CN216483999U

CN216483999U - Thermal vacuum testing device for space actuating mechanism

Info

Publication number: CN216483999U
Application number: CN202122885046.4U
Authority: CN
Inventors: 黄振国; 肖英
Original assignee: Shaanxi Ally Environmental Testing Technology Service Co ltd
Current assignee: Shaanxi Ally Environmental Testing Technology Service Co ltd
Priority date: 2021-11-23
Filing date: 2021-11-23
Publication date: 2022-05-10
Anticipated expiration: 2031-11-23

Abstract

The utility model discloses a thermal vacuum testing device for a space actuating mechanism, which comprises: the device comprises an experiment cabin, a heat sink device, a load system cabin, an electromagnetic braking subsystem, a heat shield and a sealing flange; the experiment cabin is connected and communicated with the load system cabin through a sealing flange, and a space execution mechanism to be tested is arranged in the experiment cabin; the heat sink device is arranged inside the experiment cabin; the electromagnetic braking subsystem is arranged in the load system cabin and is in transmission connection with the space actuating mechanism to be tested through a mechanical transmission mechanism; and the heat shield is arranged at the communication position of the experiment cabin and the load system cabin. The electromagnetic braking subsystem and the mechanical transmission mechanism are mechanically connected to transmit the resistance torque to the space actuating mechanism to be tested in the experiment cabin, and the load torque transmission path is not attenuated, so that the electromagnetic braking subsystem and the mechanical transmission mechanism are suitable for loading various loads and testing the space actuating mechanism with smaller output torque. Meanwhile, the temperature fields between the experiment cabin and the loading system cabin are independent of each other through the heat shield.

Description

Thermal vacuum testing device for space actuating mechanism

Technical Field

The utility model belongs to the technical field of thermal vacuum test of space actuating mechanisms, and particularly relates to a thermal vacuum test device of a space actuating mechanism.

Background

With the development of the aerospace technology towards intellectualization, precision and economy, various extravehicular single machines are required to have the deployable property to adapt to the size of a rocket fairing and the trackability to adapt to the signal transmission and capture of a spacecraft, and the requirements all need a space execution mechanism to be used as an execution unit to complete preset actions, so that the space execution mechanism is more and more widely applied in the aerospace field, such as a satellite sailboard deployment mechanism, a mars detector driving mechanism, a large antenna deployment mechanism and the like. The single machines generally bear important functions of the spacecraft, and the space execution mechanism becomes an important component of the performance of the spacecraft and even one of key factors of success and failure, so test items of space environment adaptability, reliability and the like of the space execution mechanism become necessary links for single machine development. Particularly, the space environment is different from the ground environment, which may cause the phenomena of increased thermal mismatching resistance, even jamming, lubrication failure, increased friction, weakened power, shortened service life and the like of the space execution mechanism to happen occasionally, and the thermal vacuum test gradually becomes the most important link for exposing the defects of the links such as design, processing, manufacturing, assembly and the like of the space execution mechanism.

The space executing mechanism is used as a power source, and the performance of the space executing mechanism under a real load must be tested under a thermal vacuum environment, and the existing on-load test systems can be divided into the following two types:

(1) a constant load or step load system within a thermal vacuum system, as shown in figure 1. Therefore, a relatively stable and accurate load source can be provided for the space actuator by the mode of forming the step load through the constant load or the multiple constant loads connected in series. This method has a great limitation, which is mainly embodied as follows:

firstly, due to acceleration action and load shaking in the starting process, the load is unstable in the initial stage, and a longer load stabilization stage is needed, so that the size of the needed thermal vacuum equipment is larger; particularly, during the step load test, because a plurality of loads need a stable stage, the size requirement of the thermal vacuum equipment is higher;

secondly, due to the limitation of the load running path, the requirement of long-time unidirectional test on a space actuating mechanism cannot be met;

because the load shaking is difficult to completely avoid in the process of load lifting, the method is not suitable for high-precision load testing of a precise space actuating mechanism.

