JP2023112528A - Satellite control method - Google Patents

Abstract

To provide a satellite control method capable of suppressing cost for purchase, operation and the like of an artificial satellite.SOLUTION: A satellite control method according to the present invention comprises: an orbit-lowering step of moving a platform satellite P, which revolves along a first orbit while being joined to a first mission satellite M1, to a second orbit closer to the earth than the first orbit; a separation step of separating the first mission satellite M1 from the platform satellite P in the second orbit; a joining step of joining the platform satellite P to a second mission satellite M2 injected into the second orbit; and an orbit-moving step of moving, to the first orbit, the platform satellite P joined to the second mission satellite M2.SELECTED DRAWING: Figure 4

Description

The present invention relates to a satellite control method.

Conventionally, artificial satellites are manufactured by integrating a platform unit that has basic functions such as power generation, power control, propulsion, attitude and trajectory control, and thermal control, and a mission function that carries out a given mission. Operated in outer space. It is known that an artificial satellite that has reached its expiration date is discarded as a whole. Further, in the case of an artificial satellite orbiting a geostationary orbit, it is known to transfer the artificial satellite to an orbit called a graveyard orbit and discard it (see, for example, Patent Document 1).

U.S. Patent No. 10513352

In the conventional technology, when the satellite reaches its expiration date, the entire satellite is scrapped, even though the satellite's control unit, propulsion device, power supply, etc., can still be used. However, there was a problem that the purchase cost and operation cost were high.

SUMMARY OF THE INVENTION It is therefore an object of the present invention to provide a satellite control method capable of reducing the cost of purchasing and operating artificial satellites by reusing usable parts.

A satellite control method of the present invention for solving the above problems moves a platform satellite orbiting in a first orbit coupled with a first mission satellite to a second orbit closer to the earth than the first orbit. a separation step of separating the first mission satellite from the platform satellite in the second orbit; and a coupling step of coupling the second mission satellite inserted into the second orbit and the platform satellite. ,
an orbital movement step of moving the platform satellite coupled with the second mission satellite to the first orbit or a third orbit different from the first and second orbits.

The separating step may include separating the first mission satellite from the platform satellite and injecting the first mission satellite into an orbit for entry into the atmosphere.

The satellite control method of the present invention further comprises a time zone determination step of determining a time zone in which the platform satellite should arrive on the second orbit, wherein the time zone determination step comprises: determining a second time period for the platform satellite to reach the second orbit based on a first time period for the platform satellite to reach the first orbit; determining a third time period to initiate movement toward said second orbit, wherein said orbital descent step includes moving said platform satellite toward said second orbit during said third time period. An initiating step may be included.

The step of lowering the orbit may include moving the platform satellite to a predetermined position on the second orbit determined based on the position on the second orbit to be reached by the second mission satellite.

The first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit, and the orbit descending step initiates movement of the platform satellite to the geostationary transfer orbit, as transmitted by a satellite manager on the ground. The platform satellite may initiate movement from the geostationary orbit to the geostationary transfer orbit when the platform satellite receives a first command signal to.

The orbit moving step moves the platform satellite coupled with the second mission satellite to a predetermined position on the first orbit based on position information indicating the position where the second mission satellite should be positioned on the first orbit. A step of moving may be included.

The first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit, and the step of separating comprises a second orbit transmitted by a satellite management device on the ground for separating the first mission satellite from the platform satellite. Two command signals may include the platform satellite separating the first mission satellite.

The combining step comprises combining the platform satellite with the second mission satellite based on a third command signal transmitted by a satellite management device on the ground for combining the second mission satellite and the platform satellite. may contain.

The first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit, and the orbit movement step moves the platform satellite from the geostationary transfer orbit to the geostationary orbit transmitted by a satellite management device on the ground. moving said platform satellite to said geostationary orbit based on a fourth command signal to cause said platform satellite to move to said geostationary orbit;

The satellite control method of the present invention is a method for re-entering the atmosphere while the platform satellite is coupled with the second mission satellite or a third mission satellite different from the second mission satellite. It may further comprise the step of moving to orbit.

The platform satellite has a power generator, and the first mission satellite and the second mission satellite do not have a power generator, are detachably coupled to the platform satellite, and are powered by the platform satellite. may

In the satellite control method of the present invention, after injecting the platform satellite and the first mission satellite into the second orbit by the same or different rockets in an uncoupled state, The method may further include a satellite introducing step of coupling with the first mission satellite and moving the platform satellite and the first mission satellite from the second orbit to the first orbit.

