Spacecraft vacuum thermal test motion simulation device

Abstract

The invention relates to the technical field of spacecraft vacuum thermal tests, in particular to a spacecraft vacuum thermal test motion simulation device, which comprises a base, a pitching mechanism, a rotating mechanism and a transmission monitoring assembly, and is characterized in that the pitching mechanism is arranged on the base; the rotating mechanism is arranged on the pitching mechanism and connected with the pitching mechanism, and the rotating mechanism can drive the load to rotate around the first axis; the pitching mechanism drives the rotating mechanism to swing around a second axis, so that the load can swing around the second axis; the transmission monitoring assembly is connected with the rotating mechanism and used for detecting whether the power input end of the rotating mechanism and the power output end of the rotating mechanism conduct synchronous transmission or not. According to the application, the power input end of the rotating mechanism and the power output end of the rotating mechanism can be ensured to keep synchronous transmission in the test process, so that when the rotating mechanism rotates at a certain speed, the load can be effectively ensured to complete the operation at a set angle within a set time, thereby restoring the trueness of the vacuum thermal test of the spacecraft, and improving the test efficiency. And the accuracy of test data is improved.

Description

Technical Field

[0001] The present application relates to the technical field of spacecraft vacuum thermal testing, and in particular to a spacecraft vacuum thermal testing motion simulation device. Background Art

[0002] For spacecraft, vacuum thermal test is an extremely important test, which is usually carried out before leaving the factory. It is time-sensitive and costly. Spacecraft vacuum thermal test is usually carried out in a space environment simulator, which can simulate the vacuum, cold black environment and solar radiation (heat flow) of space. There are generally two ways of heat flow simulation, arrival heat flow simulation and incident heat flow simulation.

[0003] For a long time, the heat flow simulation of my country's spacecraft ground thermal tests has been using infrared heating simulation methods (arrival heat flow simulation). Due to the limitation of equipment capabilities, the simulation method of direct heating by solar simulators (incident heat flow simulation) is rarely used. In 2019, the solar simulation system began to be used for thermal balance tests of large and medium-sized satellites. The solar simulation system generally includes a solar simulation device for heating and a motion simulation device for carrying satellite operations.

[0004] Among them, the motion simulation device needs to carry a load of less than 1 t and move at a set speed in a vacuum and low temperature environment. Due to transmission problems, the motor will rotate but the rotating table will not move, or the motor and the rotating table will be out of sync, and the load will not be able to complete the operation of the set angle within the specified time, resulting in failure of normal testing, etc. Therefore, a highly reliable motion simulation device is required to ensure the smooth progress of the test. Summary of the invention

[0005] The present application provides a spacecraft vacuum thermal test motion simulation device to solve the problem in the prior art that due to transmission problems, the motor rotates but the turntable does not move, or the motor and the turntable are out of sync, and the load cannot complete the operation of a predetermined angle within the specified time, resulting in the inability to test normally.

[0006] On the one hand, the present application provides a spacecraft vacuum thermal test motion simulation device, comprising:

[0007] Pedestal;

[0008] A pitch mechanism is arranged on the base;

[0009] A rotating mechanism is disposed on the pitch mechanism and connected to the pitch mechanism, and the rotating mechanism can drive the load to rotate around the first axis;

[0010] The pitch mechanism can make the load swing around the second axis by driving the rotating mechanism to swing around the second axis;

[0011] The transmission monitoring component is connected to the rotating mechanism and is used to detect whether the power input end of the rotating mechanism and the power output end of the rotating mechanism are synchronously transmitted.

[0012] In one possible design, the rotating mechanism includes:

[0013] First Drive;

[0014] A worm gear drivingly connected to an output shaft of the first driver;

[0015] A worm wheel connected to the worm drive;

[0016] The rotating table is installed on the end face of the worm wheel. The rotating table can rotate around the axis of the worm wheel under the drive of the worm wheel. The rotating table is used to bear the load.

