Space actuator thermal vacuum test system and method

Abstract

The application discloses a space actuator thermal vacuum test system, which comprises a data acquisition and control subsystem, a vacuum air extractor unit, a re-pressurization subsystem, a first temperature sensor, an experiment cabin, a heat sink device, at least one load system cabin, an electromagnetic brake subsystem, at least one heat shield and at least one sealing flange; the data acquisition and control subsystem is electrically connected with the space actuator to be tested, the electromagnetic brake subsystem and the first temperature sensor; the experiment cabin is connected and communicated with the load system cabin through the sealing flange, and the inside of the experiment cabin is provided with the space actuator to be tested; the electromagnetic brake subsystem is in transmission connection with the space actuator to be tested through a mechanical transmission mechanism. The application also provides a space actuator thermal vacuum test method. The application greatly improves the test efficiency, has a high degree of automation, can be applied to the test of the space actuator with a small output torque, and makes the temperature fields between the experiment cabin and the load system cabin independent of each other through the heat shield.

Description

Technical Field

[0001] This invention belongs to the field of thermal vacuum testing technology for space actuators, and specifically relates to a thermal vacuum testing system and method for space actuators. Background Technology

[0002] As aerospace technology develops towards intelligence, precision, and economy, various extravehicular units are required to be deployable to accommodate rocket fairing sizes and trackable to facilitate spacecraft signal transmission and acquisition. These requirements necessitate space actuators as execution units to complete predetermined actions. Therefore, space actuators are increasingly widely used in the aerospace field, such as satellite solar panel deployment mechanisms, Mars rover drive mechanisms, and large antenna deployment mechanisms. These units typically perform crucial functions for spacecraft, making space actuators a vital component of spacecraft performance, and even a key factor in its success or failure. Consequently, testing the space environment adaptability and reliability of space actuators has become an essential part of their development. In particular, the space environment differs from the ground environment, which can lead to thermal mismatch, increased drag or even jamming, lubrication failure, increased friction, reduced power, and shortened lifespan in space actuators. Thermal vacuum testing has gradually become the most important step in exposing defects in the design, processing, manufacturing, and assembly of space actuators.

[0003] In the prior art, thermal vacuum systems with external braking load systems, such as Figure 1 As shown, it is impossible to test multiple space actuators simultaneously, resulting in low testing efficiency and low system automation. Moreover, this method uses a magnetic fluid seal transmission system to transfer the load generated by the external braking system of the thermal vacuum system to the space actuators within the thermal vacuum system. Compared with the first method (1) of the above-mentioned constant / stepped load system within the thermal vacuum system, this method solves the problem of the size requirements of the thermal vacuum equipment and the problem of not being able to perform long-term unidirectional rotation tests. However, this method still has insurmountable defects: the resistance torque of the magnetic fluid seal transmission system is generally >0.5Nm, which can meet the requirements of large space actuators (output torque >10Nm), and the load error (which includes the resistance torque of the magnetic fluid seal transmission system) can meet the test requirements. However, for the test of micro-space actuators (output torque <10Nm), the loaded load value is smaller, and the load error requirement is smaller. However, the resistance torque of the magnetic fluid seal transmission system cannot be ignored, resulting in an excessive load transmission error (the actual loaded load value exceeds the required load value), which affects the test results and may even prevent normal use. Summary of the Invention

[0004] To address the aforementioned problems in the prior art, this invention provides a thermal vacuum testing system and method for space actuators. The technical problem to be solved by this invention is achieved through the following technical solution:

[0005] A first aspect of the present invention provides a thermal vacuum testing system for a space actuator, comprising: a data acquisition and control subsystem, a vacuum pumping unit, a repressurization subsystem, a first temperature sensor, an experimental chamber, a heat sink device, at least one load system chamber, an electromagnetic braking subsystem, at least one heat insulation screen, and at least one sealing flange.

[0006] The data acquisition and control subsystem is electrically connected to the space actuator under test, the electromagnetic braking subsystem, and the first temperature sensor.

[0007] The vacuum pump unit is connected to the experimental chamber;

[0008] The pressure-reinforcement subsystem is connected to the experimental chamber;

[0009] The experimental chamber is connected and communicates with the load system chamber via a sealing flange, and the space under test actuator is installed inside the chamber.

[0010] The heat sink device is installed inside the experimental chamber;

[0011] The electromagnetic braking subsystem is located inside the load system compartment and is connected to the space under test actuator via a mechanical transmission mechanism.

