Claims
- 1. A method of deploying a payload satellite into a target orbit having an associated target-orbit energy-level, comprising:
attaching the payload satellite to an orbit-transfer vehicle, attaching the orbit-transfer vehicle and the payload satellite to a launch vehicle, launching the launch vehicle, deploying the orbit-transfer vehicle with the attached payload satellite from the launch vehicle with an associated kinetic energy, the kinetic energy associated with the orbit-transfer vehicle being substantially different from the target-orbit energy-level associated with the target orbit, and maneuvering the orbit-transfer vehicle into the target orbit via a change in the kinetic energy associated with the orbit-transfer vehicle, to an energy level corresponding to the target-orbit energy-level, wherein the maneuvering of the orbit-transfer vehicle is effected via a plurality of functional components, and at least a subset of the functional components are also used by the payload satellite.
- 2. The method of claim 1, wherein the subset of functional components used by the payload satellite includes at least one of:
a communications device, a power regulation device, an energy storage device, a heating system, a navigation device, and an attitude control device.
- 3. The method of claim 1, further including detaching at least some components of the orbit-transfer vehicle from the payload satellite when the payload satellite is maneuvered to the target orbit.
- 4. The method of claim 1, further including
aerobraking the payload satellite to effect at least a portion of the change in the kinetic energy associated with the payload satellite.
- 5. The method of claim 1, further including
applying thrust to the payload satellite to effect at least a portion of the change in the kinetic energy associated with the payload satellite.
- 6. A method of facilitating the deployment of a payload satellite into a target orbit having an associated target-orbit energy-level, comprising:
identifying an excess capacity on a scheduled launch vehicle having an associated transfer orbit that has an associated orbit-transfer energy level that is substantially different than the target-orbit energy-level, facilitating an attachment of the payload satellite to an orbit-transfer vehicle, facilitating an attachment of the orbit-transfer vehicle with payload satellite to the launch vehicle, facilitating a deployment of the orbit-transfer vehicle into the transfer orbit via the launch vehicle, the orbit-transfer vehicle thereby having a kinetic energy corresponding to the orbit-transfer energy level, facilitating a maneuvering of the orbit-transfer vehicle to the target orbit via a substantial change in the kinetic energy of the orbit-transfer vehicle, from the orbit-transfer energy level to the target-orbit energy-level, and facilitating a sharing of functional components used for maneuvering the orbit-transfer vehicle with the payload satellite.
- 7. The method of claim 6, wherein the functional components used by the payload satellite includes at least one of:
a communications device, a power regulation device, an energy storage device, a navigation device, and an attitude control device.
- 8. The method of claim 6, further including
facilitating an aerobraking of the orbit-transfer vehicle so as to achieve the target orbit.
- 9. An orbit-transfer vehicle that facilitates the deployment of a payload satellite into a target orbit, comprising
a navigation and control system that is configured to maneuver the orbit-transfer vehicle and the payload satellite from a launch orbit to the target orbit, the launch orbit having an associated launch-orbit-energy that is substantially different than a target-orbit-energy associated with the target orbit, wherein the orbit-transfer vehicle is configured to facilitate:
an attachment of the payload satellite to the orbit-transfer vehicle, and an attachment of the orbit-transfer vehicle to a launch vehicle that is configured to deploy the orbit-transfer vehicle with attached payload satellite to the first orbit, and the orbit-transfer vehicle is configured to provide functional services to the payload satellite.
- 10. The orbit transfer vehicle of claim 9, wherein the orbit transfer vehicle includes at least one of the following components that is configured to provide the functional services to the payload satellite:
a communications device, a power regulation device, an energy storage device, a navigation device, and an attitude control device.
- 11. The orbit-transfer vehicle of claim 9, further including
the payload satellite that is configured to receive the functional services.
- 12. The orbit-transfer vehicle of claim 9, wherein
the navigation and control system is configured to provide a thrust that is sufficient to force the orbit-transfer vehicle from the launch orbit into a portion of atmosphere to effect a decrease in kinetic energy of the orbit-transfer vehicle.
- 13. The orbit-transfer vehicle of claim 12, wherein
the navigation and control system is further configured to apply thrust to the payload satellite so as to force the payload satellite beyond the atmosphere when the payload satellite substantially reaches apogee at an elevation corresponding to the target orbit.
- 14. The orbit-transfer vehicle of claim 9, wherein
at least some components of the orbit-transfer vehicle are configured to be released from the payload satellite when the orbit-transfer vehicle and payload satellite are maneuvered to the target orbit.
- 15. The orbit-transfer vehicle of claim 9, wherein
the orbit-transfer vehicle is configured to facilitate communications between an earth station and the payload satellite.
- 16. The orbit-transfer vehicle of claim 9, wherein
the orbit-transfer vehicle is configured to provide energy to the payload satellite to facilitate temperature control within the payload satellite.
- 17. An orbit-transfer vehicle comprising:
a coupling that facilitates an attachment of a payload satellite to the orbit-transfer vehicle, a propulsion system that is configured to facilitate maneuvering the payload satellite from a first orbit to a target orbit, and a spacecraft kernel that is designed independent of the orbit-transfer vehicle, and independent of the payload satellite, and is configured to provide an integrated communications system for use by the orbit-transfer vehicle.
- 18. The orbit-transfer vehicle of claim 17, wherein
the spacecraft kernel is further configured to provide regulated power to the orbit-transfer vehicle.
- 19. The orbit-transfer vehicle of claim 18, wherein
the spacecraft kernel is further configured to provide regulated power to the payload satellite.
- 20. The orbit-transfer vehicle of claim 17, wherein
the spacecraft kernel is further configured to provide communications to the orbit-transfer vehicle.
- 21. The orbit-transfer vehicle of claim 20, wherein
the spacecraft kernel is further configured to provide regulated power to the payload satellite.
- 22. The orbit-transfer vehicle of claim 17, further including
a second coupling that facilitates attaching the orbit-transfer vehicle to a launch vehicle, the launch vehicle being configured to deploy the orbit-transfer vehicle to the first orbit.
- 23. The orbit-transfer vehicle of claim 17, wherein
the kernel is configured to remain with the payload satellite when the payload satellite is placed in the target orbit.
- 24. An orbit-transfer vehicle comprising
a propulsion system that is configured to provide thrust for maneuvering a payload satellite from a first orbit to a target orbit, and a plurality of functional elements that facilitate the control of the propulsion system to facilitate the maneuvering of the payload satellite to the target orbit, wherein at least one of the plurality of functional elements includes an interface that is configured to provide a corresponding function to the payload satellite.
- 25. The orbit-transfer vehicle of claim 24, wherein
the at least one of the plurality of functional elements includes at least one of:
a communications device, a power regulation device, an energy storage device, a navigation device, and an attitude control device.
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This is a Continuation-In-Part of U.S. patent application Ser. No. 09/350,813, filed Jul. 9, 1999.
Continuation in Parts (1)
|
Number |
Date |
Country |
Parent |
09350813 |
Jul 1999 |
US |
Child |
09925206 |
Aug 2001 |
US |