number: US3368775A
Application number: US573766A
Authority: US
Inventors: Frank R Larsen; Roy K Trelle
Original assignee: Navy Usa
Current assignee: US Department of Navy
Priority date: 1966-08-18
Filing date: 1966-08-18
Publication date: 1968-02-13
Anticipated expiration: 1985-02-13

Description

Feb. 13, 1968 LARSEN ET AL 3,368,775

SEPARABLE CONNECTOR Filed Aug. 18, 1966 2 Sheets-Sheet 1 INVENTORE FRANK R. LARSEN BY ROY K. TRELLE Q/aa M74:

4 TTOR/VE) Feb. 13, 1968 R LARSEN ET AL 3,368,775

SEPARABLE CONNECTOR Filed Aug. 18, 1966 2 Sheets-Sheet 2 WWW 1m! Fm:

United States Patent 3,368,775 SEPARABLE CONNECTOR Frank R. Larsen, Saratoga, Calif., and Roy K. Trelle, Seattle, Wash, assignors, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Aug. 18, 1966, Ser. No. 573,766 9 Claims. (Cl. 2441) ABSTRACT OF THE DISCLOSURE Resilient means in the form of torsion bars are mounted in the coupling area between a missile and its booster to impart spin to the missile about its longitudinal axis when the booster is separated by destruction of explosive bolts.

The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

This invention relates to separation devices for parts normally retained in engagement and for forceful disengagement of said parts upon command.

Heretofore spin has been imparted to a body in flight by the use of air engaging vanes or by slanted nozzles through which expanding gasses are exhausted. The former method is limited to low altitude regions having atmosphere and the latter requires a complex and sometimes hazardous gas generating system. By the present invention it is contemplated that the above disadvantages can be avoided and portions of a multistage missile or other vehicle in flight may be separated with simultaneous application to the separating parts of predetermined spin and/ or linear motions.

An object of this invention is to provide a simple, strong and effective connection between objects traveling in space and for effectively breaking such connection upon command.

Another object is to provide such connection wherein spinning and/ or linear motions are imparted to a separating part or parts but wherein no expanding gas is utilized nor aerodynamic surfaces required.

Still another object is to provide such construction wherein the spin or motion imparting apparatus is mounted up on and stays with one of the separating parts.

Other objects, advantages, and novel features of the invention will become apparent from the following detailed description when considered in conjunction with the accompanying drawings wherein:

FIG. 1 is an end view of a vehicle stage embodying one form of the present invention.

FIG. 2 is a longitudinal sectional view taken along a line substantially corresponding to line 22 of FIG. 1.

FIG. 3 is a similar view taken along a line substantially corresponding to line 3-3 of FIG. 1.

Referring now to the drawings in detail there are disclosed two axially aligned vehicle stages -12 (FIG. 2) in end abutting engagement. Stage 10 may be considered the parent or booster stage and has an end opening 14 defined by an inwardly projecting rim 16. Rim 16 has a plurality of spaced inwardly extending bosses 18 to re-- ice prevent the torsion bars from slipping out of place during mating'of the sections.

Torsion bars 28 may be round in cross section as illustrated and have a straight central portion 32. The extremity of each bar may be provided with oppositely slanting end arms 34 each terminating in

rounded knobs

36, 37.

As best shown in FIG. 1 each

rounded knob

36, 37 rests against an abutment 38 in the adjoining missile stage and applies a constant pressure thereto which tends to re tate stage 12 about the common cenral axis 40 of the vehicles. The degree of pressure so exerted will depend upon the material of which the torque bar is made, its size, and proportions. Also the torque may be varied within limits by torque adjustment screws 42 which are retained in adjusted position by lock nuts 44.

In operation, the explosive bolts when fired free the stages for relative rotation and the opposed ends of the torque member 28 being freely journaled in slots 26 exert equal and opposite torqueing force on the opposed abutments 38. The stages are therefore simultaneously separated and a spin is imparted thereto. Obviously the degree of spin is proportional to the respective masses of the two stages and each will tend to rotate. However if the parent vehicle is suitably stabilized by other means only the detached stage will rotate.

It will be apparent that if desired the opposed legs 34 can be separated at an even greater angle and thereby the lineal component of force may be increased, oppositely it will be decreased when the legs are at less divergence when cocked.

Also it will be apparent that more than one torque member may be suitably supported in place and when so employed will materially increase the spin imparted upon stage separation. Thus torque bars may be mounted so as to cross the axis of the stages at different angles and each end of each bar may engage suitable abutments on the other stage.

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

We claim:

1. Interstage coupling means for a multi-stage vehicle wherein at least two stage members are positioned in end to end relationship, the combination of:

releasable fastening means interconnecting said stages;

said means being released upon command to thereby allow physical separation of said stages;

and a resilient member supported on one of said stages and engaging the other of said stages;

said resilient member normally urging opposite rotation of the assembled stages about their longitudinal axes; said member being released by stage separation to impart a relative spin to the released parts.

2. A device of claim 1 wherein the resilient member comprises at least one elongate torque bar.

3. The device of claim 2 wherein the elongate torque bar has upturned ends which extend adjacent the end of the other stage.

4. The device of claim 3 wherein the upturned ends are oppositely directed and engage abutments on the other stage.

5. The device of claim 4 wherein the abutments are equidistant from the longitudinal axis of the stage.

6. The device of claim 5 wherein the torque bar is freely journaled so as to apply equal and opposite reaction forces to the other stage.

7. The device of claim 6 wherein adjusting means is provided to vary the tension stored in the torque bar.

3 4 8. The device of claim 4 wherein the abutment against References Cited which the arm ends bear is slanted so as to impart a lineal UNITED STATES PATENTS movement to the other stage parallel to the axis of the 3 116 895 1/1964 Mitchum ("her stage- 3,174,706 3/1965 Wagner 244 1 9. The device of claim 8 wherein both a rotary and a 5 lin l m Bm H i $0 imp r FERGUS S. MIDDLETON, Primary Examiner.