An experimental device for both thermal-optical test and thermal balance test of an optical remote sensing satellite

Abstract

The present invention discloses a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite, which includes a satellite support tooling, which is arranged on a load platform and is thermally insulated from the remote sensing satellite; a first radiation metal plate installed at the light incident port of the optical camera; a second radiation metal plate placed parallel to the outer surface of the remote sensing satellite at a distance of 100 mm to 200 mm; a thin film heating sheet arranged on the outer surfaces of the first radiation metal plate and the second radiation metal plate; a rotating link device connected to the first radiation metal plate; and further includes a driving device and a locking mechanism arranged on the mechanism base. The present invention can not affect the field of view of the optical camera when the driving device rotates to 0°, enabling the optical camera to conduct thermal-optical tests in a reasonable vacuum and low-temperature environment; when the driving device rotates to 90°, the radiation plate temperature control and the low-temperature heat sink are reasonably utilized to conduct the thermal balance test of the remote sensing satellite; at the same time, it ensures that the mechanism components will not pose a threat to the safety of the satellite.

Description

Technical Field

[0001] The present invention relates to the technical field of environmental testing for optical remote sensing satellites, and particularly to a dual-purpose testing device for thermal-optical testing and thermal balance testing of an optical remote sensing satellite. Background Art

[0002] An optical remote sensing satellite is an artificial satellite used as an outer space remote sensing platform, and its remote sensing information products create high economic benefits in various aspects such as national land census, crop yield estimation, disaster prevention and mitigation, and urban planning. During the on-orbit operation of the remote sensing satellite, the drastic change of the external heat flux will cause fluctuations and uneven distribution in the temperature control of the remote sensing satellite and the optical camera payload. Therefore, during the development process of the remote sensing satellite, its optical camera payload needs to undergo strict vacuum thermal-optical testing to verify the imaging quality, and after the remote sensing satellite is assembled, it also needs to undergo vacuum thermal balance testing to verify the whole-satellite temperature control ability and temperature distribution.

[0003] The vacuum thermal-optical testing of the camera and the vacuum thermal balance testing of the satellite are both large-scale tests that need to be carried out in a space environment simulator. The liquid nitrogen cost and vacuum equipment usage cost required to construct a vacuum low-temperature environment are in the range of several hundred thousand to one million. Usually, the camera development team and the satellite development team are not the same, and the environmental conditions required for the two tests are also different. Therefore, the two tests are generally carried out separately, resulting in a high total test cost and a long overall R & D cycle. In addition, the vacuum thermal balance test system of the satellite generally has an external heat flux simulation device (such as an infrared heating cage, an infrared lamp array, an electric heater, etc.) at the light entrance of the camera, which partially or completely blocks the light entrance of the optical camera, causing a significant attenuation of the incident energy of the parallel light source and having a great impact on the imaging quality test or even making it impossible to carry out the camera thermal-optical test. Therefore, the current satellite vacuum thermal balance test external heat flux simulation system cannot meet the needs of the camera thermal-optical test.

[0004] (Patent Name: Earth External Heat Flux Simulator for Vacuum Thermal Test of Space Optical Remote Sensor, Patent Number: CN203550988U) describes an external heat flux simulator used to meet the synchronous thermal balance test and thermal-optical test of an optical camera itself. The device consists of a conical front cylinder, a cylindrical rear cylinder, a support ring, a bracket, an infrared heat flux generating device, etc. It can increase the required earth infrared heat flux at the light entrance by controlling the infrared heat flux of the conical cylinder and the cylindrical cylinder, and does not affect the thermal-optical test field of view required by the camera. However, this device only provides earth infrared heat flux simulation for the thermal balance test and thermal-optical test of the camera itself, and cannot meet the requirements of the thermal balance test of the remote sensing satellite for the comprehensive effects of various space heat fluxes.

[0005] (Patent Name: Shutter-Type Rotatable Infrared Heating Cage, Patent Number: CN106275523A) describes a shutter-type infrared heating cage that can accelerate the cooling of spacecraft and shorten the test cycle. This device consists of an infrared cage frame, a reduction motor, connecting rods and pin shafts, heating wires, angle sensors, etc. It can control the rotation angle of the heating wires through a closed-loop control method, thereby controlling the shielding of the heating cage on the surface of the spacecraft to accelerate the cooling of the spacecraft. However, this device is only beneficial for the thermal balance test of satellites, and the shielding of the heating wires and other tooling makes it unable to be used for the thermal-optical test of cameras.