[0017] In one possible design, the transmission monitoring assembly includes:

[0018] A grating ruler is connected to the worm gear and is used to detect the change in angular displacement of the worm gear within a preset time;

[0019] The first encoder is provided with a first synchronous wheel, the worm is provided with a second driving wheel, the first synchronous wheel and the second synchronous wheel have equal diameters and are connected through a belt drive, and the first encoder is used to detect the angular displacement change of the worm within a preset time.

[0020] In a possible design, the rotating mechanism further includes a bottom plate, a central shaft is arranged on the bottom plate, the worm gear is sleeved on the central shaft, an adapter plate is installed on the end surface of the worm gear away from the bottom plate, and the central shaft passes through the central hole of the adapter plate;

[0021] The grating ruler includes a scale grating and a grating reading head. The scale grating is ring-shaped and installed at the center hole of the adapter plate. The scale grating is coaxially arranged with the central axis. There is a gap between the outer wall of the central axis and the inner wall of the scale grating; the grating reading head is installed on the central axis.

[0022] In a possible design, the central shaft is a hollow shaft penetrating through the bottom plate.

[0023] In a possible design, it also includes an adapter flange, which is detachably connected to the rotating table and is used to be detachably connected to the load;

[0024] And / or, it also includes a cold plate, which is arranged between the rotating mechanism and the load, and the cold plate is used to separate the load from the pitch mechanism and the rotating mechanism.

[0025] In a possible design, the first driver includes a first motor and a second motor, and an output shaft of the first motor and an output shaft of the second motor are drivingly connected to opposite ends of the worm respectively.

[0026] In one possible design, the pitch mechanism includes:

[0027] Second drive;

[0028] A transmission shaft drivingly connected to an output shaft of the second driver;

[0029] A transmission gear is sleeved on the transmission shaft;

[0030] The sector gear is installed on the base and connected to the rotating mechanism. The sector gear can make the rotating mechanism swing around the axis of the transmission shaft by meshing with the transmission gear.

[0031] In a possible design, the pitch mechanism further includes a second encoder, which is coaxially connected to the transmission shaft.

[0032] In one possible design, it also includes:

[0033] The guide slide is arranged between the rotating mechanism and the load, has an annular groove structure, and has a radial opening. The guide slide is used to place the cable of the load;

[0034] A film heater is attached to the outer wall of the guide slide and is used to heat the guide slide;

[0035] The temperature sensor is arranged on the guide slide and is used to detect the temperature of the guide slide.

[0036] The beneficial effects of this application are as follows:

[0037] The spacecraft vacuum thermal test motion simulation device of the present application can enable the load to achieve state changes of different rotation speeds and different pitch angles by setting a pitch mechanism and a rotation mechanism, so that the load can adapt to the different requirements of low orbit, medium orbit or high orbit operation; by setting a transmission monitoring component, the transmission monitoring component is used to detect whether the power input end of the rotating mechanism and the power output end of the rotating mechanism are synchronously transmitted. During the test, it is ensured that the power input end of the rotating mechanism and the power output end of the rotating mechanism maintain synchronous transmission. In this way, when the rotating mechanism rotates at a certain speed, it can effectively ensure that the load completes the operation of a predetermined angle within the specified time, thereby restoring the authenticity of the spacecraft vacuum thermal test and improving the accuracy of the test data. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0039] Figure 1 A schematic diagram of the use status of the spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application;

[0040] Figure 2 A schematic diagram of the overall structure of a spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application;

[0041] Figure 3 A schematic diagram of the structure of the pitch mechanism of the spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application;

[0042] Figure 4 A schematic diagram of the structure of the rotating mechanism of the spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application;

[0043] Figure 5 for Figure 4 A cross-sectional view along the middle line AA;

[0044] Figure 6 A schematic diagram of the internal structure of the rotating mechanism of the spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application;

[0045] Figure 7 A schematic diagram of the mechanism of the photoelectric sensor of the rotating mechanism of the spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application.

