Self-checking device, system and method of sensor for satellite propulsion polarity test

Abstract

The invention discloses a self-checking device, system and method of a sensor for satellite propulsion polarity test, the self-checking device comprises a base, a wind speed generator, an air duct cylinder and an air volume adjusting assembly, and an air outlet hole with adjustable aperture is formed in the middle of an air volume adjusting mechanism of the air volume adjusting assembly; a self-checking hole used for being connected with a sensor clamping device is formed in the air duct cylinder, the self-checking hole and the air outlet holes are arranged at intervals, the self-checking system comprises a self-checking device and self-checking equipment, and the self-checking equipment is provided with a power module, a comprehensive control module and control and processing software. The system and the method overcome the defects that self-inspection of the wind speed sensor is easily influenced by environmental airflow interference and the self-inspection condition is harsh, can quickly construct a self-inspection scene and complete self-inspection in a full-automatic manner, effectively reduce time cost, improve test accuracy and reliability, and are suitable for large-scale popularization and application. The method is suitable for self-inspection and health state inspection of the sensor for propulsion polarity testing in a satellite factory and a launching site stage before related testing work is carried out.

Description

Technical Field

[0001] The present invention relates to the field of automated testing technology, and in particular to a self-testing device, system and method for a sensor for satellite propulsion polarity testing. Background Art

[0002] The sensor for satellite propulsion polarity testing is a wind speed sensor based on thermal sensor technology and is an important component of satellite propulsion polarity testing equipment. The sensor probe uses a thin metal wire (hot wire) that is heated by electricity to collect the wind speed emitted by the thruster nozzle corresponding to the attitude control or orbit control of the satellite propulsion subsystem. The temperature change caused by the heat of the hot wire is carried away by the airflow, which in turn affects its resistance value. The resistance change is converted into an electrical signal, thereby measuring the thruster nozzle airflow velocity information. The electrical signal is input into the propulsion polarity testing equipment in the form of a serial port and the data logic is interpreted to realize the detection of the satellite propulsion polarity relationship.

[0003] As an important means to judge the health status of polarity test equipment before propulsion polarity test, the self-inspection of equipment is particularly important, especially the self-inspection of sensors. At present, the self-inspection of sensors used for satellite propulsion polarity test can only be carried out by using fans as wind sources, and performing simple functional checks, that is, checking whether there are measured values. However, thermal wind speed sensors are highly sensitive to external conditions such as temperature and airflow, the impact and fluctuation of fan air output are large, and the test distance and wind speed are not easy to control. Therefore, the self-inspection data cannot match the accuracy requirements of the sensor during actual use. Although wind tunnel equipment with higher airflow stability and uniformity can obtain high-quality self-inspection data, it is large in size and has a complicated installation and debugging process. It is not suitable for the requirements of satellite propulsion polarity test equipment to switch between different test scenarios, quickly complete equipment construction, equipment self-inspection, and complete on-board product testing. Summary of the invention

[0004] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a self-test device, system and method for a sensor for satellite propulsion polarity testing, which overcomes the many limitations of the self-test conditions and environment of the sensor for satellite propulsion polarity testing, solves the problem of complex self-test process, and achieves the purpose of quickly setting up the self-test environment and automating the self-test process.

[0005] To achieve the above-mentioned object of the invention, the present invention provides a self-test device for a sensor for satellite propulsion polarity testing, comprising:

[0006] A base, one end of which is sealed and connected to a wind speed generator;

[0007] An air duct cylinder is installed at the end of the base away from the wind speed generator, and an air volume adjustment component is installed at the end of the base. The air volume adjustment component has an air volume adjustment mechanism, and an air outlet hole with an adjustable aperture is formed in the middle of the air volume adjustment mechanism;

[0008] Among them, the air duct tube is also provided with a self-inspection hole for connecting with the sensor retainer, and the self-inspection hole is spaced apart from the air outlet, so that the air outlet and the wind speed sensor probe in the sensor retainer form a detection distance.

[0009] Furthermore, the ratio of the windward area of ​​the hot wire part of the wind speed sensor probe in the sensor positioner to the cross-sectional area of ​​the wind duct working section of the wind duct cylinder is not greater than 5%;

[0010] The detection interval l can be obtained by the formula l=0.25d~0.5d;

[0011] The length L of the air duct can be obtained by the formula L=2.0d~4.0d;

[0012] Wherein, d is the inner diameter of the air duct tube.

