Spacecraft vacuum thermal test motion simulation device

Abstract

The application relates to the field of spacecraft vacuum thermal test technology, 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, the pitching mechanism is arranged on the base; the rotating mechanism is arranged on the pitching mechanism and is connected with the pitching mechanism, the rotating mechanism can drive a load to rotate around a first axis; the pitching mechanism can drive the rotating mechanism to swing around a second axis, so that the load swings around the second axis; the transmission monitoring assembly is connected with the rotating mechanism and is used for detecting whether the power input end of the rotating mechanism and the power output end of the rotating mechanism are synchronously transmitted. The application can ensure that the power input end of the rotating mechanism and the power output end of the rotating mechanism are synchronously transmitted during the test process, so that when the rotating mechanism rotates at a certain speed, the load can effectively complete the rotation of a specified angle within a specified time, thereby restoring the authenticity of the spacecraft vacuum thermal test and improving the accuracy of the test data.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of spacecraft vacuum thermal test technology, in particular to a spacecraft vacuum thermal test motion simulation device. BACKGROUND

[0002] For spacecraft, vacuum thermal test is an extremely important test, which is generally carried out before delivery, and the time is tight and the cost is extremely high. The spacecraft vacuum thermal test is generally carried out in a space environment simulator, which can simulate the vacuum, cold black environment and solar irradiation (heat flow) of space. Among them, there are generally two ways to simulate heat flow, namely, arriving heat flow simulation and incident heat flow simulation.

[0003] For a long time, the heat flow simulation of the ground thermal test of China's spacecraft has always used the infrared heating simulation method (arriving heat flow simulation). Due to the limitation of equipment capacity, the direct heating simulation method (incident heat flow simulation) of the solar simulator is rarely used. In 2019, the solar simulation system began to be used for large and medium-sized satellite thermal balance test work. The solar simulation system generally includes a solar simulation device for heating and a motion simulation device for carrying the satellite operation.

[0004] Among them, the motion simulation device needs to carry a load of less than 1t to move at a set speed in a vacuum and low-temperature environment. Due to the transmission problem, the motor may rotate but the rotary table may not move, or the motor and the rotary table may be out of sync, which cannot make the load complete the predetermined angle operation within the specified time, resulting in failure to test normally. Therefore, a motion simulation device with high reliability is needed to ensure that the test is carried out smoothly. SUMMARY

[0005] The present application provides a spacecraft vacuum thermal test motion simulation device to solve the problem that in the prior art, due to the transmission problem, the motor may rotate but the rotary table may not move, or the motor and the rotary table may be out of sync, which cannot make the load complete the predetermined angle operation within the specified time, resulting in failure to test normally.

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

[0007] a base;

[0008] a pitching mechanism arranged on the base;

[0009] a rotating mechanism arranged on the pitching mechanism and connected with the pitching mechanism, the rotating mechanism being capable of driving the load to rotate around a first axis;

[0010] the pitching mechanism is capable of driving the rotating mechanism to swing around a second axis to make the load swing around the second axis;

[0011] The transmission monitoring assembly is connected with 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 a possible design, the rotating mechanism comprises:

[0013] The first driver;

[0014] The worm is in transmission connection with the output shaft of the first driver;

[0015] The worm gear is in transmission connection with the worm;

[0016] The rotating table is installed on the end face of the worm gear and can rotate around the axis of the worm gear under the driving of the worm gear, and the rotating table is used to carry the load.

[0017] In a possible design, the transmission monitoring assembly comprises:

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

[0019] The first encoder is sleeved with the first synchronous wheel, the worm is sleeved with the second synchronous wheel, the diameters of the first synchronous wheel and the second synchronous wheel are equal and the first synchronous wheel and the second synchronous wheel are in transmission connection through the belt, and the first encoder is used to detect the angular displacement change amount of the worm within a preset time.

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

[0021] The grating ruler comprises a scale grating and a grating reading head, the scale grating is annular, the scale grating is installed at the center hole of the adapter plate, the scale grating is coaxially arranged with the central shaft, and there is a gap between the outer wall of the central shaft and the inner wall of the scale grating; and the grating reading head is installed on the central shaft.

