KR102589825B1 - Satellite device and method for operating thereof - Google Patents

Abstract

The present invention relates to an artificial satellite and a method of operating the same, which includes an auxiliary power generation unit capable of producing electrical energy using vibration; And a storage unit that can store the electrical energy produced by the auxiliary power generation unit and is connected to the auxiliary power generation unit. It can shorten the time required for a satellite to perform its mission from launch.

Description

Satellite device and method for operating the same}

The present invention relates to a satellite and a method of operating the same, and more specifically, to a satellite that can produce electrical energy using vibrations generated from the satellite and a method of operating the same.

Recently, the utilization and importance of satellites are gradually increasing in the military industry and military strategy establishment. Such satellites are generally equipped with solar panels so that the satellite can produce power to perform its mission.

Satellites are launched by being mounted on a launch vehicle with the solar panel folded. After the satellite reaches the mission orbit and the launch vehicle is separated, the solar panel is deployed from the satellite to receive sunlight and generate power.

On the other hand, when the satellite is separated from the launch vehicle, it moves irregularly for a certain period of time, then maneuvers, corrects its attitude, and deploys solar panels. However, the satellite cannot produce power until the solar panel is deployed, and even after the solar panel is deployed, it is difficult to produce sufficient power for a certain period of time, so there is a problem that it takes a lot of time to carry out the original mission. .

KR 10-1754362 B

The present invention provides an artificial satellite and a method of operating the same that can shorten the time required from satellite launch to mission performance.

An artificial satellite according to an embodiment of the present invention includes an auxiliary power generation unit capable of producing electrical energy using vibration; And a storage unit capable of storing electrical energy produced by the auxiliary power generation unit and connected to the auxiliary power generation unit.

A frame part forming the external shape of the satellite; And an electronic module unit installed in the frame unit, wherein the auxiliary power generation unit and the storage unit may be connected to the electronic module unit.

The electronic module unit includes at least one electronic module; and a cable for supplying at least one of a signal and power to the electronic module, wherein the auxiliary power generation unit may be connected to the cable.

The auxiliary power generation unit may be installed in the frame unit to separate a portion of the cable from the frame unit.

The auxiliary power generation unit includes a first support connected to a first position of the cable and installed on the frame unit to extend in a direction intersecting the direction in which the cable extends; a second support connected to a second position of the cable and installed on the frame to be spaced apart from the first support; An auxiliary generator capable of producing electrical energy using vibration and disposed between the first support and the second support; And it may include a vibration transmission member connected to the cable and the auxiliary generator.

The auxiliary generator may be fixedly installed on the frame part.

The vibration transmission member may include an elastic body.

The distance between the first support and the second support may be shorter than the length from the first position to the second position of the cable.

The auxiliary generator may include a vibration energy harvester using at least one of a piezoelectric method, an electrostatic method, and an electromagnetic method.

A plurality of auxiliary power generation units may be connected to the cable.

The cable includes a harness cable formed in a bundle, and the auxiliary power generation unit may be connected to two or more cables of the harness cable.

It may further include a main power generation unit installed on the frame unit to produce electric energy using solar heat, and the main power generation unit may be connected to the storage unit.

A method of operating a satellite according to an embodiment of the present invention includes the processes of launching and flying a satellite; and a process of producing and storing electrical energy using vibration generated from the satellite.

The process of producing and storing the electrical energy includes: producing electrical energy using vibration generated from a cable installed on the satellite; and a process of storing the produced electrical energy.

After the process of producing and storing the electrical energy, the process of operating the satellite using the stored electrical energy may be further included.

The process of operating the satellite may include the process of controlling the attitude of the satellite.

The process of controlling the attitude of the satellite may include changing the attitude of the satellite so that the solar collector faces the sun.

A process of producing electrical energy using solar energy after the process of controlling the attitude of the satellite; and a process of storing the produced electrical energy.

After the process of controlling the attitude of the satellite, the mission can be performed using the electrical energy produced by solar heat.

According to an embodiment of the present invention, electrical energy can be produced and stored using vibration generated from a satellite. In other words, a vibration energy harvester that can convert vibration into electrical energy can be installed on a satellite, and the vibration generated during the launch and flight of the satellite can be produced and stored as electrical energy. The electrical energy produced and stored in this way can be used as initial energy to operate the satellite before the satellite produces electrical energy using solar heat. Therefore, the time it takes for a satellite to complete its mission from launch can be shortened.

