US2967482A

US2967482A - Release mechanism

Info

Publication number: US2967482A
Application number: US775664A
Authority: US
Inventors: Jr John B Toomey
Original assignee: Individual
Current assignee: Individual
Priority date: 1958-11-21
Filing date: 1958-11-21
Publication date: 1961-01-10
Anticipated expiration: 1978-01-10

Description

Jan. 10, 1961 J, TQOMEY JR 2,967,482

RELEASE MECHANISM Filed Nov. 21, 1958 2 Sheets-Sheet 1 FlG.l

BOOSTER MISSILE INVENTOR JOHN B. TOOMEY, JR.

ATTORNEYS Jan. 10, 1961 J B, TOOMEY JR 2,967,482

RELEASE MECHANISM Filed Nov. 21, 1958 2 Sheets-Sheet 2 h I 32 :30 2a 42 i 32 so 2 A? 42 D 25 I 26 I 2e l4 /|4 l6 as FIG. 6 FIG. 7

24 32 as so 2 2 29 24 I 4/ 1/ I 1 A 5| 53 38 y E 39 4s 52 INVENTOR JOHN B. TOOMEY, JR.

BY zaam W Maw ATTORNEYS United States Patent RELEASE MECHANISM John B. Toomey, Jr., Alexandria, Va., assignor, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Nov. 21, 1958, Ser. No. 775,664

6 Claims. (Cl. 102-49) This invention relates to release mechanisms, and more particularly to a mechanism for releasably locking a booster rocket to a missile and for effecting in-flight release of the booster rocket from the missile.

In practice, certain missile-booster combinations are stored in readiness for launching in a locked condition, such for example, as with the missile locked to the booster thereby to minimize the amount of time required for the delivery of the missile-booster combination to the launcher. Heretofore, in certain types of missile-booster combinations, the missile became unelamped from the booster as the aforesaid combination was forcibly ejected from the launcher, the combination, however, remained coupled in response to the force of the booster impulse.

Coupled conditions prevail between the aforesaid elements during flight until the booster thrust decays and the force therebetween approaches a zero value. When this occurs, separation of missile and booster is effected. The rate of separation, however, depends upon the rate of booster thrust decay. Test flights have been made in which separation of the missile and booster have been accomplished with success. Of the portion of flights that have resulted in failures, a considerable percentage of such failures have been attributed to an unsuccessful separation of the booster from the missile.

Moreover, test data has indicated, when flight failures have occurred, that separation of the booster and missile was not instantaneous. Such a condition causes recontact between the missile and the booster. After a careful study one possible explanation advanced for such recontact between the missile and booster, apparently was caused by the combination of a slow booster tail-off and pressure oscillations in the missile diffuser. Further more, it is possible to assume that this recontact caused such misalignment of the missile, as to result in flight instability.

Although, no definite proof has been established that a slow booster tail-off would result in a flight failure, it is apparent that with an unlocked missile-booster joint' and a slow booster tail-off, the missile-booster combination is subjected to instability at separation, and the destabilizing forces will have a greater time interval in which to act.

The present invention provides a release mechanism for use with a booster-missile combination which overcomes all the disadvantages encountered in prior art devices by providing means for releasably locking the booster to the missile and for unlocking the clamping ring at the desired instant, such for example, as when the acceleration forces have decreased to a zero value thereby to allow instantaneous separation of the booster rocket and missile. Furthermore, if the clamping ring is released slightly later than the time separation would normally occur if the missile and booster were not in a locked condition, a tension force is built up across the missile-booster joint, as a result of the decay of thrust below the drag differential between the missile and the booster. This tension force would insure that separation 2,967,482 Patented Jan. 10, 1961 "ice proceeds rapidly thereby shortening the time of application of any destabilizing force by the booster on the missile which, in turn, substantially eliminates the possibility of damaging recontact between the missile and the booster.

