A scalable space solar panel structure

Abstract

The present invention discloses an expandable space solar panel structure, including a hollow truss structure, a foldable solar panel sub-array, a connection joint, a push track device and a control circuit, wherein the hollow truss structure is composed of a cylindrical surface; the connection joint is at both ends of the hollow truss structure; the foldable solar panel sub-array is on the left and right sides of the hollow truss structure, the electromagnetic force push track is on the upper side of the hollow truss structure; the armature is on the lower side of the hollow truss structure, and the electromagnetism module and the control circuit are inside the hollow truss structure. The present invention can increase the number of solar panels as the power supply of the space solar power station increases, improves the flexibility of the space solar panel structure, and has the advantages of stability, safety and convenience.

Description

Technical Field

[0001] The invention relates to the technical field of space solar power stations and provides an expandable space solar panel structure. Background Art

[0002] With the rapid development of society, the amount of electricity we need will increase. However, the energy sources such as coal, oil, and natural gas we need for power generation are limited. In addition, burning these energy sources is very harmful to the environment. Therefore, it is inevitable to eliminate the old power generation methods and develop clean new energy power stations in the future. The sunlight in space will not be attenuated by the atmosphere, nor will it be affected by seasonal and day-night changes. The solar radiation intensity is stable, about 1353 W / m 2 , which is more than 5 times the average solar radiation intensity on the ground. Therefore, people have discovered through exploration that building a space solar power station in space is one of the ideal new ways to generate electricity.

[0003] Space solar power station (SSPS) has attracted more and more domestic and foreign experts to study with its unique advantages. Dozens of space solar power station concepts have been proposed internationally. The United States, Japan, the European Union and other countries have conducted research for many years and have proposed space solar power station solutions such as the 1979 SPS benchmark system, integrated symmetrical concentrating system, distributed rope-tethered solar power station and solar sail tower. Domestically, concepts such as multi-rotation joint space solar power station and OMEGA space solar power station have also been proposed.

[0004] Collecting solar energy is the first step in a space solar power station, and the space solar panel structure is an important part of a space solar power station. Suppose you want to build a space solar power station with a power supply of 1GW. In this case, consider that the efficiency of the silicon rectenna is 80%. Therefore, 1.25 gigawatts of microwave power is required at the ground rectenna location to generate so much electrical output. The ground 1.25 GW of microwave power is emitted by the space satellite transmitting antenna. Assuming the beam efficiency is 87%, the microwave power required for the transmitting antenna is 1.44 gigawatts. On the space satellite, there is a DC microwave conversion device that can convert DC energy into microwaves. Therefore, the DC power required for a DC to microwave conversion efficiency of 70% is 2GW. Photovoltaic power generation is used to convert solar energy into DC energy in space. Photovoltaic power generation has a 20% solar energy to DC power conversion efficiency. Therefore, 10 gigawatts of solar energy is required at the space end to provide 1 gigawatt of available electrical energy on Earth. The size of the photovoltaic array required to produce a 2 gigawatt DC power output is about 10 square kilometers (2 kilometers × 5 kilometers). Such a large photovoltaic array cannot be launched into space at one time and must be launched in batches. However, the solar panel structure of the above-mentioned space solar power station is not flexible enough and does not meet the actual requirements, and the number of solar panels cannot be increased as the power supply of the space solar power station increases. Summary of the invention

[0005] The purpose of the present invention is to overcome the shortcomings of the solar panel structure in the existing space solar power station scheme, such as insufficient flexibility, failure to meet actual requirements, and inability to increase the number of solar panels as the power supply of the space solar power station increases, and to provide a space solar panel structure with good flexibility that meets actual requirements.

