JP2018171947A - Artificial satellite and debris remover - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a technology for preventing an artificial satellite which has completed the mission from remaining in the space as a space debris.SOLUTION: An artificial satellite includes a satellite body and a debris remover. The debris remover includes: a controller which replies to a start signal received from the satellite body, and starts a super-low altitude movement sequence; and a thrust generator which is formed so as to generate no thrust until the super-low altitude movement sequence is started, and to generate thrust in a specific thrust direction fixed to a reference axis defined in the artificial satellite under control with the controller after the super-low altitude movement sequence is started. The controller, in executing the super-low altitude movement sequence, receives attitude data showing the attitude of the artificial satellite from the satellite body, replies to the attitude data, and generates thrust in the thrust generator when the artificial satellite takes an attitude by which the thrust direction of the thrust generator directs a direction of slowing down the artificial satellite.SELECTED DRAWING: Figure 1

Description

  The present invention relates to an artificial satellite and a debris remover.

  The progress of space development in recent years is remarkable, and not only the state but also various business entities have entered space development. As a result of such space development, the number of space objects has increased dramatically. Some space objects are actually used to accomplish missions, but many exist in outer space without performing any useful activities. Such space objects are called space debris. Since space debris is a threat to the activities of artificial satellites and other spacecraft, an increase in the number of space debris has become a problem in recent space development.

  There are various causes of the occurrence of space debris, but artificial satellites left in outer space after completing the mission account for a considerable proportion of space debris. For this reason, provision of a technique for preventing the artificial satellite from remaining in space as space debris after the mission is completed is required.

  Japanese Patent Application Laid-Open No. 2015-174647 includes an adhesion portion that adheres to an object existing in outer space and a propulsion portion that obtains a propulsive force, and the propulsion portion adheres to the object at the adhesion portion. Discloses a space device for transporting the object to a predetermined target position by moving with the object, and a debris removal system for removing debris using the space device.

  In addition, Japanese translations of PCT publication No. 2014-520724 discloses a device that is connected to the space satellite before launch but independent of the space satellite for the purpose of changing the orbit and / or returning to the earth. . The apparatus is operated by the control means, means for operating the movement / removal sequence operatively connected to the control means, and the control means to remove the space satellite from outer space to a target area on the earth. Propulsion means, power supply means for making the device independent of the space satellite, means for mechanically coupling the device to the space satellite prior to launch, and means for reducing propulsion vector mismatch.

  The Spaceflight Industries website also discloses a payload adapter that is used in conjunction with a launch spacecraft to increase the payload (https://www.spaceflight.com/sherpa/).

Japanese Patent Application Laid-Open No. 2015-174647 Special table 2014-520724 gazette

US Spaceflight Industries website https://www.spaceflight.com/sherpa/

  Accordingly, one of the objects of the present invention is to provide a technique for preventing an artificial satellite whose mission has been completed from remaining in space as space debris. Other objects and novel features of the invention will be apparent to those skilled in the art from the following disclosure.

  Hereinafter, means for solving the problems will be described with reference numerals used in the “DETAILED DESCRIPTION”. These symbols are added to show an example of the correspondence relationship between the description of “Claims” and “Mode for Carrying Out the Invention”.

  In one aspect of the present invention, an artificial satellite (1) includes a satellite body (11-15) on which an attitude detection sensor system (11) and a main controller (14) are mounted, and a debris remover (3). . The attitude detection sensor system (11) acquires attitude data (42) used for detecting the attitude of the artificial satellite (1). After the operation of the artificial satellite is completed, the main controller (14) determines the start of an ultra-low altitude movement sequence for decelerating the artificial satellite (1) and re-entering the atmosphere. After starting the operation, an activation signal is supplied to the debris remover. The debris remover (3) is a device dedicated to the execution of the ultra-low altitude movement sequence, and does not generate thrust until the ultra-low altitude movement sequence is started, and after the ultra-low altitude movement sequence is started. In response to the activation signal (41), a thrust generator (31) configured to generate a thrust in a specific thrust direction fixed with respect to the reference axis defined in the artificial satellite (1). I have. The main controller (14) receives the posture data (42) from the posture detection sensor system (11) and executes the thrust of the thrust generator (31) in response to the posture data (42) in executing the ultra low altitude movement sequence. An activation signal (41) is generated so that the thrust generator (31) generates thrust when the direction of the artificial satellite (1) is in the direction in which the direction of the satellite (1) decelerates.