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

[0023] In a possible design, further comprising an adapter flange, the adapter flange is detachably connected with the rotating table, and the adapter flange is used to be detachably connected with the load.

[0024] And / or, further comprising a cold plate, the cold plate is arranged between the rotating mechanism and the load, and the cold plate is used to separate the load from the pitching mechanism and the rotating mechanism.

[0025] In a possible design, the first driver comprises a first motor and a second motor, and the output shaft of the first motor and the output shaft of the second motor are respectively in transmission connection with the opposite ends of the worm.

[0026] In a possible design, the pitching mechanism comprises:

[0027] a second driver;

[0028] a transmission shaft, in transmission connection with an output shaft of the second driver;

[0029] a transmission gear, sleeved on the transmission shaft;

[0030] a sector gear, mounted on the base and connected with the rotating mechanism, the sector gear being capable of swinging the rotating mechanism around the axis of the transmission shaft by intermeshing with the transmission gear.

[0031] In a possible design, the pitching mechanism further comprises a second encoder, coaxially connected with the transmission shaft.

[0032] In a possible design, the spacecraft vacuum thermal test motion simulation device further comprises:

[0033] a guide slide, arranged between the rotating mechanism and the load, in a ring groove structure and having a radial opening, the guide slide being used for placing a cable of the load;

[0034] a film heater, attached to an outer sidewall of the guide slide, used for heating the guide slide;

[0035] a temperature sensor, arranged on the guide slide, used for detecting the temperature of the guide slide.

[0036] The spacecraft vacuum thermal test motion simulation device has the following beneficial effects:

[0037] The spacecraft vacuum thermal test motion simulation device of the present application can make the load change in different rotating speeds and different pitching angles by setting the pitching mechanism and the rotating mechanism, so that the load can adapt to different requirements of low-orbit, medium-orbit or high-orbit operation; the transmission monitoring assembly is set to detect whether the power input end of the rotating mechanism and the power output end of the rotating mechanism are synchronously transmitted, and in the test, the power input end of the rotating mechanism and the power output end of the rotating mechanism are kept synchronous transmission, so that when the rotating mechanism rotates at a certain speed, the load can effectively complete the rotation of a specified angle within a specified time, thereby restoring the authenticity of the spacecraft vacuum thermal test and improving the accuracy of the test data. BRIEF DESCRIPTION OF DRAWINGS

[0038] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the description of the specific embodiments or the prior art. Obviously, the drawings described below are some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0039] Figure 1 A schematic diagram of the use state of the spacecraft vacuum thermal test motion simulation device provided by the embodiment of the present application is shown in FIG. 1.

[0040] Figure 2 A schematic diagram of the overall structure of the spacecraft vacuum thermal test motion simulation device provided by the embodiment of the present application is shown in FIG. 2.

[0041] Figure 3 A schematic diagram of the structure of the pitching mechanism of the spacecraft vacuum thermal test motion simulation device provided by the embodiment of the present application is shown in FIG. 3.

[0042] Figure 4 A schematic diagram of the structure of the rotating mechanism of the spacecraft vacuum thermal test motion simulation device provided by the embodiment of the present application is shown in FIG. 4.

[0043] Figure 5 A schematic diagram of the internal structure of the rotating mechanism of the spacecraft vacuum thermal test motion simulation device provided by the embodiment of the present application is shown in FIG. 5. Figure 4 A sectional view along A-A.

[0044] Figure 6 A schematic diagram of the internal structure of the rotating mechanism of the spacecraft vacuum thermal test motion simulation device provided by the embodiment of the present application is shown in FIG. 5.

[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 by the embodiment of the present application is shown in FIG. 6.

[0046] Figure 8 A control logic block diagram of the spacecraft vacuum thermal test motion simulation device provided by the embodiment of the present application is shown in FIG. 7.