(2) The thermal vacuum system brakes the load system externally as shown in fig. 2. In the mode, the load generated by the external braking system of the thermal vacuum system is transferred to the space executing mechanism in the thermal vacuum system through the magnetic fluid sealing transfer system, and compared with the constant/step load system in the thermal vacuum system in the step (1), the mode solves the problems of size requirement on thermal vacuum equipment and incapability of testing unidirectional rotation for a long time. However, the method still has the defects that: the resisting moment of the magnetic fluid sealing transmission system is generally more than 0.5Nm, the large space execution mechanism (the output moment is more than 10Nm) can be met, the load error (the error comprises the resisting moment of the magnetic fluid sealing transmission system) can meet the test requirement, but for the test of the micro space execution mechanism (the output moment is less than 10Nm), the loaded load value is smaller, the load error requirement is smaller, but the resisting moment of the magnetic fluid sealing transmission system cannot be ignored, so that the load transmission error is overlarge (the actually loaded load value exceeds the required load value), and the test result is influenced or even cannot be normally used.

SUMMERY OF THE UTILITY MODEL

In order to solve the problems in the prior art, the utility model provides a thermal vacuum testing device for a space actuator. The technical problem to be solved by the utility model is realized by the following technical scheme:

a space actuator thermal vacuum test apparatus, comprising: the test chamber, the heat sink device, the load system chamber, the electromagnetic braking subsystem, the heat shield and the sealing flange;

the experiment cabin is connected and communicated with the load system cabin through a sealing flange, and a space execution mechanism to be tested is arranged in the experiment cabin;

the heat sink device is arranged inside the experiment cabin;

the electromagnetic braking subsystem is arranged in the load system cabin and is in transmission connection with the space executing mechanism to be tested through a mechanical transmission mechanism;

the heat shield is arranged at the communication position of the experiment cabin and the load system cabin.

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

one end of the transmission shaft is in transmission connection with an output shaft of the space executing mechanism to be tested through the coupler, and the other end of the transmission shaft penetrates through the sealing flange and the heat shield to be in transmission connection with the electromagnetic braking mechanism; the coupler is positioned in the experiment cabin;

the torque sensor is positioned in the load system cabin and arranged on the transmission shaft;

and a temperature adjusting device is arranged in the load system cabin.

In one embodiment of the utility model, the heat shield is disposed in a middle region of the sealing flange;

the heat shield is of an annular structure.

In one embodiment of the present invention, further comprising: a three-dimensional position adjustment platform and an axis alignment device arranged in the experimental cabin;

the shaft alignment devices are arranged on two sides of the coupler;

the space actuator to be measured is arranged on the three-dimensional position adjusting platform.

In one embodiment of the utility model, said temperature regulation means is arranged on an inner wall of said load system compartment;

the heat sink device is arranged on the inner wall of the experiment cabin.

The utility model has the beneficial effects that:

the electromagnetic braking subsystem and the mechanical transmission mechanism are mechanically connected to transmit the resistance torque to the space execution mechanism to be tested in the experiment cabin, the transmission path of the load torque is not attenuated, the transmitted load error is small, the electromagnetic braking subsystem is suitable for loading various loads, can be suitable for testing the space execution mechanism with small output torque, and meets the load loading requirement; and the experiment cabin and the load system cabin are communicated through the sealing flange to form a vacuum environment, the pressure in the two cabins is balanced, the resistance of torque transmission is further reduced, and the error of load transmission is reduced. Meanwhile, the temperature fields between the experiment cabin and the load system cabin are independent of each other through the heat shield, and the working temperature of each mechanism in the load system cabin cannot be influenced by the temperature in the experiment cabin. In addition, the experiment cabin and the loading system cabin are connected through the sealing flange, and the structure is simple.

The present invention will be described in further detail with reference to the accompanying drawings and examples.

Drawings

FIG. 1 is a schematic diagram of a test system provided in the prior art;

FIG. 2 is a schematic diagram of another test system provided in the prior art;

FIG. 3 is a schematic structural diagram of a thermal vacuum testing apparatus for a space actuator according to an embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a three-dimensional position adjustment platform and an axis alignment device provided by an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of another space actuator thermal vacuum testing apparatus according to an embodiment of the present invention;

fig. 6 is a schematic structural diagram of a thermal vacuum test system for a space actuator according to an embodiment of the present invention.

Description of reference numerals:

10-an experiment cabin; 11-heat sink means; 12-a three-dimensional position adjustment platform; 13-axis alignment means; 20-load system bay; 21-an electromagnetic braking mechanism; 22-a torque sensor; 23-a temperature regulating device; 30-a heat shield; 40-sealing the flange; 50-a space actuator to be tested; 61-a drive shaft; 62-a coupler; 70-data acquisition and control subsystem.

Detailed Description

The present invention will be described in further detail with reference to specific examples, but the embodiments of the present invention are not limited thereto.