Briefly, the present invention utilizes the force of acceleration (approximately 40 g.) to move a set-back weight an amount sufficiently to be unlatched from a hook-shaped restraining element. Upon burnout of the rocket booster charge or when the charge has been spent, the acceleration of the missile will decrease to a zero value. When this occurs a spring moves the weight in a forward direction and beyond the original restraining position thereby to actuate a linkage arrangement and unlock the restrained connection between the missile and booster whereupon the missile is released from the booster and tail-oft is instantaneous. The aforesaid linkage is constructed and arranged to return the weight from an actuated position to an initial locked position and to manually unlock the weight, if desired. The invention further; provides a release mechanism which is self-contained, free from pressure chambers, conventional pipe connections and circuitry and which is constructed and arranged to prevent premature release of the missile from the rocket booster.

An object of the present invention is to provide a new and improved mechanical release mechanism for a missile-booster combination.

Another object of the invention is the provision of a release mechanism for eifecting rapid and positive release of a missile from a rocket booster such as to prevent the effects of any destabilizing forces being imposed upon the missile by the booster.

Still another object of the invention resides in the provision of a release mechanism for effecting separation of a missile-booster combination in-flight and at the termination of the booster-thrust cycle.

A further object of the invention is the provision of a release mechanism wherein means responsive to the force of acceleration maintain a missile locked to a rocket booster until the force of acceleration has decreased to zero value.

A still further object of the invention is to provide a release mechanism wherein means prevent premature separation of the missile and the booster in-flight and damaging recontact of the missile and the booster upon separation thereof.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

Fig. 1 is a side elevation of a missile and booster rocket illustrating the missile and boosterin a locked condition in accordance with the release mechanism of the present invention;

Fig. 2 is an enlarged cross-sectional view taken on the line 2-2 of Figs. 1, illustrating the general arrangement of the release mechanism is connection with the clampmg ring;

Fig. 3 is an enlarged plan view of the release mechanism illustrating a fragmentary portion of the missile, booster and clamping ring;

Fig. 4 is an enlarged sectional view taken substantially on the line 44 of Fig. 2 with the release mechanism in a locked condition;

Fig. 5 is a view similar to Fig. 4 with the release mechanism in an unlocked condition;

Referring now to the drawings and more particularly to Fig. 1, the numeral 11 designates a missile-booster combination comprising a missile 12 and a booster rocket 13 locked together by a clamping ring assembly 14 controlled by the release mechanism constructed in accordance with the present invention and generally indicated by the reference character 15, the booster rocket being provided with the conventional propellant charge.

As more clearly shown on Fig. 2, the clamping ring assembly 14 includes a pair of complementary semicircular resilient ring sections 16 secured together in any suitable manner, as at 17. The terminal end of each ring section 16 is reduced to provide a lug or ear 18 having pivoted thereto, as at 19, one end of an arcuate-shaped lever or member 21, the other end thereof being pivoted, as at 22, to a link or member 23 adapted to be actuated by the release mechanism, the aforesaid linkage arrangement being adapted to effect locking and releasing of the clamping ring 14.

As best shown in Fig. 4, the release mechanism comprises a casing 24 having a pair of oppositely disposed ears or flanges 25 formed therewith and secured to the booster, as at 26. The casing 24 is provided at one end thereof with a cylindrical portion 27 for slidably receiving a set-back weight 28 having one end bifurcated, as at 29 and in spaced relation with respect to end wall 31 of the casing, the other end thereof being in engagement with one end of a spring 32 with the other end of the spring in engagement with the end wall 33 of the casing by the reference character 34, is pivotally mounted on wall 33 by a pin 35, the element being provided with a hook at one end for releasable engagement with a lug or pin 36 carried by the weight 28. The other end of the element 34 extends beyond wall 33 and is provided with an actuating member 37, the aforesaid element being provided with a biasing spring 38 adapted to move and maintain hook 30 out of engagement with lug 36 as the mechanism is actuated to an unlocked position.