[0047] Reference signs:

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

[0049] The technical solutions of the present application will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0050] The technical solutions of the present application will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application. Figures 1-8 , describes a spacecraft vacuum thermal test motion simulation device provided in the embodiments of the present application.

[0051] Referring to Figure 1 , Figure 2 , the present application provides a spacecraft vacuum thermal test motion simulation device, comprising a base 100, a pitch mechanism 200, a rotation mechanism 300 and a transmission monitoring assembly, wherein the load 900 is a satellite, and the satellite is installed on the rotation mechanism 300 through a satellite support 910.

[0052] Referring to Figure 3 , the pitch mechanism 200 is arranged on the base 100, and the pitch mechanism 200 comprises a second driver 210, a transmission shaft 220, a transmission gear 230 and a sector gear 240. The second driver 210 is a stepper motor, and a heat shield is arranged outside the stepper motor. The transmission shaft 220 is drivingly connected with the output shaft of the second driver 210 through a transmission structure, such as a bevel gear or a worm gear transmission structure or a shaft coupling. The transmission gear 230 is sleeved on the transmission shaft 220 and rotates with the transmission shaft 220. The sector gear 240 is rotatably installed on the base 100 through a swing shaft 290. The edge of the sector gear 240 is provided with external teeth, and the external teeth of the sector gear 240 are engaged with the external teeth of the transmission gear 230. When the second driver 210 drives the transmission gear 230 to rotate, the sector gear 240 is further driven to rotate around the swing shaft 290 by a certain angle. In some specific embodiments, the pitch mechanism 200 further comprises a second encoder 280 coaxially connected with the transmission shaft 220. The second encoder 280 is used to detect the angle through which the transmission shaft 220 rotates, so that the load 900 realizes the target attitude. Referring to Figure 7As shown, in some embodiments, the pitching mechanism 200 further comprises a first photoelectric sensor 250 and a second photoelectric sensor 260, which are installed on the base 100 and are shielded by the sector gear 240, the first photoelectric sensor 250 is located on the left side of the angular bisector of the sector gear 240, the second photoelectric sensor 260 is located on the right side of the angular bisector of the sector gear 240, the distance between the first photoelectric sensor 250 and the pivot shaft 290 is equal to the distance between the second photoelectric sensor 260 and the pivot shaft 290, both are a; a light transmission groove 270 is formed on the angular bisector of the sector gear 240, the distance between the axis of the light transmission groove 270 and the pivot shaft 290 is also a, so that the first photoelectric sensor 250, the second photoelectric sensor 260 and the light transmission groove 270 are located on the same circumference; in this way, when the sector gear 240 swings to the left limit position (the light transmission groove 270 coincides with the position of the first photoelectric sensor 250) to the left side, the first photoelectric sensor 250 can detect and timely send a stop signal to the second driver 210; similarly, when the sector gear 240 swings to the right limit position (the light transmission groove 270 coincides with the position of the second photoelectric sensor 260) to the right side, the second photoelectric sensor 260 can detect and timely send a stop signal to the second driver 210, thereby improving safety and reducing damage to the mechanical transmission structure.

[0053] Referring to Figure 2 , Figure 3 As shown, the rotating mechanism 300 is arranged on the pitching mechanism 200 and connected with the pitching mechanism 200, and the rotating mechanism 300 can drive the load 900 to rotate around the first axis; specifically, a plurality of connecting pins are arranged on the sector gear 240, and the rotating mechanism 300 is fixedly connected with the sector gear 240 through the plurality of connecting pins, when the sector gear 240 rotates around the pivot shaft 290 by a certain angle, the entire rotating mechanism 300 and the load 900 can also rotate around the pivot shaft 290 by a certain angle at the same time, so as to adjust the pitching angle of the load 900. Referring to Figure 4 , Figure 5 , Figure 6 As shown, the rotating mechanism 300 comprises a first driver 310, a worm 320, a worm gear 330 and a rotating table 340, the first driver 310 is a stepper motor, and a motor heat shield 390 is arranged outside the stepper motor, the worm 320 is arranged in a worm shell, an opening is arranged on one side of the worm shell close to the worm gear, and the worm 320 is in transmission connection with the output shaft of the first driver 310 through a shaft coupling; the worm gear 330 is in transmission connection with the worm 320; the rotating table 340 is installed on the upper end surface of the worm gear 330 through screws, and the rotating table 340 can rotate around the axis of the worm gear 330 under the driving of the worm gear 330, so that the load 900 on the rotating table 340 rotates around the axis of the worm gear 330. In this way, the load 900 can realize the change of the rotation angle and the change of the pitching angle.