[0012] The heat insulation screen is installed at the connection between the experimental chamber and the load system chamber;

[0013] The number of sealing flanges is the same as the number of load system compartments and the number of heat shields.

[0014] In one embodiment of the present invention, the mechanical transmission mechanism includes: a transmission shaft and a coupling; the electromagnetic braking subsystem includes: an electromagnetic braking mechanism and a torque sensor;

[0015] One end of the drive shaft is connected to the output shaft of the space actuator under test via the coupling, and the other end passes through the sealing flange and the heat insulation screen to be connected to the electromagnetic braking mechanism; the coupling is located inside the experimental chamber.

[0016] The torque sensor is located inside the load system compartment and is mounted on the drive shaft;

[0017] The load system compartment is equipped with a temperature regulation device and a second temperature sensor.

[0018] The data acquisition and control subsystem is electrically connected to the electromagnetic braking mechanism, the torque sensor, and the second temperature sensor.

[0019] In one embodiment of the present invention, the cable of the space actuator under test is electrically connected to the data acquisition and control subsystem via a first through-cabin electrical connector;

[0020] The cable of the electromagnetic braking mechanism is electrically connected to the data acquisition and control subsystem via a second through-cabin electrical connector, and the cable of the torque sensor is electrically connected to the data acquisition and control subsystem via a third through-cabin electrical connector.

[0021] In one embodiment of the present invention, the heat insulation screen is disposed in the middle region of the sealing flange;

[0022] The heat insulation screen has a ring structure.

[0023] In one embodiment of the present invention, it further includes: a three-dimensional position adjustment platform and an axis alignment device disposed within the experimental chamber;

[0024] The shaft alignment device is disposed on both sides of the coupling;

[0025] The space actuator to be tested is mounted on the three-dimensional position adjustment platform.

[0026] In one embodiment of the present invention, the temperature regulating device is disposed on the inner wall of the load system compartment;

[0027] The heat sink device is installed on the inner wall of the experimental chamber.

[0028] A second aspect of the present invention provides a thermal vacuum testing method for a space actuator, which, using the testing system provided in the first aspect of the present invention, includes the following steps:

[0029] Step 1: Place the drive shaft, torque sensor, and electromagnetic braking mechanism into the load system compartment. Connect the torque sensor and electromagnetic braking mechanism to the data acquisition and control subsystem outside the compartment via the through-compartment electrical connector. The data acquisition and control subsystem controls the electromagnetic braking mechanism to output different load values ​​and acquires the torque data collected by the torque sensor.

[0030] Step 2: Install the load system compartment onto the experimental compartment via a sealing flange to achieve connection, and install a heat shield to achieve vacuum insulation between the two compartments;

[0031] Step 3: Install the space actuator under test on the three-dimensional position adjustment platform, connect the space actuator to the transmission shaft through the coupling, install the shaft alignment device on the installation interface of the coupling, and check the coaxiality of the output shaft of the coupling and the transmission shaft through the shaft alignment device. When the coaxiality is poor, adjust the position of the space actuator under test by adjusting the deviation direction obtained by the shaft alignment device on the three-dimensional position adjustment platform.

[0032] Step 4: Connect the drive circuit and signal circuit of the space actuator under test to the data acquisition and control subsystem outside the cabin through the through-cabin electrical connector to realize the drive and performance testing of the space actuator under test;

[0033] Step 5: Temperature sensors are installed on the actuator and electromagnetic braking mechanism of the space under test to collect temperature information, which is then acquired through the data acquisition and control subsystem. The time source of the data acquisition and control subsystem of the synchronous experimental chamber is synchronized, achieving time source unification and sampling frequency synchronization for the actuator and torque sensor in the space under test.

[0034] Step 6: Close the doors of the experimental chamber and the load system chamber, turn on the vacuum pump unit, and as the pressure in the experimental chamber gradually decreases, the pressure in the load system chamber decreases synchronously through the sealing flange until both chambers reach the vacuum pressure specified in the test.

[0035] Step 7: Based on the temperature control requirements of the actuator in the space under test and the temperature data collected by the first and second temperature sensors, operate the heat sink device to adjust the temperature so that the actuator in the space under test can be tested under different test temperature conditions; at the same time, operate the temperature adjustment device to adjust the temperature so that the working environment of the torque sensor and the electromagnetic braking mechanism is stabilized at room temperature.