In the satellite control method of the present invention, before the orbit descent step, information indicating that the first mission satellite has failed, information indicating that the operation of the first mission satellite has ended, or information indicating that the operation of the first mission satellite has ended, or The method may further include a notification step in which the platform satellite or the first mission satellite transmits at least one of information indicating that the satellite needs to be replaced to a satellite management device on the ground.

ADVANTAGE OF THE INVENTION According to this invention, it is effective in the ability to provide the satellite control method which can hold down the cost, such as purchase / operation|use of an artificial satellite.

1 is a block diagram showing the configuration of a satellite utilization system; FIG. It is a figure which shows the structure of an artificial satellite. It is a figure which shows the state which the artificial satellite is going around the geostationary orbit. It is a block diagram which shows the structure of a satellite management apparatus. FIG. 4 is a diagram showing the movement of satellites according to the satellite control method of the embodiment of the present invention; 1 is a flow diagram of a satellite control method; FIG.

BEST MODE FOR CARRYING OUT THE INVENTION Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the embodiments and drawings, the same or corresponding elements are denoted by the same or corresponding reference numerals, and overlapping descriptions are appropriately omitted or simplified. FIG. 1 is a block diagram showing the configuration of the satellite utilization system S100. FIG. 2 is a diagram showing the configuration of the artificial satellite 1. As shown in FIG. FIG. 3 is a diagram showing a state in which the artificial satellite 1 is orbiting the geostationary orbit 101. As shown in FIG.

A satellite utilization system S100 of this embodiment includes an artificial satellite 1 and a satellite management device 2 on the ground. The artificial satellite 1 has a platform satellite P and a mission satellite M. Mission satellite M is a satellite detachably coupled to platform satellite P.

In the following description, the satellite 1 moves between a geostationary orbit 101 (see FIG. 3), which is a first orbit, and a geostationary transfer orbit 102, which is a second orbit. A geostationary orbit (GEO) 101 is a circular orbit at an altitude above the surface of the earth 10 of approximately 36,000 km above the equator. A geostationary transfer orbit 102 (GTO) is an orbit into which the artificial satellite 1 is temporarily injected before the artificial satellite 1 launched from the earth 10 moves to the geostationary orbit 101 . The geostationary transfer orbit 102 is an elliptical orbit whose perigee is at a lower altitude than the geostationary orbit 101 .

[Overview of satellite control method of this embodiment]
Before describing the details of the satellite utilization system S100, an outline of the satellite control method of this embodiment will be described with reference to FIG. FIG. 4 is a diagram illustrating satellite motion according to the satellite control method of the embodiment of the present invention. In the following, for example, the first mission satellite M1, which has reached the expiration date, is separated from the platform satellite P, and the second mission satellite M2 launched from the earth is newly coupled to the platform satellite P. A satellite control method will be described.

In the satellite control method of this embodiment, first, the artificial satellite 1 orbiting the geostationary orbit 101 is moved to the geostationary transfer orbit 102, which is a second orbit closer to the earth than the geostationary orbit 101 ((1 in FIG. 4). ) and (2)).

Next, the first mission satellite M1 is separated from the platform satellite P of the artificial satellite 1 . As a result, the platform satellite P is not coupled to the mission satellite M ((3) in FIG. 4). A second mission satellite M2 scheduled to be coupled to the platform satellite P is launched from the ground and injected into the geostationary transfer orbit 102 ((4) in FIG. 4).

Next, the platform satellite P moves toward the second mission satellite M2 on the geostationary transfer orbit 102 and couples with the second mission satellite M2 ((5) in FIG. 4).

After that, the platform satellite P coupled with the second mission satellite M2 rises again toward the geostationary orbit 101 and continues orbiting on the geostationary orbit 101 ((6) in FIG. 4).

According to the satellite control method described above, the mission satellite M coupled to the platform satellite P can be changed from the first mission satellite M1 to the second mission satellite M2. Instead of disposing of the entire satellite 1 when the deadline expires, only the first mission satellite M1 can be discarded, and the platform satellite P can continue to be used with the second mission satellite M2 coupled. can.

[Detailed Configuration of Satellite Utilization System S100]
The artificial satellite 1 has a platform satellite P and a mission satellite M as described above. Platform satellite P is the satellite to which mission satellite M is coupled. The mission satellite M is a satellite that performs a predetermined mission in outer space.