  In one embodiment, after starting the ultra-low altitude movement sequence, the main controller (14) executes the ultra-low altitude movement sequence independently from the ground station provided on the ground and controlling the artificial satellite (1). Is configured to do.

  In one embodiment, the main controller (14) determines that the attitude of the artificial satellite (1) is the thrust direction of the thrust generator (31) at a predetermined time interval after the ultra-low altitude movement sequence is started. A determination as to whether the attitude of the satellite is to be decelerated is made based on attitude data (42), and the attitude of the artificial satellite decelerates the artificial satellite (1) by the thrust direction of the thrust generator (31). Each time it is determined that the posture is in the direction to be moved, the thrust generator (31) operates to generate thrust for a certain period of time.

  In one embodiment, the debris remover (3) further includes an auxiliary power source (34) that supplies power to the thrust generator (31). The auxiliary power supply (34) is a system that mainly supplies power to the debris remover (3) and is not directly supplied from the power supply system (15), and enables independent operation. The auxiliary power source (34) detects the power supply to the attitude detection sensor system (11) and the main controller (14) in the satellite body (11-15), and detects the attitude detection sensor system (11). 11) and the main controller (14) may be configured to supply power.

  In another aspect of the present invention, it is connected to the artificial satellite (1) before launch, and after the operation of the artificial satellite (1) is finished, the ultra-low for decelerating the artificial satellite (1) and re-entering the atmosphere. A debris remover (3) is provided that is used exclusively for altitude movement sequences. The debris remover (3) includes a coupling mechanism (35) for mechanically coupling the debris remover (3) to the frame (1a) of the artificial satellite (1), and a satellite body (11-15) of the artificial satellite (1). ) From the controller (32) that receives the activation signal (41) from the controller, and a thrust generator configured to generate thrust in a specific thrust direction fixed with respect to the reference axis defined in the artificial satellite (1) ( 31). In the execution of the ultra-low altitude movement sequence, the controller (32) responds to the activation signal (41) so that the thrust direction of the thrust generator (31) is directed to the direction of decelerating the artificial satellite (1). The thrust generator (31) generates a thrust when the artificial satellite (1) is taking.

  According to the present invention, it is possible to prevent an artificial satellite whose mission has been completed from remaining in space as space debris.

It is a block diagram which shows the structure of the artificial satellite in one Embodiment. It is a block diagram which shows the structure of the artificial satellite and debris remover in the modification of this embodiment. It is a conceptual diagram which shows the outline | summary of operation | movement of the artificial satellite and debris remover in this embodiment. It is a flowchart which shows the operation | movement of an artificial satellite and a debris remover when a mission is normally completed in this embodiment. It is a flowchart which shows operation | movement of an artificial satellite and a debris remover when the operation | movement continuation of an artificial satellite becomes impossible in this embodiment.

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.
FIG. 1 is a block diagram illustrating a configuration of an artificial satellite 1 according to an embodiment. In this embodiment, the artificial satellite 1 is configured to be operated under the control of the operation control ground station 2 provided on the ground.

  The artificial satellite 1 includes an attitude detection sensor system 11, an attitude control system 12, a communication system 13, a main controller 14, and a power supply system 15. The attitude detection sensor system 11, the attitude control system 12, the communication system 13, the main controller 14, and the power supply system 15 are accommodated in the frame 1a.