[0046] Figure 8 A control logic block diagram of a spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application.

[0047] Reference numerals:

[0048] 100, base; 200, pitch mechanism; 210, second driver; 220, transmission shaft; 230, transmission gear; 240, sector gear; 250, first photoelectric sensor; 260, second photoelectric sensor; 270, light-transmitting slot; 280, second encoder; 290, swing shaft; 300, rotating mechanism; 310, first driver; 311, first motor; 312, second motor; 320, worm; 330, worm wheel; 340, rotating Turntable; 350, adapter flange; 360, base plate; 370, center axis; 380, adapter plate; 390, motor heat shield; 400, grating ruler; 410, scale grating; 420, grating reading head; 500, first encoder; 510, first synchronous wheel; 520, second synchronous wheel; 530, belt; 600, fixing plate; 700, cold plate; 800, guide slide; 900, load; 910, satellite bracket; 920, detection cable. DETAILED DESCRIPTION

[0049] The technical solution of the present application will be described clearly and completely below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0050] Combine the following Figure 1-Figure 8 , describing the spacecraft vacuum thermal test motion simulation device provided in an embodiment of the present application.

[0051] Reference Figure 1 , Figure 2 As shown, an embodiment of the present application provides a spacecraft vacuum thermal test motion simulation device, including a base 100, a pitch mechanism 200, a rotation mechanism 300 and a transmission monitoring component, wherein the load 900 is a satellite, and the satellite is installed on the rotation mechanism 300 through a satellite bracket 910.

[0052] Reference Figure 3 As shown, the pitch mechanism 200 is arranged on the base 100, and the pitch mechanism 200 includes a second driver 210, a transmission shaft 220, a transmission gear 230 and a fan gear 240. The second driver 210 adopts a stepping motor, and a heat insulation cover is arranged outside the stepping motor. The transmission shaft 220 is connected to the output shaft of the second driver 210 through a transmission structure, for example, through a bevel gear or a worm gear transmission structure or a coupling; the transmission gear 230 is sleeved on the transmission shaft 220 and rotates with the transmission shaft 220; the fan gear 240 is rotatably installed on the base 100 through the swing shaft 290, and the edge of the fan gear 240 is provided with external teeth, and the external teeth of the fan gear 240 are meshed with the external teeth of the transmission gear 230. When the second driver 210 drives the transmission gear 230 to rotate, it further drives the fan gear 240 to rotate around the swing shaft 290 through a certain angle. In some specific embodiments, the pitch mechanism 200 further includes a second encoder 280, which is coaxially connected to the transmission shaft 220. The second encoder 280 is used to detect the angle of rotation of the transmission shaft 220, so that the load 900 achieves the target posture. Figure 7As shown, in some specific embodiments, the pitch mechanism 200 further includes a first photoelectric sensor 250 and a second photoelectric sensor 260, which are installed on the base 100 and at positions blocked by the fan gear 240, the first photoelectric sensor 250 is located on the left side of the left side of the angular bisector of the fan gear 240, the second photoelectric sensor 260 is located on the right side of the angular bisector of the fan gear 240, the distance between the first photoelectric sensor 250 and the swing shaft 290 is equal to the distance between the first photoelectric sensor 250 and the swing shaft 290, both of which are a; a light-transmitting groove 270 is provided on the angular bisector of the fan gear 240, and the axis of the light-transmitting groove 270 is aligned with the swing shaft The distance 290 is also a, so that the first photoelectric sensor 250, the second photoelectric sensor 260 and the light-transmitting slot 270 are located on the same circumference; in this way, when the sector gear 240 swings to the left to the left extreme position (the position of the light-transmitting slot 270 coincides with the position of the first photoelectric sensor 250), the first photoelectric sensor 250 can detect it and promptly send a stop signal to the second driver 210; similarly, when the sector gear 240 swings to the right to the right extreme position (the position of the light-transmitting slot 270 coincides with the position of the second photoelectric sensor 260), the second photoelectric sensor 260 can detect it and promptly send a stop signal to the second driver 210, thereby improving safety and reducing damage to the mechanical transmission structure.