(platform satellite P)
The platform satellite P has, as shown in FIG. The platform satellite P also has, for example, structural and integration parts (not shown). The structural part here means a panel or the like necessary for the platform satellite P to maintain its shape. Also, the integration part means a cable, a bracket, and the like.

The solar paddle 31 is a power generator that converts sunlight into electric power. The solar array paddle 31 has, for example, a foldable power generation panel that is deployed in outer space.

The power supply unit 32 has a battery and a power control device (not shown), and the battery stores the power generated by the solar paddles 31 . The power supply unit 32 supplies power to each unit of the platform satellite P. FIG. The power supply unit 32 also supplies power to the mission satellite M coupled to the platform satellite P, as an example.

The coupling mechanism 33 is a mechanism for coupling the platform satellite P and the mission satellite M together. The coupling mechanism 33 specifically has a mechanism for mechanically coupling with the coupling mechanism 41 of the mission satellite M. As shown in FIG. The coupling mechanism 33 operates, for example, based on a control signal from the control unit 37 to switch the coupling state between the platform satellite P and the mission satellite M. FIG. When the mission satellite M is separated from the platform satellite P, the coupling mechanism 33 releases the connection between the platform satellite P and the mission satellite M, thereby separating the mission satellite M from the platform satellite P.

The propulsion device 34 is a device that generates a propulsive force for moving the platform satellite P, and is, for example, a chemical propulsion device or an electric propulsion device. Chemical propulsion devices are, by way of example, monopropellant or bipropellant thrusters. The electric propulsion device is, by way of example, an ion engine or a Hall thruster engine.

The attitude control device 35 is a device for controlling the attitude of the platform satellite P, and has an attitude sensor, an actuator (not shown), and the like. Attitude sensors are devices such as gyroscopes, earth sensors, sun sensors, star trackers and magnetic sensors. Actuators are devices such as momentum wheels, reaction wheels and control moment gyros.

The attitude control device 35 has, for example, a device (not shown) that measures the relative distance between the platform satellite P and the mission satellite M flying away from the platform satellite P in outer space. The attitude control device 35 also has a device for measuring the attitude of the mission satellite M, a device for specifying the state of motion of the mission satellite M, and the like.

The communication device 36 is, for example, a device that communicates with the communication device 44 of the mission satellite M and the satellite management device 2 on the ground. The communication device 36 transmits various data related to the platform satellite P, for example, to the satellite management device 2 . The communication device 36 may also transmit various data regarding the mission satellites M coupled to the platform satellite P to the satellite manager 2 . The communication device 36 receives various command signals transmitted by the satellite management device 2 .

For example, the communication device 36 may transmit the following information to the satellite management device 2 in order to notify the satellite management device 2 that the mission satellite M needs to be replaced. Specifically, the communication device 36 provides information indicating that the first mission satellite M1 coupled to the platform satellite P has failed, and information indicating that the first mission satellite M1 has expired and operation has ended. , or information indicating that the first mission satellite M1 needs to be replaced. Such information may be directly transmitted by the first mission satellite M1 itself to the satellite management device 2 and/or a mission control device (not shown) on the ground different from the satellite management device 2 .

The control unit 37 is a computer that controls the operation of each unit of the platform satellite P. FIG. For example, the control unit 37 controls the operation of the coupling mechanism 33 to couple or separate the platform satellite P and the mission satellite M. The control unit 37 also controls the coupling mechanism 33 and the propulsion device 34 to separate the mission satellite M from the platform satellite P such that, as an example, the mission satellite M moves to a fourth orbit that enters the atmosphere. The controller 37 also controls the operation of the propulsion device 34 to move the platform satellite P. In this embodiment, platform satellite P moves from geostationary transfer orbit 102 to geostationary orbit 101 and from geostationary transfer orbit 102 to geostationary orbit 101 .

The fourth orbit is the orbit for re-entering the atmosphere of the mission satellite M separated from the platform satellite. There may be. For example, a trajectory in which the separated mission satellite M enters the atmosphere over five years may be used. It does not matter how long it takes for the mission satellite M to enter the atmosphere after it is separated from the platform satellite P. A mode may be adopted in which a fall area is determined and the mission satellite is controlled to plunge into the atmosphere. The satellite M separated from the platform satellite P may be put into any orbit, and the orbit may be, for example, the second orbit or the third orbit.

