CN217642846U - Power supply system of spacecraft - Google Patents
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- CN217642846U CN217642846U CN202221861530.1U CN202221861530U CN217642846U CN 217642846 U CN217642846 U CN 217642846U CN 202221861530 U CN202221861530 U CN 202221861530U CN 217642846 U CN217642846 U CN 217642846U
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Abstract
The utility model provides a spacecraft power supply system, the system includes flight controller, battery pack and solar module, the battery pack includes battery, first supply cable and battery power supply controller, the solar module includes solar panel array group, second supply cable and panel power supply controller; the storage battery assembly and the solar battery assembly are installed at the tail part of the spacecraft, the storage battery is electrically connected with tail load equipment installed at the tail part of the spacecraft through the first power supply cable, and the solar panel array group is electrically connected with the tail load equipment through the second power supply cable; and the storage battery power supply controller and the battery panel power supply controller are in communication connection with the flight controller respectively. By adopting the device, the waste of power resources in the space vehicle can be avoided.
Description
Technical Field
The utility model relates to a spacecraft field particularly, relates to a spacecraft power supply system.
Background
A spacecraft is a variety of aircrafts which are used for running in the space according to the law of celestial body mechanics and executing specific tasks such as exploration, development and utilization of the space and celestial bodies, when the spacecraft flies away from the ground, functional support is provided for the spacecraft by various load devices to ensure the normal operation of the spacecraft (for example, a flight power device provides a power source for the spacecraft, an inertia sensitive device detects the attitude of the spacecraft in real time, a measuring device provides flight data for the spacecraft in real time, an initiating explosive device activates a high-voltage thermal battery for the spacecraft, and the like), and various load devices can be normally used under the power supply of a power supply.
In the prior art, when power is supplied to load equipment of a spacecraft, the load equipment of the spacecraft is only supplied with power by using a storage battery, and because the storage battery can reduce the power after supplying power to the equipment, in order to ensure that the storage battery can continuously supply power to the load equipment in the spacecraft, when the power of the storage battery is insufficient, the storage battery needs to be charged by using a solar battery.
The inventor finds in research that the output power of the solar cell is in direct proportion to the intensity of the solar cell receiving the sunlight, that is, the output power of the solar cell is larger when the intensity of the solar cell receiving the sunlight is larger, and when the spacecraft flies in a flight area with larger sunlight intensity, the output electric quantity of the solar cell is too large and exceeds the battery capacity of the storage battery, so that the electric energy generated by the solar cell cannot be fully utilized, and the waste of electric power resources in the spacecraft is caused.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a spacecraft power supply system can avoid the waste to the electric power resource in the spacecraft.
The application provides a spacecraft power supply system, which comprises a flight controller, a storage battery assembly and a solar battery assembly, wherein the storage battery assembly comprises a storage battery, a first power supply cable and a storage battery power supply controller;
the storage battery assembly and the solar battery assembly are installed at the tail part of the spacecraft, the storage battery is electrically connected with tail load equipment installed at the tail part of the spacecraft through the first power supply cable, and the solar panel array group is electrically connected with the tail load equipment through the second power supply cable;
the storage battery power supply controller and the battery panel power supply controller are in communication connection with the flight controller respectively;
the flight controller is installed on the spacecraft and used for sending a first power supply instruction to the storage battery power supply controller, so that the storage battery power supply controller can start the storage battery to supply power to the tail load equipment according to the first power supply instruction;
the flight controller is further configured to send a second power supply instruction to the panel power supply controller, so that the panel power supply controller can enable the solar panel array group to supply power to the tail load device according to the second power supply instruction.
Optionally, the solar cell module further includes a cell panel charging controller and a charging cable, the cell panel charging controller and the flight controller are communicatively connected, and the solar cell panel array set is electrically connected to the storage battery through the charging cable;
the flight controller is used for sending a charging instruction to the panel charging controller, so that the panel charging controller can start the solar panel array group to charge the storage battery through the charging cable according to the charging instruction.
Optionally, the system further comprises a secondary battery assembly comprising a secondary battery, a third power supply cable and a secondary battery power supply controller;
the auxiliary battery assembly is mounted at the head of the spacecraft, the auxiliary battery is electrically connected with head load equipment mounted at the head of the spacecraft through the third power supply cable, and the auxiliary battery power supply controller is in communication connection with the flight controller;
the flight controller is used for sending a third power supply instruction to the secondary battery power supply controller, so that the secondary battery power supply controller can enable the secondary battery to supply power to the head load equipment according to the third power supply instruction.