[0054] Due to the configuration, a single motor structure is generally adopted, and a conventional vacuum motor is usually used. During the movement, the vacuum motor may have many failure phenomena, such as failure and even burning due to poor heat dissipation, etc., causing the test to be interrupted. In order to continue the test, the environment needs to be restored to normal temperature and pressure for maintenance or replacement, which takes a long time, seriously affects the test progress, and greatly increases the cost.

[0055] Therefore, referring to Figure 6 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 in transmission connection with 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, the normal motor can drive the failed motor to rotate, solving the problem of single-point failure of the motor, avoiding the interruption of large-scale tests due to motor failure, achieving high reliability, and reducing test cost.

[0056] The transmission monitoring assembly is connected with the rotating mechanism 300, and is used for detecting 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. By detecting whether the power input end of the rotating mechanism 300 and the power output end of the rotating mechanism 300 are synchronously transmitted through the transmission monitoring assembly, 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 during the test. In this way, when the rotating mechanism 300 rotates at a certain speed, it can effectively ensure that the load 900 completes the rotation of the specified angle within the specified time.

[0057] Referring to Figure 6In some embodiments, the transmission monitoring assembly 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 is a stepper motor. However, 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, a pulley with the same diameter is installed on the worm 320 and the encoder, respectively. Specifically, a first synchronous pulley 510 is sleeved on the first encoder 500, and a second synchronous pulley is sleeved on the worm 320. The first synchronous pulley 510 and the second synchronous pulley 520 have the same diameter and are connected in transmission through a belt 530. The transmission of the belt 530 enables the encoder and the worm 320 to 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 a preset time is compared with the theoretical ratio. Thus, 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 rotation of a specified angle within a specified time, striving to restore the authenticity of the spacecraft vacuum thermal test, and improving the accuracy of the test data.

[0058] Referring to Figure 5 The rotating mechanism 300 further includes a bottom plate 360. The bottom plate 360 is provided with a central shaft 370. The worm wheel 330 is sleeved on the central shaft 370 through a bearing. A conversion plate 380 is installed on the end face of the worm wheel 330 away from the bottom plate 360. The conversion plate 380 rotates synchronously with the worm wheel 330. The central shaft 370 passes through the center hole of the conversion plate 380. The grating ruler 400 includes a scale grating 410 and a grating reading head 420. The scale grating 410 is annular. The scale grating 410 is installed at the center hole of the conversion plate 380 and rotates at the same angular velocity as the worm wheel 330 under the driving of the conversion plate 380. The scale grating 410 is coaxially arranged with the central shaft 370. There is a gap between the outer wall of the central shaft 370 and the inner wall of the scale grating 410. The grating reading head 420 is installed on the central shaft 370. A groove is arranged on the lower end face of the rotating table 340 to avoid the scale grating 410 and the grating reading head 420. In this way, the angular displacement of the worm wheel 330 can be obtained through the grating reading head 420.

[0059] In some embodiments, the central shaft 370 is a hollow shaft that penetrates the bottom plate 360. By designing the central shaft 370 as a hollow shaft, the lead wire of the grating ruler 400 and the lead wire of the temperature sensor can be drawn out from the hollow shaft.

[0060] Referring to Figure 5As shown, in some embodiments, the device further comprises an adapter flange 350, which is detachably connected with the rotating table 340, for example, by screwing, and is used to be detachably connected with the load 900, for example, by screwing, so that different adapter flanges 350 can be designed according to different loads 900, facilitating the installation and dismounting of the load 900.