Example one

Referring to fig. 3, a thermal vacuum testing apparatus for a space actuator includes: the test chamber 10, the heat sink device 11, the load system chamber 20, the electromagnetic braking subsystem, the heat shield 30 and the sealing flange 40. The experiment cabin 10 is connected and communicated with the load system cabin 20 through a sealing flange 40, and a space actuator 50 to be tested is arranged inside the experiment cabin 10. A heat sink device 11 is arranged inside the laboratory cabin 10. The heat sink device 11 can adjust the temperature in the experiment chamber 10, and can stabilize the internal environment of the experiment chamber 10 at different temperatures, so as to facilitate experiments at different temperatures. The electromagnetic braking subsystem is arranged in the load system cabin 20 and is in transmission connection with the space executing mechanism 50 to be tested through a mechanical transmission mechanism. A heat shield 30 is provided in communication between the experiment compartment 10 and the load system compartment 20. The heat shield 30 serves to insulate the temperature field of the load system compartment 20 from the test compartment 10, the temperature in the load system compartment 20 not being influenced by the temperature in the test compartment 10. The loading system compartment 20 is hermetically connected to the test compartment 10 by a sealing flange 40 and the interiors of the two compartments can be communicated, so that the loading system compartment 20 is also in a vacuum environment.

In the embodiment, the electromagnetic braking subsystem and the mechanical transmission mechanism transmit resistance torque to the space actuator 50 to be tested in the experiment chamber 10 in a mechanical connection mode, a load torque transmission path is not attenuated, the load output by the electromagnetic braking subsystem is equal to the actual load loaded on the space actuator 50 to be tested, the transmitted load error is small, the test device is suitable for loading various loads, can be suitable for testing the space actuator with small output torque, and meets the load loading and precision requirements; and the experiment chamber 10 and the load system chamber 20 are communicated through the sealing flange 40 to form a vacuum environment, the pressure in the two chambers is balanced, the resistance of torque transmission is further reduced, the error of load transmission is reduced, and the test precision is improved. Meanwhile, the temperature field between the test chamber 10 and the load system chamber 20 is independent of each other by the heat shield 30, and the working temperature of each mechanism in the load system chamber 20 is not affected by the temperature in the test chamber 10. In addition, the experiment chamber 10 and the loading system chamber 20 are connected through the sealing flange 40, and the structure is simple.

In the embodiment, when the test is performed, the chamber door is closed, the external vacuum air pump group is opened to vacuumize the experiment chamber 10, and in the process that the pressure of the experiment chamber 10 is gradually reduced, the synchronous reduction of the pressure in the load system chamber 20 is realized through the sealing flange 40 until the vacuum pressure specified in the test is realized in both chambers. According to the temperature control requirement of the experiment, the temperature change of the heat sink device 11 is adjusted, and the internal part of the experiment chamber 10 is stabilized at the required test temperature.

The load value of the electromagnetic braking subsystem is set by the external data acquisition and control subsystem 70, and the test voltage and current of the space actuator 50 to be tested are set by the data acquisition and control subsystem 70.

Starting the space actuator 50 to be tested, starting the test, controlling the electromagnetic braking subsystem to work through the data acquisition and control subsystem 70, and recording the performance test result of the space actuator 50 to be tested. After the performance tests of the space actuator 50 to be tested under different working conditions such as different temperatures and loads are completed, the test chamber 10 is restored to normal temperature, the repressing system for controlling the repressing of the test chamber 10 is started, the pressures of the test chamber 10 and the load system chamber 20 are restored to normal pressure, the test is finished, and the product and the test equipment are taken out.

Further, as shown in fig. 3, the mechanical transmission mechanism includes: a transmission shaft 61 and a coupling 62; an electromagnetic braking subsystem comprising: an electromagnetic brake mechanism 21 and a torque sensor 22. One end of the transmission shaft 61 is in transmission connection with an output shaft of the space actuator 50 to be measured through the coupler 62, and the other end of the transmission shaft 61 penetrates through the sealing flange 40 and the heat shield 30 to be in transmission connection with the electromagnetic brake mechanism 21. The coupling 62 is located in the experiment chamber 10. The torque sensor 22 is located within the load system bay 20, and the torque sensor 22 is disposed on the drive shaft 61. A thermostat 23 is provided in the load system compartment 20.