Optionally, the secondary battery is a secondary battery or a lithium battery.
Optionally, a first separation distance between the tail load device and the storage battery is less than or equal to 20 meters, and a second separation distance between the head load device and the storage battery is greater than 20 meters.
Optionally, the solar panel array group comprises at least one solar panel array, and any two solar panel arrays of the at least one solar panel array are in two planes.
Optionally, each solar cell panel array in the solar cell panel array group is provided with a cell panel switch controller for controlling the solar cell panel array to be turned on and off, and the cell panel switch controller is in communication connection with the flight controller.
Optionally, each of the at least one solar panel array is foldable;
each solar panel array includes at least one solar panel, each of the at least one solar panel being foldable.
Optionally, each solar cell panel is provided with a panel unfolding controller for controlling the solar cell panel to unfold and fold, and the panel unfolding controller is in communication connection with the flight controller.
Optionally, each solar cell panel array in the solar cell panel array group is provided with a cell panel rotation controller for controlling the solar cell panel array to rotate, and the cell panel rotation controller is in communication connection with the flight controller.
The technical scheme provided by the application comprises but is not limited to the following beneficial effects:
the application provides a spacecraft power supply system, which comprises a flight controller, a storage battery assembly and a solar battery assembly, wherein the storage battery assembly comprises a storage battery, a first power supply cable and a storage battery power supply controller; the storage battery assembly and the solar battery assembly are installed at the tail part of the spacecraft, the storage battery is electrically connected with tail part load equipment installed at the tail part of the spacecraft through the first power supply cable, and the solar panel array group is electrically connected with the tail part load equipment through the second power supply cable; through set up battery pack and solar module simultaneously in spacecraft to establish the electric connection of battery and equipment load in the aircraft simultaneously, and the electric connection of equipment load in solar cell panel array group and the aircraft, can realize using battery and solar cell panel array group to supply power to the load equipment in the aircraft simultaneously.
The storage battery power supply controller and the battery panel power supply controller are in communication connection with the flight controller respectively; the flight controller is installed on the spacecraft and used for sending a first power supply instruction to the storage battery power supply controller, so that the storage battery power supply controller can start the storage battery to supply power to the tail load equipment according to the first power supply instruction; the flight controller is further configured to send a second power supply instruction to the panel power supply controller, so that the panel power supply controller can enable the solar panel array group to supply power to the tail load device according to the second power supply instruction; the storage battery power supply controller and the battery panel power supply controller are in communication connection with the flight controller respectively, so that the flight controller can send power supply instructions to the storage battery power supply controller and the battery panel power supply controller respectively, and the storage battery and the solar battery can be started by the storage battery power supply controller and the battery panel power supply controller to supply power to the spacecraft.
By adopting the system, the storage battery assembly and the solar battery assembly are arranged in the spacecraft, and the circuit channel for supplying power to the spacecraft is established for the storage battery and the solar battery panel array group, so that the storage battery and the solar battery can be started to supply power to the spacecraft under the control of the flight controller, and the waste of power resources in the spacecraft is avoided.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 shows a schematic structural diagram of a power supply system for a spacecraft, provided by the present invention;
fig. 2 shows a schematic structural diagram of another power supply system for a spacecraft, which is provided by the present invention;
fig. 3 shows a schematic structural diagram of another spacecraft power supply system provided by the present invention;
fig. 4 is a schematic structural diagram illustrating a solar panel array set provided by the present invention;
fig. 5 shows a schematic structural diagram of another spacecraft power supply system provided by the present invention;
fig. 6 shows a schematic structural diagram of another spacecraft power supply system provided by the present invention;
fig. 7 shows a schematic structural diagram of another power supply system for a spacecraft, provided by the present invention;
fig. 8 shows a schematic structural diagram of another spacecraft power supply system provided by the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships that are conventionally placed when the products of the present invention are used, or orientations or positional relationships that are conventionally understood by those skilled in the art, and are merely for convenience of description of the present invention and for simplicity of description, and do not indicate or imply that the equipment or components that are referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
For the convenience of understanding, the present application will be described in detail below with reference to the schematic structural diagram of a spacecraft power supply system according to the present invention shown in fig. 1.
