Method of using dwell times in intermediate orbits to optimize orbital transfers and method and apparatus for satellite repair

• US 6,364,252 B1
• Filed: 03/10/2000
• Issued: 04/02/2002
• Est. Priority Date: 03/11/1999
• Status: Expired due to Fees

• Current Assignee: Constellation Services International Incorporated
• Original Assignee: Constellation Services International Incorporated
• Inventors: Anderman, David
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): Dinh, Tien
• Application Number:
  US09/523,401
• Time in Patent Office: 753 Days
• Field of Search: 244/164, 244/158.R, 244/169, 244/172
• US Class Current: 244/158.6
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/2427 Transfer orbits

Abstract

A reusable space vehicle docked in an intermediate orbit for rescue missions allows a satellite to be serviced with less delay, energy expenditure, and cost than a space vehicle launched from Earth for each mission. The reusable repair vehicle can be moved from one orbit to another with minimal energy expense while not having to wait for a launch window. Once a servicing need is identified, a destination orbit is identified for the space vehicle and a minimum energy path is identified. If the time to the next launch window between the docking orbit and the destination orbit happens to be near enough to allow for a timely rendezvous, the space vehicle is moved directly to the destination orbit. The space vehicle can be a vehicle designed to be piloted by humans or telerobotically. In one implementation, the inactive space vehicle is docked in an Intermediate LEO orbit (altitudes of approximately 250 km to approximately 500 km) and is used to rendezvous with objects in High LEO orbits (altitudes of approximately 500 km to approximately 1500 km) or objects in Low LEO orbits (altitudes of approximately 250 km or less). The space vehicle can be a modified lunar lander.

Claims

1. A lunar lander vehicle, modified to operate without a capability of landing on the lunar surface and modified to operate in a manned mission between a base orbit, a lower orbit lower than the base orbit and a higher orbit higher than the base orbit.

2. A method of operating a manned spacecraft comprising the steps of:

dropping from a base orbit to a lower orbit, wherein the lower orbit is lower than the base orbit;

remaining in the lower orbit for a first predetermined time;

rising to a higher orbit, wherein the higher orbit is higher than the base orbit;

remaining in the higher orbit for a second predetermined time; and

returning to the base orbit.

3. The method of claim 2, further comprising a step of taking on cargo at the lower orbit during the first predetermined time.

4. The method of claim 3, wherein the cargo is supplies and repair material.

5. The method of claim 2, further comprising a step of performing repairs on a satellite in the higher orbit during the second predetermined time.

6. A method of operating a manned spacecraft comprising the steps of:

rising from a base orbit to a higher orbit, wherein the higher orbit is higher than the base orbit;

remaining in the higher orbit for a first predetermined time;

dropping to a lower orbit, wherein the lower orbit is lower than the base orbit;

remaining in the lower orbit for a second predetermined time; and

returning to the base orbit.

7. The method of claim 6, further comprising a step of performing repairs on a satellite in the higher orbit during the first predetermined time.

8. The method of claim 6, further comprising a step of removing cargo from the manned spacecraft at the lower orbit during the second predetermined time.

9. The method of claim 8, wherein the cargo is repair material.