[0053] Reference Figure 2 , Figure 3 As shown, the rotating mechanism 300 is arranged on the pitch mechanism 200 and connected to the pitch mechanism 200. The rotating mechanism 300 can drive the load 900 to rotate around the first axis. Specifically, the sector gear 240 is provided with a plurality of connecting pins. The rotating mechanism 300 is fixedly connected to the sector gear 240 through the plurality of connecting pins. When the sector gear 240 rotates around the swing shaft 290 through a certain angle, it can also drive the entire rotating mechanism 300 and the load 900 to rotate around the swing shaft 290 through a certain angle at the same time, so as to adjust the pitch angle of the load 900. Figure 4 , Figure 5 , Figure 6 As shown, the rotating mechanism 300 includes a first driver 310, a worm 320, a worm wheel 330 and a rotating platform 340. The first driver 310 adopts a stepping motor, and a motor heat shield 390 is arranged outside the stepping motor. The worm 320 is arranged in a worm housing, and an opening is arranged on the side of the worm housing close to the worm wheel. The worm 320 is connected to the output shaft of the first driver 310 through a coupling; the worm wheel 330 is connected to the worm 320 through a coupling; the rotating platform 340 is installed on the upper end surface of the worm wheel 330 through screws. The rotating platform 340 can rotate around the axis of the worm wheel 330 under the drive of the worm wheel 330, so that the load 900 on the rotating platform 340 rotates around the axis of the worm wheel 330. In this way, the load 900 can achieve changes in the rotation angle and the pitch angle.

[0054] Due to the limitation of the configuration, a single motor structure is generally used, and conventional vacuum motors are mostly used. During the movement, the vacuum motor will have many fault phenomena, such as failure or even burning due to heat dissipation difficulties, causing the test to be interrupted. If the test is to be continued, the environment can only be restored to normal temperature and pressure for repair or replacement, which takes a long time, seriously affecting the progress of the test and greatly increasing the cost.

[0055] Therefore, refer to Figure 6 As shown, the first driver 310 includes a first motor 311 and a second motor 312, and the output shaft of the first motor 311 and the output shaft of the second motor 312 are respectively connected to the opposite ends of the worm 320. The first motor 311 and the second motor 312 can operate simultaneously or independently, and serve as backup for each other. In this way, when the first motor 311 or the second motor 312 fails, another normal motor can drive the failed motor to rotate, which solves the problem of single-point failure of the motor, avoids interruption of large-scale tests due to motor failure, achieves high reliability, and reduces test costs.

[0056] The transmission monitoring component is connected to the rotating mechanism 300, and is used to detect whether the power input end of the rotating mechanism 300 and the power output end of the rotating mechanism 300 are synchronously transmitted. It should be noted that synchronous transmission means that the actual transmission ratio of the power input end of the rotating mechanism 300 and the power output end of the rotating mechanism 300 is equal to the theoretical transmission ratio. The transmission monitoring component is used to detect whether the power input end of the rotating mechanism 300 and the power output end of the rotating mechanism 300 are synchronously transmitted. During the test, it can be ensured that the actual transmission ratio of the power input end of the rotating mechanism 300 and the power output end of the rotating mechanism 300 is equal to the theoretical transmission ratio, so that when the rotating mechanism 300 rotates at a certain speed, it can effectively ensure that the load 900 completes the operation of a predetermined angle within a specified time.

