Payload deployment from launch vehicle using canted springs for imparting angular and linear velocities

Claim 2

Apparatus for the gyroscopic ejection of a payload from a payload carrier comprising: a payload carrier; a payload mounted on said payload carrier; means releasably securing said payload to said payload carrier; at least two compression springs compressed between said payload carrier and said payload in positions tilted from the perpendicular on opposite sides of said payload, to apply tangential components of spring compression force in the same rotational direction to said payload and components of spring compression thrust to said payload in the same direction parallel to the rotation axis of said payload; and means supporting the ends of each of said springs to permit tilting of said springs to second angular positions when said payload is ejected; whereby said springs are held in compression by said payload and when said means releasably securing said payload to said support structure releases said payload, said payload is rotated and ejected by said springs from said payload carrier.

Claim 3

Apparatus for the gyroscopic ejection of a payload from a launch vehicle comprising: a support structure adapted for mounting in said launch vehicle and having payload mounting means thereon; a payload having mounting seat means thereon disposed on said payload mounting means of said support structure; means releasably securing said payload to said support structure; a plurality of springs compressed in uniformly tilted first angular positions between said support structure and said payload, to apply tangential components of spring compression force to said payload in the same rotational direction and components of spring compression thrust to said payload in the same direction parallel to the rotation axis of said payload; and means supporting the ends of each of said springs to permit tilting of said springs to second angular position when said payload is ejected; whereby said springs are held in compressed tilted positions by said payload and when said means releasably securing said payload to said support structure releases said payload, said payload is rotated and ejected by said springs from said support structure.

Claim 4

Apparatus for the gyroscopic ejection of a payload from a launch vehicle comprising: a support structure adapted for mounting in said launch vehicle and having payload mounting means thereon; a payload having mounting seat means thereon disposed on said payload mounting means of said support structure; means releasably securing said payload to said support structure; a plurality of springs compressed in uniformly tilted first angular positions between said support structure and said payload, to apply tangential components of spring compression force to said payload in the same rotational direction and components of spring compression thrust to said payload in the same direction parallel to the rotation axis of said payload; and means supporting the ends of each of said springs to permit tilting of said springs to second angular position when said payload is ejected; whereby said springs are held in compressed tilted positions by said payload and when said means releasably securing said payload to said support structure releases said payload, said payload is rotated and ejected by said springs from said support structure.

Claim 5

Apparatus as set forth in claim 2, in which, said payload is a spacecraft having a central axis substantially intersecting the center of mass of said spacecraft and said springs apply torque about said central axis while ejecting said spacecraft in a direction longitudinally of said central axis.

Claim 6

Apparatus as set forth in claim 3, in which, said spacecraft is a three-axis stabilized spacecraft.

Claim 7

Apparatus as set forth in claim 3, in which, said spacecraft is a spin stabilized spacecraft.

Claim 8

Apparatus as set forth in claim 3, in which, said springs are uniformly circumferentially distributed with respect to said central axis.

Claim 9

Apparatus as set forth in claim 2 in which said means supporting the ends of each of said springs comprises a pivotally mounted spring seat for each end of each spring of said plurality of springs permitting each spring seat to rotate and providing two degrees of angular freedom for the plane of each spring seat.

Claim 10

Apparatus as set forth in claim 2, in which said mounting seat means comprises an adapter secured to said payload and terminating in a circular seat; means on said payload mounting means providing a complementary circular seat engaging said circular seat of said adapter; and said means supporting the ends of each of said springs pivotally supports said springs in correspondingly tilted positions in compression in uniformly spaced circumferential positions with respect to both of said circular seats.

Claim 11

Apparatus as set forth in claims 1 or 2 in which said means supporting the ends of each of said springs comprises ball and socket spring mounts at each end of each spring.

Claim 12

Apparatus as set forth in claim 1 in which said means supporting the ends of each of said springs comprises ball and socket spring mounts at each end of each spring; and a support section on each ball and socket spring mount at the end of each spring adjacent said payload carrier securing each of such ball and socket spring mounts to said payload carrier.

Claim 13

Apparatus as set forth in claim 2 in which said means supporting the ends of each of said springs comprises ball and socket spring mounts at each end of each spring; and a support section on each ball and socket spring mount at the end of each spring adjacent said support structure securing each of such ball and socket spring mounts to said support structure.