US3262365A

US3262365A - Space capsule ejection assembly

Info

Publication number: US3262365A
Application number: US375405A
Authority: US
Inventors: Alfred P Warren; Billy D Lawson
Original assignee: Individual
Current assignee: Individual
Priority date: 1962-09-05
Filing date: 1964-06-15
Publication date: 1966-07-26
Anticipated expiration: 1983-07-26

Description

July 26, 1966 A. P. WARREN ETAL SPACE CAPSULE EJECTION ASSEMBLY Original Filed Sept. 5, 1962 3 Sheets-Sheet l ALFRED P. WARREN, BILLY D. LAWSON,

INVENTORS ATTORNEYS July 26 1966 A. P. WARREN ETAL SPACE CAPSULE EJECTION ASSEMBLY Original Filed Sept. 5, 1962 5 Sheets-Sheet 2 l22 I24 I22 I I .l i 24 ALFRED P. WARREN, BILLY D. LAWSON, Fl G. 5 INVENTORS BY ,Eim

ATTORNEYS y 1966 A. P. WARREN ETAL 3,262,365

SPACE CAPSULE EJECTION ASSEMBLY Original Filed Sept. 5, 1962 5 Sheets-Sheet 5 Fl 6 7 ALFRED P. WARREN, BILLY o. LAWSON, INVENTORS BY 9k ATTORNEYS United States Patent SPACE CAPSULE EJECTION ASSEMBLY Alfred P. Warren, Huntsville, and Billy D. Lawson,

Madison, Ala., assignors to the United States of America as represented by the Administrator of the National Aeronautics and Space Administration Original application Sept. 5, 1962, Ser. No. 221,945, now

Patent No. 3,158,336, dated Nov. 24, 1964. Divided and this application June 15, 1964, Ser. No. 375,405

- 2 Claims. (Cl. 891.5)

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 application is a division of copending application Serial No. 221,945, filed September 5, 1962, now Patent No. 3,158,336.

The present invention relates generally to means for recovering flight capsules used in space research and more particularly to an improved assembly for opening the stabilizing and decelerating flaps of such a capsule.

In the development of aerodynamic bodies or capsules which collapse for packaging purposes, it has become a common practice to provide mechanisms for stabilizing the capsule against tumble and spin and for increasing the drag force thereon during its free fall through the upper atmosphere toward the earth. These mechanisms, in general, consist of a plurality of flaps which usually form a part of the main body portion of the capsule and are pi-"votally mounted directly thereto so as to permit them to be opened and collapsed to operative and inoperative positions, respectively. Numerous mechanical devices have been devised for opening the flaps but, basically, they are of two different types. One type is a so-called umbrella opening device which operates similar to the conventional opener for umbrellas. This opening device consists of a member slidable on a trackway mounted inside of the capsule and pivotable rods or cam elements interposed between the slidable member and the pivotally mounted flaps. The other type is a spring opening device which utilizes an individual leaf or coil spring positioned between the capsule and each flap. The individual spring is normally used in conjunction with a hinge element which pivotally mounts each flap to the capsule. Various types of conventional locking mechanisms for holding the flaps in their opened and collapsed positions have also been used on the stabilization and deceleration mechanisms employing these prior types of mechanical devices for opening the flaps.

Although, in general, the above types of stabilization and deceleration mechanisms have performed satisfactorily to some extent, they have not been found to be entirely suitable where weight, size and reliability requirements are major considerations. The main disadvantage of having the flaps pivotally mounted on the capsule itself and form a part of the main body portion thereof is that such a constnuction results in a waste of vitally needed space, increases the overall weight of the capsule, and interferes with the operation of an adequate parachute assembly for recovering the capsule safely. Where the umbrella opening device is used to open the flaps, the size and weight of the capsule is increased beyond a desirable limit since such a device has to be accommodated inside of the capsule. Some difliculty has also been encountered relative to the storing and opening of the recovery parachute when the umbrella opening device is utilized. The problem presented by opening the flaps with the individual spring opening device is that of reliability. The individual springs have not been reliable to open the flaps uniformly and, accordingly, have caused some of the capsules to initially go into a critical tumble or spin. Several problems and difiiculties have also arisen with the use of prior locking mechanisms for locking the flaps in their opened and collapsed positions. In general, these locking mechanisms are bulky, inconvenient to use and unreliable, particularly the ones used to lock the flaps in their opened positions. 7

