Satellite boom end effector
An orbital satellite has a pair of multi-axis booms including both thrusters for course/attitude adjustment and an end effector for grappling payloads and manipulating other tools and objects. The satellite may launch with a primary payload affixed to a bus and one or more secondary payloads affixed to an ESPA ring. Once in orbit, the end effector may be used to grapple the primary and/or secondary payloads and rearrange them on the bus. In further aspects, the end effector may be used to make bus repairs or take measurements, or hold tools that are used to make bus repairs or take measurements.
1. A satellite, comprising:
a bus;
a boom having a first end mounted to the bus, and a second end distal from the first end;
a thruster mounted on the second end of the boom configured to provide thrust to the satellite, wherein the boom is configured to carry the thruster, the thruster facing in a first direction at the second end of the boom; and
an end effector mounted on the second end of the boom configured to acquire objects, the end effector facing in a second direction opposing the first direction such that a propulsion stream exhausted from the thruster does not impact the end effector.
2. The satellite of claim 1 , wherein the object acquired by the end effector is a payload.
3. The satellite of claim 1 , wherein the object acquired by the end effector is a secondary payload.
4. The satellite of claim 1 , wherein the object acquired by the end effector is an ESPA (evolved expendable launch vehicle (EELV) secondary payload adapter) ring.
5. The satellite of claim 1 , the satellite further comprising an earth deck adjacent the bus, wherein the end effector is configured to remove a secondary payload from an ESPA (evolved expendable launch vehicle (EELV) secondary payload adapter) ring, wherein the ESPA ring is affixed to the earth deck.
6. The satellite of claim 1 , wherein the object acquired by the end effector is a tool for affecting repairs on the satellite.
7. The satellite of claim 1 , wherein the end effector comprises three, four, five, six or seven degrees of freedom of movement.
8. A satellite, comprising:
a bus comprising components;
a payload affixed to the bus;
a boom having a first end mounted to the bus, and a second end distal from the first end;
a thruster mounted on the second end of the boom configured to provide thrust to the satellite, wherein the boom is configured to carry the thruster; and
an end effector mounted along a length of the boom, the end effector configured to grapple the components and payload, wherein in the end effector is mounted to face an opposite direction than a direction of a propulsion stream exhausted from the thruster.
9. The satellite of claim 8 , wherein the end effector is further configured to facilitate repairs on the satellite.
10. The satellite of claim 8 , wherein the end effector further comprises a power source configured to provide power to an object affixed to the end effector.
11. The satellite of claim 8 , wherein the end effector is configured to mate with a customized structural interface mounted on each of the components and payload to be acquired by the end effector.
12. The satellite of claim 11 , wherein the customized structural interface is a grappling fixture.
13. The satellite of claim 8 , wherein the end effector comprises a communications interface enabling communications to and from a component or payload acquired by the end effector.
14. A satellite, comprising:
a bus;
a boom having a first end mounted to the bus, and a second end distal from the bus;
a thruster mounted on the second end of the boom configured to exhaust a propulsion stream providing thrust to the satellite, wherein the boom is configured to carry the thruster, the thruster facing in a first direction at the second end of the boom; and
an end effector mounted on the second end of the boom, the end effector comprising grappling fingers configured to acquire a grappling fixture, and the end effector positioned at the second end of the boom, the end effector facing in a second direction opposing the first direction such that the propulsion stream exhausted from the thruster does not impact the end effector;
wherein the grappling fixture is affixed to one or more of a primary payload, a secondary payload, an ESPA (evolved expendable launch vehicle (EELV) secondary payload adapter) ring, and a tool configured to affect repairs on the satellite.
15. The satellite of claim 14 , wherein the grappling fingers are powered to move between first positions where the grappling fixture may be freely inserted into or removed from the end effector, and a second position where the grappling fingers lock the grappling fixture to the end effector.
16. The satellite of claim 14 , wherein the end effector further comprises a power source configured to provide power to an object affixed to the end effector.
17. The satellite of claim 14 , wherein the satellite further comprises batteries, momentum wheels and fuel canisters, wherein the end effector is capable of acquiring one or more of the batteries, momentum wheels and fuel canisters.
18. The satellite of claim 14 , wherein the satellite further comprises batteries, momentum wheels and fuel canisters, wherein the end effector is capable of making repairs to one or more of the batteries, momentum wheels and fuel canisters.