[0013] Furthermore, the air duct tube is located on the side of the self-inspection hole away from the air outlet and is formed with a surplus section for extending the air duct tube, and an air outlet is formed at the end of the surplus section.

[0014] Furthermore, the sensor positioner is arranged perpendicular to the axis of the air duct tube, and the sensor thermal wind speed sensor probe is placed at the geometric center position of the air duct tube through the sensor positioner.

[0015] Furthermore, the air volume adjustment assembly includes a main body installed in the air duct cylinder and an adjustment handle for adjusting the diameter of the air outlet hole of the air volume adjustment mechanism;

[0016] The air volume adjustment mechanism is installed on the main body;

[0017] The adjustment handle is placed outside the air duct tube, and an air volume adjustment scale is arranged on the outer wall of the air duct tube.

[0018] Furthermore, the adjustment range of the air outlet diameter is 0-42 mm.

[0019] Furthermore, the self-inspection device also includes a base, and the air duct tube and the lower part of the base are both fixedly connected with the base, so that the self-inspection device can be placed horizontally through the base.

[0020] The present invention discloses a self-test system, comprising the self-test device and self-test equipment of the above-mentioned sensor for satellite propulsion polarity testing, wherein the self-test equipment is connected with the sensor and the wind speed generator of the self-test device through a cable.

[0021] Furthermore, the self-test equipment includes a power supply module, an integrated control module and control and processing software;

[0022] The power module is used to receive the power supply control instruction of the integrated control module and return the instruction execution information to supply power to the sensor, wind speed generator and integrated control module;

[0023] The integrated control module receives the control and processing software instructions, outputs the PWM signal with the corresponding duty cycle according to the instructions, completes the wind speed control of the wind speed generator, receives the air flow speed information collected by the sensor, and sends it to the control and processing software.

[0024] A self-test method disclosed in the present invention includes the self-test system described above, and the method includes the following steps:

[0025] Step 1: Debug the integrated control module and complete the control voltage duty cycle parameter configuration corresponding to different wind speed control instructions;

[0026] Step 2: Write a test instruction sequence in the control and processing software according to the thruster type. The test sequence is composed of different wind speed control instructions. The wind speed value collected by the wind speed sensor is used as the post-instruction judgment of the wind speed control instruction, and the judgment threshold range is set according to the accompanying reading error;

[0027] Step 3: According to the nozzle size of the satellite thruster to be tested, adjust the air volume adjustment component so that the position of the adjustment handle corresponds to the corresponding air volume adjustment scale;

[0028] Step 4: Confirm that the self-test device is placed horizontally and properly. The wind speed sensor probe for satellite propulsion polarity test is reliably connected to the self-test device through the sensor positioner. The wind speed sensor probe is placed at the geometric center of the wind duct tube. While ensuring the polarity of the probe is correct, the wind speed sensor probe air inlet is perpendicular to the airflow direction.

[0029] Step 5: Power on the self-test system, confirm that the communication between the control and processing software, the integrated control module, and the power module is normal, and the telemetry parameters are correct, then select the self-test sequence corresponding to the wind speed sensor to be tested and run it;

[0030] Step 6: The integrated control module receives the wind speed control instruction in the self-test sequence and controls the wind speed generator of the self-test device to generate a standard airflow at a preset wind speed;

[0031] Step 7: After the self-check point is adjusted and stabilized for 2 minutes, the integrated control module receives the wind speed collection instruction in the self-check sequence, controls the wind speed sensor to collect wind speed information at a frequency of 6 times / minute, and sends the received serial port wind speed information to the control and processing software;

[0032] Step 8: After the control and processing software receives wind speed data for 6 times, it starts to make automatic judgments. If all 6 wind speed data are within the standard wind speed value range, it can be automatically judged that the performance of the wind speed sensor at the wind speed self-test point meets the requirements;

[0033] Step 9: In the same manner as steps 6 to 8, the self-test sequence continues to send the next self-test point wind speed control and automatically interprets it until the self-test of the eight wind speed self-test points corresponding to the corresponding thruster is completed;

[0034] Step 10: If the result is abnormal, terminate the self-test and troubleshoot the problem;

[0035] Step 11: Repeat steps 3 to 10 for different types of thruster states.

