A ground-based satellite solar wing deployment time testing system

Abstract

The present invention discloses a ground-based satellite solar wing deployment time test system, which belongs to the field of satellite manufacturing technology, and aims to solve the problem of large errors and uncertainties in the measurement results of the prior art. A ground-based satellite solar wing deployment time test system of the present invention comprises a mobile phone terminal and a deployment test terminal and an in-place test terminal detachably arranged on the solar wing; the deployment test terminal and the in-place test terminal transmit signals to the mobile phone terminal through their own Bluetooth communication modules respectively; the deployment test terminal and the in-place test terminal have the same structure, at least including a touch switch and a Bluetooth communication module, obtaining a deployment start signal through the touch switch of the deployment test terminal and transmitting it to the mobile phone terminal through the Bluetooth communication module to start timing, and obtaining a deployment in-place signal through the touch switch of the in-place test terminal and transmitting it to the mobile phone terminal through the Bluetooth communication module to end timing.

Description

Technical Field

[0001] The invention belongs to the technical field of satellite manufacturing, and in particular relates to a ground-based satellite solar wing deployment time testing system. Background Art

[0002] As the main energy source of satellites, ensuring the normal operation and deployment of satellite solar panels in orbit is the primary design requirement for achieving satellite functions and achieving the life of the satellite in orbit. Accurately measuring the deployment time of solar panels plays a vital role in verifying the deployment capability of the deployment mechanism, analyzing and predicting the dynamic behavior and attitude control of the entire satellite.

[0003] By simulating the solar wing deployment process through dynamic simulation software, the deployment time of the solar wing can be obtained. However, since the environment settings in the simulation software cannot match the actual solar wing deployment environment well, there is a large error. At present, the measurement of the deployment time of the solar wing in actual ground tests uses manual timing. There are no strict marks for the start and completion of deployment, and human judgment is required, resulting in large human errors and uncertainties in the measurement results. Even if the same solar wing is deployed in the same environment, there may be a large difference in the deployment time measured twice, which is very unfavorable for the confirmation of the state consistency of mass-produced satellites. Summary of the invention

[0004] The purpose of the present invention is to propose a ground-based satellite solar wing deployment time test system to solve the problem of large errors and uncertainties in the measurement results of the prior art, which is not conducive to the status consistency confirmation of mass-produced satellites.

[0005] To achieve the above-mentioned purpose, a ground-based satellite solar wing deployment time test system of the present invention comprises a mobile phone terminal and a deployment test terminal and an in-place test terminal detachably arranged on the solar wing; the deployment test terminal and the in-place test terminal respectively transmit signals to the mobile phone terminal through their own Bluetooth communication modules;

[0006] The expansion test terminal and the in-place test terminal have the same structure, and at least include a touch switch and a Bluetooth communication module. An expansion start signal is obtained through the touch switch of the expansion test terminal and transmitted to the mobile phone terminal through the Bluetooth communication module to start timing. An expansion in-place signal is obtained through the touch switch of the in-place test terminal and transmitted to the mobile phone terminal through the Bluetooth communication module to end timing.

[0007] The deployment test terminal comprises:

[0008] An elastic clamp detachably connected to the solar wing;

[0009] An electric control unit fixed on the elastic clamp, the electric control unit at least comprising a PCB board;

[0010] A touch switch, wherein the touch switch is connected to the PCB board via a wire;

[0011] And a universal shaping tube, which is a hollow structure, and the wire connected between the touch switch and the PCB board is located in the universal shaping tube, and the position and direction of the touch switch relative to the elastic clamp are adjusted through the universal shaping tube.