[0036] Step 8: Set the load value of the electromagnetic braking mechanism through the data acquisition and control subsystem; set the test voltage and current of the actuator in the space under test through the data acquisition and control subsystem; set the acquisition frequency of the actuator in the space under test and the torque sensor through the data acquisition and control subsystem.

[0037] Step 9: Start the actuator in the space under test and begin the test. Check whether the torque sensor matches the set load value. Synchronously record the performance test data of the actuator in the space under test and the torque value of the torque sensor through the data acquisition and control subsystem to obtain the correspondence between the performance of the actuator in the space under test and the torque value.

[0038] Step 10: After completing the performance tests of the actuator under different operating conditions such as temperature and load, the test chamber is restored to normal temperature. The repressurization system is turned on to restore the pressure of the test chamber and the load system chamber to normal pressure. The test is then completed, and the product and test equipment are removed.

[0039] The beneficial effects of this invention are:

[0040] This invention allows for the simultaneous connection of multiple load system chambers to test multiple space actuators under test via a single experimental chamber, significantly improving testing efficiency. Furthermore, the data acquisition and control subsystem controls the electromagnetic braking mechanism, enabling it to output different load values ​​for driving and performance testing of the space actuators under test. This allows for automated testing with a high degree of automation. Simultaneously, the electromagnetic braking subsystem and mechanical transmission mechanism transmit resistance torque to the space actuators under test within the experimental chamber via a mechanical connection, making it suitable for loading various load sizes and applicable to testing space actuators with relatively small output torques. A heat shield isolates the temperature fields between the experimental chamber and the load system chamber, ensuring that the operating temperature of each mechanism in the load system chamber is not affected by the temperature within the experimental chamber.

[0041] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0042] Figure 1 This is a schematic diagram of the structure of a testing system provided by existing technology;

[0043] Figure 2 This is a schematic diagram of the structure of a thermal vacuum testing system for a space actuator provided in an embodiment of the present invention;

[0044] Figure 3 This is a schematic diagram of the internal structure of a thermal vacuum testing system for a space actuator provided in an embodiment of the present invention;

[0045] Figure 4 This is a schematic diagram of the structure of the three-dimensional position adjustment platform and axis alignment device provided in the embodiments of the present invention;

[0046] Figure 5 This is a schematic diagram of another thermal vacuum testing system for a space actuator provided in an embodiment of the present invention.

[0047] Explanation of reference numerals in the attached figures:

[0048] 10-Experimental chamber; 11-Heat sink device; 12-Three-dimensional position adjustment platform; 13-Shaft alignment device; 20-Load system chamber; 21-Electromagnetic braking mechanism; 22-Torque sensor; 23-Temperature regulation device; 30-Heat insulation screen; 40-Sealing flange; 50-Actuator of the space under test; 61-Drive shaft; 62-Coupling; 70-Data acquisition and control subsystem. Detailed Implementation

[0049] The present invention will be further described in detail below with reference to specific embodiments, but the implementation of the present invention is not limited thereto.

[0050] Example 1

[0051] Please see Figure 2 and Figure 3 A first aspect of this invention provides a thermal vacuum testing system for a space actuator, comprising: a data acquisition and control subsystem 70, a vacuum pumping unit, a repressurization subsystem, a first temperature sensor, an experimental chamber 10, a heat sink device 11, at least one load system chamber 20, an electromagnetic braking subsystem, at least one heat shield 30, and at least one sealing flange 40. The data acquisition and control subsystem 70 is electrically connected to the space actuator 50 under test, the electromagnetic braking subsystem, and the first temperature sensor. The data acquisition and control subsystem 70 is used for driving and performance testing of the space actuator 50 under test, controlling the operation of the first temperature sensor, and controlling the electromagnetic braking subsystem to output different load values. The vacuum pumping unit is connected to the experimental chamber 10. The repressurization subsystem is connected to the experimental chamber 10. The experimental chamber 10 is connected and communicates with the load system chamber 20 via the sealing flange 40, and the space actuator 50 under test is disposed inside the experimental chamber 10. The vacuum pump unit is used to evacuate the experimental chamber 10. Through the sealing flange 40, the pressure in the load system chamber 20 is simultaneously reduced until both chambers reach the vacuum pressure specified for the test. After the test is completed, the repressurization subsystem is activated to restore the pressure in the experimental chamber 10 and the load system chamber 20 to atmospheric pressure. A heat sink device 11 is installed inside the experimental chamber 10. The heat sink device 11 can regulate the temperature inside the experimental chamber 10, stabilizing the internal environment at different temperatures to facilitate experiments at varying temperatures.

