Spacecraft support and separation system

Claim 2

A spacecraft assembly separation apparatus comprising: a support structure, latching means for releasably securing said spacecraft assembly to said structure, spacecraft assembly separation and acceleration spring means secured to said structure comprising means for applying forces in the same direction to said spacecraft assembly at points located near the center of mass of the spacecraft assembly and intermediate said latching points to accelerate said spacecraft in that direction without significant rotation and retaining means located intermediate said latching points for providing centralized single point retention of said spacecraft assembly against said acceleration spring means when said latches are opened, and means for disconnecting said retaining means for providing single point release.

Claim 3

Apparatus for separating a spacecraft assembly from a support structure such as the cargo bay of a shuttle orbiter, said apparatus comprising: multipoint latching means including multiple spaced retractable latches for latching said assembly at multiple points to the support structure, imaginary lines joining said points forming a boundary, assembly separation and acceleration means secured to said support structure comprising spring means for applying ejecting forces against said assembly within said boundary and near the center of mass of said assembly to accelerate said assembly away from the support structure without significant rotation; retaining means secured at one end to said support structure and at the other end to a single point contact on said assembly intermediate said latches and within said boundary for retaining said assembly against compressed spring means eventhough said latches are open and to allow said latches to be relatched if any failure of a latch occurs, and means for disconnecting said retaining means to provide when said latches are open a single point release.

Claim 4

Apparatus for separating a spacecraft assembly from a support structure such as the cargo bay of a shuttle orbiter, said apparatus comprising: multipoint latching means including multiple spaced retractable latches for latching said assembly at multiple points to the support structure, imaginary lines joining said points forming a boundary, assembly separation and acceleration means secured to said support structure comprising spring means for applying ejecting forces against said assembly within said boundary and near the center of mass of said assembly to accelerate said assembly away from the support structure without significant rotation; retaining means secured at one end to said support structure and at the other end to a single point contact on said assembly intermediate said latches and within said boundary for retaining said assembly against compressed spring means eventhough said latches are open and to allow said latches to be relatched if any failure of a latch occurs, and means for disconnecting said retaining means to provide when said latches are open a single point release.

Claim 5

Apparatus for separating a spacecraft assembly from a support structure such as the cargo bay of a shuttle orbiter, said apparatus comprising: three point latching means including three spaced retractable latches for latching said assembly at three points to the support structure, imaginary lines joining said points forming a triangle, assembly separation and acceleration means secured to said support structure comprising spring means for applying ejecting forces against said assembly within said triangle and near the center of mass of said assembly to accelerate said assembly away from the support structure without significant rotation; retaining means secured at one end to said support structure and at the other end to a single point contact on said assembly intermediate said latches and within said triangle for retaining said assembly against compressed spring means eventhough said latches are open and to allow said latches to be relatched if any failure of a latch occurs; and means for disconnecting said retaining means to provide when said latches are open a single point release.

Claim 6

Apparatus for separating a spacecraft assembly from a support structure such as the cargo bay of a shuttle orbiter, said apparatus comprising: three point latching means including three spaced retractable latches for latching said assembly at three points to the support structure, imaginary lines joining said points forming a triangle, assembly separation and acceleration means secured to said support structure comprising spring means for applying ejecting forces against said assembly within said triangle and near the center of mass of said assembly to accelerate said assembly away from the support structure without significant rotation; retaining means secured at one end to said support structure and at the other end to a single point contact on said assembly intermediate said latches and within said triangle for retaining said assembly against compressed spring means eventhough said latches are open and to allow said latches to be relatched if any failure of a latch occurs; and means for disconnecting said retaining means to provide when said latches are open a single point release.

Claim 7

The combination of claim 3 wherein said spring means includes a plurality of springs positioned about the center of mass of said assembly.

Claim 8

The combination of claim 4 wherein said retaining means is a cable between the support structure and the spacecraft and said disconnecting means includes a pyrotechnic device.

Claim 9

A satellite/perigee stage assembly support and separation apparatus for support of said assembly in the cargo bay of the space shuttle where the assembly includes a junction clamping means for releasably joining the perigee stage to the satellite, said apparatus comprising: a U-shaped cradle assembly removably mounted across the bay and between said cargo bay and said perigee stage, said perigee stage having starboard and port extending trunnions near the forward end of said perigee stage and an aft trunnion, first and second retractable latches when closed latching said perigee stage to said cradle assembly at said port and starboard trunnions, and a third retractable latch when closed latching the aft trunnion, assembly separation and acceleration means secured to said cradle assembly comprising acceleration spring means for applying forces in the same direction to said satellite at points located near the center of mass of the satellite/perigee stage assembly and intermediate said first and second retractable latches to accelerate said satellite/perigee stage assembly in said direction without significant rotation and single point retaining means located intermediate said first, second and third latches for retaining said satellite/perigee stage assembly against said acceleration spring means when said latches are opened, and means for disconnecting said retaining means for providing single point release.

Claim 10

A satellite/perigee stage assembly support and separation apparatus for support of said assembly in the cargo bay of the space shuttle where the assembly includes a junction clamping means for releasably joining the perigee stage to the satellite, said apparatus comprising: a U-shaped cradle assembly removably mounted across the bay and between said cargo bay and said perigee stage, said perigee stage having starboard and port extending trunnions near the forward end of said perigee stage and an aft trunnion, first and second retractable latches when closed latching said perigee stage to said cradle assembly at said port and starboard trunnions, and a third retractable latch when closed latching the aft trunnion, assembly separation and acceleration means secured to said cradle assembly comprising acceleration spring means for applying forces in the same direction to said satellite at points located near the center of mass of the satellite/perigee stage assembly and intermediate said first and second retractable latches to accelerate said satellite/perigee stage assembly in said direction without significant rotation and single point retaining means located intermediate said first, second and third latches for retaining said satellite/perigee stage assembly against said acceleration spring means when said latches are opened, and means for disconnecting said retaining means for providing single point release.

Claim 11

The combination of claim 5 wherein said spring means includes a plurality of springs positioned about the center of mass of said satellite/perigee stage assembly.

Claim 12

The combination of claim 5 wherein said disconnecting means includes a pyrotechnic device.

Claim 13

The combination of claim 6 wherein said clamping means is a Marmon clamp.

Claim 14

The combination of claim 6 wherein said retaining means is a cable.

Claim 15

The combination of claim 10 wherein said cable is of Kevlar.

Claim 16

The combination of claim 6 wherein said retaining means is a rod.