[0012] The elastic clamp comprises:

[0013] A fixing clip, the fixing clip is a T-shaped structure, one plate is used as a bottom plate, and one end surface of the other plate is in contact with the midline of one side surface of the bottom plate and is perpendicular to the mounting plate, and the electronic control unit is mounted on the mounting plate;

[0014] A movable clip hinged to the other end of the mounting plate of the fixed clip via a rotating shaft;

[0015] A torsion spring disposed on the rotating shaft;

[0016] And a swivel clip is arranged on a side surface of the movable clip opposite to the fixed clip, the swivel clip and the movable clip are hinged by a plug screw, so that the bottom plate of the fixed clip is kept parallel to the swivel clip.

[0017] The elastic clamp also includes a large silicone rubber pad and a small silicone rubber pad. The large silicone rubber pad is arranged on the side of the bottom plate of the fixed clip opposite to the rotating clip, and the small silicone rubber pad is arranged on the side of the rotating clip opposite to the bottom plate of the fixed clip.

[0018] The electronic control unit further comprises:

[0019] A PCB mounting seat mounted on the mounting plate of the fixing clip of the elastic clamp, wherein the PCB is mounted on the PCB mounting seat;

[0020] and a PCB board installation cover which is detachably connected to the PCB board installation seat to package the PCB board.

[0021] The PCB board includes a Bluetooth communication module, a power module, a data processing chip and an I / O interface; the data processing chip is electrically connected to the Bluetooth communication module and the I / O interface respectively, and the power module is connected to the Bluetooth communication module and the data processing chip respectively for power supply; the micro switch of the touch switch is connected to the I / O interface of the PCB board through a wire; the data processing chip receives the signal transmitted by the micro switch through the I / O interface, and transmits it to the mobile phone terminal through the Bluetooth communication module.

[0022] The power supply module is a 5V power supply module.

[0023] The touch switch comprises a micro switch fixing seat and a micro switch fixed on the micro switch fixing seat; the end of the universal molding tube is connected to the side wall of the micro switch fixing seat through a molding tube installation interface.

[0024] The beneficial effects of the present invention are as follows: a ground-based satellite solar wing deployment time test system of the present invention obtains the initial deployment moment of the solar wing through the micro switch of the deployment test terminal, and obtains the deployment position moment through the micro switch of the position test terminal, and has clear deployment start and deployment position marks, so that the solar wing deployment time can be accurately measured, and errors caused by human factors can be avoided, so that the accuracy of measuring the solar wing deployment time can be effectively improved; it also has the advantages of simple and fast installation and disassembly, small error in test results, etc., and can adapt to solar wings of different sizes, different installation forms and different deployment angles, so as to adapt to different models of satellite solar wings. The test operation of this patent is simple and fast, no auxiliary equipment is required, and it is suitable for mass production satellite testing; the present invention can realize fast, convenient and accurate measurement of solar wing deployment time in the ground test stage; at the same time, it has strong versatility; in addition, the system of the present invention adopts Bluetooth wireless communication, and can also be used in a vacuum environment, and can be used for solar wing deployment testing in a vacuum chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of a deployment test terminal in a ground-based satellite solar wing deployment time test system of the present invention;

[0026] Figure 2 It is a partial cross-sectional view of an upward angle of view of a deployment test terminal in a ground-based satellite solar wing deployment time test system of the present invention;

[0027] Figure 3 It is a schematic diagram of an in-place test terminal in a ground-based satellite solar wing deployment time test system of the present invention;

[0028] Figure 4 It is a partial cross-sectional view of an upward angle of view of an in-place test terminal in a ground-based satellite solar wing deployment time test system of the present invention;

[0029] Figure 5 It is a schematic diagram of the whole satellite state before the solar wings are folded in a ground-based satellite solar wing deployment time test system of the present invention;

[0030] Figure 6 for Figure 5 A partial enlarged view of

[0031] Figure 7 It is a schematic diagram of the whole satellite state before the solar wing is deployed in a ground-based satellite solar wing deployment time test system of the present invention;

[0032] Figure 8 for Figure 7 A partial enlarged view of

[0033] Fig. 9 It is a schematic diagram of the state of the whole satellite when the solar wing is fully deployed in a ground-based satellite solar wing deployment time test system of the present invention;