  The attitude detection sensor system 11 acquires various data used for detecting the attitude of the artificial satellite 1. The attitude detection sensor system 11 may include, for example, a gyro sensor, a sun sensor, an earth sensor, a star sensor, a geomagnetic sensor, and the like. Data acquired by the attitude detection sensor system 11 is sent to the main controller 14 as attitude data 42.

  The attitude control system 12 controls the attitude of the artificial satellite 1 under the control of the main controller 14. The attitude control system 12 may include, for example, a thruster, CMG (Control Moment Gyros), and the like.

  The communication system 13 communicates with the operation control ground station 2. The communication system 13 may include an antenna 21, a diplexer 22, and a transceiver 23, for example. The antenna 21 receives a signal from the operation control ground station 2 and transmits a signal to the operation control ground station 2. The diplexer 22 switches between transmission and reception of the antenna 21. The transceiver 23 modulates a signal transmitted to the operational control ground station 2 and demodulates a signal received from the operational control ground station 2.

  The main controller 14 controls each device provided in the artificial satellite 1. For example, the main controller 14 specifies the attitude of the artificial satellite 1 from the attitude data 42 acquired by the attitude detection sensor system 11, and operates the attitude control system 12 so that the attitude of the artificial satellite 1 becomes the target attitude. Is generated. The main controller 14 receives a command from the operational control ground station 2 using the communication system 13 and controls each device provided in the artificial satellite 1 in response to the command. Further, the main controller 14 monitors the state of each device provided in the artificial satellite 1 and transmits telemetry data indicating the state of each device to the operation control ground station 2 using the communication system 13. In addition, the main controller 14 controls each device so as to perform a given mission, and transmits mission data obtained by performing the mission to the operation control ground station 2 using the communication system 13.

  The power supply system 15 supplies power necessary for the operation of each device (for example, the attitude detection sensor system 11, the attitude control system 12, the communication system 13, and the main controller 14) provided in the artificial satellite 1. The power supply system 15 may include, for example, a solar battery panel 24, a secondary battery 25, and a power controller 26. The solar battery panel 24 receives sunlight and generates electric power. The secondary battery 25 has an ability to store electric power generated by the solar battery panel 24 while supplying electric power charged before launch. The power controller 26 controls generation of power by the solar battery panel 24, accumulation of power in the secondary battery 25, and supply of power from the power supply system 15 to each device.

  A debris remover 3 is further mounted on the artificial satellite 1 of the present embodiment. The debris remover 3 is a dedicated device for decelerating the artificial satellite 1 and re-entering the artificial satellite 1 into the atmosphere after the operation of the artificial satellite 1 is completed. The debris remover 3 used in the present embodiment is not used for purposes other than re-entering the artificial satellite 1 into the atmosphere. As is well known to those skilled in the art, when the artificial satellite 1 is put in a low orbit (for example, an orbit having an altitude lower than 2000 km), the artificial satellite 1 is decelerated to return to the atmosphere. It can be moved to a rush or very low altitude (e.g., an orbit with an altitude of 300-400 km or lower). At ultra-low altitude, atmospheric resistance is greater than at low orbits, so satellites that have moved to ultra-low altitude are further decelerated by atmospheric resistance and re-enter the atmosphere faster than if they do not move from low orbit. It will be. As described above, the debris remover 3 according to the present embodiment promotes re-entry into the atmosphere by decelerating the artificial satellite 1, whereby the artificial satellite 1 that has completed the mission remains in space as space debris. prevent.

  In the following, a portion of the artificial satellite 1 other than the debris remover 3 may be referred to as a “satellite body”. The satellite body is a part of the artificial satellite 1 that is involved in performing the mission. In this embodiment, the attitude detection sensor system 11, the attitude control system 12, the communication system 13, the main controller 14, and the power supply system 15 described above are included. Contains.

