Systems and methods for deploying a spacecraft arrangement

Patent metadata

Field	Value
Publication number	US-10717551-B2
Application number	US-201916430058-A
Country	US
Kind code	B2
Filing date	Jun 3, 2019
Priority date	Dec 8, 2016
Publication date	Jul 21, 2020
Grant date	Jul 21, 2020

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 an arrangement, wherein the arrangement has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably and directly coupled to one or more adjacent spacecraft in the arrangement;
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 arrangement; 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 a launch vehicle, and
after the layer releases from the launch vehicle, cause the at least two spacecraft in the layer to release from each other.

2. The spacecraft system of claim 1 , further comprising an adaptor having a first end coupled to a bottom-most layer of the arrangement, and a second end configured to couple to a launch vehicle.

3. The spacecraft system of claim 2 , further comprising a plurality of biasing devices between at least one of (i) the bottom-most layer of the arrangement and the adaptor or (ii) adjacent layers in the arrangement,
wherein the plurality of biasing devices apply a biasing force between the at least one of (i) the bottom-most layer of the arrangement and the adaptor or (ii) the adjacent layers to facilitate separating each layer from the launch vehicle after the layer releases from the launch vehicle.

4. The spacecraft system of claim 3 , wherein, for each layer of the arrangement, 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 launch vehicle.

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 characteristic that is different than a characteristic of the at least another of the plurality of biasing devices, and
wherein the characteristic is at least one of a spring constant or a length.

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 the controller is configured to:
determine that a fault condition occurred, and
responsive to a determination that the fault condition occurred, cause the arrangement to release from the launch vehicle before the controller causes at least one of the one or more layers to release from the arrangement.

8. The spacecraft system of claim 1 , wherein a quantity of layers of the one or more layers is one.

9. The spacecraft system of claim 1 , wherein each spacecraft comprises a satellite.

10. The spacecraft system of claim 1 , wherein, for each layer, the at least two spacecraft in the layer have substantially the same height.

11. The spacecraft system of claim 1 , wherein each releasable fastener comprises a pyrotechnic charge that is configured to be activated remotely by the controller to cause the pyrotechnic charge to break the releasable fastener into a plurality of pieces.

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

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

15. 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.

16. The method of claim 12 , 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.

17. The method of claim 12 , further comprising prior to releasing the one or more layers:
determining a fault condition occurred; and
responsive to determining the fault condition occurred, releasing the arrangement from the launch vehicle.

18. The method of claim 17 , wherein determining the fault condition occurred comprises determining that a layer of the one or more layers did not release responsive to a controller transmitting a signal to trigger release of the layer.

19. The method of claim 12 , wherein a quantity of layers of the one or more layers is one.

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 an arrangement, the arrangement has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably and directly coupled to one or more adjacent spacecraft in the arrangement by a respective releasable fastener, the set of acts comprising:
releasing, layer by layer, the one or more layers from a launch vehicle; and
for each layer, after releasing the layer from the launch vehicle, 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

• B64G1/6457

  Springs; Shape memory actuators · CPC title

• B64G1/643

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/64

  Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements · CPC title

• B64G1/00 Primary

  Cosmonautic vehicles · CPC title