The thermal control unit 38 is a control unit that controls the temperature of equipment such as a heater and a temperature sensor provided on the platform satellite P, and is controlled by the control unit 37, for example.

(Mission satellite M)
The mission satellite M has, as shown in FIG. The mission satellite M is, for example, a satellite that performs a mission related to meteorological observation, a mission related to land observation or ocean observation, a mission related to positioning such as a global positioning system (GPS), a mission related to air traffic management, or a mission related to communication. is. The mission satellite M, like the platform satellite P, also has, for example, a structural part and an integration part (not shown).

The coupling mechanism 41 is a mechanism for coupling the platform satellite P and the mission satellite M. The coupling mechanism 41 has a mechanism for mechanically coupling with the coupling mechanism 33 of the platform satellite P, for example.

The mission device 42 is a device for executing a mission to be performed by the mission satellite M in outer space, and has various measurement devices, for example. The power distribution device 43 is a device that supplies power supplied from the platform satellite P to each device provided on the mission satellite M. FIG.

The communication device 44 is a device that communicates with each of the communication device 36 of the platform satellite P and the mission control device on the ground. The communication device 44, for example, transmits various data obtained by the mission satellite M executing a mission to the platform satellite P and/or the mission control device on the ground.

A control unit 45 is a computer that controls the operation of each unit of the mission satellite M. FIG. Specifically, the control unit 45 controls operations of the coupling mechanism 41, the mission device 42, the power distribution device 43, the communication device 44, the heat control unit 46, and the like. The thermal control unit 46 is a control unit that controls the temperature of equipment such as a heater and a temperature sensor provided on the mission satellite M, and is controlled by the control unit 45, for example.

In this embodiment, communication between the communication device 44 and the communication device 36 is exemplified, but the present invention is not necessarily limited to this. Mission satellite M may not have the capability to communicate with platform satellite P. In this embodiment, the control unit 45 controls the operation of the connection mechanism 41, but if the connection mechanism 41 does not have an operable structure, the control unit 45 controls the connection mechanism 41. do not need to be controlled. Specifically, for example, if the coupling mechanism 41 is configured by a structure (for example, a handle) to which the coupling mechanism 33 of the platform satellite P is coupled, control by the control unit 45 is unnecessary.

Unlike the platform satellite P in this embodiment, the mission satellite M does not have the solar array paddle 31, the power supply section 32, the propulsion device 34, and the attitude control device 35. FIG. When the mission satellite M is configured in this way, there is an advantage that the mission satellite M can be made small and light. Furthermore, since the mission satellite M does not need to perform most of the various post-production/pre-launch tests that have been performed with the conventional technology, it is possible to reduce costs and greatly shorten the development period.

It is not essential in the present invention that the mission satellite M does not have the solar array paddle 31, the power supply unit 32, the propulsion device 34, the attitude control device 35, etc., and the mission satellite M may have these devices. .

In the satellite utilization system S100 of this embodiment, for example, after the use of the first mission satellite M1 is completed, the platform satellite P is coupled with the second mission satellite M2 launched from the earth. The fact that the mission satellite M can be made small and light as described above is advantageous in that the second mission satellite M2, which is coupled to the platform satellite P, can be launched with a smaller rocket.

When launching the platform satellite P and the mission satellite M, the platform satellite P and the mission satellite M may be launched by the same rocket (not shown) or may be launched by separate rockets.

(Satellite management device 2)
FIG. 5 is a block diagram showing the configuration of the satellite management device 2. As shown in FIG. The satellite management device 2 is a device placed on the ground and has a communication section 21 , a storage section 22 and a control section 23 .

A communication unit 21 communicates with the artificial satellite 1 . Specifically, the communication unit 21 receives signals transmitted from the platform satellite P of the artificial satellite 1 and transmits various command signals to the platform satellite P. FIG.

The storage unit 22 is a storage medium that stores various data, and includes a ROM (Read Only Memory), a RAM (Random Access Memory), a hard disk, and the like. The storage unit 22 stores computer programs executed by the control unit 23 .

The control unit 23 has a CPU (Central Processing Unit) and the like. The control unit 23 functions as a data acquisition unit 24 , a condition determination unit 25 , a signal generation unit 26 and a transmission unit 27 by executing computer programs stored in the storage unit 22 .

The data acquisition unit 24 receives signals transmitted from the platform satellite P via the communication unit 21 and acquires various data.