[0061] Referring to Figure 5 , Figure 6 As shown, in some embodiments, the device further comprises a fixed plate 600 and a cold plate 700, the fixed plate 600 is bolted with the bottom plate 360 and does not rotate, and the fixed plate 600 is provided with a relief 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, and is used to separate the load 900 from the pitching mechanism 200 and the rotating mechanism 300, thereby reducing the background heat flow and making the solar simulation better.

[0062] Referring to Figure 2 As shown, in some embodiments of the present application, the device further comprises a guide slide 800, a film heater and a temperature sensor, the guide slide 800 is fixedly installed on the fixed plate 600, is located between the rotating mechanism 300 and the load 900, and has a ring groove structure for bearing the detection cable 920 of the load 900, the guide slide 800 has a radial opening for leading the detection cable 920 of the load 900 outward, and when the load 900 rotates, the detection cable 920 moves orderly in the guide slide 800. In some embodiments, a ball is arranged on the inner bottom wall of the guide slide 800, which can reduce the friction between the detection cable 920 and the inner bottom wall of the guide slide 800, and 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 minus 40-50℃, the detection cable 920 is prone to hardening 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 embodiments, a film heater is attached to the outer wall of the guide slide 800 for heating the guide slide 800, and a plurality of temperature sensors are arranged on the guide slide 800 at intervals for detecting the temperature at different positions of the guide slide 800. In this way, the detection cable 920 can be ensured to be at an appropriate temperature during the test, which is conducive to maintaining stable signal transmission.

[0064] The control cabinet is also included, and a driving unit is installed in the control cabinet. The driving unit is outputted with pulse and direction signals by a PLC to control the movement of the first driving device 310 and the second driving device 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 synchronously rotate clockwise or counterclockwise to drive the worm 320 in the same direction. The first encoder 500 and the grating ruler 400 rotate with the rotation of the rotating table 340, and are used to feedback the real-time position of the movement of the load 900. The change of the pitch angle of the load 900 is relied on the second driving device 210, and the second encoder 280 is used to feedback the pitch angle of the load 900. In the case of no overload, the rotation speed and the stop position of the first motor 311 and the second motor 312 only depend on the frequency and the pulse number of the pulse signal, and are not affected by the change of the load 900. When the driving unit receives a pulse signal, it drives the first driving device 310 and the second driving device 210 to rotate in a set direction by a fixed angle. The angle displacement can be controlled by controlling the pulse number, so as to achieve the purpose of accurate positioning. Meanwhile, the speed and the acceleration of the motor rotation can be controlled by controlling the pulse frequency, so as to achieve the purpose of speed regulation.

[0065] Referring to Figure 8 The functions of the control system corresponding to the above device include power-on enable of the first driving device 310 and the second driving device 210, power-off emergency stop, fault reset, setting origin, movement speed setting, starting absolute position movement, starting relative position movement, positive rotation jog, reverse rotation jog, shaft stop, over-limit alarm limit, and over-limit alarm indication.

[0066] The device of the present application is used for thermal balance test of multiple high-orbit communication satellites, realizes rotation requirements of different working conditions, including 24h / revolution, multiple fixed-angle fixed points, completes transient state and steady state test, and achieves the requirement of verifying the rationality of satellite thermal design, and makes a contribution to the timely transition of the task satellite into the positive sample stage.

[0067] The device of the present application can also be used for thermal balance test of the Starlink satellite, realizes the high-speed rotation requirement of the low-orbit working condition, 110 minutes / revolution, simulates the thermal balance state of the satellite, completes the transient state and steady state test, and achieves the requirement of verifying the rationality of satellite thermal design, and makes a contribution to the timely transition of the task satellite into the positive sample stage.

[0068] The device of the present application can also be used for test and test of ion thruster in the field of deep space exploration, completes the first thermal deformation test of the ion thruster in China, realizes the fixed-point test of multiple fixed angles under low background heat flow, and achieves the expected effect.

[0069] In the description of the application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate the orientation or positional relationship shown in the drawings, which are only for the convenience of describing the application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the application.