[0034] Fig.10 for Fig. 9 A partial enlarged view of

[0035] Wherein: 1. Expand the test terminal, 101. Elastic clamp, 102. Fixed clip, 103. Movable clip, 104. Rotating clip, 105. Rotating shaft, 106. Torsion spring, 107. Plug screw, 108. Large silicone rubber pad, 109. Small silicone rubber pad, 110. PCB board mounting seat, 111. PCB board, 112. PCB board mounting cover, 113. Touch switch, 114. Micro switch fixing seat, 115. Micro switch, 116. Universal molding tube, 117. Molding tube installation interface, 2. In place test terminal, 3. Solar wing, 4. Satellite body, 5. Expand the hinge. DETAILED DESCRIPTION

[0036] The embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0037] The solar wing 3 is the main energy source of the satellite, and is connected to the satellite body 4 by a hinge 5 to achieve unfolding or folding.

[0038] See also Figure 1-Figure 10 A ground-based satellite solar wing 3 deployment time test system of the present invention comprises a mobile phone terminal and a deployment test terminal 1 and an in-place test terminal 2 detachably arranged on the solar wing 3; the deployment test terminal 1 and the in-place test terminal 2 transmit signals to the mobile phone terminal through their own Bluetooth communication modules respectively;

[0039] The expansion test terminal 1 and the in-place test terminal 2 have the same structure, and at least include a touch switch 113 and a Bluetooth communication module. The expansion start signal is obtained by the touch switch 113 of the expansion test terminal 1 and transmitted to the mobile phone terminal through the Bluetooth communication module to start timing. The expansion in-place signal is obtained by the touch switch 113 of the in-place test terminal 2 and transmitted to the mobile phone terminal through the Bluetooth communication module to end timing.

[0040] The deployment test terminal 1 comprises:

[0041] An elastic clamp 101 detachably connected to the solar wing 3;

[0042] An electric control unit fixed on the elastic clamp 101, the electric control unit at least comprising a PCB board 111;

[0043] A touch switch 113, wherein the touch switch 113 is connected to the PCB board 111 through a wire;

[0044] And a universal shaping tube 116, the universal shaping tube 116 is a hollow structure, the wire connected between the touch switch 113 and the PCB board 111 is located in the universal shaping tube 116, and the position and direction of the touch switch 113 relative to the elastic clamp 101 are adjusted by the universal shaping tube 116. The universal shaping tube 116 has strong plasticity, can be adjusted to any shape within a certain range, and maintain the adjusted shape with high rigidity. The universal shaping tube 116 in this embodiment is a gooseneck tube (snake tube), which is a metal shaping hose that can be bent arbitrarily and determine the direction.

[0045] The elastic clamp 101 comprises:

[0046] A fixing clip 102, wherein the fixing clip 102 is a T-shaped structure, wherein one plate is used as a bottom plate, and an end surface of the other plate is in contact with a midline position of a side surface of the bottom plate and is vertically used as a mounting plate, and the electronic control unit is mounted on the mounting plate;

[0047] A movable clip 103 hinged to the other end of the mounting plate of the fixed clip 102 via a rotating shaft 105;

[0048] A torsion spring 106 disposed on the rotating shaft 105;

[0049] And a swivel clip 104 is arranged on a side of the movable clip 103 opposite to the fixed clip 102. The swivel clip 104 and the movable clip 103 are hinged by a plug screw 107 so that the bottom plate of the fixed clip 102 remains parallel to the swivel clip 104.

[0050] The elastic clamp 101 also includes a large silicone rubber pad 108 and a small silicone rubber pad 109. The large silicone rubber pad 108 is arranged on the side of the bottom plate of the fixed clip 102 opposite to the rotating clip 104, and the small silicone rubber pad 109 is arranged on the side of the rotating clip 104 opposite to the bottom plate of the fixed clip 102.