[0052] An electromagnetic braking subsystem is located within the load system compartment 20 and is connected to the actuator 50 of the space under test via a mechanical transmission mechanism. A heat shield 30 is located at the connection between the experimental compartment 10 and the load system compartment 20. The heat shield 30 isolates the temperature fields of the load system compartment 20 and the experimental compartment 10, ensuring that the temperature inside the load system compartment 20 is not affected by the temperature inside the experimental compartment 10. The load system compartment 20 is sealed to the experimental compartment 10 via sealing flanges 40, allowing communication between the two compartments and maintaining a vacuum environment inside the load system compartment 20. The number of sealing flanges 40 is the same as the number of load system compartments 20, and the number of load system compartments 20 is the same as the number of heat shields 30.

[0053] In this embodiment, there is one experimental chamber 10 and multiple load system chambers 20, such as... Figure 2 As shown, each load system compartment 20 is connected to the test compartment 10 through a sealing flange 40 and a heat shield 30, which can meet the simultaneous testing of multiple space actuators 50 under test, improving testing efficiency and reducing equipment usage costs.

[0054] In this embodiment, during testing, the chamber door is closed, and the vacuum pump unit is turned on to evacuate the experimental chamber 10. As the pressure in the experimental chamber 10 gradually decreases, the pressure in the load system chamber 20 is synchronously reduced through the sealing flange 40 until both chambers reach the vacuum pressure specified for the test. The first temperature sensor detects the temperature in the experimental chamber 10 and sends it to the data acquisition and control subsystem 70 for storage and display. According to the temperature control requirements of the experiment, the temperature of the heat sink device 11 is adjusted to stabilize the interior of the experimental chamber 10 at the required test temperature.

[0055] The load value of the electromagnetic braking subsystem is set through the data acquisition and control subsystem 70, and the test voltage and current of the actuator 50 in the space under test are set through the data acquisition and control subsystem 70.

[0056] The test actuator 50 is activated to begin testing. The electromagnetic braking subsystem is controlled by the data acquisition and control subsystem 70, and the performance test results of the test actuator 50 are recorded. After completing the performance tests of the test actuator 50 under different temperature and load conditions, the test chamber 10 is restored to room temperature. The repressurization subsystem of the test chamber 10 is activated to restore the pressure of the test chamber 10 and the load system chamber 20 to normal pressure. The test ends, and the product and testing equipment are removed. Multiple load system chambers 20 can be connected to one test chamber 10 simultaneously to test multiple test actuators 50, greatly improving testing efficiency. Moreover, the data acquisition and control subsystem 70 controls the electromagnetic braking subsystem to output different load values, realizing the drive and performance detection of the test actuator 50. This allows for automated testing with a high degree of automation.

[0057] In this embodiment, the electromagnetic braking subsystem and the mechanical transmission mechanism transmit resistance torque to the space actuator 50 under test within the experimental chamber 10 via a mechanical connection. The load torque transmission path is unaffected, and the load output by the electromagnetic braking subsystem is equal to the actual load applied to the space actuator 50 under test. This results in a small load error, making it suitable for loading loads of various sizes and applicable to testing space actuators with small output torques, meeting their load loading and accuracy requirements. Furthermore, the experimental chamber 10 and the load system chamber 20 are connected via a sealing flange 40, both forming a vacuum environment. The pressure balance within the two chambers further reduces the resistance to torque transmission, minimizing load transmission errors and improving test accuracy. Simultaneously, the heat shield 30 isolates the temperature fields between the experimental chamber 10 and the load system chamber 20, ensuring that the operating temperature of each mechanism in the load system chamber 20 is not affected by the temperature within the experimental chamber 10. Additionally, the connection between the experimental chamber 10 and the load system chamber 20 via the sealing flange 40 results in a simple structure.

[0058] Furthermore, such as Figure 3As shown, the mechanical transmission mechanism includes a drive shaft 61 and a coupling 62; the electromagnetic braking subsystem includes an electromagnetic braking mechanism 21 and a torque sensor 22. One end of the drive shaft 61 is connected to the output shaft of the actuator 50 in the space under test via the coupling 62, and the other end of the drive shaft 61 passes through the sealing flange 40 and the heat shield 30 and is connected to the electromagnetic braking mechanism 21. The coupling 62 is located inside the experimental chamber 10. The torque sensor 22 is located inside the load system chamber 20 and is mounted on the drive shaft 61. A temperature regulating device 23 and a second temperature sensor are installed inside the load system chamber 20. The data acquisition and control subsystem 70 is electrically connected to the electromagnetic braking mechanism 21, the torque sensor 22, and the second temperature sensor.