In accordance with the present invent-ion, it has been found that the ioregoing difliculties and disadvantages presented by the prior stabilization and deceleration mechanisms may be overcome by providing a capsule assembly which comprises (1) a storage means for storing a capsule prior to its recovery, (2) an ejector device for ejecting the capsule from the storage means, (3) a plurality of stabilizing and decelerating flaps adapted to be readily detached from the capsule, and (4) a device for automatically opening and-locking the plurality of stabilizing and decelerating flaps. The storage means includes an ejection tube which is fixedly mounted on a vehicle, such, for example, as a rocket. The capsule is stored compactly in the ejection tube until the vehicle reaches a certain altitude. At a predetermined time, the capsule is ejected from the ejection tube by the ejector device. The plurality of stabilizing and decelerating flaps are pivotally mounted on a unitary body which is detachably connected to one end of the capsule. The flaps are also adapted to be collapsible to form a configuration that is similar to the configuration of the capsule. This construction permits the capsule to be stored in the ejection tube in a compact manner and thereby causes the flaps to be held in collapsed positions without the use of a latching mechanism. The device 'for automatically and uniformly opening the flaps is composed of a plurality of links and a rotatable disc or plate. Each of the links has one end thereof pivotally connected to the plate and the other end pivotally connected to a corresponding flap. The flaps are automatically locked in their opened positions by having the links in direct alignment with the rotary axis of the plates. This arrangement causes each of the links to be in a dead-center position and thereby prevents each flap from collapsing.

Other advantages and objects of this invention will become more apparent from a reading of the following detailed description and appended claims taken in conjunction with the accompanying drawing wherein:

FIGURE 1 is an elevational view showing capsule assemblies mounted on a rocket vehicle.

FIGURE 2 is an elevational view of a capsule assembly with portions broken away to show the capsule.

FIGURE 3 is a perspective view showing the capsule with stabilizing and decelerating flaps flared open.

FIGUREA is an elevational view showing the recovery of the capsule by a combined balloon and parachute assembly.

FIGURE 5 is a cross sectional view taken along a plane indicated by line 5-5 in FIGURE 6.

FIGURE 6 is a plan view showing the stabilizing and decelerating flaps in their opened positions and the movement of one flap in phantom lines.

FIGURE 7 is a partial plan view showing the stabilizing and decelerating flaps in their collapsed positions.

Referring now in more detail to the drawing wherein like reference numerals designate identical or corresponding parts through the several views, and with special attention to FIGURE 1, reference numeral 10 generally designates a vehicle, shown as a rocket, which the present invention is used in conjunction with. The vehicle 10 consists of an upper stage 12 and a lower stage 14 that includes reaction motors 16. A plurality of capsule assemblies 18 are mounted in any conventional manner on a support beam 20 located between the upper and

lower stages

12 and 14. It is to be understood, however,

that the capsule assemblies 18 may be mounted on any convenient part of the vehicle 10.

As shown more clearly in FIGURE 2, each of the capsule assemblies 18 includes an ejection tube 22 and a capsule 24, the latter of which will be discussed more fully hereinafter. The ejection tube 22 comprises a hollow, cylindrical body 26 which is fixedly secured to the support beam 20 and is adapted to serve as a storage means for the capsule 24. Mounted on the hollow, cylindrical body 26 is an ejector device 28 which, in this instance, includes a conventional fluid actuator 30 having one end thereof pivotally mounted at 32. The other end of the fluid actuator slidable receives an actuating rod 34. The outer end of the actuating rod 34 has a lug mounted thereon which includes a cross member 36 and an upstanding finger 38. The ends of cross member 36 are slidably mounted in grooves 40 formed in a pair of bracket members 42 which are fixedly secured to the hollow, cylindrical body 26. The finger 38 extends through an elongated slot 44 formed in the hollow, cylindrical body 26 between the bracket members 42 and into an opening 46 formed in the capsule 24. In order to withdraw the finger 38 from the opening 46 as the capsule 24 is being ejected from the ejection tube 22, one end of each groove 40 is curved outwardly, as shown in FIGURE 2, to form cam surfaces 48 over which the ends of the cross member 36 are adapted to move. The fluid actuator 30 is actuated by hydraulic fluid or air which is supplied through a line 50 connected to a source (not shown) located inside of the vehicle 10. A cover 52 is fixedly mounted on the hollow, cylindrical body 26 and encompasses the ejector device 28 for protection purposes.