[0036] In the above technical solution, the present invention provides a self-test device, system and method for a sensor for satellite propulsion polarity testing, which has the following beneficial effects compared with the prior art:

[0037] 1) The self-test device disclosed in the present invention provides a relatively stable, uniform, and self-adjustable air fluid environment, and the device is light, compact, and easy to assemble and disassemble;

[0038] 2) The self-test device disclosed in the present invention uses an air volume adjustment component that can adjust the air volume according to the size of different types of thruster nozzles to simulate the airflow state of the nozzle when the thruster jets, creating an ideal self-test environment.

[0039] 3) The self-test device disclosed in the present invention uses a wind speed generator that optimizes the airflow using air multiplication technology to generate natural wind with stable airflow, overcoming the wind impact caused by the traditional blade fan that pushes the airflow in a cutting manner, and effectively improving the self-test stability of the sensor;

[0040] 4) The self-test system disclosed in the present invention can control the wind speed generated by the wind speed generator in the self-test device in real time, and intelligently interpret the collected air flow speed information, thereby realizing the automation of the self-test process and the quantitative collection of self-test data.

[0041] 5) The self-test method disclosed in the present invention solves the problem that the satellite propulsion polarity test equipment cannot quickly build a self-test environment, and achieves the goal of completing the self-test work of the equipment during use. In addition, the self-test system and self-test method can effectively improve the self-test efficiency while ensuring the self-test accuracy of the sensor. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0043] Figure 1 It is a schematic diagram of the overall structure of the self-checking device disclosed in the present invention;

[0044] Figure 2 It is a schematic diagram of the internal structure of the self-checking device disclosed in the present invention;

[0045] Figure 3 It is a structural schematic diagram of the air volume regulating component of the self-test device disclosed in the present invention;

[0046] Figure 4 It is a block diagram of the self-checking system disclosed in the present invention;

[0047] Figure 5 It is a flow chart of the self-checking method disclosed by the present invention.

[0048] Description of reference numerals:

[0049] 1. Base; 2. Wind speed generator; 3. Air volume adjustment component; 4. Air duct cylinder; 5. Air volume adjustment scale; 6. Sensor positioner; 7. Base; 8. Base; 9. Wind speed sensor probe;

[0050] 3.1. Main body; 3.2. Air volume adjustment mechanism; 3.3. Adjustment handle. DETAILED DESCRIPTION

[0051] In order to make the purpose, technical solution and advantages of the implementation of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the present invention.

[0052] Figure 1 The overall structure diagram of the self-test device is as follows:

[0053] Figure 2 This is a schematic diagram of the internal structure of the self-test device:

[0054] The present invention discloses a self-test device for a sensor for satellite propulsion polarity testing, comprising:

[0055] A base 1, one end of which is sealed and connected to a wind speed generator 2;

[0056] The air duct tube 4 is installed on the end of the base 1 away from the wind speed generator 2, and the air duct tube 4 is located at the end of the base 1 and is installed with an air volume adjustment component 3, the air volume adjustment component 3 has an air volume adjustment mechanism 3.2, and an air outlet hole with an adjustable aperture is formed in the middle of the air volume adjustment mechanism 3. The air duct tube 4 is also provided with a self-inspection hole for connecting with the sensor positioner 6, and the self-inspection hole is spaced apart from the air outlet, so that the air outlet and the wind speed sensor probe 9 in the sensor positioner 6 form a detection distance.

[0057] For details, see Figure 1 As shown, in this structure, the base 1 is the foundation of the entire self-test device, which is used to connect the wind speed generator 2 and the air volume adjustment component 3. A sealing ring is provided at the interface of the base 1 to ensure the airtightness of the power section and the self-test section of the self-test device while keeping the air flow direction parallel to the axis of the entire self-test device;

[0058] The wind speed generator 2 is installed on one side of the base 1, and the interface adopts a sealed design. External air is sucked in through its internal turbine, flows out through the hollow tubular ring pores and moves along the inner wall of the annular airfoil. The pressure difference formed in front and behind the center of the ring then generates a forward airflow. The wind speed generator 2 used in this embodiment is a wind speed generator that can generate a continuous and stable airflow of 0 to 24 m / s in the prior art. The wind speed generator 2 is connected to the self-test device through a special self-test cable, and the self-test device can control the wind speed generator 2 to generate a corresponding amount of wind force.

