Systems for interconnecting dual manifested spacecraft

Patent metadata

Field	Value
Publication number	US-9809329-B2
Application number	US-201414331029-A
Country	US
Kind code	B2
Filing date	Jul 14, 2014
Priority date	Jun 7, 2012
Publication date	Nov 7, 2017
Grant date	Nov 7, 2017

Abstract

Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

First claim

The invention claimed is:

1. A system for interconnecting dual manifested spacecraft for launch by a launch vehicle, the system comprising:
a coupling mechanism configured to selectively and securely couple a first spacecraft to a second spacecraft, wherein the coupling mechanism has an uncoupled configuration, in which the coupling mechanism is configured to permit the second spacecraft to become mated with the first spacecraft, and a coupled configuration, in which the coupling mechanism is configured to restrict the second spacecraft from being demated from the first spacecraft, wherein the coupling mechanism is spring-biased to the coupled configuration, and wherein the coupling mechanism includes:
a plurality of pins configured to permit mating of the first spacecraft and the second spacecraft when the coupling mechanism is in the uncoupled configuration and to restrict demating of the first spacecraft and the second spacecraft when the coupling mechanism is in the coupled configuration;
a plurality of springs associated with the plurality of pins, wherein the plurality of pins bias the coupling mechanism to the coupled configuration; and
a pneumatic system configured to selectively translate the plurality of pins responsive to an increase in pneumatic pressure operative on the plurality of pins and against the bias of the plurality of springs to reconfigure the coupling mechanism from the coupled configuration to the uncoupled configuration thereby permitting mating of the first spacecraft and the second spacecraft, and to selectively permit translation of the plurality of pins under the bias of the plurality of springs responsive to a decrease in pneumatic pressure to reconfigure the coupling mechanism from the uncoupled configuration to the coupled configuration thereby restricting demating of the first spacecraft and the second spacecraft.

2. The system of claim 1 , further comprising:
the first spacecraft and the second spacecraft;
wherein the first spacecraft defines a plurality of bores and the second spacecraft defines a plurality of bores positioned to be aligned with the plurality of bores of the first spacecraft when the second spacecraft is mated with the first spacecraft; and
wherein the plurality of pins are configured to extend through the plurality of bores of the first spacecraft and the plurality of bores of the second spacecraft when aligned and when the coupling mechanism is in the coupled configuration.

3. The system of claim 2 ,
wherein the coupling mechanism is operatively coupled to the first spacecraft;
wherein the first spacecraft and the second spacecraft each includes an interstage adapter, and wherein the coupling mechanism is operatively coupled to the interstage adapter of the first spacecraft; and
wherein the plurality of bores of the first spacecraft are defined by the interstage adapter of the first spacecraft and the plurality of bores of the second spacecraft are defined by the interstage adapter of the second spacecraft.

4. The system of claim 2 ,
wherein the plurality of pins extend radially relative to the first spacecraft and the second spacecraft and are configured to bear a vertical load associated with the second spacecraft when the second spacecraft is mated with the first spacecraft and when the coupling mechanism is in the coupled configuration; and
wherein the plurality of pins are configured to not bear a significant lateral load associated with lateral or radial movement of the second spacecraft relative to the first spacecraft when the second spacecraft is mated with the first spacecraft and when the coupling mechanism is in the coupled configuration.

5. The system of claim 4 , wherein the plurality of bores of the first spacecraft and the plurality of bores of the second spacecraft are circular, and wherein the plurality of pins have planar lateral sides and curved upper and lower sides.

6. The system of claim 2 , wherein the coupling mechanism includes a plurality of coupler assemblies, wherein each coupler assembly includes a housing and at least one pin of the plurality of pins, wherein the at least one pin is supported by the housing and configured to translate relative to the housing when the coupling mechanism transitions between the coupled configuration and the uncoupled configuration, and wherein the housing is operatively coupled to the first spacecraft.

7. The system of claim 6 , wherein the housing and the at least one pin are keyed to restrict rotation of the at least one pin relative to the housing.

8. The system of claim 1 , further comprising:
the first spacecraft and the second spacecraft;
wherein the coupling mechanism is operatively coupled to the first spacecraft;
wherein the first spacecraft and the second spacecraft each include an interstage adapter, and wherein the coupling mechanism is operatively coupled to the interstage adapter of the first spacecraft;
wherein one of the first spacecraft and the second spacecraft defines a channel and the other of the first spacecraft and the second spacecraft defines a collar configured to be positioned within the channel when the second spacecraft is mated with the first spacecraft;
wherein the interstage adapter of one of the first spacecraft and the second spacecraft defines the collar and the interstage adapter of the other of the first spacecraft and the second spacecraft defines the channel;
wherein the first spacecraft defines a plurality of bores and the second spacecraft defines a plurality of bores that are positioned to be aligned with the plurality of bores of the first spacecraft when the second spacecraft is mated with the first spacecraft;
wherein the plurality of pins are configured to extend through the plurality of bores of the first spacecraft and the plurality of bores of the second spacecraft when aligned and when the coupling mechanism is in the coupled configuration; and
wherein the plurality of bores of one of the first spacecraft and the second spacecraft extend through the collar, and wherein the plurality of bores of the other of the first spacecraft and the second spacecraft extend through structure that defines the channel.

9. The system of claim 1 , further comprising a volume of pressurized gas configured to selectively pressurize the coupling mechanism to reconfigure the coupling mechanism from the coupled configuration to the uncoupled configuration against the bias of the plurality of pins, wherein the volume of pressurized gas is a ground-based volume of pressurized gas and does not launch with the launch vehicle.

10. The system of claim 1 , further comprising a volume of pressurized gas configured to selectively pressurize the coupling mechanism to reconfigure the coupling mechanism from the coupled configuration to the uncoupled configuration against the bias of the plurality of pins, wherein the volume of pressurized gas is an on-board volume of pressurized gas and is configured to launch with the launch vehicle.

11. The system of claim 1 , wherein the system is configured to permit reconfiguring of the coupling mechanism from the coupled configuration to the uncoupled configuration only when the launch vehicle is on earth and not after launch of the launch vehicle.

12. The system of claim 1 , further comprising:
a pyrotechnic system configured to selectively demate the second spacecraft from the first spacecraft when the first spacecraft and the second spacecraft are in orbit, and wherein the pyrotechnic system is separate and distinct from the coupling mechanism.

13. The system of claim 1 , wherein the coupling mechanism is free of motors and gears.

14. The system

Assignees

• Boeing Co

Inventors

• Aston Richard William
• Langmack Michael J

Classifications

• B64G1/641 Primary

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

• B64G1/1085

  Swarms and constellations · CPC title

• B64G1/645

  Separators · CPC title

• B64G2001/643

  Operations & Transport · mapped topic

• B64G1/6455

  Pyrotechnics; Using heat · CPC title