Referring now to Fig. 4, an actuating lever 39 is pivotally mounted at one end to the casing 24 by a pin 41, the other end thereof being disposed within the bifurcated portion 29 of weight 28 and in engagement with a roller 42 carried by the weight. The lever is further provided with a notch 43 for receiving a detent 44 mounted on a sleeve 45 rotatably mounted on a shaft 46 extending therethrough and supported in a bearing 47 carried by the casing 24. It will be noted on Figs. 3 and 7 that the link 23 is carried by the sleeve 45 at the outer end adjacent a hexagonal wrench portion 48, the sleeve carrying the detent 44 at the inner end thereof. The shaft 46 is rotatably supported by and within sleeve 45, the outer end being provided with a squared wrench portion 49 and the inner end thereof carrying a link or crank 51.

A reset lever 52 is provided for the mechanism, the lever having one end pivoted to the actuating lever or arm 39 substantially midway between the pivot 41 and free end or roller engaging end thereof, as at 53, the other end of lever being pivoted to the link or crank 51, as at 54. The actuating lever 39 is maintained in an initial position by a spring 55, one end being in engagement with the aforesaid lever, the other end thereof being in engagement with wall 31 of casing 24. By the aforesaid spring arrangement, and as best shown on Fig. 4, the free end of lever 39 is maintained in engagement with roller 42, and the notch 43 being in engagement with the detent 44. Moreover, when the lever 39 is in the aforesaid position the link 23 controlled by sleeve 45, which also carries detent 44, is in a position to maintain the ring section 16 of the clamping ring 14 in clamping or locking engagement with the missile and rocket booster with the linkage including members 51 and 52in a lowermost position. Furthermore, the weight 28 is sustained between the free end of lever 39 and the spring 32 with the hook 30 of the restraining element 34 in locking enaforesaid arrangement the mechanism is maintained in a locked condition.

When the missile-booster combination is set in motion in response to the booster thrust, the acceleration forces acting upon the set-back weight 28 move the weight against the force of the spring 32 an amount sufficiently to disengage the hook 30 of the restraining element 34 out of engagement with the lug or pin 36 carried by the weight thereby releasing the weight for sliding movement within the cylindrical portion 27 of the casing'24. It will be understood, however, that the weight 28 is maintained in the moved or nonactuating position while the aforesaid forces are at a predetermined value and thus separation of the missile and booster will not occur. Upon burnout or consumption of the booster charge, the acceleration of the missile-booster combination will decrease to a zero value. When this occurs, the spring 32 moves the weight 28 forwardly or toward lever 39 and past the original restrained position, Fig. 5, whereupon the roller 42 moves the lever 39 an amount sufliciently to disengage the detent 44 from notch 43. As the detent 44 is disengaged from notch 43 the sleeve 45 is free to rotate and thus since the sleeve is coupled to the normally contracted spring sections 16 by arcuate levers 21 and link 23, it will be apparent that upon release of the sleeve 45 the aforesaid sections react sufficiently to release the sections from locking engagement with the missile and booster whereupon the booster instantly tails off from the missile.

Linkage members

51 and 52 return the weight 28 from an operated position, Fig. 5, to an initial position, Fig. 4. For example, to return the weight 28 to cocked position a wrench may be applied to the squared portion of shaft 46 to rotate the shaft in a clockwise direction (Figs. 4 and 5) which through

links

51 and 52 moves lever 39 to shift the weight 28 to the left in its cocked position by engaging roller 42. When the weight 28 has been moved to its cocked or initial position, the extension 37 of the restraining element is manually or otherwise actuated to move the hook end 30 thereof into locking engagement with pin 36 on weight 28. To manually unlock the mechanism the shaft 46 is rotated in a counterclockwise direction to move the notch 43 in lever 39 away from detent 44 on sleeve 45. Sleeve 45 is then free to rotate in a counterclockwise direction and spread the clamping rings 16. Reversely to draw the clamping rings 16 into locking engagement with the missile and booster a wrench is applied to the hexagonal portion of sleeve 45 to rotate the sleeve in a clockwise direction until detent 44 cams the lever 39 to one side and the detent is retained by notch 43.