[0059] In this embodiment, the data acquisition and control subsystem 70 acquires temperature data within the load system compartment 20 and torque data collected by the torque sensor 22. The data acquisition and control subsystem 70 also controls the electromagnetic braking mechanism 21 to output different load values. Based on the temperature control requirements of each mechanism within the load system compartment 20 (temperature sensors can also be installed on the actuator 50 and the electromagnetic braking mechanism 21 in the test space) and the temperature data collected by the second temperature sensor, the temperature regulating device 23 is operated to adjust the temperature, ensuring that the working environment of the torque sensor 22 and the electromagnetic braking mechanism 21 is stabilized at room temperature.

[0060] The electromagnetic braking mechanism 21, drive shaft 61, and coupling 62 transmit torque to the actuator 50 in the test space in a purely mechanical manner, achieving torque transmission without attenuation. The temperature control device 23 within the load system compartment 20 can regulate the temperature within the load system compartment 20, maintaining it within the temperature range required for the operation of the mechanism, such as ambient temperature. The torque sensor 22 is used to collect torque data applied to the actuator 50 in the test space.

[0061] Since there is no attenuation in the load torque transmission path, the torque data collected by the torque sensor 22 on the drive shaft 61 in the load system compartment 20 is the actual torque and actual load value applied by the electromagnetic braking mechanism 21 to the actuator 50 in the space under test. The actual torque transmitted to the actuator 50 in the space under test can be detected without setting the torque sensor 22 in the experimental compartment 10. The torque sensor 22 can operate at a suitable temperature in the load system compartment 20, thereby avoiding the temperature drift of the torque sensor 22 from affecting the detection accuracy and improving the detection accuracy of the torque sensor 22.

[0062] In one feasible implementation, the heat shield 30 is a low-emissivity multilayer structure, effectively reducing radiative heat transfer. Since the high vacuum negligibles convective heat transfer, effective heat isolation is achieved between the experimental chamber 10 and the load system chamber 20. The drive shaft 61 can be made of a high-torque, low-thermal-conductivity metal with low surface emissivity.

[0063] The first temperature sensor detects the temperature in the experimental chamber 10 and feeds it back to the data acquisition and control subsystem 70. Operators can then adjust the temperature using the heat sink device 11. A second temperature sensor is also installed in the load system chamber 20. This second temperature sensor is electrically connected to the data acquisition and control subsystem 70 and can detect the temperature in the load system chamber 20 and feed it back to the data acquisition and control subsystem 70. Operators can then adjust the temperature using the temperature control device 23.

[0064] In one feasible implementation, the data acquisition and control subsystem 70 can acquire the performance data and torque value of the actuator 50 under test to obtain test results. The data acquisition and control subsystem 70 unifies the time source and synchronizes the sampling frequency of the actuator 50 and the torque sensor 22. Since the torque sensor 22 is directly connected in series to the motor output shaft of the actuator 50 via the drive shaft 61, only the time source of the torque sensor 22 and the motor tester of the actuator 50 needs to be synchronized. The measured value of the torque sensor 22 is then the actual load value applied to the motor of the actuator 50. Specifically, when the motor tester of the actuator 50 is integrated into the data acquisition and control subsystem 70, only the time source of the torque sensor 22 and the data acquisition and control subsystem 70 needs to be synchronized.

[0065] In one feasible implementation, the data acquisition and control subsystem 70 is a control system with an industrial control computer, which can acquire the performance data and torque value of the space actuator 50 under test in order to obtain test results.

[0066] Furthermore, such as Figure 3 As shown, the temperature regulating device 23 is installed on the inner wall of the load system compartment 20. The heat sink device 11 is installed on the inner wall of the experimental compartment 10.

[0067] In one feasible implementation, the temperature control device 23 can use ambient temperature air, water, or other fluids flowing within pipes arranged on the inner wall of the load system compartment 20 for temperature control. The flow rate within the pipes is adjustable, achieving temperature stability within the load system compartment 20. By designing air-cooled / liquid-cooled pipes on the wall, the temperature of the sub-load system compartment 20 can be stabilized within the range of 0–50°C. Since the heat source within the compartment is only the heat generated by the equipment inside, without the influence of the temperature of the experimental compartment 10, the temperature stability within the load system compartment 20 is improved, which is beneficial for the stable loading of the actuator 50 during long-term testing. Correspondingly, the temperature of the heat sink device 11 can be adjusted by operating the heat sink device 11.