[0006] (Patent Name: An Infrared Heating Cage, Patent Number: CN111942622A) describes an infrared heating cage that can quickly switch the coverage coefficient under high and low temperature conditions. This device consists of an infrared cage frame, a rack, a worm and worm gear, a spring, an insulating part, etc. By driving the worm and worm gear, the rack is parallel to the satellite surface under high temperature conditions and perpendicular to the satellite surface under low temperature conditions, controlling the coverage coefficient of the heating cage on the surface of the spacecraft to achieve thermal radiation testing under different conditions. However, this device is only designed for the thermal balance test of satellites, and the shielding of the heating wires and other tooling makes it unable to be used for the thermal-optical test of cameras.

[0007] Based on the above technical problems, those skilled in the art urgently need to develop a dual-purpose test device that can shorten the test cycle, reduce the R & D cost of satellites, and can be used for both the thermal-optical test of optical cameras and the thermal balance test of remote sensing satellites. Summary of the Invention

[0008] The object of the present invention is to provide a dual-purpose test device that can shorten the test cycle, reduce the R & D cost of satellites, and can be used for both the thermal-optical test of optical cameras and the thermal balance test of remote sensing satellites.

[0009] In order to achieve the above object, the present invention provides the following technical solutions:

[0010] A dual-purpose test device for the thermal-optical test and thermal balance test of an optical remote sensing satellite, the test device includes:

[0011] A satellite support tooling, which is arranged on the loading platform and connected to the remote sensing satellite, and thermal insulation treatment is performed at the connection between the satellite support tooling and the remote sensing satellite;

[0012] A first radiation metal plate installed at the light inlet of the optical camera;

[0013] A second radiation metal plate placed parallel to the outer surface of the remote sensing satellite at a distance of 100 mm to 200 mm, and the thicknesses of the first radiation metal plate and the second radiation metal plate are both 1 to 3 mm;

[0014] The thin-film heating sheets disposed on the outer surfaces of the first radiation metal plate and the second radiation metal plate;

[0015] The test device further includes:

[0016] The rotating link device connected to the first radiation metal plate; and

[0017] The driving device, which can drive the rotating end of the rotating link device to rotate;

[0018] The locking mechanism, which is disposed on the mechanism base and used to lock the rotation angle of the rotating link device.

[0019] Furthermore, both the first radiation metal plate and the second radiation metal plate are radiation aluminum plates, and the thickness of the radiation aluminum plate is 2 mm. The inner surface of the radiation aluminum plate facing the satellite body is subjected to black anodizing electroplating treatment, and the surface emissivity ≥ 0.85;

[0020] Four pieces of the thin-film heating sheets are pasted on the outer surfaces of both the first radiation metal plate and the second radiation metal plate facing the space environment simulator.

[0021] Furthermore, the satellite support tooling includes four support columns erected vertically, and four angular polyimide heat insulation pads 8 are embedded at the connection between the satellite support tooling and the remote sensing satellite.

[0022] Furthermore, the driving device includes a motor bracket; and

[0023] The stepping motor and the worm installed on the motor bracket through the first bearing. Two pieces of the second thin-film heating sheets are pasted on the outer surfaces of both the stepping motor housing and the motor bracket;

[0024] The worm gear meshing with the worm.

[0025] Furthermore, the rotating link device includes a connecting rod; and

[0026] One end is sleeved on the connecting rod and fixed by a shaft pin, and the other end is fixedly installed in the installation bayonet of the first radiation metal plate by a screw. The worm gear is fixed on the connecting rod through the shaft pin;

[0027] The first aluminum column and the second aluminum column welded to the lower part of the connecting rod from different directions.

[0028] Furthermore, the locking mechanism includes the third aluminum column and the fourth aluminum column fixedly connected to the upper end of the mechanism base; and

[0029] Two vertical ears oppositely arranged on the mechanism base;

[0030] A spring and a steel pressing piece connected to the two lugs through a spring shaft form a movable mechanism through the spring and the steel pressing piece.

[0031] Further, the mechanism base includes an aluminum plate with a thickness of 5 mm; and

[0032] A second bearing provided at the center of the aluminum plate body, and the connecting rod can be inserted into the second bearing.