The condition determination unit 25 is a functional unit that determines various conditions regarding the operations of the platform satellite P and the mission satellite M. The condition determining unit 25 autonomously determines operating conditions for the platform satellite P and the mission satellite M based on various parameters relating to the operation of the platform satellite P and the mission satellite M, for example. The condition determining unit 25 may also determine operating conditions for the platform satellite P and the mission satellite M by accepting conditions determined by the operator.

Here, the condition determining unit 25 determines various conditions regarding the operation of the mission satellite M, but the condition determining unit 25 may determine only various conditions regarding the operation of the platform satellite P. good. That is, in the present invention, whether or not the satellite management device 2 controls the mission satellite M is optional.

(Processing to determine the time zone)
When the platform satellite P is moved from the geostationary orbit 101 to the geostationary transfer orbit 102 in order to couple the second mission satellite M2 to the platform satellite P (FIG. 4), at what time period does the platform satellite P move from the geostationary orbit 101 to the geostationary transfer orbit? A decision needs to be made to start moving towards 102 .

Therefore, the condition determination unit 25 determines the time zone in which the movement of the platform satellite P is to be started. Specifically, the condition determining unit 25 first determines whether the platform satellite P is stationary based on the first time zone in which the second mission satellite M2 scheduled to be coupled to the platform satellite P should reach the geostationary orbit 101. A second time period to reach the transfer trajectory 102 is determined. Then, the condition determination unit 25 determines a third time period for starting the movement of the platform satellite P toward the geostationary transfer orbit 102 based on the second time period.

As a specific example, it is assumed that the second mission satellite M2 needs to reach the geostationary orbit 101 by "April 1, 2022", which is the first time zone. The condition determination unit 25 determines the time period before the first time period as the time period in which the platform satellite P should reach the geostationary transfer orbit 102 (second time period). Then, the condition determining unit 25 sets the time period before the second time period so that the platform satellite P reaches the geostationary transfer orbit 102 in the second time period. A time period (third time period) for starting movement toward the transfer orbit 102 is determined.

By moving the platform satellite P according to the time period thus determined by the condition determination unit 25, the platform satellite P and the second mission satellite M2 can be systematically coupled.

(Processing to determine position)
The condition determination unit 25 also determines a target position to be reached by the platform satellite P when the platform satellite P is lowered to the geostationary transfer orbit 102 . The condition determining unit 25 determines the target position of the platform satellite P based on, for example, the position in the geostationary transfer orbit 102 that the second mission satellite M2 should reach. Specifically, the condition determination unit 25 determines a position that is a distance X [m] away from the second mission satellite M2 as the target position.

The signal generation unit 26 generates a command signal including information on various operating conditions determined by the condition determination unit 25 . The signal generator 26 generates various signals related to the operations of the platform satellite P and the mission satellite M. Specifically, for example, a command signal (third command signal). This command signal may contain only information that serves as a trigger for causing the platform satellite P to start a predetermined operation, or information indicating the operating conditions of predetermined equipment (for example, the coupling mechanism 33, etc.) of the platform satellite P. may contain

The signal generator 26 may also generate a command signal (fourth command signal) for moving the platform satellite P from the geostationary transfer orbit 102 to the geostationary orbit 101 . This command signal may also contain only information serving as a trigger for causing the platform satellite P to start a predetermined operation, or information indicating the operating conditions of predetermined equipment (for example, the propulsion device 34, etc.) of the platform satellite P. may contain

The transmission unit 27 transmits the command signal generated by the signal generation unit 26 to the platform satellite P via the communication unit 21 . The transmitting unit 27 may transmit, for example, a command signal for starting the movement of the platform satellite P to the geostationary transfer orbit 102 to the platform satellite P as the first command signal. The first command signal may include information of the target position determined based on the position in the geostationary transfer orbit 102 that the second mission satellite M2 should reach, determined by the condition determination unit 25 .

The transmitter 27 may also transmit a command signal for separating the first mission satellite M1 from the platform satellite P to the platform satellite P as a second command signal. The second command signal may contain information of the operating conditions under which platform satellite P separates first mission satellite M1.

The transmitter 27 also transmits the third command signal and the fourth command signal generated by the signal generator 26 to the platform satellite P. Note that each of the first to fourth command signals may include a plurality of commands.