As is clearly shown in FIGURES 3 and 5, the capsule 24 has a stabilization and deceleration unit 54 detachably connected to the upper end thereof. To make the capsule assembly 18 as compact as possible, the stabilization and deceleration unit 54 is constructed of a hollow, unitary body 56 having a plurality of stabilizing and decelerating flaps 58 pivotally connected adjacent to the lower end thereof by hinge elements 60. The flaps 58 are adapted to be opened and collapsed to operative and inoperative positions, respectively. Each of the flaps 58 includes a curved outer surface 62 which increases the aerodynamic characteristics thereof. When the flaps 58 are collapsed in inoperative positions, as shown in FIG- URE 7, the curved outer surfaces 62 also form a configuration which is similar to the configuration of the capsule 24. Such a construction permits the stabilization and deceleration unit 54 and capsule 24 to fit snugly within the ejection tube 22 and thereby eliminates the use of a latching mechanism for latching the flaps 58 in their collapsed positions.

The hollow, unitary body 56 includes an upper end wall 64 which is adapted to receive a device for opening and collapsing the flaps 58, such as the rotary device designated generally by reference numeral 68 in FIG- URE- 5. The rotary device 68 comprises a disc or plate 70 rotatably mounted on a bearing post 72 that is fixedly mounted on the upper end wall 64. To prevent excessive play in the plate 70, a washer element 74 and cotter pin 76 is positioned on the bearing post 72 above the plate 70. The plate 70 is rotated by a spiral spring 78 positioned around the bearing post 72 with one end thereof anchored to the plate 70 by an anchor bolt 80 and the other end fixedly positioned in a slot 82 in the bearing post 72. The

spiral spring 78 is held in place around the bearing post coupling pin 98. The horizontal coupling pin 96 pivotally connects one end of the bifurcated element 94 to a bifurcation 100 located on the upper end of the flap 58; whereas, the vertical coupling pin 98 pivotally connects the other end thereof to the outer end of the link 88.

FIGURES 5 and 6 show a latching mechanism 102 for latching the plate 70 in a position to thereby prevent collapsing of the flaps 58 when they are in their opened or fully pivoted positions. The latching mechanism 102 includes a latch arm 104 pivotally mounted at 106 to the plate 70, a stop pin 108 fixedly mounted on the plate 70, and a slot 110 in the latch arm 104 for slidably receiving the stop pin 108. The latch arm 104 has a cam surface 112 intermediate the ends thereof and a slot 114 adjacent the free end. A latch pin 116 is fixedly mounted on the upper end wall 64 in such a position as to engage the cam surface 112 and be received in the slot 114 when the plate 70 is rotated. One end of a leaf spring 118 is connected to the plate 70 by a bracket 120 and the other end thereof slidable engages the latch arm 104 so as to urge the latter in a clockwise direction. When the plate 70 is rotated by the spiral spring 78, the latch arm 104 moves therewith and is rotated in a counterclockwise direction by engagement of the cam surface 112 with the latch pin 116'. After the plate 70 has rotated through approximately 90, the latch pin 116 is in alignment with the slot 114 and the leaf spring 118 rotates the latch arm 104 clockwise to engage the latch pin 116 in the slot 114. While only one latching mechanism 102 is illustrated, it is apparent that two or more may be employed if deemed necessary. The latching mechanism 102 may also be reversed by mounting the latch arm- 104 on the upper end wall 64 and latch pin 116 on the plate 70.