[0068] Furthermore, the cable of the space actuator 50 under test is electrically connected to the data acquisition and control subsystem 70 via the first through-cabin electrical connector. The cable of the electromagnetic braking mechanism 21 is electrically connected to the data acquisition and control subsystem 70 via the second through-cabin electrical connector, and the cable of the torque sensor 22 is electrically connected to the data acquisition and control subsystem 70 via the third through-cabin electrical connector.

[0069] Furthermore, such as Figure 3 As shown, the heat insulation screen 30 is located in the middle region of the sealing flange 40. The heat insulation screen 30 has a ring-shaped structure. The drive shaft 61 can pass through the middle of the heat insulation screen 30.

[0070] Furthermore, such as Figure 4 and Figure 5 As shown, a thermal vacuum testing system for a space actuator further includes a three-dimensional position adjustment platform 12 and a shaft alignment device 13 disposed within the experimental chamber 10. The shaft alignment device 13 is disposed on both sides of the coupling 62. The space actuator 50 under test is disposed on the three-dimensional position adjustment platform 12.

[0071] In this embodiment, the three-dimensional position adjustment platform 12 can adjust the position of the space actuator 50 under test, for example, by adjusting its position in the front-back, left-right, up-down directions, so as to achieve concentricity between the space actuator 50 under test, the coupling 62, and the transmission shaft 61, and avoid introducing eccentric torque that affects the test results. The shaft alignment device 13 is installed on the mounting interface of the coupling 62. The shaft alignment device 13 can detect the coaxiality between the output shaft of the coupling 62 and the transmission shaft 61. When the coaxiality is poor, the shaft alignment device 13 obtains the deviation direction, and the three-dimensional position adjustment platform 12 adjusts the position of the space actuator 50 under test to achieve a high degree of coaxiality between the space actuator 50 under test, the coupling 62, and the transmission shaft 61.

[0072] Example 2

[0073] A second aspect of this invention also provides a thermal vacuum testing method for a space actuator, applied to the system in Embodiment 1, comprising the following steps:

[0074] Step 1: During testing, the drive shaft 61, torque sensor 22, and electromagnetic brake mechanism 21 are placed inside the load system compartment 20. The torque sensor 22 and electromagnetic brake mechanism 21 are connected to the data acquisition and control subsystem 70 outside the compartment via the through-compartment electrical connector. The data acquisition and control subsystem 70 controls the electromagnetic brake mechanism 21 to output different load values ​​and acquires the torque data collected by the torque sensor 22.

[0075] Step 2: Install the load system compartment 20 onto the experimental compartment 10 via the sealing flange 40 to establish connection. Install the heat insulation screen 30 to achieve vacuum insulation between the two compartments.

[0076] Step 3: Install the space actuator 50 to be tested on the three-dimensional position adjustment platform 12, connect the space actuator to the transmission shaft 61 through the coupling 62, install the shaft alignment device 13 on the mounting interface of the coupling 62, and check the coaxiality of the output shaft of the coupling 62 and the transmission shaft 61 through the shaft alignment device 13. When the coaxiality is poor, adjust the position of the space actuator 50 to be tested by adjusting the deviation direction obtained by the shaft alignment device 13 to adjust the three-dimensional position adjustment platform 12.

[0077] Step 4: Connect the drive circuit and signal circuit of the space actuator 50 under test to the data acquisition and control subsystem 70 outside the cabin through the through-cabin electrical connector to realize the drive and performance testing of the space actuator 50 under test.

[0078] Step 5: Temperature sensors are installed on the actuator 50 and electromagnetic braking mechanism 21 in the space under test to collect temperature information, which is then acquired through the data acquisition and control subsystem 70. The time source of the data acquisition in the synchronous experimental chamber 10 and the data acquisition and control subsystem 70 is synchronized, ensuring that the time source and sampling frequency of the actuator 50 and torque sensor 22 are unified. When the motor tester for the actuator 50 is integrated into the data acquisition and control subsystem 70, only the time source of the torque sensor 22 and the data acquisition and control subsystem 70 needs to be synchronized.

[0079] Step 6: Close the doors of the experimental chamber 10 and the load system chamber 20, and turn on the vacuum pump unit. As the pressure in the experimental chamber 10 gradually decreases, the pressure in the load system chamber 20 is simultaneously reduced through the sealing flange 40 until both chambers reach the vacuum pressure specified in the test.