[0051] The large silicone rubber pad 108 and the small silicone rubber pad 109 are provided to increase the friction force while preventing damage to the surface of the solar wing 3. The movable clip 103 is hinged with the rotating clip 104 to ensure that the large silicone rubber pad 108 and the small silicone rubber pad 109 are always parallel. The torsion spring 106 clamps the two fixed clips 102 and the movable clip 103 on the solar wing 3 with a certain force, ensuring that the elastic clamp 101 remains in the same position during the unfolding of the solar wing 3.

[0052] The electronic control unit further comprises:

[0053] A PCB mounting seat 110 mounted on a mounting plate of a fixing clip 102 of the elastic clamp 101, wherein the PCB board 111 is mounted on the PCB mounting seat 110;

[0054] A PCB board installation cover 112 detachably connected to the PCB board installation seat 110 is used to package the PCB board 111 .

[0055] The PCB board 111 includes a Bluetooth communication module, a power module, a data processing chip and an I / O interface; the data processing chip is electrically connected to the Bluetooth communication module and the I / O interface respectively, and the power module is connected to the Bluetooth communication module and the data processing chip respectively for power supply; the micro switch 115 of the touch switch 113 is connected to the I / O interface of the PCB board 111 through a wire; the data processing chip receives the signal transmitted by the micro switch 115 through the I / O interface, and transmits it to the mobile phone terminal through the Bluetooth communication module.

[0056] The power supply module is a 5V power supply module.

[0057] The touch switch 113 includes a micro switch fixing seat 114 and a micro switch 115 fixed on the micro switch fixing seat 114; the end of the universal shaping tube 116 is connected to the side wall of the micro switch fixing seat 114 through the shaping tube installation interface 117. The micro switch 115 has elastic contacts, and pressing the contacts can realize the on and off of the electrical signal. The state of the micro switch 115 is determined by the level of the pin connected to the micro switch 115. When the state of the micro switch 115 changes, a signal is sent to the mobile phone terminal through the Bluetooth communication module.

[0058] The large silicone rubber pad 108 is bonded to the fixed clip 102, the small silicone rubber pad 109 is bonded to the rotating clip 104, and the rotating clip 104 is hinged with the movable clip 103 by the plug screw 107, so as to ensure that the large silicone rubber pad 108 and the small silicone rubber pad 109 can always remain parallel when the angle between the fixed clip 102 and the movable clip 103 changes, so as to adapt to the substrates of the solar wing 3 of different thicknesses. The small silicone rubber pad 109 can increase the friction between the clip and the substrate of the solar wing 3, prevent the deployment test terminal 1 and the in-place test terminal 2 from falling off during the deployment of the solar wing 3, and at the same time avoid damage to the surface of the solar wing 3. The PCB board mounting seat 110 is connected to the mounting plate of the fixing clip 102 by bolts, the PCB board 111 is connected to the PCB board mounting seat 110 by bolts, and the PCB board mounting cover 112 is connected to the PCB board mounting seat 110 by bolts to realize the packaging of the PCB board 111. The micro switch 115 is connected to the PCB board 111 by a connecting wire passing through the inside of the universal molding tube 116. The universal molding tube 116 is respectively connected to the micro switch fixing seat 114 and the PCB board mounting seat 110 through the mounting interface of the universal molding tube 116, and the micro switch 115 is installed on the micro switch fixing seat 114.

[0059] The deployment test terminal 1 and the in-place test terminal 2 have the same working principle and similar structural form. The difference lies in that the installation position of the universal molding tube 116 relative to the in-place test terminal 2 is opposite to the installation position of the universal molding tube 116 relative to the deployment test terminal 1. Considering that the distance from the in-place test terminal 2 to the satellite body 4 is far after the solar wing 3 is deployed, the length of the universal molding tube 116 of the in-place test terminal 2 is slightly longer than that of the universal molding tube 116 of the deployment test terminal 1.