Referring to fig. 1, fig. 1 shows a schematic structural diagram of a power supply system for a spacecraft, wherein the system includes a flight controller 1, a battery assembly 2 and a solar battery assembly 3, the battery assembly 2 includes a battery 21, a first power supply cable 22 and a battery power supply controller 23, and the solar battery assembly 3 includes a solar panel array group 31, a second power supply cable 32 and a panel power supply controller 33.
The storage battery assembly 2 and the solar battery assembly 3 are installed at the tail part of the spacecraft 4, the storage battery 21 is electrically connected with a tail load device 41 installed at the tail part of the spacecraft 4 through the first power supply cable 22, and the solar panel array group 31 is electrically connected with the tail load device 41 through the second power supply cable 32.
The storage battery power supply controller 23 and the battery panel power supply controller 33 are respectively in communication connection with the flight controller 1.
The flight controller 1 is installed on the spacecraft 4, and the flight controller 1 is configured to send a first power supply instruction to the battery power supply controller 23, so that the battery power supply controller 23 can enable the battery 21 to supply power to the tail load device 41 according to the first power supply instruction.
The flight controller 1 is further configured to send a second power supply instruction to the panel power supply controller 33, so that the panel power supply controller 33 can enable the solar panel array group 31 to supply power to the tail load device 41 according to the second power supply instruction.
Specifically, the load devices in the spacecraft can be divided into tail load devices and head load devices according to the positions of the load devices in the spacecraft, wherein the tail load devices are the load devices arranged at the tail of the spacecraft, and the head load devices are the load devices arranged at the head of the spacecraft; for the tail load equipment, a storage battery in the storage battery assembly is connected with the tail load equipment through a first power supply cable, and a solar cell panel array group in the solar cell assembly is connected with the tail load through a second power supply cable, so that the storage battery and the solar cell panel array group can be used for supplying power to the tail load equipment at the same time.
In a possible embodiment, referring to fig. 2, fig. 2 shows a schematic structural diagram of another spacecraft power supply system provided by the present invention, wherein the solar cell module 3 further includes a cell panel charging controller 34 and a charging cable 35, the cell panel charging controller 34 and the flight controller 1 establish a communication connection, and the solar cell panel array group 31 establishes an electrical connection with the storage battery 21 through the charging cable 35.
The flight controller 1 is configured to send a charging instruction to the panel charging controller 34, so that the panel charging controller 34 can enable the solar panel array group 31 to charge the storage battery 21 through the charging cable 35 according to the charging instruction.
Specifically, the electric quantity of battery storage in the use can be consumed gradually, connects battery and solar cell panel array group through charging cable, can realize when solar cell panel array group turns into the electric energy with light energy, charges the battery through panel charge controller control solar cell panel array group.
In a possible embodiment, referring to fig. 3, fig. 3 shows a schematic structural diagram of another power supply system for a spacecraft, which is provided by the present invention, and the system further includes a secondary battery assembly 5, where the secondary battery assembly 5 includes a secondary battery 51, a third power supply cable 52 and a secondary battery power supply controller 53.
The secondary battery pack 5 is mounted on the head of the spacecraft 4, the secondary battery 51 is electrically connected with the head load device 42 mounted on the head of the spacecraft 4 through the third power supply cable 52, and the secondary battery power supply controller 53 is in communication connection with the flight controller 1.
The flight controller 1 is configured to send a third power supply instruction to the secondary battery power supply controller 53, so that the secondary battery power supply controller 53 can enable the secondary battery 51 to supply power to the head load device 42 according to the third power supply instruction.
Specifically, because the distance between the head load device and the tail load device of the spacecraft is usually large, if only the storage battery assembly and the solar assembly arranged at the tail of the spacecraft are used for supplying power to the head load of the spacecraft, the problem that the voltage drop caused by long-distance power supply is too high or the cable is too heavy and too thick can occur.
In order to avoid the problems, an auxiliary battery assembly is arranged at the head of the spacecraft, the auxiliary battery assembly comprises an auxiliary battery, a third power supply cable and an auxiliary battery power supply controller, the auxiliary battery is connected with the head load equipment through the third power supply cable, and the auxiliary battery power supply controller is used for controlling the auxiliary battery to supply power to the head load equipment through the third power supply cable so as to reduce the distance for supplying power to the head load equipment of the spacecraft.
In one possible embodiment, the secondary battery is a secondary battery or a lithium battery.
Specifically, the type of the secondary battery may be a storage battery or a lithium battery, and may be specifically set according to actual requirements, which is not specifically limited herein.
In one possible embodiment, the first distance between the rear load device and the battery is less than or equal to 20 m, and the second distance between the head load device and the battery is greater than 20 m.