[0057] Reference Figure 6As shown, in some specific embodiments, the transmission monitoring component includes a grating ruler 400 and a first encoder 500. The grating ruler 400 is connected to the worm wheel 330 and is used to detect the angular displacement change of the worm wheel 330 within a preset time; the first encoder 500 is connected to the output shaft of the first driver 310 and is used to detect the angular displacement change of the worm 320 within a preset time. The first driver 310 adopts a stepper motor, but since the stepper motor has only a single output shaft, it is impossible to install an encoder at the rear end of the stepper motor. Therefore, pulleys with equal diameters are installed on the worm 320 and the encoder respectively. Specifically, the first encoder 500 is provided with a first synchronous wheel 510, and the worm 320 is provided with a second driving wheel. The first synchronous wheel 510 and the second synchronous wheel 520 have equal diameters and are connected through a belt 530. The belt 530 transmission makes the encoder and the worm 320 rotate synchronously. Therefore, the first encoder 500 can detect the angular displacement change of the worm 320 within a preset time. The ratio of the angular displacement changes of the worm wheel 330 and the worm 320 within the preset time are compared with the theoretical ratio, so that the transmission mechanism can be adjusted in time before the test to ensure the synchronous transmission of the rotating mechanism 300, thereby effectively ensuring that the load 900 completes the operation of the predetermined angle within the specified time, trying to restore the authenticity of the spacecraft vacuum thermal test and improve the accuracy of the test data.

[0058] Reference Figure 5 As shown, the rotating mechanism 300 also includes a base plate 360, on which a central shaft 370 is arranged, and the worm wheel 330 is sleeved on the central shaft 370 through a bearing, and an adapter plate 380 is installed on the end surface of the worm wheel 330 away from the base plate 360, and the adapter plate 380 rotates synchronously with the worm wheel 330, and the central shaft 370 passes through the central hole of the adapter plate 380; the grating ruler 400 includes a scale grating 410 and a grating reading head 420, the scale grating 410 is annular, and the scale grating 410 is installed on the adapter plate 380 At the center hole of the rotating table 340, the scale grating 410 rotates at an angular velocity equal to that of the worm gear 330 driven by the adapter plate 380; the scale grating 410 is coaxially arranged with the center shaft 370, and there is a gap between the outer wall of the center shaft 370 and the inner wall of the scale grating 410; the grating reading head 420 is installed on the center shaft 370, and a groove is provided on the lower end surface of the rotating table 340 for avoiding the scale grating 410 and the grating reading head 420, so that the angular displacement of the worm gear 330 can be obtained through the grating reading head 420.

[0059] In some specific embodiments, the central shaft 370 is a hollow shaft that passes through the base plate 360. By designing the central shaft 370 as a hollow shaft, the lead wires of the grating scale 400 and the lead wires of the temperature sensor can be led out from the hollow shaft.

[0060] Reference Figure 5As shown, in some specific embodiments, the device also includes an adapter flange 350, and the adapter flange 350 is detachably connected to the rotating table 340, such as a bolt connection, and the adapter flange 350 is used to be detachably connected to the load 900, such as a bolt connection. In this way, different adapter flanges 350 can be designed according to different loads 900, which facilitates the installation and disassembly of the load 900.

[0061] Reference Figure 5 , Figure 6 As shown, in some specific embodiments, the device also includes a fixed plate 600 and a cold plate 700. The fixed plate 600 is bolted to the base plate 360 ​​and neither rotates. The fixed plate 600 is provided with an avoidance hole for avoiding the adapter flange 350 and the load 900. The cold plate 700 is installed on the fixed plate 600, and the cold plate 700 is located between the rotating mechanism 300 and the load 900. The cold plate 700 is used to separate the load 900 from the pitch mechanism 200 and the rotating mechanism 300, thereby reducing the background heat flow and achieving a better solar simulation effect.