[0033] Further, the lengths of the first aluminum column and the second aluminum column are both 95 mm and form a horizontal plane with an angle of 110°;

[0034] The heights of the third aluminum column and the fourth aluminum column are both 90 mm, and the distances from the axes of the third aluminum column and the fourth aluminum column to the axis of the connecting rod are equal, which is 80 mm;

[0035] When the rotation angle of the stepper motor is 0°, the first aluminum column contacts the edge of the third aluminum column, and when the rotation angle of the stepper motor is 90°, the second aluminum column contacts the edge of the fourth aluminum column.

[0036] Further, four height adjustment bolts are installed at the bottom of the satellite support tooling to make the optical axis of the optical camera parallel to that of the collimator and within the imaging range.

[0037] Preferably, the diameters of the first aluminum column, the second aluminum column, the third aluminum column, and the fourth aluminum column are all 7 mm, and the thickness of the steel pressing piece is 3 mm.

[0038] In the above technical solution, a dual-purpose test device for thermal optical test and thermal balance test of an optical remote sensing satellite provided by the present invention has the following beneficial effects:

[0039] The dual-purpose test device for thermal optical test and thermal balance test of an optical remote sensing satellite of the present invention can not affect the field of view of the optical camera when the driving device rotates to 0°, so that the optical camera can perform thermal optical tests in a reasonable vacuum and low-temperature environment; when the driving device rotates to 90°, the radiation plate temperature control and the cryogenic heat sink are reasonably utilized to perform the thermal balance test of the remote sensing satellite; at the same time, it is ensured that the mechanism components will not pose a threat to the safety of the satellite.

[0040] The present invention allows the environmental simulator to cross-perform the camera thermal optical test and the satellite thermal balance test at the same time under the condition of only being turned on once, which can at least shorten the test cycle by about 5 days, save satellite test costs, reduce labor costs, and at the same time reduce the risks in multiple satellite transportation operations. Description of the Drawings

[0041] To more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the accompanying drawings required for use in the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments recorded in the present invention. For those of ordinary skill in the art, other accompanying drawings can also be obtained based on these drawings.

[0042] Figure 1 It is a three-dimensional view of the overall structure of a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite provided by an embodiment of the present invention;

[0043] Figure 2 It is a schematic structural diagram of a driving device in a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite provided by an embodiment of the present invention;

[0044] Figure 3 It is a schematic diagram of the composition and positional relationship of the first radiation metal plate of the rotating link device in a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite provided by an embodiment of the present invention;

[0045] Figure 4 It is a schematic diagram of the composition and positional relationship of the locking mechanism - the mechanism base device in a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite provided by an embodiment of the present invention;

[0046] Figure 5 It is a schematic diagram of the positional relationship of the metal columns of four aluminum columns at 0° and 90° of the motor rotation in a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite provided by an embodiment of the present invention;

[0047] Figure 6 It is a schematic diagram of the positional relationship between the angular heat insulation pad and the satellite support tooling in a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite provided by an embodiment of the present invention;

[0048] Figure 7 It is a schematic diagram of the use of a dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite provided by an embodiment of the present invention when working in a thermal-optical test.

[0049] Explanation of reference numerals:

[0050] 1. Satellite support tooling; 2. First radiation metal plate; 3. Thin film heating sheet; 4. Rotating link device; 5. Driving device; 6. Locking mechanism; 7. Mechanism base; 8. Angular polyimide heat insulation pad; 9. Second radiation metal plate; 11. Space environment simulator; 12. Carrying platform; 13. Remote sensing satellite; 14. Optical camera; 15. Collimator;

[0051] 101. Height adjustment bolt; 102. Support column;

[0052] 401, connecting rod; 402, axle pin; 403, mounting bayonet; 404, first aluminum column; 405, second aluminum column;

[0053] 501, motor bracket; 502, first bearing; 503, stepper motor; 504, worm; 505, worm gear; 506, second film heating element;

[0054] 601, third aluminum column; 602, fourth aluminum column; 603, lug; 604, spring shaft; 605, spring; 606, steel pressing plate;

[0055] 701, aluminum plate; 702, second bearing. Detailed implementation manners

[0056] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further introduced in detail below with reference to the accompanying drawings.