[0006] The technical solution of the present invention is: the present invention discloses an expandable space solar panel structure, including a hollow truss structure, a foldable solar panel sub-array, a connection joint, a push track device and a control circuit, and is characterized in that the hollow truss structure is composed of two inner and outer cylindrical surfaces. The outer cylindrical surface is an insulating outer cylinder made of insulating material, connected to the connection joint and the control circuit, and the inner cylindrical surface is a conductive inner cylinder made of conductive material, connected to the foldable solar panel sub-array to output electrical energy outward; the connection joint is at both ends of the hollow truss structure, and is composed of a connection joint 1 and a connection joint 2. The connection joint 1 has a rotating joint 1, a rotating joint 2 and a lead wire connected to the motor 1, the motor 2 and the motor 3 respectively, and the connection joint 2 has a circular hole. The connection joint 1 and the connection joint 2 are connected by a connecting fixing structure; an infrared corrector is installed on the lead wire and the surface with the circular hole to correct the lead wire so that the lead wire just enters the circular hole; the push track device is composed of an electromagnetic force push track, an armature, and an electromagnetism module. The present invention improves the flexibility of the space solar cell panel structure, can increase the number of solar cell panels as the power supply of the space solar power station increases, and has good economy and flexibility.

[0007] The foldable solar panel sub-arrays are on the left and right sides of the hollow truss structure. The solar cells of the solar panel sub-arrays are triple-junction gallium arsenide cells, and their electrical energy is output to the outside through the conductive rotating structure and the conductive inner cylinder.

[0008] The connection fixing structure is composed of a connection fixing structure 1 and a connection fixing structure 2, which are used to fix two connection joints to ensure that the structures of the two connected space solar cell panel units are stable and reliable.

[0009] The electromagnetic force pushes the track on the upper side of the hollow truss structure, and the track is two parallel aluminum alloy grooves that cooperate with the armature to transport the space solar panel unit.

[0010] The armature is located at the lower side of the hollow truss structure and is made of aluminum alloy. Its shape is consistent with the electromagnetic force-propelled track, and cooperates with the electromagnetic force-propelled track to transport the expandable space solar panel structural unit.

[0011] The electromagnetism module is located at both ends of the inner side of the hollow truss structure, and is a single-phase winding that generates a constant magnetic field to provide a magnetic field for the electromagnetic force to push the track, and requires that the magnetic fields on both sides have opposite directions.

[0012] The control circuit is respectively connected to the connecting joint and the pushing track device to control the operation thereof.

[0013] The insulating outer cylinder and the conductive inner cylinder are connected by a conductive rotating structure; the inner wall of the insulating outer cylinder and the outer wall of the conductive inner cylinder are both provided with a plurality of grooves surrounding the circumference thereof, the grooves provided on the inner wall of the insulating outer cylinder correspond one to one with the grooves provided on the outer wall of the conductive inner cylinder, and a conductive rotating structure is provided between every two corresponding grooves.

[0014] Beneficial effects of the present invention:

[0015] The hollow truss structure of this scheme is composed of an outer insulating outer cylinder and an inner conductive inner cylinder. The two cylindrical surfaces are connected by a rolling ring. When necessary, the angle of the solar panel can be adjusted by rotating the insulating outer cylinder to ensure the flexibility of the solar panel. The connecting joint is responsible for connecting and splitting the two panel units, and the number of spatial solar panel structural units can be flexibly adjusted. The push track device pushes the panel unit through electromagnetic force, and the magnitude and direction of the driving force are adjusted by controlling the current magnitude and magnetic field direction. The present invention has the advantages of flexibility, economy, safety and structural stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is the overall structure diagram of an expandable space solar panel.

[0017] Figure 2 This is a structural diagram of a space solar panel unit.

[0018] Figure 3 This is a structural diagram of a hollow truss.

[0019] Figure 4 This is a structural diagram of the connecting joint.

[0020] Figure 5 Diagram of the orbital structure driven by electromagnetic force.

[0021] Figure 6 This is the armature structure diagram.

[0022] Figure 7 This is the schematic diagram of the electromagnetism module.

[0023] Figure 8 This is the schematic diagram of the electromagnetic force driving principle.