[0062] Reference Figure 2 As shown, in some embodiments of the present application, the device further includes a guide slide 800, a film heater and a temperature sensor. The guide slide 800 is installed and fixed on the fixed plate 600. The guide slide 800 is located between the rotating mechanism 300 and the load 900, and is in an annular groove structure, used to carry the detection cable 920 of the load 900. The guide slide 800 has a radial opening, which is used to lead the detection cable 920 of the load 900 outward. When the load 900 rotates, the detection cable 920 moves orderly in the guide slide 800. In some specific embodiments, a ball is provided on the inner bottom wall of the guide slide 800, and the ball can reduce the friction between the detection cable 920 and the inner bottom wall of the guide slide 800, so as to ensure that the detection cable 920 can slide smoothly in the guide slide 800.

[0063] Since the test needs to reach a low temperature environment of -40-50℃, the detection cable 920 is easy to harden in the low temperature environment, affecting the signal transmission of the detection cable 920. Especially when the load 900 moves, the unstable signal transmission of the detection cable 920 will affect the normal progress of the test. Therefore, in some specific embodiments, a thin film heater is attached to the outer wall of the guide slide 800 to heat the guide slide 800; a plurality of temperature sensors are also arranged at intervals on the guide slide 800 to detect the temperature at different positions of the guide slide 800. In this way, it can ensure that the detection cable 920 is at a suitable temperature during the test, which is conducive to maintaining stable signal transmission.

[0064] The control cabinet also includes a drive unit installed in the control cabinet, and the PLC outputs pulses and direction signals to the drive unit to control the movement of the first driver 310 and the second driver 210; specifically, the rotation of the load 900 is driven by the first motor 311 and the second motor 312, and the first motor 311 and the second motor 312 move synchronously clockwise or counterclockwise, so that the worm 320 is driven in the same direction; the first encoder 500 and the grating ruler 400 rotate with the rotation of the rotating table 340 to feedback the real-time position of the load 900; the change of the pitch angle of the load 900 depends on the second driver 210, the second The encoder 280 is used to feedback the pitch angle of the load 900; in the case of non-overload, the rotation speed and stop position of the first motor 311 and the second motor 312 depend only on the frequency and number of pulses of the pulse signal, and are not affected by changes in the load 900. When the drive unit receives a pulse signal, it drives the first driver 310 and the second driver 210 to rotate a fixed angle in the set direction. The angular displacement can be controlled by controlling the number of pulses, thereby achieving the purpose of accurate positioning; at the same time, the speed and acceleration of the motor rotation can be controlled by controlling the pulse frequency, thereby achieving the purpose of speed regulation.

[0065] Reference Figure 8 As shown, the functions of the control system corresponding to the above-mentioned device include power-on enabling of the first driver 310 and the second driver 210, power-off emergency stop, fault reset, setting the origin, setting the movement speed, starting the absolute position movement, starting the relative position movement, forward jogging, reverse jogging, axis stop, out-of-tolerance alarm limit, and out-of-tolerance alarm indication.

[0066] The device of the present application is used for thermal balance tests of multiple high-orbit communication satellites, achieving the rotation requirements of different working conditions, including 24h / circle, multiple fixed-angle fixed points, completing the tests of transient and steady-state conditions, meeting the requirements for verifying the rationality of the satellite's thermal design, and contributing to the satellite of this mission entering the prototype stage as scheduled.

[0067] The device of the present application can also be used for the thermal balance test of Starlink satellites to achieve the high-speed rotation requirements of low-orbit conditions, 110 minutes per revolution, simulate the thermal balance state of the satellite, complete the tests of transient and steady-state conditions, and meet the requirements for verifying the rationality of the satellite's thermal design, contributing to the scheduled transition of the satellite for this mission into the prototype stage.

[0068] The device of the present application can also be used for testing of ion thrusters in the field of deep space exploration. It has completed the first domestic thermal deformation test of ion thrusters and realized multiple fixed-angle fixed-point tests under low background heat flux, achieving the expected results.

[0069] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships 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 referred device or element 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.