In this embodiment, the electromagnetic braking mechanism 21, the transmission shaft 61 and the coupling 62 realize torque transmission to the space actuator 50 to be measured in a purely mechanical manner, and realize torque transmission without attenuation. The temperature regulating device 23 in the load system compartment 20 can regulate the temperature in the load system compartment 20, and can maintain the temperature in the load system compartment 20 within a temperature range required for the operation of the in-compartment mechanism, for example, a normal temperature. The torque sensor 22 is used to collect torque data applied to the actuator 50 in the space to be measured.

Because the load torque transmission path is not attenuated, the torque data acquired by the torque sensor 22 on the transmission shaft 61 in the load system compartment 20 is also the actual torque (actual load value) applied to the execution mechanism 50 in the space to be measured by the electromagnetic braking mechanism 21, the actual torque transmitted to the execution mechanism 50 in the space to be measured can be detected without arranging the torque sensor 22 in the experiment compartment 10, and the torque sensor 22 can work at a proper temperature in the load system compartment 20, so that the torque sensor 22 is prevented from generating temperature drift to influence the detection accuracy, and the detection accuracy of the torque sensor 22 is improved.

In one possible implementation, the heat shield 30 is a low emissivity multilayer structure, which effectively reduces the amount of radiative heat transfer, and due to the high vacuum, the convective heat transfer of the system can be ignored, thereby effectively isolating the heat from the test chamber 10 and the load system chamber 20. The drive shaft 61 may be a high torque, low thermal conductivity metal with low surface emissivity.

In one possible implementation, the data acquisition and control subsystem 70 is capable of obtaining performance data and torque values of the space actuator 50 under test to obtain test results.

Further, as shown in fig. 3, the temperature adjusting device 23 is provided on the inner wall of the load system compartment 20. The heat sink device 11 is arranged on the inner wall of the experiment chamber 10.

In a possible implementation manner, the temperature adjusting device 23 may control the temperature by using a fluid such as normal temperature air, water, etc. flowing in a pipeline arranged on the inner wall of the load system compartment 20, and the flow rate in the pipeline may be adjusted to realize the temperature stability in the load system compartment 20. The wall is provided with the air cooling/liquid cooling pipeline, so that the temperature of the sub-load system cabin 20 can be stabilized within the range of 0-50 ℃, and the heat source in the cabin only heats the equipment in the cabin during working, so that the temperature influence of the experiment cabin 10 is avoided, the temperature stability in the load system cabin 20 is improved, and the stable loading of the space executing mechanism 50 to be tested in the long-time testing process is facilitated. Accordingly, the temperature of the heat sink device 11 can be adjusted by operating the heat sink device 11.

Further, as shown in fig. 3, a heat shield 30 is provided at a central region of the sealing flange 40. The heat shield 30 is of annular configuration. The shaft 61 may pass through the heat shield 30.

Further, as shown in fig. 4 and 5, a space actuator thermal vacuum test apparatus further includes: a three-dimensional position adjustment platform 12 and an axis alignment device 13 arranged in the laboratory 10. The shaft aligning devices 13 are disposed at both sides of the coupling 62. The space-to-be-measured actuator 50 is provided on the three-dimensional position adjustment platform 12.

In this embodiment, the three-dimensional position adjusting platform 12 can adjust the position of the space actuator 50 to be tested, for example, adjust the position in the front-back, left-right, up-down directions, so as to realize that the space actuator 50 to be tested and the coupling 62 are concentric with the transmission shaft 61, thereby avoiding introducing an eccentric moment to affect the test result. The shaft alignment device 13 is installed on the installation interface of the coupler 62, the shaft alignment device 13 can detect the coaxiality of the output shaft of the coupler 62 and the transmission shaft 61, when the coaxiality is poor, the deviation direction is obtained through the shaft alignment device 13, and the position of the space execution mechanism 50 to be measured is adjusted through the three-dimensional position adjusting platform 12, so that the space execution mechanism 50 to be measured and the coupler 62 and the transmission shaft 61 can achieve high coaxiality.

Specifically, the testing method of the thermal vacuum testing device of the space actuating mechanism specifically comprises the following steps: during testing, the transmission shaft 61, the torque sensor 22 and the electromagnetic braking mechanism 21 are placed in the load system cabin 20, the torque sensor 22 and the electromagnetic braking mechanism 21 are connected with the data acquisition and control subsystem 70 outside the cabin through cabin penetrating electric connectors, and the data acquisition and control subsystem 70 controls the electromagnetic braking mechanism 21 to enable the electromagnetic braking mechanism 21 to output different load values and acquire torque data acquired by the torque sensor 22.

