Systems and methods for deploying spacecraft

Patent metadata

Field	Value
Publication number	US-10351268-B2
Application number	US-201615373166-A
Country	US
Kind code	B2
Filing date	Dec 8, 2016
Priority date	Dec 8, 2016
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

A spacecraft system includes a plurality of spacecraft in a stack. The stack has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably coupled to one or more adjacent spacecraft in the stack. The spacecraft system also includes a controller configured to, for each layer, (i) cause the layer to release from the stack, and (ii) after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.

First claim

What is claimed is:

1. A spacecraft system, comprising:
a plurality of spacecraft in a stack, wherein the stack has a plurality of layers, each layer includes at least two spacecraft, and each spacecraft is releasably and directly coupled to one or more adjacent spacecraft in the stack;
a plurality of releasable fasteners, wherein each releasable fastener releasably couples a respective one of the plurality of spacecraft to a respective one of the one or more adjacent spacecraft in the stack; and
a controller configured to perform a set of acts, wherein the set of acts comprise, for each layer:
cause the layer to release from the stack, and
after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.

2. The spacecraft system of claim 1 , further comprising a plurality of biasing devices between adjacent layers in the stack,
wherein the plurality of biasing devices apply a biasing force between the adjacent layers to facilitate separating each layer from the stack after the layer releases from the stack.

3. The spacecraft system of claim 2 , wherein, for each layer of the stack, at least one of the plurality of biasing devices applies a different biasing force to the layer than at least another of the plurality of biasing devices such that the layer rotates as the layer separates from the stack.

4. The spacecraft system of claim 3 , further comprising a navigation system for determining an orientation of the spacecraft system relative to the sun, wherein the controller is configured to:
determine, based on the navigation system, when the spacecraft system is oriented such that a longitudinal axis of the spacecraft system is parallel with a direction of the sun, and
responsive to a determination that the longitudinal axis of the spacecraft system is parallel with the direction of the sun, cause each layer to release from the stack such that the plurality of biasing devices cause the layer to rotate about an axis normal to the sun.

5. The spacecraft system of claim 3 , wherein the plurality of biasing devices comprises a plurality of springs, and
wherein the at least one of the plurality of biasing devices has a different spring constant than the at least another of the plurality of biasing devices.

6. The spacecraft system of claim 1 , further comprising a plurality of biasing devices between the at least two spacecraft of each layer,
wherein the plurality of biasing devices apply a biasing force between the at least two spacecraft that facilitates separating the at least two spacecraft from each other after the at least two spacecraft are released from each other.

7. The spacecraft system of claim 1 , wherein one or more of the plurality of releasable fasteners couple the stack to a launch vehicle, and wherein the controller is configured to cause the stack to release from the launch vehicle before the controller causes at least one of the plurality of layers to release from the stack.

8. The spacecraft system of claim 1 , wherein the controller is configured to release the plurality of layers, layer by layer, in an order from a top-most layer of the stack to a bottom-most layer of the stack.

9. The spacecraft system of claim 8 , further comprising an adaptor having a first end coupled to the bottom-most layer of the stack, and a second end configured to couple to a launch vehicle.

10. The spacecraft system of claim 1 , wherein the plurality of spacecraft include a first spacecraft, a second spacecraft, and a third spacecraft,
wherein the first spacecraft and the second spacecraft are in a first layer of the plurality of layers of the stack,
wherein the third spacecraft is in a second layer of the plurality of layers of the stack, and
wherein the first spacecraft is releasably coupled to the second spacecraft and the third spacecraft.

11. The spacecraft system of claim 10 , further comprising a nut releasably coupling the first spacecraft to the second spacecraft,
wherein the nut is actuatable by the controller between a first state and a second state,
wherein, in the first state, the nut is configured to couple the first spacecraft to the second spacecraft, and
wherein, in the second state, the nut is configured to release the first spacecraft and the second spacecraft from each other.

12. A method of dispensing a plurality of spacecraft from a launch vehicle, wherein the plurality of spacecraft are in a stack having a plurality of layers, each layer includes at least two spacecraft, and each spacecraft is releasably and directly coupled to one or more adjacent spacecraft in the stack by a respective releasable fastener, the method comprising:
releasing, layer by layer, the plurality of layers from the stack; and
for each layer, after releasing the layer from the stack, releasing the at least two spacecraft of the layer from each other.

13. The method of claim 12 , further comprising, for each layer, responsive to releasing the layer from the stack, separating the layer from the stack using a plurality of biasing devices applying a biasing force between the layer and the stack.

14. The method of claim 13 , further comprising, for each layer, rotating the layer about an axis as the layer separates from the stack.

15. The method of claim 14 , further comprising:
determining that the launch vehicle is oriented such that a longitudinal axis is parallel with a direction of the sun; and
responsive to a determination that the longitudinal axis of the launch vehicle is parallel with the direction of the sun, releasing each layer from the stack and applying the biasing force between the layer and the stack to cause the layer to rotate about the axis, which is normal to the sun.

16. The method of claim 14 , wherein rotating the layer about the axis comprises applying a first biasing force to first portion of the layer and applying a second biasing force to a second portion of the layer, and
wherein the first biasing force is different than the second biasing force.

17. The method of claim 13 , further comprising responsive to releasing the at least two spacecraft of the layer from each other, separating the at least two spacecraft from each other using a biasing device that applies a biasing force between the one or more adjacent spacecraft.

18. The method of claim 17 , wherein separating the layer from the stack and separating the at least two spacecraft from each other is entirely passive.

19. The method of claim 12 , further comprising prior to releasing at least one of the plurality of layers, releasing the stack from the launch vehicle.

20. A non-transitory computer-readable medium having stored thereon, program instructions that when executed by a controller, cause a spacecraft system to perform a set of acts, wherein the spacecraft system includes a plurality of spacecraft in a stack, the stack has a plurality of layers, each layer includes at least two spacecraft, and each spacecraft is releasably and directly coupled to one or more adjacent spacecraft in the stack by a respective releasable fastener, the set of acts comprising:
releasing, layer by layer, the plurality of layers from the stack; and
for each layer, after releasing the layer from the stack, releasing the at least two spacecraft of the layer from each other.

Assignees

• Boeing Co

Inventors

• Estevez Miguel A
• Flathom Jason D
• Lemke Gary E
• Nakasone Dennis Yoichi
• Volk Christopher P
• Silva Elvis D

Classifications

• B64G1/002 Primary

  Launch systems · CPC title

• B64G1/10 Primary

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• B64G1/1085

  Swarms and constellations · CPC title

• B64G1/22

  Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles · CPC title

• B64G1/641

  Interstage or payload connectors (docking systems B64G1/646) · CPC title