Spacecraft payload ejection system
View Patent ↗There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset center of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to center of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset center-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.
1. A system configured to host and controllably eject a payload from a host spacecraft, comprising:
a payload ejection mechanism attached to the host spacecraft, said payload ejection mechanism including a base plate attached to said host spacecraft and a payload release plate;
a payload assembly releasably attached to said payload release plate, a payload being attachable to said payload assembly; and
said payload ejection mechanism including at least two deployment assemblies coupled to said base plate via a first hinge coupling at one end thereof to the base and at another end thereof to said payload release plate via a second hinge coupling, said at least two deployment assemblies being extendable between a stowed position and a fully extended position, said first and second hinge coupling each having a hinge axis, said hinge axes being non parallel to each other so that upon deployment said at least two deployment assemblies are constrained to deploy such that a plane of said payload assembly remains parallel to said base plate;
wherein said payload ejection mechanism to accommodates payloads having centers of mass not coincident with the geometric center of mass of said payload release plate in order to eject said payload assembly away from said host spacecraft such that an effective force vector generated by said payload ejection mechanism acts through a center of mass of said payload at a moment of release of said payload assembly from said payload ejection mechanism regardless of the location of said payload center of mass with respect to the geometric center of said payload release plate.
2. The system according to claim 1 wherein said said at least two deployment assemblies are at least two deployment hinge assemblies, said at least two deployment hinge assemblies each including two hinge plates hinged together along a common mid-axis axis along the lengths of each of said hinge plates, and one hinge plate of each of said at least two deployment hinge assemblies being hinged to said base plate along along said first hinge coupling and defining a lower hinge axis and the other hinge plate being hinged to said payload release plate along said first hinge coupling and defining an upper hinge axis, and wherein each said common mid-axis, lower hinge axis and upper hinge axis of a given deployment hinge assembly is coplanar with each respective said common mid-axis, lower hinge axis and upper hinge axis of all other deployment hinge assemblies.
3. The system according to claim 2 wherein said payload ejection mechanism includes at least four deployment hinge assemblies with a first of two pairs of said at least four deployment hinge assemblies being in opposed relationship, and with a second of two pairs of said at least four deployment hinge assemblies also being in opposed relationship such said at least four deployment hinge assemblies form a rectangular shape.
4. The system according to claim 2 wherein said payload ejection mechanism includes a release mechanism for releasing said payload assembly from payload ejection mechanism upon command.
5. The system according to claim 2 including at least one launch lock mechanism for restraining and securing said payload ejection system and said payload assembly until a commanded time of deployment.
6. The system according to claim 2 wherein said payload ejection mechanism includes an actuator to actuate said payload ejection mechanism.
7. The system according to claim 6 wherein said actuator includes springs to actuate said payload ejection mechanism.
8. The system according to claim 6 wherein said actuator includes a motor to actuate said payload ejection mechanism.
9. The system according to claim 1 wherein said payload assembly is permanently attachable to the payload.
10. The system according to claim 1 wherein said payload assembly is releasably attachable to the payload.
11. A system for hosting and controllably ejecting a payload in a microgravity environment, comprising:
a host spacecraft including propulsion, guidance and telemetry systems; a payload ejection mechanism attached to the host spacecraft, said payload ejection mechanism including a base plate attached to said host spacecraft and a payload release plate;
a payload assembly releasably attached to said payload release plate, a payload being attached to said payload assembly;
said payload ejection mechanism including at least two deployment assemblies coupled to said base plate via a first hinge coupling at one end thereof to the base and at another end thereof to said payload release plate via a second hinge coupling, said at least two deployment assemblies being extendable between a stowed position and a fully extended position, said first and second hinge coupling each having a hinge axis, said hinge axes being non parallel to each other so that upon deployment said at least two deployment assemblies are constrained to deploy such that a plane of said payload assembly remains parallel to said base plate;
wherein said payload ejection mechanism accommodates payloads having centers of mass not coincident with the geometric center of mass of said payload release plate in order to eject said payload assembly away from said host spacecraft such that an effective force vector generated by said payload ejection mechanism acts through a center of mass of said payload at a moment of release of said payload assembly from said payload ejection mechanism regardless of the location of said payload center of mass with respect to the geometric center of said payload release plate;
a computer control system programmed to control the release of said payload assembly from said payload ejection mechanism; and
a communication system configured to allow remote operation of said payload ejection mechanism.
12. The system according to claim 11 wherein said said at least two deployment assemblies are at least two deployment hinge assemblies, said at least two deployment hinge assemblies each including two hinge plates hinged together along a common mid-axis axis along the lengths of each of said hinge plates, and one hinge plate of each of said at least two deployment hinge assemblies being hinged to said base plate along along said first hinge coupling and defining a lower hinge axis and the other hinge plate being hinged to said payload release plate along said first hinge coupling and defining an upper hinge axis, and wherein each said common mid-axis, lower hinge axis and upper hinge axis of a given deployment hinge assembly is coplanar with each respective said common mid-axis, lower hinge axis and upper hinge axis of all other deployment hinge assemblies.
13. The system according to claim 12 wherein said payload ejection mechanism includes at least four deployment hinge assemblies with a first of two pairs of said at least four deployment hinge assemblies being in opposed relationship, and with a second of two pairs of said at least four deployment hinge assemblies also being in opposed relationship such said at least four deployment hinge assemblies form a rectangular shape.
14. The system according to claim 12 wherein said payload ejection mechanism includes a release mechanism for releasing said payload assembly from payload ejection mechanism upon command.
15. The system according to claim 12 including at least one launch lock mechanism for restraining and securing said payload ejection system and said payload assembly until a commanded time of deployment.
16. The system according to claim 12 wherein said payload ejection mechanism includes an actuator to actuate said payload ejection mechanism.
17. The system according to claim 16 wherein said actuator includes springs to actuate said payload ejection mechanism.
18. The system according to claim 16 wherein said actuator includes a motor to actuate said payload ejection mechanism.
19. The system according to claim 11 wherein said payload assembly is permanently attachable to the payload.
20. The system according to claim 11 wherein said payload assembly is releasably attachable to the payload.
21. The system of claim 1 wherein the payload ejection system is resettable for multiple payload ejection procedures.
22. The system of claim 21 including an automatic loading mechanism for placing additional berthed payloads on said host satellite on said payload release plate once a previous payload has been ejected.
23. The system according to claim 11 wherein power and data transfer between the host spacecraft and the payload is via an electro-mechanical connection.
24. The system according to claim 11 including recapturing features mounted on the payload assembly such that the recapturing features enable recapture of payloads.
25. The system according to claim 24 wherein at least one of the recapturing features is comprised of a grappling device.
26. The system according to claim 11 wherein said payload ejection mechanism includes a defined volume in which a center of mass of the payload is located to ensure that the payload is generally non-rotating once ejected from said payload ejection mechanism.