Spacecraft stack assembly configured for stacking, securing, and releasing spacecraft
A system for securing spacecraft to a rocket and deploying the spacecraft into orbit includes a stack having a plurality of spacecraft arranged in layers, with each spacecraft being releasably mated with at least one spacecraft in an adjacent layer, and at least one hold down and deploy assembly configured to, in a first configuration, secure the layers of the stack together and secure the entire stack to the rocket, and, in a second configuration, release the entire stack from the rocket into orbit such that the layers passively separate.
1. A system for securing spacecraft to a rocket and deploying the spacecraft into orbit, comprising:
a stack having a plurality of spacecraft arranged in layers, with each spacecraft being releasably mated with at least one spacecraft in an adjacent layer; and
at least one hold down and deploy assembly extending along a length of the stack and configured to, in a first configuration, secure the layers of the stack together and secure the entire stack to the rocket, and, in a second configuration, release the entire stack from the rocket into orbit such that the layers are free to separate.
2. The system of claim 1 , wherein each spacecraft includes at least one separation fitting configured to releasably mate with a separation fitting of the at least one spacecraft in an adjacent layer.
3. The system of claim 2 , wherein, in the hold down configuration, the hold down and deploy assembly imposes a compressive load along an axis defined by the mated separation fittings to secure the spacecraft in the stack and to the rocket.
4. The system of claim 3 , wherein the at least one hold down and deploy assembly applies the compressive load in the first configuration and releases the compressive load in the second configuration.
5. The system of claim 4 , wherein the at least one hold down and deploy assembly comprises:
a tension rod assembly extending along the length of the stack;
an aft tensioning and release mechanism disposed between the tension rod assembly and the rocket and configured to generate tension in the tension rod assembly; and
a forward tensioning and release mechanism configured to apply the compressive load to the stack when tension is imposed in the tension rod assembly.
6. The system of claim 1 , wherein the at least one hold down and deploy assembly applies a compressive load along a length of the stack in the first configuration and releases the compressive load in the second configuration.
7. The system of claim 6 , wherein the at least one hold down and deploy assembly comprises:
a tension rod assembly extending along the length of the stack;
an aft tensioning and release mechanism disposed between the tension rod assembly and the rocket and configured to generate tension in the tension rod assembly; and
a forward tensioning and release mechanism configured to apply the compressive load to the stack when tension is imposed in the tension rod assembly.
8. The system of claim 7 , wherein the aft tensioning and release mechanism releasably and hingedly secures the tension rod assembly to the rocket.
9. The system of claim 7 , wherein the aft tensioning and release mechanism generates tension in the tension rod assembly with an actuator.
10. The system of claim 7 , wherein the forward tensioning and release mechanism is releasably engageable with a top portion of the stack.
11. The system of claim 10 , wherein the forward tensioning and release mechanism is configured as a latch mechanism engageable with a top portion of the stack and releasable from engagement with the stack when tension is released in the tension rod assembly.
12. A system for securing spacecraft to a rocket and deploying the spacecraft into orbit, comprising:
a stack having a plurality of spacecraft arranged in layers, with each spacecraft having first and second separation fittings configured to releasably mate with first and second separation fittings of a spacecraft in an adjacent layer, wherein mated separation fittings between adjacent layers of the stack define first and second columns extending along the length of the stack;
a first hold down and deploy assembly extending along a length of the stack that is moveable between a hold down configuration, wherein a compressive load is applied along the first column, and a deploy configuration, wherein the compressive load is released from the first column such that the stack is free to release from the rocket into orbit; and
a second hold down and deploy assembly extending along a length of the stack that is moveable between a hold down configuration, wherein a compressive load is applied along the second column, and a deploy configuration, wherein the compressive load is released from the second column such that the stack is free to release from the rocket into orbit.
13. The system of claim 12 , wherein the first hold down and deploy assembly comprises:
a tension rod assembly extending along the length of the first column;
an aft tensioning and release mechanism disposed between the tension rod assembly and the rocket and configured to generate tension in the tension rod assembly; and
a forward tensioning and release mechanism configured to apply the compressive load to the first column when tension is imposed in the tension rod assembly.
14. The system of claim 13 , wherein the aft tensioning and release mechanism releasably and hingedly secures the tension rod assembly to the rocket.
15. The system of claim 14 , wherein the aft tensioning and release mechanism generates tension in the tension rod assembly with an actuator.
16. The system of claim 13 , wherein the forward tensioning and release mechanism is releasably engageable with a top portion of the stack.
17. The system of claim 13 , wherein the forward tensioning and release mechanism is configured as a latch mechanism engageable with a top portion of the stack and releasable from engagement with the stack when tension is released in the tension rod assembly.
18. A system for releasably securing spacecraft in adjacent layers in a stack, comprising:
a first spacecraft in a first layer of the stack having a first separation fitting defining a first interface on a first side and a second interface on a second side;
a second spacecraft in a second layer of the stack adjacent to the first layer, the second spacecraft having a second separation fitting defining a first interface on a first side and a second interface on a second side, the second separation fitting releasably mateable with the first separation fitting to define a first load column when mated;
a third spacecraft in a third layer of the stack having a third separation fitting defining a first interface on a first side and a second interface on a second side;
a fourth spacecraft in a fourth layer of the stack adjacent to the third layer, the fourth spacecraft having a fourth separation fitting defining a first interface on a first side and a second interface on a second side, wherein the second interface of the third separation fitting is releasably mated with the first interface of the fourth separation fitting to define a second load column when mated;
wherein
the first spacecraft has a fifth separation fitting defining a first interface on a first side and a second interface on a second side,
the third spacecraft has a seventh separation fitting defining a first interface on a first side and a second interface on a second side,
the first interface of the fifth separation fitting is releasably mated with the second interface of the seventh separation fitting, and
the first and third spacecraft are arranged side by side in the stack with a vertical offset defined between the first and third spacecraft with a length of the stack defining a vertical axis.
19. The system of claim 18 , further comprising a biasing member disposed between mated separation fittings that is configured to urge separation of the mated separation fittings.
20. The system of claim 18 , wherein
the second spacecraft has a sixth separation fitting defining a first interface on a first side and a second interface on a second side,
the fourth spacecraft has an eighth separation fitting defining a first interface on a first side and a second interface on a second side,
the second interface of the sixth separation fitting is releasably mated with the first interface of the seventh separation fitting, and the first interface of the sixth separation fitting is releasably mated with the second interface of the eighth separation fitting, and
the first and third spacecraft are arranged side by side in the stack with a vertical offset defined between the first and third spacecraft, and the second and fourth spacecraft are arranged side by side in the stack with a vertical offset defined between the second and fourth spacecraft, with a length of the stack defining a vertical axis.