1 is a diagram schematically showing an artificial satellite according to an embodiment of the present invention.
Figure 2 is a block diagram schematically showing the internal structure of a satellite according to an embodiment of the present invention.
Figure 3 is a diagram showing an auxiliary power generation unit installed on a satellite according to an embodiment of the present invention.
Figure 4 is a diagram showing the operating state of the auxiliary power generation unit.
Figure 5 is a flow chart showing a satellite operation method according to an embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the attached drawings. However, the present invention is not limited to the embodiments disclosed below and will be implemented in various different forms. The embodiments of the present invention only serve to ensure that the disclosure of the present invention is complete and to those of ordinary skill in the art. It is provided to provide complete information. In order to explain the invention in detail, the drawings may be exaggerated, and like symbols in the drawings refer to like elements.

The artificial satellite and its operating method according to an embodiment of the present invention produce electrical energy using vibration generated from the satellite when the artificial satellite is mounted on a satellite loading device and launched into space by a launch vehicle, and the produced electrical energy Can be used in the operation of artificial satellites. Meanwhile, artificial satellites can be divided into large and medium-sized satellites in which the main body and payload are separated, and small or micro satellites in which the main body and payload are formed as one piece. At this time, the weight of a large satellite is 1000 kg or more, the weight of a medium-sized satellite is about 500 to 1000 kg, the weight of a small satellite is about 100 to 500 kg, and the weight of a micro-satellite is 100 kg or less. Hereinafter, an artificial satellite is exemplified as a micro-satellite whose main body and payload are formed as one piece and weighs less than 100 kg. However, satellites are not limited to micro-satellites and can be diverse.

FIG. 1 is a block diagram schematically showing the structure of an artificial satellite according to an embodiment of the present invention, FIG. 2 is a diagram exemplarily showing an artificial satellite according to an embodiment of the present invention, and FIG. 3 is a diagram schematically showing the structure of an artificial satellite according to an embodiment of the present invention. This is a diagram showing the auxiliary power generation unit installed on the satellite, and Figure 4 is a diagram showing the operating state of the auxiliary power generation unit.

Referring to FIGS. 1 and 2, the satellite 100 according to an embodiment of the present invention includes an auxiliary power generation unit 132 capable of producing electrical energy using vibration, storing the produced electrical energy, and auxiliary power generation unit 132 capable of producing electrical energy using vibration. It may include a storage unit 133 connected to the power generation unit 132. Additionally, the satellite 100 may include a frame unit 110 that forms the external shape of the satellite 100 and an electronic module unit 120 installed in the frame unit 110.

The frame unit 110 may form a space capable of accommodating and supporting the electronic module unit 120, the auxiliary power generation unit 132, and the storage unit 133 therein. The frame unit 110 may include a plurality of horizontal frames 111 and vertical frames 112. At this time, the plurality of horizontal frames 111 are formed in a rectangular frame shape and include a first horizontal frame 111a, a second horizontal frame 111b, and a third horizontal frame 111c that are spaced apart in the vertical direction and arranged side by side. It can be included. The plurality of vertical frames 112 are formed in a bar shape extending in the vertical direction, and connect the first vertical frame 112a, the second horizontal frame 111b, and the third horizontal frame 111c ( 112a), a second vertical frame 112b, a third vertical frame (not shown), and a fourth vertical frame (not shown). The plurality of horizontal frames 111 and the plurality of vertical frames 112 may be connected to each other to form a frame structure of approximately a hexahedron shape. At this time, the first vertical frame (112a), the second vertical frame (112b), the third vertical frame (not shown), and the fourth vertical frame (not shown) are the first horizontal frame (111a) and the second horizontal frame (111b). ) and can be connected to each corner of the third horizontal frame 111c. Through this configuration, the frame unit 110 has an electronic module unit 120 between the first horizontal frame 111a and the second horizontal frame 111b, and between the second horizontal frame 111b and the third horizontal frame 111c. ) can be installed and supported. In this way, if the satellite 100 is manufactured using a plurality of frames, the weight of the satellite 100 can be reduced.

The frame portion 110 may be formed to have a rectangular parallelepiped shape, or may be formed to have various shapes such as a polyhedron such as a cube or a sphere. Here, it has been described that the frame unit 110 is manufactured only with frame-shaped and bar-shaped frames, but a plate-shaped frame may also be used as needed.