(Example of satellite control method)
An example of a satellite control method in the satellite utilization system S100 configured as described above will be described with reference to FIGS. 4 and 6. FIG. FIG. 6 is a flow diagram of a satellite control method. In the initial state of FIG. 4 ((1) of FIG. 4), the platform satellite P to which the first mission satellite M1 is coupled is orbiting the geostationary orbit 101 .

First, the platform satellite P is lowered from the geostationary orbit 101 to the geostationary transfer orbit 102 in step S1, which is an orbital descent step. Specifically, the platform satellite P receives the first command signal for starting the descent of the platform satellite P transmitted by the satellite management device 2 . The platform satellite P starts moving from the geostationary orbit 101 to the geostationary transfer orbit 102 when it receives this first command signal.

Note that "to start moving when a command signal is received" does not necessarily mean that the platform satellite P starts moving immediately upon receiving the command signal. , the platform satellite P begins to move.

After reaching the geostationary transfer orbit 102, the platform satellite P moves to a target position determined based on the position on the geostationary transfer orbit 102 to be reached by the second mission satellite M2, which is included in the first command signal as an example. .

The second mission satellite M2 is launched by a rocket from the ground, is put into the geostationary transfer orbit 102, and is positioned at a predetermined position in the geostationary transfer orbit 102 during a predetermined time period.

Then, in a separation step, step S2, the platform satellite P separates the first mission satellite M1. For example, based on the second command signal for separating the first mission satellite transmitted from the satellite management device 2, the platform satellite P separates the first mission satellite M1 according to the separation operation conditions indicated by this signal. As an example, platform satellite P launches first mission satellite M1 into fourth orbit. As a result, the first mission satellite M1 is burned in the atmosphere and discarded.

Next, in step S3, which is a combining step, the platform satellite P from which the first mission satellite M1 has been separated into a single unit moves toward the second mission satellite M2 located at a predetermined position on the geostationary transfer orbit 102. do. Platform satellite P then mates with second mission satellite M2. Platform satellite P is coupled to second mission satellite M2, for example, by mechanically coupling coupling 33 of platform satellite P and coupling 41 of second mission satellite M2.

A second mission satellite M2 coupled to the platform satellite P is powered by the platform satellite P, thereby enabling the second mission satellite M2 to perform a given mission.

Next, in step S4, which is an orbit raising step (orbit moving step), the platform satellite P coupled with the second mission satellite M2 is raised to the geostationary orbit 101 again. Specifically, the platform satellite P moves to a predetermined position on the geostationary orbit 101 indicated by the positional information based on the positional information indicating the position in the geostationary orbit 101 where the second mission satellite M2 should be located. After that, the platform satellite P orbits the geostationary orbit 101 with the second mission satellite M2 coupled thereto, and the second mission satellite M2 performs a predetermined mission in the geostationary orbit 101.

(Action and effect of the present embodiment)
According to the satellite control method of the present embodiment described above, for example, when the first mission satellite M1 reaches its expiration date, instead of discarding the entire artificial satellite 1, only the first mission satellite M1 is discarded and the platform Satellite P can continue to be used with second mission satellite M2 coupled. In other words, since the platform satellite P can be used for a long period of time by replacing the mission satellite M, the cost of purchasing/operating the artificial satellite 1 can be reduced as a result. Also, since the entire satellite 1 is not discarded, the amount of waste is also reduced.

In the satellite control method of this embodiment, the platform satellite P descended from the geostationary orbit 101 to the geostationary transfer orbit 102 for coupling with the second mission satellite M2 moves the first mission satellite M1 to the fourth After being injected into orbit, it couples to the next second mission satellite M2 without changing its orbit. Such a method is advantageous in comparison with, for example, platform satellite P moving from geostationary orbit 101 to graveyard orbit and then descending to geostationary transfer orbit 102 for disposal of first mission satellite M1. It requires less fuel for the movement of satellite P and is efficient. In addition, space disposal (to graveyard orbit) can be eliminated.

Further, in this embodiment, the mission satellite M does not have a power generator or the like, and is detachably coupled to the platform satellite P so that power is supplied from the platform satellite P. Therefore, the mission satellite M can be made small, light, and easy.

(Modification of the first embodiment)
This embodiment is not limited to the specific aspects described above, and may be modified as follows, for example. For example, although the geostationary orbit 101 and the geostationary transfer orbit 102 are illustrated above as the first orbit and the second orbit, the first orbit and the second orbit may be other arbitrary orbits.

