Device and method for carrying out heat balance test by adopting solar simulator

Abstract

The invention provides a device and a method for carrying out a heat balance test by adopting a solar simulator. The device comprises space environment simulation equipment, a test simulation board, the solar simulator and an unloading tool, light of the solar simulator enters the space environment simulation equipment, the test simulation board is vertically mounted in the space environment simulation equipment, and an included angle of 23.5 degrees is formed between the test simulation board and the light of the solar simulator; and the unloading tool is located in the space environment simulation equipment and is used for carrying out gravity unloading on the test product, so that the test product can freely rotate 360 degrees in the horizontal direction. The solar simulator is adopted to accurately simulate the external heat flow absorbed by the surface of the spacecraft, the simulation precision of the external heat flow is higher than 5%, the reliability of a rotating mechanism of a test product is verified, one-time tank opening is reduced, the test time and the test cost are greatly saved, and reference is provided for subsequent related tests.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft environment simulation, and in particular to a device and method for conducting a thermal balance test using a solar simulator. Background Art

[0002] Before a spacecraft is launched, it is generally necessary to conduct a thermal balance test in a space environment simulator that simulates the cold and dark environment of space. This is to assess the ability of the spacecraft thermal control subsystem to maintain spacecraft components and subsystems within the specified operating temperature range and to verify the correctness of the spacecraft thermal mathematical model.

[0003] During the thermal balance test of spacecraft, the simulation of heat flow outside space is generally carried out by infrared heating cages, infrared lamp arrays, heating plates and solar simulators. Solar simulators can accurately simulate the collimation, uniformity and spectral characteristics of solar radiation, and have high simulation accuracy for heat flow outside space, so they are widely used in thermal balance tests of spacecraft.

[0004] Therefore, a device and method for conducting a thermal balance test using a solar simulator is needed to meet the above requirements. Summary of the invention

[0005] In view of the defects in the prior art, the object of the present invention is to provide a device and method for conducting a thermal balance test using a solar simulator.

[0006] According to the present invention, a device for conducting a thermal balance test using a solar simulator comprises: a space environment simulation device, a test simulation board, a solar simulator and an unloading tool;

[0007] The light of the solar simulator is incident on the space environment simulation device, and the test simulation board is vertically installed in the space environment simulation device and forms an angle of 23.5° with the light of the solar simulator;

[0008] The unloading tool is located in the space environment simulation device, and is used to perform gravity unloading of the test product so that the test product can freely rotate 360° in the horizontal direction.

[0009] Preferably, the test simulation board includes two simulation boards, and the two simulators are stacked parallel to each other in the space environment simulation device.

[0010] Preferably, the distance between the two simulation plates is 200 mm.

[0011] Preferably, the test simulation board is a 5 mm thick aluminum alloy plate, with an OSR secondary surface mirror consistent with the satellite heat dissipation surface pasted on the front, an electric heater pasted on the back to compensate for the power consumption of the single unit on the satellite, a thermocouple pasted for temperature measurement, and a multi-layer insulation component coated.

[0012] Preferably, the unloading tool is made of stainless steel 1Cr18Ni9Ti.

[0013] Preferably, the unloading tooling is pickled to meet the anti-pollution requirements of spacecraft vacuum thermal testing.

[0014] Preferably, the unloading tooling includes a support seat and a rotating assembly, and the rotating assembly is provided with a screw universal ball, a double-headed screw and a spring for completely unloading the gravity of the test product; the rotating assembly is freely placed in the unloading tooling support seat, and realizes 360° free rotation in the horizontal direction through the screw universal ball at the bottom.

[0015] A method for conducting a thermal balance test using a solar simulator according to the present invention comprises:

[0016] The test simulation board and the unloading tooling enter the space environment simulation equipment together with the test product to carry out a thermal balance test;

[0017] Before the test begins, turn off the solar simulator first, so that the test product is perpendicular to the solar simulator; after the test conditions are established, rotate the test product to face the solar simulator, turn on the solar simulator, apply the power of the electric heater on the test simulation board, and complete the thermal balance test conditions; after all test conditions are completed, rotate the test product to face the solar simulator, turn off the solar simulator, and the test ends.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The present invention accurately simulates the external heat flux absorbed by the surface of the spacecraft product, and the external heat flux simulation accuracy is better than 5%.

[0020] 2. The present invention verifies the reliability of the rotating mechanism of the test product, reduces the need to open the can once, greatly saves test time and test costs, and provides a reference for subsequent related tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0022] Figure 1 A schematic diagram of the position of the test product in the space environment simulation equipment (front view);

[0023] Figure 2 This is a schematic diagram of the test product facing the solar simulator;

[0024] Figure 3 This is a schematic diagram of the vertical state of the test product and the solar simulator;

[0025] Figure 4 This is a schematic diagram of the position of the test product in the vacuum tank;

[0026] Figure 5 This is a schematic diagram of the test simulation board status;

[0027] Figure 6 It is a schematic diagram of unloading tooling;

[0028] Figure 7 This is a schematic diagram of the structure of the rotating assembly of the unloading tooling.