  An operation performed by the debris remover 3 to decelerate the artificial satellite 1 and re-enter the artificial satellite 1 or to lower the orbital altitude and move the artificial satellite 1 to an ultra-low altitude is referred to as an “ultra-low altitude movement sequence”. Sometimes. Furthermore, the operation mode of the artificial satellite 1 that causes the debris remover 3 to execute the “ultra-low altitude movement sequence” may be referred to as “de-orbit mode”.

  Since the debris remover 3 is not directly involved in performing the mission of the artificial satellite 1, it is desired that the debris remover 3 be small and lightweight. In addition, the debris remover 3 is autonomous as much as possible (ie, not subject to control from the operation control ground station 2 and independent from the operation control ground station 2) in executing the ultra low altitude movement sequence. It is desirable to perform an operation to re-enter 1. If the debris remover 3 is configured to autonomously re-enter the artificial satellite 1, it is not necessary to control the artificial satellite 1 after the mission is completed, and the operation of the artificial satellite 1 is facilitated.

  From such a viewpoint, in the present embodiment, the debris remover 3 is configured as follows. The debris remover 3 of this embodiment includes a thrust generator 31, a controller 32, and an auxiliary power source 33.

  The thrust generator 31 generates a thrust for decelerating the artificial satellite 1. In the present embodiment, the thrust generator 31 is configured to generate a thrust in a specific thrust direction fixed with respect to a reference axis defined in the artificial satellite 1. The thrust generator 31 does not have a control mechanism that actively controls the direction of thrust. This is because the structure of the thrust generator 31 is simplified to facilitate the reduction in size and weight. As described above, the debris remover 3 is desirably small and lightweight, and can be widely used in satellites and other spacecrafts by having a small size and light weight and easy connection, thereby suppressing an increase in space debris. One possibility. When the thrust generating device 31 having a variable thrust direction is used, it is necessary to provide a sensor for detecting the thrust direction of the thrust generating device 31, and the calculation amount of the controller 32 increases due to calculation of the deceleration direction or the like. Furthermore, the required power increases with an increase in the calculation amount. These can be factors that make it difficult to reduce the size and weight of the debris remover 3. The fixing of the thrust direction of the thrust generator 31 and the simplification of the calculation of the controller 32 facilitate the reduction in size and weight of the debris remover 3.

  The controller 32 receives the activation signal 41 from the satellite body of the artificial satellite 1 and controls the generation of thrust by the thrust generator 31. Here, the activation signal 41 is a signal that instructs the debris remover 3 to generate thrust by the thrust generator 31.

  In the present embodiment, the activation signal 41 is supplied from the main controller 14 of the satellite body of the artificial satellite 1 to the controller 32 of the debris remover 3. As will be described later, the main controller 14 sends the activation signal 41 to the thrust generating device 31 when the artificial satellite 1 is in such a posture that the thrust direction of the thrust generating device 31 faces the direction of decelerating the artificial satellite 1. Generate to generate thrust.

  The auxiliary power source 33 includes a power storage device (for example, a secondary battery, a large capacity capacitor), and supplies power to the thrust generator 31 and the controller 32 when an ultra-low altitude movement sequence is being executed. . The auxiliary power source 33 supplies power to each device of the debris remover 3 when executing the ultra-low altitude movement sequence, and ensures the operation of the debris remover 3.

  Specifically, the auxiliary power supply 33 receives power from the power supply system 15 through the power supply line 43 (power line supplying power from the power supply system 15 to the debris remover 3) until the ultra-low altitude movement sequence is started. Stores power in the power storage device. After the re-entry sequence is started, the auxiliary power source 33 supplies power to the thrust generator 31 and the controller 32 to enable the operation of the debris remover 3. However, a system configuration that can supply power from the power supply system 15 may be adopted when it is difficult to supply power due to some trouble.