While the device has been described in connection with a missile-booster combination, it will be understood that the device may advantageously be used in connection with many other devices such as in-flight arming devices, electrical' switches and mechanical linkages or any other type of mechanism to be actuated in response to a decrease or change in the acceleration forces acting thereon. Moreover, the point at which actuation of the device occurs may be varied by modifying the relative weights and spring characteristics as will be apparent to one skilled in the art.

Briefly stated in summary, the invention provides a new and improved release mechanism which utilizes the force of acceleration to render the mechanism efiective to release the restrained connection between the missile and rocket booster and which is devoid of pressure chambers, pipe connections and other relatively complex components, such for example, as ratchets and pressure actuated pistons.

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.

What is claimed is:

1. In combination with a missile and an axially disposed booster rocket, and a releasable clamping ring for clamping the missile to the booster rocket, a mechanism on the booster rocket for efifecting in-fiight release of the clamping ring comprising, a normally locked device including linkage members connected to said ring for constraining said ring in clamping position as the missile and booster rocket travel along a trajectory in response to acceleration forces acting thereon, means including a normally locked set-back element for actuating said constraining device and linkage members to release said ring as said forces decrease to zero value and said set-back element has been unlocked and means actuated by said set-back element as the initial acceleration forces are applied thereto for unlocking the element.

2. In combination with a missile and a booster rocket, and an expandable clamping ring for clamping the missile to the booster rocket, a mechanism on the booster rocket for elfecting in-flight release of the clamping ring comprising, constraining means for constraining said clamping ring in a clamping position as the missile and booster rocket travel along a trajectory in response to acceleration forces acting thereon, normally locked actuating means unlocked in response to initial acceleration forces applied thereto and movable a predetermined amount when unlocked and said acceleration forces have decreased to zero value, means for moving said actuating means said predetermined amount as said forces decrease to said zero value, and means included in said constraining means and controlled by said movement of the actuating means and linked to said clamping ring for operating said constraining means to release said clamping ring when the actuating means is moved said predetermined amount.

3. The combination as recited in claim 2, wherein means including a pivotally mounted lever are provided for moving the actuating means from an operated position to an initial position.

4. A release mechanism for effecting in-flight release of a clamping ring having a pair of arms coupling a missile to a booster rocket and comprising movable means releasably locked in an initial position and being moved in one direction to a release position in response to an initial acceleration force applied thereto, means including a linkage connected to said arms and operated by said movable means for effecting release of said arms as said movable means is moved in a reverse direction, means for moving said movable means in said reverse direction when saidforce has decreased to zero value, means for maintaining said linkage in a locked condition until said movable means is moved in said reverse direction, and means included in said linkage for efiecting return of said linkage to said locked condition and the arms to said initial position.

5. A release mechanism for effecting in-fiight release of a clamping ring having a pair of arcuate shaped resilient arms coupling a missile to a booster rocket and comprising a casing, a set-back element releasably locked to said casing in an initial position and movable in one direction to a release position in response to an initial acceleration force applied thereto, an actuating lever having one end pivoted to the casing and the other end thereof in engagement with said set-back element and operated by said element as the element is moved in a reverse direction, means for moving said element in a reversedirection as said force decreases to zero value, and means controlled by said lever for effecting release of said arms as the lever is operated by said element.

6. A mechanism according to claim 5, including a spring actuated lever having one end pivoted on said casing and the other end thereof releasably locked to said set-back element for maintaining said element in said initial position until said initial acceleration force is applied to said element.

References Cited in the file of this patent UNITED STATES PATENTS 2,692,557 Wales Oct. 26, 1954 2,779,283 Baughman Jan. 29, 1957 2,792,784 Corrick et a1. May 21, 1957 2,809,584 Smith Oct. 15, 1957 2,833,494 Parker et a1. May 6, 1958 FOREIGN PATENTS 653,024 Great Britain May 9, 1951