Specifically, the tail load equipment is load equipment which is separated from a storage battery arranged at the tail part by a distance of less than or equal to 20 meters in the aircraft, and the partial load equipment is powered by the storage battery and the solar panel array group; the head load is a load in the aircraft which is spaced from the battery by more than 20 meters, this part of the load being supplied by the secondary battery.
In a possible embodiment, referring to fig. 4, fig. 4 shows a schematic structural diagram of a solar panel array group provided by the present invention, wherein the solar panel array group 31 includes at least one solar panel array 311, and any two solar panel arrays 311 in the at least one solar panel array 311 are located in two planes.
Specifically, the solar cell panel array group is composed of at least one solar cell panel array, wherein every two solar cell panel arrays are located on two planes, that is, every two solar cell panel arrays are not located on the same plane, the specific arrangement mode includes setting according to actual requirements, and no specific limitation is made herein.
In a possible embodiment, referring to fig. 5, fig. 5 shows a schematic structural diagram of another power supply system for a spacecraft, provided by the present invention, wherein each solar panel array 311 in the solar panel array group 31 is provided with a panel switch controller 312 for controlling the solar panel array to be turned on and off, and the panel switch controller 312 is in communication connection with the flight controller 1.
Specifically, each solar cell panel array is provided with a cell panel switch controller for controlling the solar cell panel array to be started and closed, and the number of the solar cell panel arrays is the same as that of the cell panel switch controllers; each solar panel switch controller is in communication connection with the flight controller, and each solar panel switch controller can receive a switch control instruction sent by the flight controller and then can start or close the corresponding solar panel array according to the switch control instruction.
In one possible embodiment, each solar panel array 311 of the at least one solar panel array 311 is foldable.
Specifically, the solar cell panel array in the solar cell panel array group can be folded, and the space occupied by the solar cell panel array can be reduced after the solar cell panel array group is folded.
Referring to fig. 6, fig. 6 shows a schematic structural diagram of another power supply system for a spacecraft, according to the present invention, wherein each solar panel array 311 includes at least one solar panel 3111, and each solar panel 3111 of the at least one solar panel 3111 is foldable.
Specifically, the solar cell panel in the solar cell panel array can also be folded, and the space occupied by the solar cell panel can be reduced after the solar cell panel is folded.
In a possible embodiment, referring to fig. 7, fig. 7 shows a schematic structural diagram of another power supply system for a spacecraft, according to the present invention, wherein each solar panel 3111 is provided with a panel unfolding controller 3112 for controlling the solar panel 3111 to unfold and fold, and the panel unfolding controller 3112 is in communication with the flight controller 1.
Specifically, each solar cell panel is provided with a cell panel unfolding controller for controlling the solar cell panel to unfold and fold, and the number of the solar cell panels is the same as that of the cell panel unfolding controllers; each battery panel unfolding controller is in communication connection with the flight controller, and each battery panel unfolding controller can receive a control instruction (an unfolding instruction and a folding instruction) sent by the flight controller, can control the corresponding solar battery panel to unfold according to the unfolding control instruction, or can control the corresponding solar battery panel to fold according to the folding instruction.
In a possible embodiment, referring to fig. 8, fig. 8 shows a schematic structural diagram of another power supply system for a spacecraft, where each solar cell panel array 311 in the solar cell panel array group 31 is provided with a cell panel rotation controller 313 for controlling the solar cell panel array 311 to rotate, and the cell panel rotation controller 313 establishes a communication connection with the flight controller 1.
Specifically, each solar cell panel array is provided with a cell panel rotation controller for controlling the solar cell panel array to rotate, and the number of the solar cell panel arrays is the same as that of the cell panel rotation controllers; and each battery panel rotation controller is in communication connection with the flight controller, can receive a rotation control instruction sent by the flight controller, and then controls the corresponding solar battery panel array to rotate according to the rotation control instruction.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A spacecraft power supply system is characterized by comprising a flight controller, a storage battery assembly and a solar battery assembly, wherein the storage battery assembly comprises a storage battery, a first power supply cable and a storage battery power supply controller, and the solar battery assembly comprises a solar battery panel array group, a second power supply cable and a battery panel power supply controller;
the storage battery assembly and the solar battery assembly are installed at the tail part of the spacecraft, the storage battery is electrically connected with tail load equipment installed at the tail part of the spacecraft through the first power supply cable, and the solar panel array group is electrically connected with the tail load equipment through the second power supply cable;
the storage battery power supply controller and the battery panel power supply controller are in communication connection with the flight controller respectively;
the flight controller is installed on the spacecraft and used for sending a first power supply instruction to the storage battery power supply controller so that the storage battery power supply controller can start the storage battery to supply power to the tail load equipment according to the first power supply instruction;
the flight controller is further used for sending a second power supply instruction to the panel power supply controller, so that the panel power supply controller can start the solar panel array group to supply power to the tail load device according to the second power supply instruction.