The load system compartment 20 is mounted to the test compartment 10 via a sealing flange 40 to provide communication. The heat shield 30 is installed to achieve vacuum insulation of the two compartments.

The method comprises the steps of installing a space actuator 50 to be measured on a three-dimensional position adjusting platform 12, connecting the space actuator with a transmission shaft 61 through a coupler 62, installing a shaft alignment device 13 on an installation interface of the coupler 62, checking the coaxiality of an output shaft of the coupler 62 and the transmission shaft 61 through the shaft alignment device 13, and adjusting the position of the space actuator 50 to be measured by adjusting the three-dimensional position adjusting platform 12 through the deviation direction obtained by the shaft alignment device 13 when the coaxiality is poor.

The driving circuit and the signal circuit of the space actuator 50 to be tested are connected with the data acquisition and control subsystem 70 outside the cabin through the cabin-penetrating electric connector, so that the driving and performance detection of the space actuator 50 to be tested are realized.

Temperature sensors are respectively arranged on the space actuator 50 to be measured and the electromagnetic braking mechanism 21 to acquire temperature information so as to acquire temperature data through the data acquisition and control subsystem 70. The synchronous experiment chamber 10 is used for realizing the time source unification and the sampling frequency synchronization of the data acquisition and control subsystem 70 of the space executing mechanism 50 to be tested and the torque sensor 22. When the motor tester of the space actuator 50 to be tested is integrated in the data acquisition and control subsystem 70, only the time sources of the torque sensor 22 and the data acquisition and control subsystem 70 need to be synchronized.

Closing the cabin doors of the experiment cabin 10 and the load system cabin 20, starting the vacuum air extractor set, and realizing synchronous pressure reduction of the load system cabin 20 through the sealing flange 40 in the process of gradually reducing the pressure of the experiment cabin 10 until the two cabins realize the vacuum pressure specified in the experiment.

Operating the heat sink device 11 to adjust the temperature according to the temperature control requirement of the space actuator 50 to be tested and the temperature data collected by the temperature sensors in the experiment chamber 10 and the load system chamber 20, so that the space actuator 50 to be tested can perform experiments under different experiment temperature conditions; meanwhile, the temperature adjusting device 23 is operated to adjust the temperature, so that the working environments of the torque sensor 22 and the electromagnetic brake mechanism 21 are stabilized at the normal temperature.

The load value of the electromagnetic braking mechanism 21 is set through the data acquisition and control subsystem 70, and the test voltage and current of the space actuator 50 to be tested are set through the data acquisition and control subsystem 70. The data acquisition and control subsystem 70 sets the acquisition frequency of the space actuator 50 and the torque sensor 22.

Starting the space executing mechanism 50 to be tested, starting testing, checking whether the torque sensor 22 is matched with a set load value, synchronously recording performance test data of the space executing mechanism 50 to be tested and a torque value of the torque sensor 22 through the data acquisition and control subsystem 70, and obtaining a corresponding relation between the performance of the space executing mechanism 50 to be tested and the torque value.

After the performance tests of the space actuator 50 to be tested under different working conditions such as different temperatures and loads are completed, the experiment chamber 10 is restored to normal temperature, the repressing subsystem is started, the pressures of the experiment chamber 10 and the load system chamber 20 are restored to normal pressure, and after the test is finished, the product and the test equipment are taken out.

Example two

As shown in fig. 1, the present embodiment further provides a thermal vacuum testing system for a space actuator, which includes the thermal vacuum testing apparatus for a space actuator in the first embodiment, and a data acquisition and control subsystem 70, a vacuum pump set, and a repressing subsystem. The number of the experiment chamber 10 is one, the number of the load system chambers 20 is multiple, and as shown in fig. 6, each load system chamber 20 is connected with the experiment chamber 10 through the structure of the first embodiment, so that a plurality of space actuators 50 to be tested can be tested simultaneously, the test efficiency is improved, and the use cost of equipment is reduced.