[0057] See Figures 1 to 7 as shown in;

[0058] A dual-purpose test device for thermal optical test and thermal balance test of an optical remote sensing satellite of the present invention, the test device includes:

[0059] A satellite support tooling 1, which is arranged on the loading platform 12 and connected to the remote sensing satellite 13, and a thermal insulation treatment is performed at the connection between the satellite support tooling 1 and the remote sensing satellite 13;

[0060] A first radiation metal plate 2 installed at the light inlet of the optical camera 14;

[0061] A second radiation metal plate 9 placed in parallel at a position 100 mm to 200 mm from the +Y surface of the body of the remote sensing satellite 13, and the thicknesses of the first radiation metal plate 2 and the second radiation metal plate 9 are both

[0062] 1 - 3 mm;

[0063] Four film heating elements 3 provided on the outer surfaces of the first radiation metal plate 2 and the second radiation metal plate 9 facing the space environment simulator 11, providing the required external heat flux for the closed-loop temperature control of the body of the remote sensing satellite 13;

[0064] The test device further includes:

[0065] A rotating link device 4 connected to the first radiation metal plate 2; and

[0066] A driving device 5, which can drive the rotating end of the rotating link device 4 to rotate;

[0067] The locking mechanism 6 is provided on the mechanism base 7 and is used to lock the rotation angle of the rotating link device 4.

[0068] As a further introduction to this embodiment, both the first radiation metal plate 2 and the second radiation metal plate 9 are radiation aluminum plates, and the thickness of the radiation aluminum plate is 2 mm. The radiation aluminum plate is subjected to black anodic electroplating treatment towards the inner surface of the satellite body, and the surface emissivity ≥ 0.85;

[0069] When the starting angle is 0°, the driving device 5, the rotating link device 4, and the first radiation metal plate 2 are all outside the field of view of the optical camera 14 and will not interfere with the thermal-optical test of the optical camera 14.

[0070] The required space external heat flux on the +X / -X / -Y / -Z surfaces of the remote sensing satellite 13 without a radiation aluminum plate is provided by the liquid nitrogen heat sink on the inner surface of the space environment simulator 11; in this embodiment, the heat sink temperature for the thermal-optical test of the optical camera 14 is -20 °C, and the two first radiation metal plates are not temperature-controlled. The remote sensing satellite 13 operates in the standard normal mode; in this embodiment, when the remote sensing satellite 13 is in the thermal balance test, the inner surface temperature of the space environment simulator 11 under the low-temperature condition is -55 °C, the closed-loop temperature control temperature of the first radiation metal plate 2 is -12 °C, and the closed-loop temperature control temperature of the second radiation metal plate 9 is -35 °C; under the high-temperature condition, the inner surface temperature of the space environment simulator 11 is -30 °C, the closed-loop temperature control temperature of the first radiation metal plate 2 is -2 °C, and the closed-loop temperature control temperature of the first radiation metal plate 2 is -15 °C.

[0071] As a further introduction to this embodiment, the satellite support tooling 1 includes four support columns 102 erected vertically, and four angular polyimide heat insulation pads 8 are embedded at the connection between the satellite support tooling 1 and the remote sensing satellite 13 for thermal insulation between the satellite body and the tooling. The outer surfaces of the support columns 102 and the power cables, control signal cables, and temperature measurement cables are wound with 20-unit multi-layer heat insulation components.

[0072] As a further introduction to this embodiment, the driving device 5 includes a motor bracket 501; and

[0073] A stepping motor 503 and a worm 504 installed on the motor bracket 501 through a first bearing 502, and two second film heating sheets 506 are pasted on the outer surfaces of the housing of the stepping motor 503 and the motor bracket 501;

[0074] A worm gear 505 that meshes with the worm 504. The worm gear 505 meshes with the worm 504 and is driven by the stepper motor 503. To adapt to the cryogenic heat sink environment of the space environment simulator 11, two film heating sheets and a thermistor are pasted on the outer surface of the housing of the stepper motor 503 and the motor bracket 501 for closed-loop temperature control. At the same time, the whole is covered with a 20-unit multi-layer insulation assembly to keep the driving device 5 warm, and the target temperature for temperature control is 20 °C.

[0075] As a further introduction to this embodiment, the rotating link device 4 includes a link 401; and

[0076] One end is sleeved on the link 401 and fixed by a shaft pin 402, and the other end is fixedly installed in the mounting bayonet 403 of the first radiation metal plate 2 by a screw. The worm gear 505 is fixed on the link 401 by the shaft pin 402;

[0077] A first aluminum column 404 and a second aluminum column 405 welded to the lower part of the link 401 from different directions.