It should be noted that-when collapsed, as shown in FIGURE 7, the flaps 58'extend above the plate 70, thereby causing the outer end of each of the links 88 to be raised sufficiently to permit each link to overlap an adjacent link. The links 88 are connected to the plate 70 in such a manner as to allow the plate 70 (to rotate through 90 between the fully collapsed and fully opened positions of the flaps 58. The movement of one link 88' and one flap 58 is shown in phantom lines in FIGURE 6. When the plate 70 is latched in place by the latching mechanism 102, the longitudinal axis of each of the links 88 is in direct alignment with the rotary axis of the plate 70. Such an arrangement causes each of the links 88 to be in a dead-center position with respect to the center of the bearing post 72 and thereby serve as an additional locking device to further prevent the flaps 58 from collapsing when outer forces are applied thereagainst.

As mentioned hereinbefore, the stabilization and deceleration unit 54 is detachably connected to the upper end of the capsule 24. As shown in FIGURE 5, this is accomplished by means of shear screws 122 which extend through the lower end of the hollow, unitary body 56 and a depressed ring 124 formed integrally with the upper end of the capsule 24. The hollow, unitary body 56 houses a combined balloon and parachute assembly 126 which is inflated by an inflation device (not shown) located inside of the capsule 24. Inflation of the combined balloon and parachute assembly 126 takes place at a predetermined altitude causing the shear screws 122 to be sheared and the stabilization and deceleration unit 54 to thereby be detached from the capsule 24. By so removing the stabilization and deceleration unit 54, the capsule 24 becomes substantially lighter and is more easily recovered by the combined balloon and parachute assembly 126. After the stabilization and deceleration unit 54 is completely separated from the capsule 24, the balloon and parachute assembly 126 becomes operative as shown in FIGURE 4. If the capsule 24 lands in water, the balloon will prevent it from sinking and will also serve as a marker so that it may be readily found.

The operation of the recovery means of the instant invention will now be summarized. The vehicle which carries the capsule assembly 18, as illustrated in FIG- URE 1, is launched in any suitable manner and is propelled away from the earth by the reaction motors 16. At a predetermined time and altitude, liquid or gas is supplied to the actuator 30, thereby causing the finger 38 to eject the stored capsule 24 from the ejection tube 22. Immediately after the capsule 24 leaves the ejection tube 22, the spiral spring 78 automatically rotates the disc 70 and the links 88 move the stabilizing and decelerating flaps 58 uniformly to their opened positions. The elongated flaps 58 are locked in their opened positions in the manner described hereinbefore. As the capsule 24 falls freely through the upper atmosphere, as shown in FIG- URE 3, the flaps 58 stabilize the capsule against tumble and spin and increase the drag force thereon. When the capsule 24 reaches a predetermined altitude, the combined balloon and parachute assembly 126 inflates and thereby disconnects thestabilization and deceleration unit 54 from the capsule by shearing the shear screws 122. The stabilization and deceleration unit 54 then completely separates from the capsule 24 and the combined balloon and parachute assembly 126 becomes operative, as shown in FIGURE 4, to deliver the capsule 24 safely to the earth. Where the ocean is choosen as the recovery site and the capsule 24 lands therein, the combined balloon and parachute assembly 126 will also serve as a means for floating and marking the capsule so that it may be retrieved readily by a ship or helicopter.

Obviously numerous 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. An assembly mounted on a space vehicle for storing and ejecting a space capsule contained therein, said assembly comprising:

(a) a hollow cylinder for storing said capsule, said cylinder having one open end through which the space capsule is ejected,

(b) an elongated slot formed in said cylinder that terminates near the open end thereof,

(0) a pair of spaced elongated bracket members mounted to said hollow cylinder, said brackets being positioned such that the elongated slot in said hollow cylinder is between said pair of bracket members and parallel thereto,

(d) said pair of bracket members each having an arcuate slot formed therein that curves away from said hollow cylinder,

(e) a fluid actuated ejector device pivotally mounted at one end thereof to said hollow cylinder, said ejector device including an extensible rod having a lug mounted on one end thereof, said lug including a cross member that rides in said arcuate slots formed in said bracket members and an upstanding finger which extends through said elongated slot in said hollow cylinder and engages said space capsule; whereby, actuation of said ejector device will result in said rod being rapidly extended to eject said space capsule, and said arcuate slots in said bracket members will deflect said lug member away from said hollow cylinder to withdraw said upstanding finger from engagement with said space capsule.

