Space debris interception

Patent metadata

Field	Value
Publication number	US-10640239-B2
Application number	US-201515518072-A
Country	US
Kind code	B2
Filing date	Oct 30, 2015
Priority date	Oct 30, 2014
Publication date	May 5, 2020
Grant date	May 5, 2020

Abstract

A vehicle for intercepting a target object orbiting in space is provided, comprising a launching portion for driving the vehicle into an orbit, and an interception portion for intercepting a target object when the vehicle is in orbit, wherein the interception portion comprises means for engaging with the target object and wherein the launching portion is arranged to drive the vehicle into a first elliptical orbit and the vehicle is arranged to adopt a second elliptical orbit when engaged with the target object in which the first elliptical orbit is arranged so as to intersect the orbit of the target object at an interception point, and the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object. A method of controlling a vehicle for intercepting a target object orbiting in space is also provided, comprising controlling the vehicle to be driven into a first elliptical orbit to intersect the orbit of the target object at an interception point and controlling the vehicle to engage with the target object at the interception point and to adopt a second elliptical orbit when engaged with the target object in which the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object.

First claim

The invention claimed is:

1. A vehicle for intercepting a target object orbiting in space, comprising:
an interception portion for intercepting a target object when the vehicle is in orbit, wherein the interception portion comprises a means for engaging with the target object when the vehicle is at an interception point; and
a launching portion arranged to launch the vehicle from Earth into a first elliptical orbit which intersects an orbit of the target object at the interception point, the vehicle being arranged to adopt a second elliptical orbit on engagement with the target object, wherein the second elliptical orbit is determined prior to launch;
wherein in which the first elliptical orbit is arranged so as to intersect the orbit of the target object at an interception point, and
wherein the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object.

2. The vehicle according to claim 1 , wherein the interception portion comprises:
a means for tracking the target object, the tracking means comprising one or more of an optical sensor, an infra-red sensor, and radar.

3. The vehicle according to claim 2 , further comprising:
a means for controlling movement of the vehicle in the first or second elliptical orbits.

4. The vehicle according to claim 3 , wherein the means for controlling movement of the vehicle is arranged to receive feedback from the tracking means and to impart corrective motion to the vehicle.

5. The vehicle according to claim 3 , wherein the means for controlling movement of the vehicle comprises one or more thrusters controlled by a control means associated with the interception portion.

6. The vehicle according to claim 3 , wherein the first and second elliptical orbits are such that a transition from the first elliptical orbit to the second elliptical orbit utilizes minimum operation of the means for controlling movement of the vehicle.

7. The vehicle according to claim 1 , wherein trajectories of the first and second elliptical orbits are predetermined and stored in a memory associated with the vehicle.

8. The vehicle according to claim 1 , wherein the interception portion comprises a controller configured to calculate the second elliptical orbit based on information relating to the target object.

9. The vehicle according to claim 1 , further comprising:
a communication means for communicating with a ground station to receive trajectory information defining the first and second elliptical orbits.

10. The vehicle according to claim 1 , wherein the engaging means comprises at least one of a harpoon, a grappling device or hook, a net, and one or more airbags.

11. The vehicle according to claim 10 , wherein the engagement means is arranged to cause the interception portion to combine with the target to form a composite body.

12. The vehicle according to claim 10 , wherein the engagement means is arranged to cause the interception portion to combine with the target object to tow the target object in the second elliptical orbit.

13. The vehicle according to claim 1 , further comprising:
a retardation means for slowing the vehicle from the first elliptical orbit to the second elliptical orbit on or after engaging the target object,
wherein the second elliptical orbit is a lower orbit than the first elliptical orbit.

14. A method of controlling a vehicle for intercepting a target object orbiting in space, comprising:
controlling the vehicle to cause the vehicle to be launched from Earth into a first elliptical orbit to intersect an orbit of the target object at an interception point; and
controlling the vehicle to cause the vehicle to engage with the target object at the interception point and to adopt a second elliptical orbit on engagement with the target object,
wherein the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object, and is determined prior to launch.

15. The method according to claim 14 , further comprising:
tracking the target object to determine a closing velocity of the vehicle with respect to the target object at the interception point,
wherein the closing velocity of the vehicle enables engagement of the vehicle with the target object and a transition from the first elliptical orbit to the second elliptical orbit utilizing minimum corrective control over the movement of the vehicle.

16. The method according to claim 14 , further comprising:
tracking the vehicle when engaged with the target object; and
controlling the second elliptical orbit such that the vehicle enters the Earth's atmosphere at a predetermined location.

17. The method according to claim 14 , wherein trajectories of the first and second elliptical orbits are predetermined and stored in a memory associated with the vehicle.

18. The method according to claim 14 , further comprising:
calculating the second elliptical orbit based on information relating to the target object.

19. The method according to claim 14 , further comprising:
communicating with a ground station to receive trajectory information defining the first and second elliptical orbits.

20. The method according to claim 14 , further comprising:
slowing the vehicle from the first elliptical orbit to the second elliptical orbit on or after engaging the target object,
wherein the second elliptical orbit is a lower orbit than the first elliptical orbit.

Assignees

• Airbus Defence & Space Ltd

Inventors

• Reed Jaime
• Barraclough Simon
• Ratcliffe Andrew

Classifications

• B64G1/242 Primary

  Orbits and trajectories · CPC title

• B64G3/00

  Observing or tracking cosmonautic vehicles · CPC title

• B64G1/62

  Systems for re-entry into the earth's atmosphere; Retarding or landing devices · CPC title

• B64G1/646 Primary

  Docking or rendezvous systems (refuelling in space B64G1/4024) · CPC title

• B64G1/007

  Operations & Transport · mapped topic