Spacecraft and control system

Patent metadata

Field	Value
Publication number	US-12049331-B2
Application number	US-201917423995-A
Country	US
Kind code	B2
Filing date	Jan 21, 2019
Priority date	Jan 21, 2019
Publication date	Jul 30, 2024
Grant date	Jul 30, 2024

Abstract

A spacecraft for changing an orbit or an attitude of a target in outer space by irradiating the target with a laser, the spacecraft includes: a laser apparatus configured to generate the laser; a focusing unit configured to converge the laser; a detecting unit configured to acquire detection information including a distance between the spacecraft and the target; and an irradiation control unit configured to control the focusing unit on the basis of the distance so that the laser converges on the target.

First claim

The invention claimed is:

1. A method for changing an orbit or an attitude of a target in outer space by irradiating the target with a laser, the method comprising:
acquiring detection information including a distance between a spacecraft and the target with a detecting unit of the spacecraft;
controlling a focusing unit of the spacecraft with an irradiation control unit of the spacecraft on the basis of the distance to converge a laser generated by a laser apparatus on the target, and to determine an irradiation position of the laser on the target;
acquiring a captured image of the target by an acquisition unit of the spacecraft;
acquiring the position on the target that has been irradiated by the laser with the irradiation control unit on the basis of the captured image, and determining a new irradiation position on the basis of the position that has been irradiated with the laser;
controlling the laser with the irradiation control unit to output at a first output value in a case where the laser is emitted for aiming, and
controlling the laser to output at a second output value with the irradiation control unit, which is larger than the first output value, in a case where the orbit or the attitude of the target is to be changed.

2. The method according to claim 1 , wherein the irradiation control unit determines an initial irradiation position of the laser on the target on the basis of the captured image, irradiates the initial irradiation position with the laser, acquires the position on the target that has been irradiated with the laser on the basis of the captured image, and determines a new irradiation position on the basis of the position that has been irradiated with the laser.

3. The method according to claim 1 , wherein the irradiation control unit determines an irradiation position of the laser on the target and/or an output value of the laser on the basis of the detection information.

4. The method according to claim 1 , wherein the irradiation control unit determines a new irradiation position and/or a new output value on the basis of the detection information acquired after the irradiation with the laser.

5. The method according to claim 1 , wherein the detection information includes at least one of the distance between the spacecraft and the target, a position, size, shape, captured image, and rotational state of the target.

6. The method according to claim 1 , wherein the irradiation control unit changes the emission direction of the laser by using a mirror that reflects the laser emitted from the laser apparatus.

7. The method according to claim 1 , wherein a propulsion strengthening member is attached to the target, and wherein the irradiation control unit further controls the focusing unit to converge the laser on the propulsion strengthening member, and to determine the irradiation position so that the propulsion strengthening member is irradiated with the laser.

8. The method according to claim 7 , wherein the propulsion strengthening member includes:
a transparent member through which the emitted laser passes; and
an opaque member that is provided between the transparent member and the target and absorbs the laser such that at least a part thereof is evaporated by energy of the laser.

9. The method of claim 1 , wherein a monitoring apparatus provided on Earth comprising a detecting unit detects a position of the target; and a transmission unit transmits position information about the target to the spacecraft, and a reception unit of the spacecraft receives the position from the monitoring apparatus.

10. A non-transitory computer-readable storage medium storing instructions that, when executed by a computer, cause a computer to execute the method of claim 1 .

Assignees

• Sky Perfect Jsat Corp
• Riken

Inventors

• Fukushima Tadanori
• Yamada Jun
• Hirata Daisuke
• Ebisuzaki Toshikazu
• Wada Satoshi

Classifications

• B64G1/62

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

• B64G1/1081

  for debris removal · CPC title

• B64G1/242 Primary

  Orbits and trajectories · CPC title

• B64G1/66

  Arrangements or adaptations of apparatus or instruments, not otherwise provided for · CPC title

• B64G1/10

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title