[0024] Fig. 9 This is the structural diagram of the infrared corrector.

[0025] Description of reference numerals:

[0026] (1) Hollow truss structure; (2) Foldable solar panel array; (3) Connection joint; (4) Track driving device; (101) Insulating outer cylinder; (102) Conductive inner cylinder; (103) Conductive rotating structure; (104) Groove; (105) Motor 4; (301) Connection joint 1; (302) Connection joint 2; (303) Motor 1, (304) Motor 2; (305) Motor 3; (306) Circular hole; (307) Rotating joint 1; (308) Rotating joint 2; (309) Lead wire; (310) Infrared corrector; (3101) Infrared transmitter; (3102) Sensor receiving surface; (401) Electromagnetic force driving track; (402) Armature; (403) Electromagnetic module; (404) Motor 5. DETAILED DESCRIPTION

[0027] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0028] like Figure 1 As shown, the present invention provides an expandable space solar panel structure, which can increase the number of solar panels as the capacity of the space solar power station increases. Figure 2 This is a structural diagram of a space solar panel unit, including a hollow truss structure, a foldable solar panel sub-array, connecting joints, a propulsion track device, and a control circuit. Figure 3 This is a diagram of a hollow truss structure. The insulating outer cylinder of the hollow truss structure is fixedly connected to the electromagnetic force driving track, the armature, the rotating joint and the foldable solar cell panel sub-array respectively. Figure 4 To connect the joint structure diagram, it is mainly responsible for connecting and fixing the two space solar panel units. The electric energy from the foldable solar panel sub-array is output to the outside through the conductive inner tube of the hollow truss structure. Figure 5 , Figure 6 and Figure 7 In order to promote the track structure diagram, the present invention mainly uses electromagnetic force to promote the space solar panel unit to be connected. Fig. 9 This is the structure diagram of the infrared corrector, which ensures the circuit connection of the two space solar panel units.

[0029] The hollow truss structure is composed of an insulating outer cylinder, a conductive inner cylinder, a conductive rotating structure and a motor 4. The control circuit can complete the angle adjustment of the foldable solar panel subarray by controlling the motor. The insulating outer cylinder is the outer side of the hollow truss structure. Its main function is to protect the internal structure and connect various structural parts (conductive parts, control circuits and motors are inside; the outside is connected to the push track device and the foldable solar panel subarray). The function of the conductive inner cylinder and the conductive rotating structure is to conduct electricity and ensure stable and safe power supply when the external foldable solar panel subarray and the insulating outer cylinder are rotated and adjusted. Motor 4 provides power for the foldable solar panel subarray and the insulating outer cylinder to rotate and adjust.

[0030] The push rail is installed on the upper side of the hollow truss structure. The rail is two parallel aluminum alloy grooves, which cooperate with the armature and the electromagnetism module to transport the space solar panel unit. After the armature of the space solar panel unit is aligned with the electromagnetic force push rail, the control circuit supplies power to the electromagnetic force push rail and the electromagnetism module. When the electromagnetic force push rail and the electromagnetism module are powered on, the armature part can be affected by the electromagnetic force. . Electromagnetic force The size is:

[0031]

[0032] Where: is the magnetic field strength, is the current magnitude, is the effective length of the armature. , , Controlling electromagnetic force .

[0033] The electromagnetism module of this scheme is located at both ends of the inner side of the hollow truss structure. It is a single-phase winding. A DC current is passed through it to generate a constant magnetic field, which provides a magnetic field for the electromagnetic force to push the track. The calculation formula for the magnetic field strength is:

[0034]

[0035] Where: H is the magnetic field strength, in units of A / m ; N is the number of turns of the excitation coil; I is the DC current, the unit is A; l is the effective magnetic path length of the test sample, in units of m ; and it is required that the magnetic fields on both sides have opposite directions, that is, acceleration at the beginning and deceleration at the end, to ensure that the speed and impulse of the space solar panel unit are small when it reaches the end.

