Triggered satellite deployment mechanism

Patent metadata

Field	Value
Publication number	US-10538348-B2
Application number	US-201615383968-A
Country	US
Kind code	B2
Filing date	Dec 19, 2016
Priority date	Dec 19, 2016
Publication date	Jan 21, 2020
Grant date	Jan 21, 2020

Abstract

Provided herein are various improvements to satellite or payload deployment systems and equipment. In one example, a satellite deployment apparatus is provided. The satellite deployment apparatus includes opposing retention members configured to engage protrusions of a satellite and hold the satellite with respect to a baseplate. The satellite deployment apparatus includes at least one pusher element configured to preload a deployment force on the satellite against the opposing retention members when the protrusions of the satellite are captive in the opposing retention members, and a deployment mechanism configured to spread the opposing retention members responsive to triggering by an actuator system and release the protrusions of the satellite for deployment of the satellite away from the baseplate using at least the deployment force.

First claim

What is claimed is:

1. A satellite deployment apparatus, comprising:
opposing retention members configured to engage protrusions of the satellite and hold the satellite with respect to a baseplate;
at least one pusher element configured to preload a deployment force on the satellite against the opposing retention members when the protrusions of the satellite are captive in the opposing retention members;
a deployment mechanism configured to spread the opposing retention members responsive to triggering by an actuator system, and release the protrusions of the satellite for deployment of the satellite away from the baseplate using at least the deployment force.

2. The satellite deployment apparatus of claim 1 , wherein the opposing retention members comprise roller portions that couple to the protrusions of the satellite and allow rolling of the opposing retention members with respect to the protrusions when the opposing retention members are spread.

3. The satellite deployment apparatus of claim 1 , wherein the opposing retention members are mounted in linear rails coupled to the baseplate and configured to slide along the linear rails.

4. The satellite deployment apparatus of claim 1 , wherein the opposing retention members restrain movement of the satellite in at least two dimensions when the protrusions of the satellite are engaged by the opposing retention members.

5. The satellite deployment apparatus of claim 1 , wherein the at least one pusher element comprises a compressive spring system compressed when the satellite is engaged into the opposing retention members to establish the deployment force.

6. The satellite deployment apparatus of claim 1 , wherein the deployment mechanism comprises:
a hammer arm coupled to a hammer member, wherein the hammer member is held against a sear member by an extension spring;
the sear member coupled to the actuator system, and when triggered by the actuator system, releases the hammer member and hammer arm; and
action bars coupled to the hammer arm and the opposing retention members and move the opposing retention members responsive to movement of the hammer arm.

7. The satellite deployment apparatus of claim 6 , wherein the hammer member and the sear are each pivotably coupled to the baseplate by associated bearing features.

8. The satellite deployment apparatus of claim 1 , wherein the actuator system comprises a linear actuator comprising at least one of a leadscrew actuator, ballscrew actuator, linear motor actuator, paraffin actuator, and solenoid actuator.

9. The satellite deployment apparatus of claim 1 , wherein the satellite comprises a CubeSat form factor satellite, and wherein the protrusions of the satellite comprise rails of the CubeSat.

10. The satellite deployment apparatus of claim 9 , wherein at least one end of the rails of the satellite comprises at least one pressure switch, and wherein the at least one pressure switch is depressed by a corresponding one of the opposing retention members when the satellite is captive in the opposing retention members.

11. A payload deployer, comprising:
sliding retention members that engage a payload chassis and hold the payload with respect to a baseplate when the sliding retention members are in a first relative position;
a deployment mechanism that moves the sliding retention members to a second relative position responsive to triggering of a sear element by an actuator, wherein the second relative position disengages the payload chassis and accelerates the payload away from the baseplate using at least a deployment force established against the payload based at least on insertion of the payload into the payload deployer.

12. The payload deployer of claim 11 , wherein the sliding retention members comprise roller portions that couple to the payload chassis and allow rolling of the roller portions of the sliding retention members with respect to the payload chassis when the opposing retention members are moved to the second relative position.

13. The payload deployer of claim 11 , wherein at least one pusher plate comprising one or more compressive springs is compressed based at least on the insertion of the payload into the payload deployer to establish the deployment force.

14. The payload deployer of claim 11 , wherein the sliding retention members are mounted on linear rails coupled to the baseplate and configured to slide along the linear rails.

15. The payload deployer of claim 14 , wherein the deployment mechanism comprises:
a hammer element held in contact with the sear element member;
the sear element coupled to the actuator, and based at least on being rotatably moved past a threshold angle by the actuator, the sear element releases the hammer element to be rotated; and
action bars coupled to the hammer element and the sliding retention members, wherein the action bars move the sliding retention members along the linear rails into the second relative position responsive to rotation of the hammer element.

16. The payload deployer of claim 15 , wherein the hammer member and the sear are each pivotably coupled to the baseplate.

17. The payload deployer of claim 11 , wherein the actuator comprises a linear actuator comprising at least one of a leadscrew actuator, ballscrew actuator, linear motor actuator, paraffin actuator, and solenoid actuator.

18. The payload deployer of claim 11 , wherein the payload comprises a CubeSat form factor satellite in a 1 U or larger form factor, and wherein the payload chassis comprises rails of the CubeSat form factor satellite.

19. The payload deployer of claim 18 , wherein at least one end of the rails comprises at least one pressure switch depressed by a corresponding one of the sliding retention members based at least on the rails being captive in the sliding retention members.

Assignees

• Vector Launch Inc

Inventors

• Riskas Brian James

Classifications

• B64G1/10 Primary

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

• B64G1/645 Primary

  Separators · CPC title

• B64G1/643

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/6457

  Springs; Shape memory actuators · CPC title

• B64G1/641 Primary

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