  FIG. 1 illustrates a configuration in which the debris remover 3 is mounted on the artificial satellite 1 (a configuration in which at least a part of each device of the debris remover 3 is located inside the frame 1a of the artificial satellite 1). However, the debris remover 3 may be connected to the frame 1a so as to be located outside the frame 1a of the artificial satellite 1. Even in this case, the debris remover 3 is connected to the frame 1 a before launching the artificial satellite 1 and launched together with the artificial satellite 1.

  FIG. 2 shows the debris remover 3 having such a configuration. The debris remover 3 includes a frame 3a, and a portion of the debris remover 3 other than a part of the nozzle 31a of the thrust generating device 31 is accommodated in the frame 3a. The frame 3 a is provided with a coupling mechanism 34, and the debris remover 3 is mechanically coupled to the frame 1 a of the artificial satellite 1 by the coupling mechanism 34.

  Next, operations of the artificial satellite 1 and the debris remover 3 in this embodiment will be described. FIG. 3 is a conceptual diagram showing an outline of operations of the artificial satellite 1 and the debris remover 3 in the present embodiment.

  The artificial satellite 1 is launched, put into a desired orbit, and operated in the orbit. In this embodiment, the artificial satellite 1 is put into a so-called low orbit (for example, an orbit having an altitude lower than 2000 km). The artificial satellite 1 receives a command from the operational control ground station 2, performs a desired mission, and transmits mission data to the operational control ground station 2. In addition, the artificial satellite 1 transmits telemetry data indicating the state of each device of the artificial satellite 1 to the operation control ground station 2 in executing the mission. It should be noted that the debris remover 3 is mounted on or connected to the artificial satellite 1 before the artificial satellite 1 is launched.

  When the operation of the artificial satellite 1 is terminated (for example, when the mission is completed or when the operation of the artificial satellite 1 cannot be continued due to some trouble), the operation of the debris remover 3 is started, and the artificial satellite 1 Is slowed down. When the artificial satellite 1 is decelerated, the altitude of the orbit of the artificial satellite 1 decreases and the artificial satellite 1 re-enters the atmosphere. This prevents the artificial satellite 1 from remaining in space as space debris.

  FIG. 4 is a flowchart showing operations of the artificial satellite 1 and the debris remover 3 when the mission is normally completed and the operation of the artificial satellite 1 is finished.

  The artificial satellite 1 performs a desired mission after being put into a desired orbit (step S01). The auxiliary power supply 33 receives power from the power supply system 15 via the power supply line 43 while the artificial satellite 1 is performing a mission, and stores the power in the power storage device.

  When the mission is executed and completed normally, the artificial satellite 1 is shifted to the de-orbit mode (step S02). Specifically, a command instructing the shift to the deorbit mode is transmitted from the operation control ground station 2 to the artificial satellite 1, and the main controller 14 shifts the artificial satellite 1 to the deorbit mode in response to the command. .

  When the artificial satellite 1 shifts to the de-orbit mode, the artificial satellite 1 shifts to a state where only the minimum components are operating (step S03). For example, the operation of the device for performing the mission is stopped. At this time, the operation of the communication system 13 may also be stopped. As will be described later, since the debris remover 3 operates independently from the operation control ground station 2, even if the operation of the communication system 13 is stopped, the operation of the debris remover 3 is not affected. The operation of the attitude control system 12 may also be stopped. As will be understood from the following description, the operation of the debris remover 3 assumes that the attitude control of the artificial satellite 1 is not sufficiently performed after the operation of the artificial satellite 1 is completed. Therefore, when the artificial satellite 1 shifts to the deorbit mode, the operation of the attitude control system 12 may be stopped.

  Further, the main controller 14 starts an ultra-low altitude movement sequence in response to a command for instructing the transition to the de-orbit mode (steps S04 to S06).