[0059] The different missions performed by small satellites determine the differences in the thruster models of satellite propulsion systems. Commonly used thrusters in propulsion systems can be generally divided into 1N, 5N, 10N, etc. according to the thrust size. The size of the thruster nozzle also increases as the thrust increases, and its diameter generally ranges from 15mm to 40mm. From the nozzle airflow velocity calculation formula v = (Fs*p) / m, it can be seen that the size of the wind speed v depends not only on the thrust F, the nozzle pressure p, and the mass flow m, but also on the nozzle cross-sectional area s. Therefore, the self-test device needs to have the ability to adjust the air volume and be able to simulate the airflow injection width of thruster nozzles of different sizes;

[0060] Figure 3 It is a structural schematic diagram of the air volume adjustment component of the self-test device;

[0061] See also Figure 2 , 3 As shown, the air volume adjustment component 3 is installed on the other side of the base 1, and the air volume adjustment component 3 is built into the air inlet end of the air duct tube 4. The plane of the air volume adjustment component 3 is parallel to the cross section of the wind speed generator 2, so that the air flow enters the air duct tube 4 in the direction consistent with the axis of the air duct tube 4. The air volume adjustment component 3 includes: a main body 3.1, an air volume adjustment mechanism 3.2, and an adjustment handle 3.3;

[0062] The main body 3.1 is the basis of the air volume adjustment assembly 3, the air volume adjustment mechanism 3.2 is installed on the main body 3.1, and the adjustment handle 3.3 is installed on the air volume adjustment mechanism 3.2. The wind flap of the air volume adjustment mechanism 3.2 is controlled by the adjustment handle 3.3 to adjust the size of the air outlet, so as to achieve the purpose of adjusting the air volume according to the jet state of different types of satellite thrusters. Specifically, Figure 3 As shown, the air volume adjustment mechanism 3.2 can freely adjust the air outlet aperture under the control of the adjustment handle 3.3. Preferably, the air outlet aperture is designed with a minimum aperture of 0 mm and a maximum aperture of 42 mm. While adapting to the jet state of the above three commonly used types of thrusters of existing small satellites (diameter 15 mm to 40 mm), it also meets the self-inspection compatibility requirements of the thruster nozzles of smaller-sized micro-nano satellites or mass-produced small satellites;

[0063] See also Figure 1 As shown:

[0064] The air duct tube 4 is located at the end of the base 1 and is tightly connected to the base 1, providing a relatively stable flow field environment for the thermal wind speed sensor. The self-test hole at the upper middle section of the air duct tube 4 is well connected to the sensor positioner 6. Since the windward area of ​​the hot wire part of the sensor probe for the small satellite propulsion polarity test is 1 cm 2 According to the standard design requirement that the ratio of the windward area of ​​the wind speed sensor to the cross-sectional area of ​​the working section of the air duct tube 4 should not be greater than 5%, the cross-sectional area of ​​the air duct tube 4 should be greater than 20cm 2 (diameter d is greater than 5cm); at the same time, in order to make the wind speed sensor probe in a uniform flow field, a certain distance should be maintained from the probe to the wind source outlet. This distance is the detection interval. The detection interval l can be obtained by the formula l = 0.25d ~ 0.5d, and the length L of the air duct tube 4 can be obtained by the formula L = 2.0d ~ 4.0d;

[0065] Wherein, d is the inner diameter of the air duct cylinder (4);

[0066] In addition, considering the influence of the airflow environment of the wind speed generator 2 and the air volume adjustment component 3, the air duct tube 4 increases the tube length margin of 20 cm. Preferably, the air duct tube 4 is located on the side of the self-test hole away from the air outlet and is formed with a margin section for extending the air duct tube 4, and an air outlet is formed at the end of the margin section;

[0067] Specifically, the air duct tube 4 is an acrylic round tube with a length of 32 cm, an inner diameter of 6 cm, a thickness of 0.4 cm, and a smooth inner wall. The air volume adjustment component is installed at a length of 9 cm of the air duct tube 4. The self-test hole is opened at a length of 12 cm of the air duct tube 4 and connected to the sensor positioner 6. This structure effectively ensures the stable and uniform flow of the self-test airflow.