Also, the platform satellite P may move the second mission satellite M2 not to the geostationary orbit 101 but to a third orbit different from the first orbit and the second orbit. Here, the third orbit may be, for example, a middle orbit or a quasi-zenith orbit.

In the above description, the first mission satellite M1 is rammed into the atmosphere, but the platform satellite P does not ram the first mission satellite M1 into the atmosphere. Satellite M1 may be separated. Platform satellite P may separate first mission satellite M1, for example, in a graveyard orbit.

Although the single platform satellite P orbiting the geostationary orbit 101 and the geostationary transfer orbit 102 is illustrated above, multiple platform satellites P launched by rockets may orbit the geostationary orbit 101 .

In this case, each satellite is controlled such that, for example, the satellite management device 2 selects one platform satellite P from among a plurality of platform satellites P and couples the selected platform satellite P with the second mission satellite M2. may

<Modification>
(Method of introducing platform satellite P and mission satellite M into orbit)
In the above embodiments, it was explained that the platform satellite P and the mission satellite M were launched by the same or separate rockets. In the present invention, the introduction of the platform satellite P and the mission satellite M into the geostationary orbit 101 or the geostationary transfer orbit 102 may be carried out by any procedure. For example, the following satellite introduction steps may be used. .

Specifically, in this satellite introduction step, as an example, after launching the platform satellite P and the first mission satellite M1 by the same or different rockets in a state in which they are not coupled with each other, the platform satellite P and the It is coupled with the first mission satellite M1. Then, the platform satellite P coupled with the first mission satellite M1 is raised from the geostationary transfer orbit 102 to the geostationary orbit 101 .

Of the platform satellite P and the mission satellite M launched by the rocket, the platform satellite P is first separated from the rocket and put into the geostationary transfer orbit 102, and then the mission satellite M is separated from the rocket and put into the geostationary transfer orbit 102. may be

(Replacement of mission satellite M)
In the above embodiment, when the first mission satellite M1 has expired, the platform satellite P moves from the geostationary orbit 101 to the geostationary transfer orbit 102 to separate the first mission satellite M1. The first mission satellite M1 may be replaced by other conditions other than the expiration of the service life. For example, when the platform satellite P detects a failure of the first mission satellite M1 and receives a command signal to separate the first mission satellite M1 from the satellite management device 2, the platform satellite P separates the first mission satellite M1, It may be coupled with a second mission satellite M2 launched from the ground.

In the above embodiments, it was described that the platform satellite P separates the first mission satellite M1, and then the second mission satellite M2 merges with the platform satellite P. The platform satellite P may move to the fourth orbit together with the mission satellite M instead of injecting the mission satellite M into the fourth orbit, for example. That is, in one example of the satellite control method of the present invention, in a state in which the mission satellite M (for example, the second mission satellite M2 or a third mission satellite different from the second mission satellite) is coupled to the platform satellite P, Platform satellite P may be moved to a fourth orbit. It should be noted that the third mission satellite may be any mission satellite M that is coupled to the platform satellite P after, for example, the second mission satellite M2 has been separated.

(Replacement of platform satellite P)
It is conceivable that the platform satellite P will fail (for example, equipment other than the communication device will fail) during operation of the artificial satellite 1 . In this case, the satellite management device 2 may control the satellites in the following manner. First, the satellite management device 2 selects, from among the plurality of platform satellites P orbiting the geostationary orbit 101, the second platform satellite P2 that can be coupled to the mission satellite M separated from the first platform satellite P1. A movement instruction command signal is transmitted to the two-platform satellite P2 to move it to a predetermined position where it can be coupled to the mission satellite M. The satellite management device 2 transmits a separation instruction command signal for separating the mission satellite M to the failed first platform satellite P1.

The second platform satellite P2 receives the movement instruction command signal from the satellite management device 2 and moves toward the mission satellite M separated from the first platform satellite P1. Next, the first platform satellite P1 receives a separation instruction command signal from the satellite management device 2 and separates the mission satellite M. After that, the second platform satellite P2 is coupled to the mission satellite M so that the mission satellite M can continue to be used in the geostationary orbit 101 .

Although the present invention has been described above using the embodiments, the technical scope of the present invention is not limited to the scope described in the above embodiments, and various modifications and changes are possible within the scope of the gist thereof. be. For example, all or part of the device can be functionally or physically distributed and integrated in arbitrary units. In addition, new embodiments resulting from arbitrary combinations of multiple embodiments are also included in the embodiments of the present invention. The effect of the new embodiment caused by the combination has the effect of the original embodiment.

