Dual port payload attach ring compatible satellite

Patent metadata

Field	Value
Publication number	US-9796488-B2
Application number	US-201514873990-A
Country	US
Kind code	B2
Filing date	Oct 2, 2015
Priority date	Oct 2, 2015
Publication date	Oct 24, 2017
Grant date	Oct 24, 2017

Abstract

Systems, methods, and apparatus for dual port ring compatible satellites are disclosed. In one or more embodiments, a method for removably attaching at least one spacecraft to a payload attach ring on a launch vehicle involves attaching a strongback of each of the spacecrafts to two respective payload ports of the payload attach ring on the launch vehicle. In one or more embodiments, the strongback of each of the spacecrafts is attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate. The method further involves separating the strongback of each of the spacecrafts from the two respective payload ports of the payload attach ring on the launch vehicle by using at least one mechanical actuator on each of the beams.

First claim

We claim:

1. A method for removably attaching at least one spacecraft to a payload attach ring on a launch vehicle, the method comprising:
attaching a strongback of each of the at least one spacecraft to two respective payload ports of the payload attach ring on the launch vehicle,
wherein the strongback of each of the at least one spacecraft is attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate, and
wherein each of the beams is mounted to each of the respective port adaptor plates via at least one bolt.

2. The method of claim 1 , wherein the strongback of each of the at least one spacecraft is attached to each of the beams via at least one coupler.

3. The method of claim 2 , wherein the at least one coupler is one of a cup/cone interface or a load bearing interface.

4. The method of claim 1 , wherein each of the port adaptor plates is mounted to one of the respective payload ports via at least one bolt.

5. The method of claim 1 wherein each of the beams comprises at least one spring, and wherein when the strongback of each of the at least one spacecraft is attached to each of the two respective payload ports, the at least one spring is in a pre-separation position.

6. The method of claim 1 , wherein the method further comprises separating the strongback of each of the at least one spacecraft from the two respective payload ports of the payload attach ring on the launch vehicle.

7. The method of claim 6 , wherein each of the beams comprises at least one mechanical actuator, and wherein the separating of the strongback of each of the at least one spacecraft from each of the two respective payload ports is achieved by the at least one mechanical actuator activating to allow for separation of the strongback of each of the at least one spacecraft from each of the two respective payload ports.

8. The method of claim 6 , wherein each of the beams comprises at least one spring, and wherein when the strongback of each of the at least one spacecraft is separated from each of the two respective payload ports, the at least one spring is extended to a post-separation position.

9. A system for removably attaching at least one spacecraft to a payload attach ring on a launch vehicle, the system comprising:
the launch vehicle comprising the payload attach ring; and
each of the at least one spacecraft comprising a strongback, wherein the strongback of each of the at least one spacecraft is configured to be attached to two respective payload ports of the payload attach ring on the launch vehicle,
wherein the strongback of each of the at least one spacecraft is configured to be attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate, and
wherein each of the beams is configured to be mounted to each of the respective port adaptor plates via at least one bolt.

10. The system of claim 9 , wherein the strongback of each of the at least one spacecraft is configured to be attached to each of the beams via at least one coupler.

11. The system of claim 10 , wherein the at least one coupler is one of a cup/cone interface or a load bearing interface.

12. The system of claim 9 , wherein each of the port adaptor plates is configured to be mounted to one of the respective payload ports via at least one bolt.

13. The system of claim 9 , wherein each of the beams comprises at least one spring, and wherein when the strongback of each of the at least one spacecraft is attached to each of the two respective payload ports, the at least one spring is in a pre-separation position.

14. The system of claim 9 , wherein the strongback of each of the at least one spacecraft is configured to be separated from the two respective payload ports of the payload attach ring on the launch vehicle.

15. The system of claim 14 , wherein each of the beams comprises at least one mechanical actuator, and wherein the separating of the strongback of each of the at least one spacecraft from each of the two respective payload ports is achieved by the at least one mechanical actuator activating to allow for separation of the strongback of each of the at least one spacecraft from each of the two respective payload ports.

16. The system of claim 14 , wherein each of the beams comprises at least one spring, and wherein when the strongback of each of the at least one spacecraft is separated from each of the two respective payload ports, the at least one spring is extended to a post-separation position.

17. An apparatus for removably attaching at least one spacecraft to a payload attach ring on a launch vehicle, the apparatus comprising:
a pair of beams; and
a pair of port adaptor plates,
wherein a strongback of each of the at least one spacecraft is attached to two respective payload ports of the payload attach ring on the launch vehicle via a respective beam of the pair of beams mounted to a respective port adaptor plate of the pair of port adaptor plates, and
wherein each beam of the pair of beams is mounted to each of the respective port adaptor plates via at least one bolt.

18. The apparatus of claim 17 , wherein the pair of beams are connected to each other via at least one crossbar.

Assignees

• Boeing Co

Inventors

• Cook Timothy Scott
• Friend Robert Bruce

Classifications

• B64G1/64 Primary

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

• B64G2001/643

  Operations & Transport · mapped topic

• B64G1/641 Primary

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

• B64G1/645

  Separators · CPC title

• B64G1/646

  Docking or rendezvous systems (refuelling in space B64G1/4024) · CPC title