The electronic module unit 120 is installed in the frame unit 110 and may include a plurality of electronic modules capable of performing various functions. For example, the electronic module unit 120 includes a frame unit 110, that is, an attitude control module 121a for controlling the attitude of the satellite 100, a communication module 121b such as a transceiver, and an imaging module such as an infrared optical device ( 121d) and a control module 121c.

The attitude control module 121a can control the attitude and orbit of the satellite for operational purposes, such as stabilization of the frame unit 110, precise attitude control, antenna orientation, and solar panel and thruster control. The posture control module 121a consists of a sensor, a driver, and an algorithm. The algorithm determines the current posture and position of the frame unit 110 by calculating the data received from the sensor and generates force and torque by giving appropriate commands to the driver. It can be precisely controlled to obtain the desired trajectory and attitude.

The communication module 121b is connected to the antenna 123 installed on the frame unit 110, and transmits data obtained through the satellite's mission performance to the ground through the antenna 123, and transmits data from the ground station to the satellite for the operation of the satellite. Relevant commands can be received and transmitted to the control module 121c. The communication module 121b is largely divided into S-band and By receiving information, the X-band transmitter can transmit large amounts of data, such as information observed from the payload, to the ground at high speed.

The control module 121c can receive ground remote commands through an S-band uplink communication link and perform the functions of authenticating, decoding, storing, executing, and distributing commands. In addition, the control module 121c can periodically collect, format, store, and reproduce remote metering information of the entire satellite and transmit it to the ground station through an S-band downward communication link according to ground remote commands. Additionally, the control module 121c manages satellites and payloads according to ground remote commands and can provide an operating environment for flight software. The control module 121c includes a telemetry telecommand unit that provides an S-band up/down communication link between the satellite and the ground station, an on-board computer unit that provides an operating platform for flight software, an in-out unit that provides digital and analog interfaces, And it may be configured as a platform for operation and interface connection of the units constituting the control module 121c.

The photographing module 121d photographs subjects in space or the Earth, and the communication module can transmit the video or image captured by the photographing module to a communication center on the ground.

However, the electronic module unit 120 is not limited to this and may vary. That is, the electronic module unit 120 may be composed of modules that perform various functions depending on the mission of the satellite.

The electronic module unit 120 may include a cable 122 for transmitting and receiving signals between modules. At this time, the cable 122 may be provided as a bundle of cables having various lengths, for example, a harness cable. Such a harness cable may have a connector installed at the end of the cable so that it can be used by inserting the connector into a socket installed in the electronic module. However, the harness cable may be connected to the electronic module by welding, etc.

The electronic module unit 120 may be operated by receiving electrical energy from the power supply unit 130.

The power unit 130 includes a power generation unit 131 and 132 capable of producing electrical energy using vibration and solar heat, and a storage unit 133 capable of storing and regenerating the electrical energy produced by the power generation units 131 and 132. ) may include.

The power generation units 131 and 132 include a main power generation unit 131 capable of producing electrical energy using solar heat, and an auxiliary power generation unit 132 capable of producing electrical energy using vibration generated from the satellite 100. can do.

The main power generation unit 131 may include a heat collecting plate 131a capable of collecting solar heat, and a main generator 131b capable of converting the heat collected by the heat collecting plate 131a into electrical energy. At this time, the heat collecting plate 131a may be installed on one side of the frame portion 110, for example, the first horizontal frame 111a, and the main generator 131b may be installed on the inside of the frame portion 110, for example, the first horizontal frame 111a. ) and the second horizontal frame (111b). In addition, the heat collecting plate 131a is connected to the main generator 131b and transfers the collected heat to the main generator 131b, and the main generator 131b converts the transferred heat into electrical energy and stores it in the storage unit 133. You can. When the main power generation unit 131 is arranged so that the collector plate 131a faces the sun, the main power generation unit 131 can collect solar heat and produce electrical energy. Additionally, the electrical energy produced by the main power generation unit 131 can be used as energy for the satellite 100 to perform its actual mission.