In this embodiment, the data acquisition and control subsystem 70 is electrically connected to the electromagnetic braking mechanism 21 and the torque sensor 22, and the data acquisition and control subsystem 70 acquires torque data through the torque sensor 22 and controls the electromagnetic braking mechanism 21 to output different resisting torques (loads) through current. The data acquisition and control subsystem 70 is electrically connected with the space actuator 50 to be tested, the voltage and the current of the space actuator 50 to be tested are set through the data acquisition and control subsystem 70, the driving and the performance detection of the space actuator 50 to be tested are realized, the time source unification and the sampling frequency synchronization of the space actuator 50 to be tested and the torque sensor 22 are realized through the data acquisition and control subsystem 70, meanwhile, as the torque sensor 22 is directly connected in series to the motor output shaft of the space actuator 50 to be tested through the transmission shaft 61, only the time sources of the motor testers of the torque sensor 22 and the space actuator 50 to be tested are needed to be synchronized, and the measured value of the torque sensor 22 is the real load value of the motor applying the space actuator 50 to be tested. Wherein, when the motor tester is integrated into the data acquisition and control subsystem 70, only the time sources of the torque sensor 22 and the data acquisition and control subsystem 70 need to be synchronized.

Wherein, still be provided with first temperature sensor in the experiment cabin 10, first temperature sensor is connected with data acquisition and control subsystem 70 electricity, and first temperature sensor can detect the temperature in the experiment cabin 10 and feed back to data acquisition and control subsystem 70, and the staff can carry out temperature control according to this temperature control heat sink device 11. The load system cabin 20 is further provided with a second temperature sensor, the second temperature sensor is electrically connected with the data acquisition and control subsystem 70, the second temperature sensor can detect the temperature in the load system cabin 20 and feed back the temperature to the data acquisition and control subsystem 70, and a worker can control the temperature adjusting device 23 to adjust the temperature according to the temperature. Temperature sensors are also mounted on the space-to-be-measured actuator 50 and the electromagnetic brake mechanism 21.

Further, the cable of the space actuator 50 to be measured is electrically connected with the data acquisition and control subsystem 70 through a first cabin penetrating electrical connector, the cable of the electromagnetic braking 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.

In one possible implementation, the data collection and control subsystem 70 is a control system with an industrial control computer, and is capable of obtaining performance data and torque values of the space actuator 50 to be tested to obtain test results.

The test method of the system of the embodiment is the same as that of the first embodiment.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating 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 the present invention, "a plurality" means two or more unless specifically defined otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or may be connected through the use of two elements or the interaction of two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by those skilled in the art.

The foregoing is a more detailed description of the utility model in connection with specific preferred embodiments and it is not intended that the utility model be limited to these specific details. For those skilled in the art to which the utility model pertains, several simple deductions or substitutions can be made without departing from the spirit of the utility model, and all shall be considered as belonging to the protection scope of the utility model.

Claims

1. A space actuator thermal vacuum test apparatus, comprising: the test device comprises an experiment cabin (10), a heat sink device (11), a load system cabin (20), an electromagnetic braking subsystem, a heat shield (30) and a sealing flange (40);

the experiment cabin (10) is connected and communicated with the load system cabin (20) through a sealing flange (40), and a space execution mechanism (50) to be tested is arranged in the experiment cabin;

the heat sink device (11) is arranged inside the experiment cabin (10);

the electromagnetic braking subsystem is arranged in the load system cabin (20) and is in transmission connection with the space executing 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).

2. The space actuator thermal vacuum test apparatus of claim 1, wherein the mechanical transmission comprises: a transmission shaft (61) and a coupling (62); the electromagnetic braking subsystem, comprising: an electromagnetic brake mechanism (21) and a torque sensor (22);

one end of the transmission shaft (61) is in transmission connection with an output shaft of the space execution mechanism (50) to be tested through the coupler (62), and the other end of the transmission shaft penetrates through the sealing flange (40) and the heat shield (30) to be in transmission connection with the electromagnetic braking mechanism (21); the coupling (62) is positioned in the experiment cabin (10);

the torque sensor (22) is positioned in the load system cabin (20) and is arranged on the transmission shaft (61);

and a temperature adjusting device (23) is arranged in the load system cabin (20).

3. A space actuator thermal vacuum test apparatus according to claim 2, wherein the heat shield (30) is provided in a central region of the sealing flange (40);

the heat shield (30) is of an annular structure.

4. The space actuator thermal vacuum test apparatus of claim 2, further comprising: a three-dimensional position adjustment platform (12) and an axis alignment device (13) arranged in the experiment chamber (10);

the shaft alignment devices (13) are arranged on two sides of the coupling (62);

the space actuator (50) to be measured is arranged on the three-dimensional position adjusting platform (12).

5. A space actuator thermal vacuum test apparatus according to claim 2, wherein the temperature adjustment means (23) is provided on an inner wall of the load system bay (20);

the heat sink device (11) is arranged on the inner wall of the experiment cabin (10).