[0060] To prevent the unfolded test terminal 1 and the in-place test terminal 2 from contacting the solar cells on the front of the solar wing 3 and causing damage to the solar cells after being installed on the solar wing 3 substrate, the small silicone rubber pad 109 has a smaller width than the large silicone rubber pad 108, which is less than the required minimum distance between the solar cell and the edge of the substrate.

[0061] The working principle of the present invention is:

[0062] When conducting the solar wing 3 deployment test on the ground, the Bluetooth modules of the deployment test terminal 1 and the arrival test terminal 2 are connected to the mobile phone terminal to confirm the connection status.

[0063] When the solar wing 3 is not folded, the in-place test terminal 2 is fixed to a suitable position on the side of the solar wing 3 by the elastic clamp 101, and the position and direction of the micro switch 115 are adjusted by the universal molding tube 116 of the in-place test terminal 2, so that the micro switch 115 contacts the satellite body 4 and is just in the on state. Then the solar wing 3 is folded.

[0064] Before the solar wing 3 is unfolded, the unfolding test terminal 1 is installed and fixed to a suitable position on the side of the solar wing 3 by the elastic clamp 101, and the position and direction of the micro switch 115 are adjusted by the universal molding tube 116 of the in-place test terminal 2 so that the micro switch 115 contacts the satellite body 4 and is just in the on state.

[0065] Then, the solar wing 3 is deployed. When the solar wing 3 begins to deploy, the micro switch 115 of the deployment test terminal 1 changes from the on state to the off state, the data processing chip detects that the level state of the peripheral I / O interface has changed, and sends a signal instruction to the mobile phone terminal through the Bluetooth communication module, and the mobile phone terminal records the time at this time. When the solar wing 3 is deployed in place, the micro switch 115 of the in-place test terminal 2 changes from the off state to the on state, the data processing chip detects that the level state of the peripheral I / O interface has changed, and sends a signal instruction to the mobile phone terminal through the Bluetooth communication module, and the mobile phone terminal records the time at this time. The time interval between the two records is the deployment time of the solar wing 3.

[0066] The specific operation process of this application is as follows:

[0067] Test preparation stage 1: The solar wing 3 is in the unfolded state, the in-place test terminal 2 is installed and fixed on the solar wing 3, and the position and direction of the micro switch 115 of the in-place test terminal 2 are adjusted so that the micro switch 115 contacts the satellite body 4 and is just in the conducting state;

[0068] Test preparation stage 2: The solar wing 3 is in a folded state, the deployment test terminal 1 is installed and fixed on the solar wing 3, and the position and direction of the micro switch 115 of the deployment test terminal 1 are adjusted so that the micro switch 115 contacts the satellite body 4 and is just in a conducting state;

[0069] During the test, the solar wing 3 begins to unfold, and the contact of the micro switch 115 of the unfolding test terminal 1 is separated from the satellite body 4, changing from the on state to the off state. The data processing chip detects the change in the level state of the peripheral I / O interface and sends a signal instruction to the mobile terminal through the Bluetooth communication module, and the mobile terminal records the time at this time;

[0070] During the test phase, when the solar wing 3 is deployed, the contact of the micro switch 115 of the test terminal 2 contacts the satellite body 4, and the switch changes from an off state to an on state. The data processing chip detects that the level state of the peripheral I / O interface has changed and sends a signal instruction to the mobile phone terminal through the Bluetooth communication module. The mobile phone terminal records the time at this time, and the time interval between the two records is the deployment time of the solar wing 3.