[0036] The connection joints are at both ends of the hollow truss structure and are composed of connection joints 1 and 2. Connection joint 1 has rotation joint 1, rotation joint 2 and lead wires connected to motor 1, motor 2 and motor 3 respectively, and connection joint 2 has a round hole, such as Figure 4 In addition, there are fixing devices to ensure the safety of the two connecting joints and ensure a firm connection.

[0037] The connection fixing devices are respectively located on the connection joint 1 and the connection joint 2. Figure 4 As shown, the connection and fixing part in the connection joint 1 is a thicker cylinder with a large circular hole in the middle and several small circular holes around the large circular hole. There are several cylinders on the connection joint 2 corresponding to the circular holes of the connection joint 1. The large cylinder in the middle is connected to the lead wire through the large circular hole and does not play a fixed connection role. The small cylinders around the large cylinder in the middle are composed of cylinders and cones and cooperate with the small circular holes to fix the two connection joints.

[0038] The infrared corrector is composed of an infrared emitter and a receiving surface, which provides a correction angle for the control circuit. The receiving surface surrounds the circular hole and is composed of multiple light sensors. When the lead wire does not correspond to the circular hole, the infrared ray will shine on the receiving surface, and the sensor on the receiving surface will generate voltage. At this time, we can know the position of the generated voltage, and compare it with the position of the circular hole to get the angle that the lead wire needs to be adjusted. When the center of the circle is the coordinate origin (0,0), the coordinates of the circular hole are set to ( a , b ), assume the coordinates of the sensor to be ( x , y ). Assume that the light is irradiated on ( x 1, y 1 ), the lead wire needs to be adjusted.

[0039] The control circuit is connected to the multiple motors of the connection joint, the track and electromagnetism module of the track device, and the control motor of the hollow truss structure. When the armature of the space solar panel unit enters the electromagnetic force to push the track, the magnitude and direction of the current added to the electromagnetic track and the electromagnetism module are controlled according to the kinetic energy required when the corresponding fixing device of the connection joint 1 is connected with the corresponding fixing device of the connection joint 2. It is connected to the multiple motors in the connection joint and truss result to control the angle of rotation, and is connected to the infrared light sensor to calculate the distance that the lead wire needs to be adjusted and control the motor to adjust it.

[0040] The specific operation process of each part is described below.

[0041] A satellite carrying a space solar panel is launched from the ground and docked with a space solar power station. At this time, the space solar panel unit is adjusted on the push track. After the armature of the space solar panel unit is aligned with the electromagnetic force push track, the staff supplies power to the electromagnetic force push track and the electromagnetism module through the control circuit. When the electromagnetic force push track and the electromagnetism module are powered on, the armature part can be affected by the electromagnetic force. When the armature slides in the magnetic field, the space solar panel unit slides forward at an accelerated speed, and the armature slides past the electromagnetism module 1 and then moves forward at a constant speed. After sliding for a period of time, the armature enters the electromagnetism module 2. Since the magnetic field direction of the electromagnetism module 2 is opposite to that of the electromagnetism module 1, the armature slides forward at a decelerated speed. When the connection joint 1 of the space solar panel unit 1 and the connection joint 2 of the space solar unit 2 are just connected through the connection fixture, the armature speed is zero. At this time, the control circuit shuts off the power supply to the electromagnetic force to push the track and the electromagnetism module.