[0070] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0071] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0072] In the present application, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0073] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A spacecraft vacuum thermal test motion simulation device, characterized in that: include: Pedestal; A pitch mechanism, arranged on the base; A rotating mechanism, disposed on the pitch mechanism and connected to the pitch mechanism, the rotating mechanism being capable of driving the load to rotate around a first axis; The pitch mechanism can make the load swing around the second axis by driving the rotating mechanism to swing around the second axis; The transmission monitoring component is connected to the rotating mechanism and is used to detect whether the power input end of the rotating mechanism and the power output end of the rotating mechanism are synchronously transmitted.

2. The spacecraft vacuum thermal test motion simulation device according to claim 1, characterized in that: The rotating mechanism comprises: First Drive; a worm gear drivingly connected to an output shaft of the first drive; A worm wheel, drivingly connected to the worm; A rotating table is installed on the end surface of the worm wheel. The rotating table can rotate around the axis of the worm wheel when driven by the worm wheel. The rotating table is used to carry the load.

3. The spacecraft vacuum thermal test motion simulation device according to claim 2, characterized in that: The transmission monitoring component comprises: A grating ruler connected to the worm gear and used to detect the angular displacement change of the worm gear within a preset time; A first encoder, wherein a first synchronous wheel is sleeved on the first encoder, and a second driving wheel is sleeved on the worm. The first synchronous wheel and the second synchronous wheel have the same diameter and are connected through a belt drive. The first encoder is used to detect the angular displacement change of the worm within a preset time.

4. The spacecraft vacuum thermal test motion simulation device according to claim 3, characterized in that: The rotating mechanism further comprises a bottom plate, a central shaft is arranged on the bottom plate, the worm gear is sleeved on the central shaft, an adapter plate is mounted on the end surface of the worm gear away from the bottom plate, and the central shaft passes through the central hole of the adapter plate; The grating ruler includes a scale grating and a grating reading head. The scale grating is ring-shaped and is installed at the center hole of the adapter plate. The scale grating is coaxially arranged with the central axis. There is a gap between the outer wall of the central axis and the inner wall of the scale grating; the grating reading head is installed on the central axis.

5. The spacecraft vacuum thermal test motion simulation device according to claim 4, characterized in that: The central axis is a hollow axis passing through the bottom plate.

6. The spacecraft vacuum thermal test motion simulation device according to claim 2, characterized in that: It also includes an adapter flange, which is detachably connected to the rotating table and is used to be detachably connected to the load; And / or, it further includes a cold plate, which is arranged between the rotating mechanism and the load, and the cold plate is used to separate the load from the pitch mechanism and the rotating mechanism.

7. The spacecraft vacuum thermal test motion simulation device according to claim 2, characterized in that: The first driver includes a first motor and a second motor. The output shaft of the first motor and the output shaft of the second motor are respectively drivingly connected to opposite ends of the worm.

8. The spacecraft vacuum thermal test motion simulation device according to any one of claims 1 to 7, characterized in that: The pitch mechanism comprises: Second drive; a transmission shaft, drivingly connected to an output shaft of the second driver; A transmission gear, sleeved on the transmission shaft; A sector gear is mounted on the base and connected to the rotating mechanism. The sector gear can make the rotating mechanism swing around the axis of the transmission shaft by meshing with the transmission gear.

9. The spacecraft vacuum thermal test motion simulation device according to claim 8, characterized in that: The pitch mechanism further includes a second encoder, which is coaxially connected to the transmission shaft.

10. The spacecraft vacuum thermal test motion simulation device according to any one of claims 1 to 7, characterized in that: Also includes: A guide slideway is provided between the rotating mechanism and the load, has an annular groove structure, and has a radial opening, and the guide slideway is used to place the cable of the load; A film heater is attached to the outer wall of the guide slide and is used to heat the guide slide; A temperature sensor is arranged on the guide slide and is used to detect the temperature of the guide slide.

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