Claims

1. A ground-based satellite solar wing deployment time test system, characterized in that: It comprises a mobile phone terminal and a deployment test terminal (1) and an in-place test terminal (2) which are detachably arranged on the solar wing (3); the deployment test terminal (1) and the in-place test terminal (2) respectively transmit signals to the mobile phone terminal through their own Bluetooth communication modules; The unfolding test terminal (1) and the in-place test terminal (2) have the same structure, and at least comprise a touch switch (113) and a Bluetooth communication module. An unfolding start signal is obtained through the touch switch (113) of the unfolding test terminal (1) and transmitted to the mobile phone terminal through the Bluetooth communication module to start timing. An unfolding in-place signal is obtained through the touch switch (113) of the in-place test terminal (2) and transmitted to the mobile phone terminal through the Bluetooth communication module to end timing. The expansion test terminal (1) comprises: An elastic clamp (101) detachably connected to the solar wing (3); An electric control unit fixed on the elastic clamp (101), the electric control unit comprising at least a PCB board (111); A touch switch (113), wherein the touch switch (113) is connected to the PCB board (111) via a wire; and a universal shaping tube (116), wherein the universal shaping tube (116) is a hollow structure, a wire connected between the touch switch (113) and the PCB board (111) is located inside the universal shaping tube (116), and the position and direction of the touch switch (113) relative to the elastic clamp (101) are adjusted through the universal shaping tube (116).

2. A ground-based satellite solar wing deployment time test system according to claim 1, characterized in that: The elastic clamp (101) comprises: A fixing clip (102), the fixing clip (102) being a T-shaped structure, with one plate serving as a bottom plate, and one end surface of the other plate contacting a midline position of a side surface of the bottom plate and serving as a mounting plate vertically, the electronic control unit being mounted on the mounting plate; A movable clip (103) hingedly connected to the other end of the mounting plate of the fixed clip (102) via a rotating shaft (105); A torsion spring (106) disposed on the rotating shaft (105); and a swivel clip (104) arranged on a side of the movable clip (103) opposite to the fixed clip (102); the swivel clip (104) and the movable clip (103) are hingedly connected via a plug screw (107) so that the bottom plate of the fixed clip (102) remains parallel to the swivel clip (104).

3. A ground-based satellite solar wing deployment time test system according to claim 2, characterized in that: The elastic clamp (101) also includes a large silicone rubber pad (108) and a small silicone rubber pad (109), wherein the large silicone rubber pad (108) is arranged on the side of the bottom plate of the fixed clip (102) opposite to the rotating clip (104), and the small silicone rubber pad (109) is arranged on the side of the bottom plate of the rotating clip (104) opposite to the bottom plate of the fixed clip (102).

4. A ground-based satellite solar wing deployment time test system according to claim 2, characterized in that: The electronic control unit further comprises: A PCB board mounting seat (110) mounted on a mounting plate of a fixing clip (102) of the elastic clamp (101), the PCB board (111) being mounted on the PCB board mounting seat (110); and a PCB board installation cover (112) detachably connected to the PCB board installation seat (110) for packaging the PCB board (111).

5. A ground-based satellite solar wing deployment time test system according to claim 2, characterized in that: The PCB board (111) comprises a Bluetooth communication module, a power module, a data processing chip and an I / O interface; the data processing chip is electrically connected to the Bluetooth communication module and the I / O interface respectively, and the power module is connected to the Bluetooth communication module and the data processing chip respectively for power supply; the micro switch (115) of the touch switch (113) is connected to the I / O interface of the PCB board (111) via a wire; the data processing chip receives a signal transmitted by the micro switch (115) via the I / O interface, and transmits the signal to the mobile phone terminal via the Bluetooth communication module.

6. A ground-based satellite solar wing deployment time test system according to claim 5, characterized in that: The power supply module is a 5V power supply module.

7. A ground-based satellite solar wing deployment time test system according to claim 1, characterized in that: The touch switch (113) comprises a micro switch fixing seat (114) and a micro switch (115) fixed on the micro switch fixing seat (114); the end of the universal molding tube (116) is connected to the side wall of the micro switch fixing seat (114) via a molding tube installation interface (117).

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