[0042] When the space solar panel structure unit 2 slides over, the control circuit controls the motor 1 to rotate 180° counterclockwise, and then controls the motor 2 to rotate 180°. When the connection joint 1 and the connection joint 2 are connected and fixed, the motor 5 is controlled to rotate the armature to separate from the electromagnetic force to push the track, and then the motor 2 is controlled to rotate 180° in the opposite direction. At this time, the two space solar panel structure units are on the same line, and then the infrared calibrators on the two connection surfaces work to determine whether the lead wire of the connection joint 1 and the circular hole on the connection joint 2 are on the same horizontal plane. If not, the infrared calibrator calculates the angle that needs to be corrected and feeds it back to the control device, and the control device commands the motor 4 to complete the correction work. Finally, the motor 3 is controlled to insert the lead wire into the circular hole on the connection joint 2. At this time, the connection of the two solar panel units is completed. Finally, the control circuit controls the motor 1 to rotate 180° clockwise, and the push tracks of the two space solar panel units are docked with each other. The number of solar panels can be expanded according to the above steps.

Claims

1. An expandable space solar panel structure, characterized in that: The invention comprises a hollow truss structure (1), a foldable solar panel array (2), a connection joint (3), a propulsion track device (4) and a control circuit (5); the hollow truss structure (1) is composed of two inner and outer cylinders, a conductive rotating structure (103) and a motor 4 (105); the outer cylinder is an insulating outer cylinder (101) made of insulating material, connected to the connection joint (3) and the control circuit (5), and the inner cylinder is a conductive inner cylinder (102) made of conductive material; the connection joint (3) is connected to the hollow truss structure ( 1) two ends, consisting of a connecting joint 1 (301) and a connecting joint 2 (302); the connecting joint 1 (301) and the connecting joint 2 (302) respectively have a connecting fixing structure 1 (311) and a connecting fixing structure 2 (312) for fixing the two connecting joints; the rotating joint 1 (307), the rotating joint 2 (308) and the lead wire (309) of the connecting joint 1 (301) are respectively connected to the motor 1 (303), the motor 2 (304) and the motor 3 (305), and the connecting joint 2 (302) has a circular The lead wire (309) and the surface with the circular hole (306) are provided with an infrared corrector (310) for correcting the lead wire (309) so that the lead wire (309) just enters the circular hole (306); the pushing track device (4) is composed of an electromagnetic force pushing track (401), an armature (402), and an electromagnetism module (403); the electromagnetic force pushing track (401) is on the upper side of the hollow truss structure (1), and the track is two parallel aluminum alloy grooves, which cooperate with the armature (402) to transport and expand The space solar panel structural unit is a space solar panel structural unit; the armature (402) is located at the lower side of the hollow truss structure (1), connected to the motor 5 (404), and is made of aluminum alloy. Its shape is consistent with the electromagnetic force driving track (401), and cooperates with the electromagnetic force driving track (401) to transport the expandable space solar panel structural unit; the electromagnetism module (403) is located at both ends of the inner side of the hollow truss structure (1), is a single-phase winding, generates a constant magnetic field, and provides a magnetic field for the electromagnetic force driving track (401), and the magnetic fields on both sides are in opposite directions.

2. The expandable space solar panel structure according to claim 1, characterized in that: The foldable solar cell panel sub-arrays (2) are located on the left and right sides of the hollow truss structure (1), and the solar cells of the solar cell panel sub-arrays are triple-junction gallium arsenide cells.

3. The expandable space solar panel structure according to claim 1, characterized in that: The infrared corrector (310) is composed of an infrared emitter (3101) and a sensor receiving surface (3102), and provides correction value for the control circuit.

4. The expandable space solar panel structure according to claim 1, characterized in that: The control circuit (5) is respectively connected to the connecting joint (3) and the pushing track device (4).

5. The expandable space solar panel structure according to claim 1, characterized in that: The insulating outer cylinder (101) and the conductive inner cylinder (102) are connected by a conductive rotating structure (103); the inner wall of the insulating outer cylinder (101) and the outer wall of the conductive inner cylinder (102) are both provided with a plurality of grooves (104) surrounding the circumference thereof; the grooves (104) provided on the inner wall of the insulating outer cylinder (101) correspond to the grooves (104) provided on the outer wall of the conductive inner cylinder (102) one by one, and a conductive rotating structure (103) is provided between every two corresponding grooves (104).

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