[0080] Step 7: Based on the temperature control requirements of the space actuator 50 under test and the temperature data collected by the first temperature sensor and the second temperature sensor, operate the heat sink device 11 to adjust the temperature so that the space actuator 50 under test can be tested under different test temperature conditions; at the same time, operate the temperature adjustment device 23 to adjust the temperature so that the working environment of the torque sensor 22 and the electromagnetic braking mechanism 21 is stable at room temperature.

[0081] Step 8: Set the load value of the electromagnetic braking mechanism 21 through the data acquisition and control subsystem 70; set the test voltage and current of the actuator 50 in the space under test through the data acquisition and control subsystem 70; set the acquisition frequency of the actuator 50 in the space under test and the torque sensor 22 through the data acquisition and control subsystem 70.

[0082] Step 9: Start the actuator 50 under test and begin testing. Check whether the torque sensor 22 matches the set load value. The data acquisition and control subsystem 70 synchronously records the performance test data of the actuator 50 under test and the torque value of the torque sensor 22 to obtain the correspondence between the performance and torque value of the actuator 50 under test.

[0083] Step 10: After completing the performance tests of the actuator 50 under different operating conditions such as temperature and load, the test chamber 10 is restored to normal temperature, the repressurization system is turned on, and the pressure of the test chamber 10 and the load system chamber 20 is restored to normal pressure. The test is completed, and the product and test equipment are taken out.

[0084] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0085] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0086] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0087] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0088] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0089] The above description, in conjunction with specific preferred embodiments, provides a further detailed explanation of the present invention. It should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, various simple deductions or substitutions can be made without departing from the concept of the present invention, and all such modifications and substitutions should be considered within the scope of protection of the present invention.

Claims

1. A space actuator thermal vacuum test system, characterized by, The system comprises a data acquisition and control subsystem (70), a vacuum air extractor unit, a pressure recovery subsystem, a first temperature sensor, an experiment cabin (10), a heat sink device (11), at least one load system cabin (20), an electromagnetic brake subsystem, at least one heat shield (30), and at least one sealing flange (40). The data acquisition and control subsystem (70) is electrically connected with a space execution mechanism (50) to be tested, the electromagnetic brake subsystem, and the first temperature sensor. The vacuum air extractor unit is connected with the experiment cabin (10). The pressure recovery subsystem is connected with the experiment cabin (10). The experiment cabin (10) is connected and communicated with the load system cabin (20) through the sealing flange (40), and the space execution mechanism (50) to be tested is arranged inside the experiment cabin (10). The heat sink device (11) is arranged inside the experiment cabin (10). The electromagnetic brake subsystem is arranged in the load system cabin (20) and is in driving connection with the space execution mechanism (50) to be tested through a mechanical transmission mechanism. The heat shield (30) is arranged at the communication position of the experiment cabin (10) and the load system cabin (20). The number of the sealing flange (40) is the same as the number of the load system cabin (20) and the number of the heat shield (30). The mechanical transmission mechanism comprises a transmission shaft (61) and a shaft coupling (62), and the electromagnetic brake subsystem comprises an electromagnetic brake mechanism (21) and a torque sensor (22). One end of the transmission shaft (61) is in driving connection with an output shaft of the space execution mechanism (50) to be tested through the shaft coupling (62), and the other end of the transmission shaft (61) penetrates through the sealing flange (40) and the heat shield (30) and is in driving connection with the electromagnetic brake mechanism (21); and the shaft coupling (62) is located in the experiment cabin (10). The torque sensor (22) is located in the load system cabin (20) and is arranged on the transmission shaft (61). The load system cabin (20) is provided with a temperature adjusting device (23) and a second temperature sensor. The data acquisition and control subsystem (70) is electrically connected with the electromagnetic brake mechanism (21), the torque sensor (22), and the second temperature sensor. The system further comprises a three-dimensional position adjusting platform (12) and an axis alignment device (13) arranged in the experiment cabin (10). The axis alignment device (13) is arranged on both sides of the shaft coupling (62). The space execution mechanism (50) to be tested is arranged on the three-dimensional position adjusting platform (12). The cable of the space execution mechanism (50) to be tested is electrically connected with the data acquisition and control subsystem (70) through a first cabin-penetrating electrical connector.