2. An assembly mounted on the exterior of a space vehicle for storing and ejecting a space capsule; said assembly comprising:

(a) a hollow cylinder for storing said capsule, said cylinder having one end thereof attached to said space vehicle and the other end open to permit ejection of the space capsule,

(c) a pair of spaced elongated bracket members mounted to said hollow cylinder, said bracket members being positioned such that the elongated slot in said hollow cylinder is between said pair of bracket members and parallel thereto,

(e) ejector means pivotally mounted at one end thereof to said hollow cylinder, said ejector means including an extensible rod having a lug mounted on one end thereof, said lug comprising a cross member that rides in said arcuate slots formed in said bracket members and an upstanding finger which extends through said elongated slot in said hollow cylinder and. engages said space capsule; whereby, actuation of said ejector means will result in said rod being rapidly extended to eject said space capsule, and said arcuate slots in said bracket members will deflect said lug member away from said hollow cylinder to withdraw said upstanding finger from engagement with said space capsule.

References Cited by the Examiner UNITED STATES PATENTS 3/1927 Boos 89-1.5 2/1932 Stevens 24463

Claims

1. AN ASSEMBLY MOUNTED ON A SPACE VEHICLE FOR STORING AND EJECTING A SPACE CAPSULE CONTAINED THEREIN, SAID ASSEMBLY COMPRISING: (A) A HOLLOW CYLINDER FOR STORING SAID CAPSULE SAID CYLINDER HAVING ONE OPEN END THROUGH WHICH THE SPACE CAPSULE IS EJECTED, (B) AN ELONGATED SLOT FORMED IN SAID CYLINDER THAT TERMINATES NEAR THE OPEN END THEREOF, (C) A PAIR OF SPACED ELONGATED BRACKET MEMBERS MOUNTED TO SAID HOLLOW CYLINDER, SAID BRACKETS BEING POSITIONED SUCH THAT THE ELONGATED SLOT IN SAID HOLLOW CYLINDER IS BETWEEN SAID PAIR OF BRACKET MEMBERS AND PARALLEL THERETO, (D) SAID PAIR OF BRACKET MEMBERS EACH HAVING AN ARCUATE SLOT FORMED THEREIN THAT CURVES AWAY FROM SAID HOLLOW CYLINDER, (E) A FLUID ACTUATED EJECTOR DEVICE PIVOTALLY MOUNTED AT ONE END THEREOF TO SAID HOLLOW CYLINDER, SAID EJECTOR DEVICE INCLUDING AN EXTENSIBLE ROD HAVING A LUG MOUNTED ON ONE END THEREOF, SAID LUG INCLUDING A CROSS MEMBER THAT RIDES IN SAID ARCUATE SLOTS FORMED IN SAID BRACKET MEMBERS AND AN UPSTANDING FINGER WHICH EXTENDS THROUGH SAID ELONGATED SLOT IN SAID HOLLOW CYLINDER AND ENGAGES SAID SPACE CAPSULE; WHEREBY, ACTUATION OF SAID EJECTOR DEVICE WILL RESULT IN SAID ROD BEING RAPIDLY EXTENDED TO EJECT SAID SPACE CAPSULE, AND SAID ARCUATE SLOTS IN SAID BRACKET MEMBERS WILL DEFLECT SAID LUG MEMBER AWAY FROM SAID HOLLOW CYLINDER TO WITHDRAW SAID UPSTANDING FINGER FROM ENGAGEMENT WITH SAID SPACE CAPSULE.