2. The system of claim 1, wherein the solar module further comprises a panel charge controller and a charging cable, the panel charge controller and the flight controller being communicatively coupled, the solar panel array set being electrically coupled to the battery via the charging cable;
the flight controller is used for sending a charging instruction to the panel charging controller, so that the panel charging controller can start the solar panel array group to charge the storage battery through the charging cable according to the charging instruction.
3. The system of claim 1, further comprising a secondary battery assembly comprising a secondary battery, a third power supply cable, and a secondary battery power supply controller;
the auxiliary battery assembly is mounted at the head of the spacecraft, the auxiliary battery is electrically connected with head load equipment mounted at the head of the spacecraft through the third power supply cable, and the auxiliary battery power supply controller is in communication connection with the flight controller;
the flight controller is used for sending a third power supply instruction to the secondary battery power supply controller, so that the secondary battery power supply controller can enable the secondary battery to supply power to the head load equipment according to the third power supply instruction.
4. The system of claim 3, wherein the secondary battery is a secondary battery or a lithium battery.
5. The system of claim 3, wherein a first separation distance between the rear load device and the battery is 20 meters or less, and a second separation distance between the head load device and the battery is greater than 20 meters.
6. The system of claim 1, wherein the set of solar panel arrays comprises at least one solar panel array, any two solar panel arrays of the at least one solar panel array lying in two planes.
7. The system of claim 6, wherein each solar panel array in the set of solar panel arrays is provided with a panel switch controller for controlling the solar panel array to be turned on and off, the panel switch controller being in communication with the flight controller.
8. The system of claim 6, wherein each of the at least one solar panel array is foldable;
each solar panel array includes at least one solar panel, each of the at least one solar panel being foldable.
9. The system of claim 8, wherein each solar panel is provided with a panel deployment controller for controlling the deployment and folding of the solar panel, the panel deployment controller being in communication with the flight controller.
10. The system of claim 6, wherein each solar panel array in the solar panel array group is provided with a panel rotation controller for controlling the solar panel array to rotate, and the panel rotation controller is in communication with the flight controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221861530.1U CN217642846U (en) | 2022-07-18 | 2022-07-18 | Power supply system of spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221861530.1U CN217642846U (en) | 2022-07-18 | 2022-07-18 | Power supply system of spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217642846U true CN217642846U (en) | 2022-10-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221861530.1U Active CN217642846U (en) | 2022-07-18 | 2022-07-18 | Power supply system of spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217642846U (en) |
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2022
- 2022-07-18 CN CN202221861530.1U patent/CN217642846U/en active Active
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Address after: 100176 room 12b03, 12b floor, building 40, yard 1, Desheng North Street, Beijing Economic and Technological Development Zone, Beijing Patentee after: Oriental space technology (Beijing) Co.,Ltd. Country or region after: Zhong Guo Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Country or region after: China Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Address before: 100176 room 12b03, 12b floor, building 40, yard 1, Desheng North Street, Beijing Economic and Technological Development Zone, Beijing Patentee before: Oriental space technology (Beijing) Co.,Ltd. Country or region before: Zhong Guo Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Country or region before: China Patentee before: Oriental space (Xi'an) Aerospace Technology Co.,Ltd. |
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Effective date of registration: 20240320 Address after: Room 12B03, Floor 12B, Building 40, No.1 Courtyard, Desheng North Street, Beijing Economic and Technological Development Zone, Daxing District, Beijing, 100000 Patentee after: Oriental space technology (Beijing) Co.,Ltd. Country or region after: Zhong Guo Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Country or region after: China Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee after: Orient Space (Hainan) Technology Co.,Ltd. Address before: 100176 room 12b03, 12b floor, building 40, yard 1, Desheng North Street, Beijing Economic and Technological Development Zone, Beijing Patentee before: Oriental space technology (Beijing) Co.,Ltd. Country or region before: Zhong Guo Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Country or region before: China Patentee before: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. |