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

[0071] In this application, unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected or communicate with each other; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0072] In this application, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" and the like 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 application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine the different embodiments or examples described in the specification and the features of the different embodiments or examples without contradiction.

[0073] Although the embodiments of the application have been shown and described above, it should be understood that the above embodiments are exemplary and cannot be understood as a limitation of the application, and those skilled in the art can make changes, modifications, replacements and variations to the above embodiments within the scope of the application.

Claims

1. A spacecraft vacuum thermal test motion simulation apparatus, characterized by, The utility model relates to a kind of rotary mechanism, including: Base; Pitch mechanism, is set on the base; Rotary mechanism, is set on the pitch mechanism, is connected with the pitch mechanism, the rotary mechanism can drive load rotates around first axis; The pitch mechanism can make the load swing around second axis by driving the rotary mechanism swing around second axis; Transmission monitoring component, is connected with the rotary mechanism, for detecting whether the power input end of the rotary mechanism and the power output end of the rotary mechanism are synchronous transmission; The rotary mechanism includes: First driver; Worm, is drivingly connected with the output shaft of the first driver; Worm wheel, is drivingly connected with the worm; Rotary table, is installed on the end surface of the worm wheel, the rotary table can rotate around the axis of the worm wheel under the driving of the worm wheel, and the rotary table is used to carry the load; The transmission monitoring component includes: Grating ruler, is connected with the worm wheel, for detecting the angular displacement variation amount of the worm wheel within preset time; First encoder, first synchronizing wheel is sleeved on the first encoder, second synchronizing wheel is sleeved on the worm, the diameter of the first synchronizing wheel and the second synchronizing wheel is equal and is connected by belt drive, and the first encoder is used to detect the angular displacement variation amount of the worm within preset time; Guide slide, is set between the rotary mechanism and the load, is annular groove structure, and has opening along radial direction, and the guide slide is used to place the cable of the load; Thin film heater, is attached to the outer side wall of the guide slide, for heating the guide slide; Temperature sensor, is set on the guide slide, for detecting the temperature of the guide slide.

2. The spacecraft vacuum thermal test motion simulation apparatus of claim 1, wherein, The rotary mechanism further includes a bottom plate, a central shaft is provided on the bottom plate, the worm wheel is sleeved on the central shaft, an adapter plate is installed on the end face of the worm wheel away from the bottom plate, and the central shaft passes through the center hole of the adapter plate. The grating ruler includes a scale grating and a grating reading head. The scale grating is annular, is installed at the center hole of the adapter plate, is coaxially arranged with the central shaft, and has a gap between the outer wall of the central shaft and the inner wall of the scale grating. The grating reading head is installed on the central shaft.

3. The spacecraft vacuum thermal test motion simulation apparatus of claim 2, wherein: The central shaft is a hollow shaft penetrating through the bottom plate.

4. The spacecraft vacuum thermal test motion simulation apparatus of claim 1, wherein: Further comprising an adapter flange, the adapter flange is detachably connected with the rotary table, and the adapter flange is used to be detachably connected with the load. And / or, further comprising a cold plate, which is arranged between the rotary mechanism and the load, and is used to separate the load from the pitch mechanism and the rotary mechanism.

5. The spacecraft vacuum thermal test motion simulation apparatus of claim 1, wherein: The first driver includes a first motor and a second motor, and the output shaft of the first motor and the output shaft of the second motor are drivingly connected with opposite ends of the worm, respectively.

6. The spacecraft vacuum thermal test motion simulation apparatus according to any one of claims 1 to 5, characterized by, The pitch mechanism includes: Second driver; Transmission shaft, is drivingly connected with the output shaft of the second driver; Transmission gear, is sleeved on the transmission shaft; Sector gear, is installed on the base, is connected with the rotary mechanism, and the sector gear can make the rotary mechanism swing around the axis of the transmission shaft by intermeshing with the transmission gear.

7. The spacecraft vacuum thermal test motion simulation apparatus of claim 6, wherein: The pitch mechanism further comprises a second encoder coaxially connected with the transmission shaft.

Images