  When the ultra-low altitude movement sequence is started, the main controller 14 receives the posture data 42 from the posture detection sensor system 11 (step S04). Further, the main controller 14 determines, based on the attitude data 42, whether or not the artificial satellite 1 is in an attitude such that the thrust direction of the thrust generating device 31 is in the direction of decelerating the artificial satellite 1 (step S05). When the artificial satellite 1 determines that the thrust direction of the thrust generating device 31 is oriented in the direction in which the artificial satellite 1 is decelerated, the main controller 14 activates the activation signal 41. When detecting that the activation signal 41 has become active, the controller 32 of the debris remover 3 causes the thrust generator 31 to generate thrust for a certain period of time (step S06). In such an operation, the thrust is generated by the thrust generator 31 intermittently.

  The operations in steps S04 to S06 are repeated until the artificial satellite 1 re-enters the atmosphere. The operations in steps S04 to S06 may be performed at predetermined time intervals. In this case, the main controller 14 determines at a predetermined time interval whether the artificial satellite 1 is in such a posture that the thrust direction of the thrust generating device 31 is directed in the direction in which the artificial satellite 1 is decelerated. Each time it is determined that the artificial satellite 1 is in such a posture that the thrust direction is directed to the direction in which the artificial satellite 1 is decelerated, the activation signal 41 is activated and the thrust generating device 31 generates the thrust.

  According to such an operation, the configuration of the thrust generator 31 can be simplified, and the operation of the controller 32 in the ultra-low altitude movement sequence can be simplified. This contributes to reducing the size and weight of the debris remover 3.

  When executing the ultra low altitude movement sequence, there is a possibility that power supply from the power supply system 15 of the artificial satellite 1 to the attitude detection sensor system 11 and the main controller 14 may be interrupted. The auxiliary power supply 33 monitors the supply of power by the power supply system 15 while the ultra-low altitude movement sequence is being executed, and detects the interruption of the supply of power from the power supply system 15 to the attitude detection sensor system 11 and the main controller 14. In this case, power may be supplied to the posture detection sensor system 11 and the main controller 14 in addition to the devices (for example, the thrust generation device 31 and the controller 32) of the debris remover 3.

  By executing the ultra-low altitude movement sequence as described above, the artificial satellite 1 is gradually decelerated. As a result, the altitude of the artificial satellite 1 gradually decreases, and the artificial satellite 1 re-enters the atmosphere. Such an operation prevents the artificial satellite 1 that has completed the mission from remaining in space as space debris.

  FIG. 5 is a flowchart showing the operations of the artificial satellite 1 and the debris remover 3 when a problem occurs during the execution of the mission and the operation of the artificial satellite 1 cannot be continued.

  If a problem occurs during the execution of the mission in the artificial satellite 1 (step S01) and the controller of the operation control ground station 2 determines that the operation cannot be continued from the mission data and telemetry data, the operation control ground station 2 Transmits a command for instructing the satellite 1 to shift to the de-orbit mode, and the satellite 1 shifts to the de-orbit mode in response to the command (step S02).

  At this time, when the main controller 14 detects a serious failure in the artificial satellite 1, it may determine that the main controller 14 autonomously shifts to the de-orbit mode. For example, when it is detected that a serious failure has occurred in the communication system 13 and communication with the operational control ground station 2 has become impossible, the main controller 14 autonomously places the satellite 1 in the deorbit mode. It may be migrated.

  When the artificial satellite 1 shifts to the de-orbit mode, the artificial satellite 1 shifts to a state where only the minimum components are operating (step S03). Further, the main controller 14 autonomously starts an ultra-low altitude movement sequence (steps S04 to S06). The operations of the main controller 14 and the debris remover 3 in the ultra low altitude movement sequence are as described above.

  According to such an operation, the artificial satellite 1 can be prevented from remaining in space as space debris even when a problem occurs during the execution of the mission.

  Although the embodiment of the present invention has been specifically described above, the present invention is not limited to the above embodiment. Those skilled in the art will appreciate that the invention may be practiced with various modifications.