1 Artificial satellite 2 Satellite management device 10 Earth 21 Communication unit 22 Storage unit 23 Control unit 24 Data acquisition unit 25 Condition determination unit 26 Signal generation unit 27 Transmission unit 31 Solar paddle 32 Power supply unit 33 Coupling mechanism 34 Propulsion device 35 Attitude control device 36 communication device 37 control unit 41 coupling mechanism 42 mission device 43 power distribution device 44 communication device 45 control unit 101 geostationary orbit 102 geostationary transfer orbit M mission satellite M1 first mission satellite M2 second mission satellite P platform satellite P1 first platform satellite P2 2nd platform satellite S100 Satellite utilization system

Claims (13)

an orbital descent step of moving a platform satellite coupled orbiting a first mission satellite in a first orbit to a second orbit closer to the earth than the first orbit;
separating the first mission satellite from the platform satellite in the second orbit;
a coupling step of coupling the second mission satellite inserted into the second orbit and the platform satellite;
an orbit movement step of moving the platform satellite coupled with the second mission satellite to the first orbit or a third orbit different from the first orbit and the second orbit;
A satellite control method comprising: The separating step comprises:
separating the first mission satellite from the platform satellite and injecting the first mission satellite into an orbit for entry into the atmosphere;
A satellite control method according to claim 1. further comprising a time zone determination step of determining a time zone for the platform satellite to reach the second orbit;
The time zone determination step includes:
determining a second time period for the platform satellite to reach the second orbit based on a first time period for the second mission satellite to reach the first orbit;
determining a third time period to initiate movement of the platform satellite toward the second orbit based on the second time period;
including
said orbit descent step includes initiating movement of said platform satellite toward said second orbit during said third time period;
A satellite control method according to claim 1 or 2. The orbital descent step includes:
moving the platform satellite to a predetermined position on the second orbit determined based on the position on the second orbit to be reached by the second mission satellite;
A satellite control method according to any one of claims 1 to 3. the first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit,
In the orbital descent step,
said platform satellite transferring from said geostationary orbit when said platform satellite receives a first command signal transmitted by a satellite manager on the ground to initiate movement of said platform satellite to said geostationary transfer orbit; to initiate movement into orbit,
A satellite control method according to any one of claims 1 to 4. The orbital movement step includes:
moving the platform satellite coupled with the second mission satellite to a predetermined position on the first orbit based on position information indicating the position where the second mission satellite should be positioned on the first orbit;
A satellite control method according to any one of claims 1 to 5. the first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit,
The separating step comprises:
said platform satellite detaching said first mission satellite based on a second command signal transmitted by a satellite manager on the ground to detach said first mission satellite from said platform satellite;
A satellite control method according to any one of claims 1 to 6. The combining step includes:
said platform satellite docking with said second mission satellite based on a third command signal transmitted by a satellite manager on the ground to dock said second mission satellite and said platform satellite;
A satellite control method according to any one of claims 1 to 7. the first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit,
The orbital movement step includes:
moving the platform satellite to the geostationary orbit based on a fourth command signal transmitted by a satellite manager on the ground to move the platform satellite from the geostationary transfer orbit to the geostationary orbit;
A satellite control method according to any one of claims 1 to 8. moving the platform satellite into an orbit for entry into the atmosphere while the platform satellite is coupled to the second mission satellite or a third mission satellite different from the second mission satellite; ,
A satellite control method according to any one of claims 1 to 9. the platform satellite has a power generator,
said first mission satellite and said second mission satellite having no power generator and being detachably coupled to said platform satellite and powered by said platform satellite;
A satellite control method according to any one of claims 1 to 10. After injecting the platform satellite and the first mission satellite uncoupled into the second orbit by the same or separate rockets, coupling the platform satellite and the first mission satellite in the second orbit. and moving the platform satellite and the first mission satellite from the second orbit to the first orbit.
A satellite control method according to any one of claims 1 to 11. Prior to the orbital descent step,
information indicating that the first mission satellite has failed;
At least one of information indicating that the operation of the first mission satellite has ended, or information indicating that the replacement of the first mission satellite is necessary, the platform satellite or the first mission satellite is a satellite on the ground further comprising a notification step of sending to the management device;
A satellite control method according to any one of claims 1 to 12.