The auxiliary power generation unit 132 may produce electrical energy using vibration generated from the satellite 100. That is, the artificial satellite 100 is launched and flies by being mounted on a launch vehicle, and during the process of launch and flight, vibration is generated due to collisions with the propellant and the atmosphere. Vibrations generated by such various factors can be transmitted to and vibrate the entire satellite 100, for example, the electronic modules as well as the cable 122 connected to the electronic modules. Accordingly, in an embodiment of the present invention, the auxiliary power generation unit 132 is connected to the cable 122, and vibration of the cable 122 is used to produce electrical energy capable of operating at least one of the electronic modules in space. . At this time, the auxiliary power generation unit 132 produces electrical energy before the main power generation unit 131 produces electrical energy, and the electrical energy produced in this way can be used in the preparation process for the satellite 100 to perform its actual mission. there is.

Referring to FIG. 3, the auxiliary power generation unit 132 may separate a portion of the cable 122 from the frame unit 110. That is, in order to produce electric energy using the vibration of the cable 122, the auxiliary power generation unit 132 may be spaced apart from the frame unit 110 so that the cable 122 can vibrate.

The auxiliary power generation unit 132 is connected to the first position P1 of the cable 122, and has a first support 132a installed on the frame unit 110 to extend in a direction intersecting the direction in which the cable 122 extends. ) and a second support (132b) connected to the second position (P2) of the cable 122 and installed on the frame portion 110 to be spaced apart from the first support (132a), and electrical energy using vibration. Can be produced and transmitted vibration connected to the auxiliary generator (132c) and cable 122 and the auxiliary generator (132c) installed on the frame portion 110 to be disposed between the first support (132a) and the second support (132b) It may include a member 132d. The cable 122 is fixed at the first position (P1) and the second position (P2) to the first support (132a) and the second support (132b), and is located between the first position (P1) and the second position (P2). can vibrate or move.

The first support 132a and the second support 132b may be made of a material similar to or the same as the frames constituting the frame portion 110. At this time, the first support 132a, the second support 132b, and the frame portion 110 may be formed of an insulating material.

The first support 132a and the second support 132b may have the same or different shapes and sizes. For example, the first support (132a) and the second support (132b) may position the first position (P1) and the second position (P2) of the cable 122 at the same height, and the first position (P1) and the second support (132b) may be positioned at the same height. Position 2 (P2) can also be placed at different heights. That is, the first support 132a and the second support 132b may be formed to separate a portion of the cable 122 from the frame portion 110. In this case, the distance L between the first support 132a and the second support 132b is preferably shorter than the length from the first position to the second position of the cable 122. This is to separate the cable 122 from the frame unit 110 to efficiently generate vibration, or movement, during launch and flight of the satellite 100.

The vibration transmission member 132d can transmit vibration generated from the cable 122 to the auxiliary generator (132c). Referring to FIG. 4, when vibration occurs in the cable 122, the cable 122 moves in the direction (x) in which the cable 122 extends, for example, in the direction (y) that intersects the horizontal direction, for example, in the up and down direction. . Accordingly, the vibration transmission member 132d may be formed of an elastic body that can transmit the vibration or movement of the cable 122 to the auxiliary generator 132c while expanding and contracting in the direction in which the cable 122 moves. This vibration transmission member 132d may be provided with a spring, a rubber band, etc.

Here, the cable 122 is described as vibrating or moving in the up and down direction (y), but it can also vibrate or move in the up and down direction (y) as well as the horizontal direction (x) and diagonal directions, that is, in all directions. In addition, although the first support 132a and the second support 132b have been described as arranging the cable 122 in the horizontal direction (x), the first support 132a and the second support 132b are arranged in the cable 122. ) can also be placed in various directions, including the up and down direction (y).

The auxiliary generator 132c is fixedly installed on the frame unit 110 and can produce electrical energy using the vibration of the cable 122 transmitted by the vibration transmission member 132d.

The auxiliary generator 132c may be provided as a vibration energy harvester using at least one of a piezoelectric method, an electrostatic method, and an electromagnetic method.

Here, the piezoelectric auxiliary generator 132c uses the principle of generating a voltage on the crystal surface of a piezoelectric material such as quartz, tourmaline, Rochelle salt, PZT, ZnO, AlN, PVDF, etc. due to vibration or shock generated in the surrounding environment. Thus, electrical energy can be produced. At this time, the vibration transmission member 132d transmits vibration to the auxiliary generator 132c, and the auxiliary generator 132c receives vibration from the vibration transmission member 132d and applies vibration to the piezoelectric material, thereby producing electrical energy. .