[0078] As a further introduction to this embodiment, the locking mechanism 6 includes a third aluminum column 601 and a fourth aluminum column 602 fixedly connected to the upper end of the mechanism base 7; and

[0079] Two vertical ears 603 oppositely arranged on the mechanism base 7;

[0080] A spring 605 and a steel pressing sheet 606 connected to the two vertical ears 603 by a spring shaft 604. An active mechanism is formed by the spring 605 and the steel pressing sheet 606. When the stepper motor 503 rotates, it can synchronously drive the worm 504, the worm gear 505, the link 501, the mounting bayonet 403 and the first radiation metal plate 2 to rotate; the first aluminum column 404 and the second aluminum column 405 are welded to the bottom of the link 401.

[0081] As a further introduction to this embodiment, the mechanism base 7 includes an aluminum plate 701 with a thickness of 5 mm; and

[0082] A second bearing 702 provided in the center of the plate body of the aluminum plate 701. The link 401 can be inserted into the second bearing 702, and the bottom of the link 401 is inserted into the center of the second bearing 702 for easy rotation.

[0083] As a further introduction to this embodiment, the lengths of the first aluminum column 404 and the second aluminum column 405 are both 95 mm and form a horizontal plane with an angle of 110°;

[0084] The heights of the third aluminum column 601 and the fourth aluminum column 602 are both 90 mm, and the distances from the axes of the third aluminum column 601 and the fourth aluminum column 602 to the axis of the connecting rod 401 are equal, being 80 mm;

[0085] When the rotation angle of the stepping motor 503 is 0°, the first aluminum column 404 contacts the edge of the third aluminum column 601. When the rotation angle of the stepping motor 503 is 90°, the second aluminum column 405 contacts the edge of the fourth aluminum column 602. When the starting angle of the stepping motor 503 is 0°, the first aluminum column 404 is stuck by the third aluminum column 601, making the minimum rotation angle of the entire rotating device the starting angle of 0°. When the driving device 5 drives the rotating connecting rod device 4 and the first radiation metal plate 2 to rotate 90° through the shaft pin 402, the first aluminum column 404 passes over the moving mechanism composed of the spring 605 and the steel pressing sheet 606. The steel pressing sheet 606 returns to its original position under the action of the spring 605, causing the first aluminum column 404 to finally be stuck inside the angle of the steel pressing sheet 606, making the entire moving device unable to retreat. At this time, the second aluminum column 405 is stuck by the fourth aluminum column 602, making the maximum rotation angle of the entire moving device the final angle of 90°.

[0086] As a further introduction of this embodiment, four height adjustment bolts 101 are installed at the bottom of the satellite support tooling 1 to make the optical axis of the optical camera 14 parallel to that of the collimator 15 and within the imaging range.

[0087] As a preferred technical solution of this embodiment, the diameters of the first aluminum column 404, the second aluminum column 405, the third aluminum column 601, and the fourth aluminum column 602 are all 7 mm, and the thickness of the steel pressing sheet 606 is 3 mm.

[0088] In the above technical solution, a dual-purpose test device for thermal optical test and thermal balance test of an optical remote sensing satellite provided by the present invention has the following beneficial effects:

[0089] When the driving device rotates to 0°, it does not affect the field of view of the optical camera, enabling the optical camera to conduct thermal optical tests in a reasonable vacuum and low-temperature environment. When the driving device rotates to 90°, the radiation plate temperature control and the cryogenic heat sink are reasonably utilized to conduct the thermal balance test of the remote sensing satellite. At the same time, it ensures that the mechanism components will not pose a threat to the safety of the satellite.

[0090] The present invention allows the environmental simulator to conduct the camera thermal optical test and the satellite thermal balance test crosswise in the same session with only one startup. It can at least shorten the test cycle by about 5 days, save more than 30% of the satellite test costs, reduce the labor cost by 40%, and at the same time reduce the risks in multiple satellite transportation operations.

[0091] Only some exemplary embodiments of the present invention have been described by way of illustration. Without doubt, for those of ordinary skill in the art, the described embodiments can be modified in various different ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and description are illustrative in nature and should not be construed as limiting the scope of the claims of the present invention.