2. The system of claim 1, wherein, The cable of the electromagnetic brake mechanism (21) is electrically connected with the data acquisition and control subsystem (70) through a second cabin-penetrating electrical connector, and the cable of the torque sensor (22) is electrically connected with the data acquisition and control subsystem (70) through a third cabin-penetrating electrical connector. The heat shield (30) is arranged in the middle region of the sealing flange (40).

3. The system of claim 1, wherein, ​ The heat shield (30) is an annular structure.

4. The system of claim 1, wherein, The temperature adjusting device (23) is arranged on the inner wall of the load system cabin (20); The heat sink device (11) is arranged on the inner wall of the experiment cabin (10).

5. A method for thermal vacuum testing of a space actuator, characterized in that The application is applied to the test system in any one of claims 1-4, comprising the following steps: Step 1, the transmission shaft (61), the torque sensor (22), the electromagnetic brake mechanism (21) are put into the load system cabin (20), the torque sensor (22) and the electromagnetic brake mechanism (21) are connected with the data acquisition and control subsystem (70) outside the cabin through the cabin-penetrating electrical connector, the data acquisition and control subsystem (70) controls the electromagnetic brake mechanism (21), so that the electromagnetic brake mechanism (21) outputs different load values, and the torque data collected by the torque sensor (22) is obtained; Step 2, the load system cabin (20) is installed on the experiment cabin (10) through the sealing flange (40), the communication is realized, the heat shield (30) is installed, and the vacuum heat insulation of the two cabin bodies is realized; Step 3, the space execution mechanism (50) to be measured is installed on the three-dimensional position adjusting platform (12), the space execution mechanism to be measured is connected with the transmission shaft (61) through the shaft coupling (62), the shaft alignment device (13) is installed on the mounting interface of the shaft coupling (62), and the coaxiality of the output shaft of the shaft coupling (62) and the transmission shaft (61) is checked through the shaft alignment device (13), when the coaxiality is poor, the position of the space execution mechanism (50) to be measured is adjusted by adjusting the three-dimensional position adjusting platform (12) according to the deviation direction obtained by the shaft alignment device (13); Step 4, the drive circuit and signal circuit of the space execution mechanism (50) to be measured are connected with the data acquisition and control subsystem (70) outside the cabin through the cabin-penetrating electrical connector, so that the driving and performance detection of the space execution mechanism (50) to be measured are realized; Step 5, temperature sensors are respectively installed on the space execution mechanism (50) to be measured and the electromagnetic brake mechanism (21) to collect temperature information, so that the temperature data is obtained through the data acquisition and control subsystem (70); the time source of the experiment cabin (10) data acquisition and the data acquisition and control subsystem (70) are synchronized, and the time source of the space execution mechanism (50) to be measured and the torque sensor (22) is unified and the sampling frequency is synchronized through the data acquisition and control subsystem (70); Step 6, the cabin doors of the experiment cabin (10) and the load system cabin (20) are closed, and the vacuum air extractor is started, in the process that the pressure of the experiment cabin (10) gradually decreases, the pressure of the load system cabin (20) is synchronously reduced through the sealing flange (40), until the two cabins realize the vacuum pressure required by the test; Step 7, according to the temperature control requirements of the space actuator (50) to be tested and the temperature data collected by the first and second temperature sensors, the heat sink device (11) is operated to adjust the temperature, so that the space actuator (50) to be tested can be tested under different test temperature conditions; at the same time, the temperature adjusting device (23) is operated to adjust the temperature, so that the working environment of the torque sensor (22) and the electromagnetic brake mechanism (21) is stable at room temperature. Step 8, set the load value of the electromagnetic brake mechanism (21) through the data acquisition and control subsystem (70), set the test voltage and current of the space actuator (50) to be tested through the data acquisition and control subsystem (70), and set the collection frequency of the space actuator (50) to be tested and the torque sensor (22) through the data acquisition and control subsystem (70); Step 9, start the space actuator (50) to be tested, start the test, check whether the torque sensor (22) matches the set load value, record the performance test data of the space actuator (50) to be tested and the torque value of the torque sensor (22) through the data acquisition and control subsystem (70) synchronously, and obtain the corresponding relationship between the performance and torque value of the space actuator (50) to be tested; Step 10, after completing the performance test of the space actuator (50) to be tested under different temperature and load conditions, the experimental cabin (10) returns to room temperature, the re-pressurization system is started, and the pressure of the experimental cabin (10) and the load system cabin (20) is restored to normal pressure, the test is ended, and the product and the test equipment are taken out.

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