The electrostatic-type auxiliary generator 132c can produce electrical energy by generating voltage through charging and discharging phenomena that occur when the capacitance size changes to the maximum and minimum as the capacitance plate moves due to vibration. At this time, the vibration transmission member 132d transmits vibration to the auxiliary generator 132c, and the auxiliary generator 132c receives vibration from the vibration transmission member 132d to deform the capacitor plate to generate static electricity to produce electrical energy. You can.

The electromagnetic auxiliary generator 132c is based on Faraday's law and can produce electrical energy using external shock or vibration as an energy source using a coil and a permanent magnet. At this time, the vibration transmission member 132d transmits vibration to the auxiliary generator 132c, and the auxiliary generator 132c receives the vibration from the vibration transmission member 132d and moves the permanent magnet or coil to induce electromagnetism to generate electrical energy. can produce.

This auxiliary generator 132c is a known technology, and its internal structure can be changed in various ways.

The auxiliary generator 132c produces electrical energy using vibration generated from the cable 122, and the produced electrical energy can be transferred to the storage unit 133 and stored.

Meanwhile, a plurality of auxiliary power generation units 132 may be provided. At this time, as long as there is no difficulty in launching a satellite, the number of auxiliary power generation units 132 is not particularly limited.

A plurality of auxiliary power generation units 132 may be installed to be spaced apart from one cable 122. For example, a plurality of auxiliary power generation units 132 may be installed on the longest cable 122 among the harness cables.

Alternatively, a plurality of auxiliary power generation units 132 may be installed on some cables 122 of the harness cables. For example, the auxiliary power generation unit 132 may be formed on cables having a separation distance between cables among harness cables. Alternatively, the auxiliary power generation unit 132 may be installed in cables connected to an electronic module located at a relatively long distance among the harness cables. The auxiliary power generation unit 132 may be connected to the cable 122 in various ways.

Below, a satellite operation method according to an embodiment of the present invention will be described. The satellite operation method according to the embodiment of the present invention can be applied to the artificial satellite described above.

Figure 5 is a flowchart showing a satellite operation method according to an embodiment of the present invention.

Referring to FIG. 5, the method of operating a satellite according to an embodiment of the present invention includes a process of launching and flying a satellite 100 (S101) and producing and storing electrical energy using vibration generated from the satellite 100. It may include a process (S102).

First, a satellite 100 may be prepared and the satellite 100 may be mounted on a mounting device (not shown). The satellite 100 may include a micro-satellite, a synthetic aperture radar (SAR) satellite formed in a cuboid or rectangular plate shape, or a cube-shaped satellite. However, the shape or type of the plurality of artificial satellites (AS) is not limited to this and may vary. A plurality of such satellites 100 are provided, and a plurality of satellites can be mounted on a mounting device.

After mounting the satellite 100 on the payload device, the payload device can be connected to the launch vehicle. After moving the launch vehicle to which the payload device is connected to a satellite launcher (not shown), the satellite payload device and launch vehicle can be launched from the ground into space by the propulsion force of the propellant installed on the launch vehicle.

The payload device and launch vehicle launched from the ground take off and fly toward space, and when they reach a predetermined height, the launch vehicle may be separated from the payload device (S103). At this time, vibration occurs in the launch vehicle and the loading device due to the operation of the propellant of the launch vehicle and collision with the atmosphere. The vibration generated in this way can also be transmitted to the satellite 100 mounted inside the payload device. Vibration transmitted to the satellite 100 may also be transmitted to the cable 122 of the satellite 100 to cause vibration or movement in the cable 122. In this way, when the cable 122 vibrates, the auxiliary power unit 130 connected to the cable 122 produces electrical energy by receiving the cable 122 through the vibration transmission member 132d, and stores the produced electrical energy. It can be saved at (133).

And when the launch vehicle is separated from the payload device, the propellant installed in the payload device can be ignited to fly the payload device to a predetermined orbit. When the payload device reaches a predetermined orbit, the payload device can be opened and the artificial satellite 100 mounted inside can be ejected into space.

When the satellite 100 is ejected from the mounting device, the attitude of the satellite 100 can be controlled by driving an attitude control module to produce electric energy using solar heat (S104). In other words, when the satellite 100 is ejected from the mounting device, it moves in the shape of a rolling ball, and then can perform a process of changing its posture to have an attitude capable of performing its mission.

Thereafter, when the attitude of the satellite 100 is controlled, electrical energy can be produced using solar heat, and the produced electrical energy can be stored in the storage unit (S105).