[0029] Description of reference numerals:

[0030] DETAILED DESCRIPTION

[0031] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0032] This paper presents a device for thermal balance test using a solar simulator. Figure 1-Figure 7 As shown, the device is developed by developing a set of test simulation board 4 and unloading tooling 5. The test simulation board 4 is vertically installed on the special vehicle 6 in the tank in the space environment simulation equipment 1, and forms an angle of 23.5° with the solar simulator 2, simulating the angle of solar radiation and the 23.5° angle of satellite formation, so that the test product 3 can be vertically installed on the test simulation board 4. At the same time, the gravity of the test product 3 is unloaded by the unloading tooling 5 to realize the horizontal rotation of the test product 3 in the space environment simulation equipment 1. When the test conditions are established, the test product 3 is rotated to a state facing the solar simulator 2, and then the solar simulator 2 is turned on, and the power of the electric heater on the test simulation board 4 is applied to complete the thermal balance test condition. After all the test conditions are completed, the test product 3 is rotated to a state perpendicular to the solar simulator 2. The purpose of rotating to a vertical state is to restore the initial state, verify the reliability of the rotation mechanism of the test product 3, turn off the solar simulator 2, and the test ends.

[0033] See attached Figure 1 and attached Figure 2The test product 3 is installed on the test simulation board 4. Due to the limited size of the vacuum tank, in order to ensure that the test product 3 is within the light spot range of the solar simulator 2, the test simulation board 4 in the present application is divided into two pieces. The two test simulation boards 4 are arranged parallel to each other with a front-to-back spacing of 200 mm. They are vertically installed on the special vehicle 6 in the tank in the space environment simulation equipment 1, and form an angle of 23.5° with the solar simulator 2. The test product 3 is unloaded by gravity using the unloading tooling 5, and the test product 3 is within the light spot range of the solar simulator 2.

[0034] See attached Figure 3 The test simulation board 4 is made of aluminum alloy. The front side is consistent with the thermal control coating on the surface of the spacecraft, which is an OSR secondary surface mirror 7. The back side is pasted with an electric heater 8, and a thermocouple 9 is pasted to measure the temperature. It is also covered with 15 layers of multi-layer thermal insulation components 10.

[0035] See attached Figure 4 and attached Figure 5 The unloading fixture 5 includes a support seat 12 and a rotating assembly 11. The rotating assembly 11 is composed of a connecting rod 13, a fixing nut 14, a sleeve 15, a double-headed connecting screw 16, a sleeve 17, a YSWH-D25-L40 spring 18, a QDE31-25 screw universal ball 19 and a disc 20. The test product 3 is installed on the rotating assembly connecting rod 13, and the gravity of the test product 3 is unloaded at all times through the double-headed connecting screw 16 and the YSWH-D25-L40 spring 18. The rotating assembly is freely placed in the support seat of the unloading fixture 5, and the 6 screw universal balls at the bottom can realize 360° free rotation in the horizontal direction.

[0036] The present invention also discloses a method for conducting a thermal balance test using a solar simulator 2, see the attached Figure 2 When the test product 3 is subjected to the thermal balance test in the space environment simulation device 1, the solar simulator 2 is turned off first, and the test product 3 is in a vertical state with the solar simulator 2. When the test conditions are established, the test product 3 is rotated to face the solar simulator 2, and then the solar simulator 2 is turned on, and the power of the electric heater on the test simulation board 4 is applied to complete the test conditions. After all the test conditions are completed, the test product 3 is rotated to a vertical state with the solar simulator 2, and the solar simulator 2 is turned off, and the test ends.

[0037] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0038] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A device for conducting a thermal balance test using a solar simulator, characterized in that: include: Space environment simulation equipment, test simulation panels, solar simulators and unloading tooling; The light of the solar simulator is incident on the space environment simulation device, and the test simulation board is vertically installed in the space environment simulation device and forms an angle of 23.5° with the light of the solar simulator; The unloading tool is located in the space environment simulation device, and is used to perform gravity unloading of the test product so that the test product can freely rotate 360° in the horizontal direction.

2. The device for performing a thermal balance test using a solar simulator according to claim 1, characterized in that: The test simulation board includes two simulation boards, and the two simulators are stacked parallel to each other and arranged in the space environment simulation device.

3. The device for performing a thermal balance test using a solar simulator according to claim 2, characterized in that: The distance between the two simulation boards is 200 mm.

4. The device for performing a thermal balance test using a solar simulator according to claim 1, characterized in that: The test simulation board is a 5mm thick aluminum alloy plate, with an OSR secondary surface mirror consistent with the satellite heat dissipation surface pasted on the front, an electric heater pasted on the back to compensate for the power consumption of the single unit on the satellite, and a thermocouple pasted for temperature measurement, and covered with a multi-layer insulation component.

5. The device for performing a thermal balance test using a solar simulator according to claim 1, characterized in that: The unloading tool is made of stainless steel 1Cr18Ni9Ti.

6. The device for performing a thermal balance test using a solar simulator according to claim 1, characterized in that: The unloading tooling is pickled to meet the anti-pollution requirements of spacecraft vacuum thermal testing.

7. The device for performing a thermal balance test using a solar simulator according to claim 1, characterized in that: The unloading tooling includes a support seat and a rotating assembly, in which a screw universal ball, a double-headed screw and a spring are arranged for completely unloading the gravity of the test product; the rotating assembly is freely placed in the unloading tooling support seat, and can achieve 360° free rotation in the horizontal direction through the screw universal ball at the bottom.

8. A method for conducting a thermal balance test using a solar simulator, based on the device for conducting a thermal balance test using a solar simulator according to any one of claims 1 to 7, characterized in that: include: The test simulation board and the unloading tooling enter the space environment simulation equipment together with the test product to carry out a thermal balance test; Before the test begins, turn off the solar simulator first, so that the test product is perpendicular to the solar simulator; after the test conditions are established, rotate the test product to face the solar simulator, turn on the solar simulator, apply the power of the electric heater on the test simulation board, and complete the thermal balance test conditions; after all test conditions are completed, rotate the test product to face the solar simulator, turn off the solar simulator, and the test ends.

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