1: Satellite 1a: Frame 2: Operation control ground station 3: Debris remover 3a: Frame 11: Attitude detection sensor system 12: Attitude control system 13: Communication system 14: Main controller 15: Power supply system 21: Antenna 22: Diplexer 23 : Transceiver 24: Solar battery panel 25: Secondary battery 26: Power controller 31: Thrust generator 31a: Nozzle 32: Controller 33: Auxiliary power supply 34: Connection mechanism 41: Start signal 42: Attitude data 43: Power line

Claims (7)

A satellite body equipped with an attitude detection sensor system and a main controller;
A satellite equipped with a debris remover,
The attitude detection sensor system acquires attitude data used to detect the attitude of the artificial satellite,
After the operation of the artificial satellite is completed, the main controller determines the start of an ultra-low altitude movement sequence for decelerating the artificial satellite to lower the orbital altitude or to re-enter the atmosphere. After starting the sequence, it is configured to supply an activation signal to the debris remover,
The debris remover is a device dedicated to the execution of the ultra-low altitude movement sequence, does not generate thrust until the ultra-low altitude movement sequence is started, and the ultra-low altitude movement sequence is started. And a thrust generator configured to generate a thrust in a specific thrust direction fixed with respect to a reference axis defined for the artificial satellite in response to the activation signal.
The main controller receives the attitude data from the attitude detection sensor system and executes the ultra-low altitude movement sequence, and the thrust direction of the thrust generator decelerates the artificial satellite in response to the attitude data. An artificial satellite that generates the activation signal so as to cause the thrust generating device to generate a thrust when the artificial satellite takes a pose in a direction. The artificial satellite according to claim 1,
The main controller is configured to execute the ultra low altitude movement sequence independently from a ground station provided on the ground and controlling the artificial satellite after starting the ultra low altitude movement sequence. . The artificial satellite according to claim 1,
The main controller has an attitude in which the attitude of the artificial satellite is oriented in a direction in which the thrust direction of the thrust generator decelerates the artificial satellite at a predetermined time interval after the ultra-low altitude movement sequence is started. Is determined based on the attitude data, and every time it is determined that the attitude of the artificial satellite is an attitude in which the thrust direction of the thrust generator is oriented in the direction of decelerating the artificial satellite, An artificial satellite that operates to generate thrust in a thrust generator. The artificial satellite according to claim 1,
The debris remover further includes an auxiliary power supply that supplies power to the thrust generator,
The auxiliary power supply is configured to supply power to the attitude detection sensor system and the main controller when it is detected that supply of power to the attitude detection sensor system and the main controller in the satellite body is interrupted. Was an artificial satellite. Debris that is connected to an artificial satellite before launch and is used exclusively for ultra-low altitude movement sequences to decelerate the artificial satellite to lower its orbital altitude or to re-enter the atmosphere after the operation of the artificial satellite ends. A remover,
A coupling mechanism for mechanically coupling the debris remover to the frame of the artificial satellite;
A controller for receiving an activation signal from the satellite body of the artificial satellite;
A thrust generator configured to generate a thrust in a specific thrust direction fixed with respect to a reference axis defined in the satellite,
The controller, when executing the ultra-low altitude movement sequence, when the artificial satellite is in a posture in which the thrust direction of the thrust generating device is directed to decelerate the artificial satellite in response to the activation signal A debris remover that generates thrust in the thrust generator. The debris remover according to claim 5,
The controller is a debris remover that operates to generate a thrust for a certain period of time each time the activation signal becomes active after the ultra-low altitude movement sequence is started. The debris remover according to claim 5,
In addition, it has an auxiliary power supply,
When the auxiliary power source detects that the power supply to the attitude detection sensor system for detecting the attitude of the artificial satellite and the main controller for generating the activation signal is interrupted in the satellite body, the main controller and the attitude A debris remover configured to supply power to the sensing sensor system.

Images