Conventionally, when the heat collecting plate 131a installed on the frame unit 110 is oriented towards the sun, the satellite 100 changes its attitude to produce electrical energy using solar heat to have an attitude capable of performing its mission. and performed the mission. Therefore, there was a problem that it took a relatively long time for the satellite 100 to be launched into space and perform its mission.

Accordingly, in the present invention, the time required for the satellite 100 to be launched into space and perform its mission can be shortened by producing and storing electrical energy using vibrations generated during the launch and flight of the payload device and launch vehicle. . In other words, the time required to position the satellite 100 toward the sun can be shortened by using the electrical energy produced during the launch and flight of the payload device and launch vehicle to control the attitude of the satellite 100. .

Accordingly, since the time required to produce electrical energy using solar heat can be shortened, electrical energy for operating the electronic modules accommodated in the frame portion 110 of the satellite 100 can be quickly and sufficiently produced. Additionally, if the amount of electrical energy produced during the launch and flight of the payload device and launch vehicle is sufficient, it can be used to operate electronic modules until electrical energy is produced using solar heat. Therefore, the mission can be performed (S106) by operating the electronic modules quickly and stably.

In the above, preferred embodiments of the present invention have been described and illustrated using specific terms, but such terms are only for clearly describing the present invention, and the embodiments of the present invention and the described terms are in accordance with the technical spirit of the following claims. It is obvious that various changes and changes can be made without departing from the scope. These modified embodiments should not be understood individually from the spirit and scope of the present invention, but should be regarded as falling within the scope of the claims of the present invention.

100: satellite 110: frame unit
120: Electronic module unit 130: Power unit
131: Main power generation department 132: Auxiliary power generation department
133: storage unit

Claims (19)

As a satellite,
A frame part forming the external shape of the satellite;
An electronic module unit installed on the frame unit;
An auxiliary power generation unit capable of producing electrical energy using vibration and connected to the electronic module unit; and
A storage unit capable of storing electrical energy produced by the auxiliary power generation unit and connected to the electronic module unit and the auxiliary power generation unit,
The electronic module part,
at least one electronic module; and
Includes a cable for supplying at least one of a signal and power to the electronic module,
The auxiliary power generation unit is a satellite installed in the frame unit to separate a portion of the cable from the frame unit in order to produce electric energy using vibration generated in the cable. delete delete delete In claim 1,
The auxiliary power generation unit,
a first support connected to a first position of the cable and installed on the frame to extend in a direction intersecting the direction in which the cable extends;
a second support connected to a second position of the cable and installed on the frame to be spaced apart from the first support;
An auxiliary generator capable of producing electrical energy using vibration and disposed between the first support and the second support; and
A satellite including a vibration transmission member connected to the cable and the auxiliary generator. delete In claim 5,
The vibration transmission member is an artificial satellite including an elastic body. In claim 5,
A satellite wherein the distance between the first support and the second support is shorter than the length from the first to the second position of the cable. In claim 5,
The auxiliary generator is a satellite including a vibration energy harvester using at least one of a piezoelectric method, an electrostatic method, and an electromagnetic method. In claim 5,
The auxiliary power generation unit is a satellite connected to the cable in plural numbers. In claim 5,
The cable includes a harness cable formed in a bundle,
The auxiliary power generation unit is a satellite connected to two or more cables among the harness cables. The method of any one of claims 1, 5, 7 to 11,
It further includes a main power generation unit installed on the frame unit to produce electrical energy using solar heat,
The main power generation unit is a satellite connected to the storage unit. The process of launching and flying a satellite; and
Including a process of producing and storing electrical energy using vibration generated from the satellite,
The process of producing and storing the electrical energy is,
A process of producing electrical energy using vibration generated from a cable installed on the satellite; and
A method of operating a satellite including a process of storing generated electrical energy. delete In claim 13,
After the process of producing and storing the electrical energy,
A method of operating a satellite further comprising: operating the satellite using stored electrical energy. In claim 15,
The process of operating the satellite includes the process of controlling the attitude of the satellite. In claim 16,
The process of controlling the attitude of the satellite includes changing the attitude of the satellite so that the solar collector faces the sun. The method of claim 16 or 17,
After the process of controlling the attitude of the satellite,
The process of producing electrical energy using solar energy; and
A method of operating a satellite including a process of storing generated electrical energy. In claim 18,
A satellite operation method that performs a mission using electrical energy produced by solar heat after the process of controlling the attitude of the satellite.

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