Claims

1. An experimental device for both thermal-optical test and thermal balance test of an optical remote sensing satellite, characterized in that, the experimental device includes: a satellite support tooling (1), which is arranged on a load platform (12) and connected to a remote sensing satellite (13), and thermal insulation treatment is performed at the connection between the satellite support tooling (1) and the remote sensing satellite (13); a first radiation metal plate (2) installed at the light inlet of an optical camera (14); a second radiation metal plate (9) placed parallel to the outer surface of the remote sensing satellite (13) at a distance of 100 mm to 200 mm, and the thicknesses of both the first radiation metal plate (2) and the second radiation metal plate (9) are 1 to 3 mm; a thin film heating sheet (3) provided on the outer surfaces of the first radiation metal plate (2) and the second radiation metal plate (9); the experimental device further includes: a rotating link device (4) connected to the first radiation metal plate (2), the rotating link device (4) includes a link (401), and one end is sleeved on the link (401) and fixed by a shaft pin (402), and the other end is fixedly installed in an installation bayonet (403) of the first radiation metal plate (2) by a screw. A worm gear (505) is fixed on the link (401) through the shaft pin (402), and further includes a first aluminum column (404) and a second aluminum column (405) welded to the lower part of the link (401) from different directions; a driving device (5) capable of driving the rotating end of the rotating link device (4) to rotate, the driving device (5) includes a motor bracket (501), and a stepping motor (503) and a worm (504) installed on the motor bracket (501) through a first bearing (502). Two second thin film heating sheets (506) are pasted on the outer surface of the stepping motor (503) housing and the motor bracket (501), and further includes a worm gear (505) meshing with the worm (504); a locking mechanism (6) arranged on a mechanism base (7) and used to lock the rotation angle of the rotating link device (4), the locking mechanism (6) includes a third aluminum column (601) and a fourth aluminum column (602) fixedly connected to the upper end of the mechanism base (7), and two upright ears (603) oppositely arranged on the mechanism base (7), and further includes a spring (605) and a steel pressing sheet (606) connected to the two upright ears (603) through a spring shaft (604), and an active mechanism is formed by the spring (605) and the steel pressing sheet (606); the lengths of the first aluminum column (404) and the second aluminum column (405) are both 95 mm and form a horizontal plane, and the angle is 110°; the heights of the third aluminum column (601) and the fourth aluminum column (602) are both 90 mm, and the axial distances between the axes of the third aluminum column (601) and the fourth aluminum column (602) and the axis of the link (401) are equal, which is 80 mm; When the rotation angle of the stepper motor (503) is 0°, the edge of the first aluminum column (404) contacts the edge of the third aluminum column (601). When the rotation angle of the stepper motor (503) is 90°, the edge of the second aluminum column (405) contacts the edge of the fourth aluminum column (602). The mechanism base (7) includes an aluminum plate (701) with a thickness of 5 mm, and a second bearing (702) provided at the center of the plate body of the aluminum plate (701). The connecting rod (401) can be inserted into the second bearing (702).

2. A dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite according to claim 1, characterized in that, Both the first radiation metal plate (2) and the second radiation metal plate (9) are radiation aluminum plates, and the thickness of the radiation aluminum plate is 2 mm. The inner surface of the radiation aluminum plate facing the satellite body is subjected to black anodizing electroplating treatment, and the surface emissivity is ≥ 0.85; Four pieces of the film heating sheets (3) are pasted on the outer surfaces of the first radiation metal plate (2) and the second radiation metal plate (9) facing the space environment simulator (11).

3. A dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite according to claim 1, characterized in that, The satellite support tooling (1) includes four support columns (102) erected vertically, and four angular polyimide heat insulation pads (8) are embedded at the connection between the satellite support tooling (1) and the remote sensing satellite (13).

4. A dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite according to claim 1, characterized in that, Four height adjustment bolts (101) are installed at the bottom of the satellite support tooling (1) so that the optical axis of the optical camera (14) is parallel to that of the collimator (15) and within the imaging range.

5. A dual-purpose test device for thermal-optical test and thermal balance test of an optical remote sensing satellite according to claim 1, characterized in that, The diameters of the first aluminum column (404), the second aluminum column (405), the third aluminum column (601) and the fourth aluminum column (602) are all 7 mm, and the thickness of the steel pressing sheet (606) is 3 mm.

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