Method for deploying multiple spacecraft

• US 20060016934A1
• Filed: 07/06/2004
• Published: 01/26/2006
• Est. Priority Date: 07/06/2004
• Status: Active Grant

• Current Assignee: Johns Hopkins University
• Original Assignee: Johns Hopkins University
• Inventors: Sharer, Peter J.
• Granted Patent: US 7,219,858 B2
• Time in Patent Office: Days
• US Class Current: 244/158.400
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/2427 Transfer orbits
• CPC Class Codes: B64G 1/34 using gravity gradient

Abstract

A method for deploying multiple spacecraft is disclosed. The method can be used in a situation where a first celestial body is being orbited by a second celestial body. The spacecraft are loaded onto a single spaceship that contains the multiple spacecraft and the spacecraft is launched from the second celestial body towards a third celestial body. The spacecraft are separated from each other while in route to the third celestial body. Each of the spacecraft is then subjected to the gravitational field of the third celestial body and each of the spacecraft assumes a different, independent orbit about the first celestial body. In those situations where the spacecraft are launched from Earth, the Sun can act as the first celestial body, the Earth can act as the second celestial body and the Moon can act as the third celestial body.

Claims

1. A method for deploying a plurality of spacecraft about a first celestial body comprising the steps of:

storing a first spacecraft and a second spacecraft aboard a spaceship;

launching the spaceship from a second celestial body different from the first celestial body;

flying the spaceship towards a third celestial body;

separating the first spacecraft and the second spacecraft from the spaceship while the spaceship is traveling towards the third celestial body;

separating the first spacecraft from the second spacecraft while the spaceship is traveling towards the third celestial body;

establishing a first trajectory for the first spacecraft and establishing a second trajectory for the second spacecraft, wherein the first trajectory is different than the second trajectory;

subjecting the first spacecraft to a gravitational force of the third celestial body whereby the first trajectory of the first spacecraft is modified and the first spacecraft assumes a first orbit about the first celestial body;

subjecting the second spacecraft to the gravitational force of the third celestial body whereby the second trajectory of the second spacecraft is modified and the second spacecraft assumes a second orbit about the first celestial body; and

wherein the first orbit is different from the second orbit.

2. The method according to claim 1, further comprising the step of separating a third spacecraft from the second spacecraft.

3. The method according to claim 1, further comprising the step of separating an Nth spacecraft from the third spacecraft.

4. The method according to claim 1, further comprising the step of subjecting at least one of the spacecraft to the gravitational field of the third celestial body a second time.

5. The method according to claim 1, wherein the first orbit is circumferentially ahead of an orbit of the second celestial body.

6. The method according to claim 1, wherein the second orbit is circumferentially behind an orbit of the second celestial body.

7. The method according to claim 1, wherein an N number of spacecraft are stored aboard the spaceship.

8. A method for deploying a plurality of spacecraft about a first celestial body comprising the steps of:

storing a first spacecraft and a second spacecraft aboard a single spaceship;

launching the spaceship from a second celestial body different from the first celestial body;

flying the spaceship toward a third celestial body;

separating the first spacecraft and the second spacecraft from the spaceship while the spaceship is traveling towards the third celestial body;

separating the first spacecraft from the second spacecraft while the spaceship is traveling towards the third celestial body;

subjecting the first spacecraft to a gravitational force of the third celestial body whereby the first spacecraft assumes a first orbit about the first celestial body;

subjecting the second spacecraft to the gravitational force of the third celestial body whereby the second spacecraft assumes a second orbit about the first celestial body; and

wherein the first orbit is circumferentially ahead of the second celestial body and the second orbit is circumferentially behind the second celestial body.

9. The method according to claim 8, further comprising the step of separating a third spacecraft from the second spacecraft.

10. The method according to claim 8, further comprising the step of separating an Nth spacecraft from the third spacecraft.

11. The method according to claim 8, further comprising the step of subjecting at least one of the spacecraft to the gravitational field of the third celestial body a second time.

12. The method according to claim 8, wherein the first spacecraft has a smaller orbit than an orbit of the second celestial body.

13. The method according to claim 8, wherein the second spacecraft has a larger orbit than orbit of the second celestial body.

14. The method according to claim 8, wherein an N number of spacecraft are stored aboard the spaceship.

15. A method of deploying a plurality of satellites from Earth, the Earth orbiting a Sun in a first heliocentric orbit about the Sun and the Earth moving in a first circumferential direction with respect to the Sun, comprising the steps of:

storing a first spacecraft and a second spacecraft in a single spaceship;

launching the spaceship containing the first satellite and the second satellite and directing the spaceship to a Moon of the Earth;

separating the first spacecraft from the second spacecraft so that the first spacecraft assumes a first trajectory and the second spacecraft assumes a second trajectory;

the first trajectory being different from the second trajectory;

subjecting the first spacecraft to a gravitational field of the Moon, the gravitational field changing the first trajectory and sending the first spacecraft to a second heliocentric orbit about the Sun;

subjecting the second spacecraft to the gravitational field of the Moon, the gravitational field changing the second trajectory and sending the second spacecraft to a third heliocentric orbit about the Sun; and

wherein the second heliocentric orbit is different than the first heliocentric orbit and wherein the second heliocentric orbit is different than the third heliocentric orbit.

16. The method according to claim 15, wherein the first spacecraft from the second spacecraft travel towards the Moon as a separated pair of spacecraft.

17. The method according to claim 15, wherein the second heliocentric orbit is ahead of the Earth.

18. The method according to claim 17, wherein the third heliocentric orbit is behind the Earth.

19. The method according to claim 15, wherein the first spacecraft and the second spacecraft are disposed on opposite sides of the Earth.

20. The method according to claim 19, wherein angular displacement of the first spacecraft from the Earth is approximately equal to the angular displacement of the second spacecraft from the Earth.