[0068] The air volume adjustment scale 5 is arranged on the air duct cylinder 4, and cooperates with the air volume adjustment component 3 to indicate different thruster nozzle states corresponding to the opening and closing sizes of the air volume adjustment mechanism. The numbers 0 to 8 correspond to 8 scales, respectively, indicating the aperture sizes of the air volume adjustment mechanism from small to large, that is, 0 is an aperture of 0mm, 1 is an aperture of 5mm, 2 is an aperture of 10mm...8 is an aperture of 40mm. During self-test, corresponding settings can be made according to the nozzle size state of the satellite thruster to be tested, and the air volume adjustment scale 5 provides a standard scale basis for the air volume adjustment component 3;

[0069] The sensor for small satellite propulsion polarity test is designed as a cylindrical structure with a length of 95mm and a diameter of 14mm. The front 15mm part is the sensor head with an embedded heating metal film. When measuring wind speed, the change of current passing through the metal film is used to keep the metal film basically at a constant temperature, that is, the resistance value is basically constant. Under different wind speeds, the current wind speed value can be measured by the functional relationship between the heat loss power of the metal film and the wind speed. When measuring wind speed, the sensor needs to measure against the wind in the direction indicated by its polarity.

[0070] The sensor positioner 6 is connected to the air duct tube 4, and the sensor positioner 6 is arranged perpendicular to the axis of the air duct tube 4. The thermal wind speed sensor probe 9 can be reliably placed at the geometric center of the air duct tube 4 through the sensor positioner 6, which ensures the correct polarity of the probe and also plays a limiting and fixing role, so that the air inlet of the sensor probe is perpendicular to the airflow direction.

[0071] See also Figure 1 As shown, the self-test device further includes a base 7 and a base 8, the base 7 is connected to the air duct cylinder 4, and the base 8 is connected to the base 1, so that the self-test device can be placed horizontally and securely;

[0072] The self-test device is small and light, weighing about 260g. Through reasonable design, it is easy to assemble and has good operability. It also builds a relatively stable, uniform and adjustable fluid gas field environment for the sensor, and completes the limit fixing installation of the sensor at the same time.

[0073] Figure 4 The block diagram of the self-check system is as follows:

[0074] A self-test system disclosed in the present invention comprises the self-test device and self-test equipment of the above-mentioned satellite propulsion polarity test sensor, and the self-test equipment is connected to the wind speed sensor and the wind speed generator 2 of the self-test device through a special self-test cable;

[0075] The self-test equipment includes a power module, an integrated control module, and control and processing software;

[0076] The power module receives the power supply control command from the integrated control module and returns the information on the execution of the command, and supplies power to the sensor, wind speed generator 2, and the integrated control module;

[0077] The integrated control module receives the control and processing software instructions, outputs the PWM signal with the corresponding duty cycle according to the instructions, and completes the wind speed control of the wind speed generator 2; receives the air flow speed information collected by the sensor and sends it to the control and processing software;

[0078] Small satellite propulsion systems are generally composed of propulsion tanks, propulsion pipelines, self-locking valves, solenoid valves, thrusters, etc. During satellite propulsion polarity testing, according to satellite-related test requirements, the propulsion tank needs to store a certain amount of test gas, and the tank pressure is generally set at 0.2 MPa. Since the thruster nozzle pressure is affected by many factors such as the propulsion tank pressure, propulsion pipeline length, self-locking valve state, solenoid valve state, etc., the wind speed generated by the thruster nozzle jet also has certain differences. Therefore, during self-test, multiple self-test points need to be selected to cover the wind speed range generated by the thruster nozzle. According to test experience, the wind speed generated by the small satellite thruster is generally concentrated in the range of 1.5m / s to 10m / s. Therefore, 1.5, 2.5, 4, 6, 8, 10, 7.5, and 3 wind speed self-test points are set in sequence, represented by N1, N2...N8 respectively, and the interpretation error range of each test point is ±0.5m / s.

[0079] During the self-test process, the air volume regulating assembly 3 can simulate the jet state of different types of thrusters by changing the aperture of the air volume regulating mechanism. According to the wind speed calculation formula, the change of the cross-sectional area will bring about the change of the wind speed. Therefore, when the same self-test point is used for self-test, the control voltage duty cycle used by the wind speed generator 2 is also different. If the thruster to be tested is a 1N thruster, the control voltage duty cycle corresponding to the wind speed self-test point N1 (1.5m / s) is 10%. If the thruster to be tested is a 5N thruster, the control voltage duty cycle corresponding to the wind speed self-test point N1 (1.5m / s) is 8%.

[0080] The control and processing software pre-compiles a self-test instruction sequence based on the 8 self-test points of the wind speed sensor to be tested. In the self-test sequence of each self-test point, the software sends a test instruction to the integrated control module to control the integrated control module to set the working gear of the wind speed generator 2, and automatically interprets the collected wind speed information and the wind speed control gear information to obtain the self-test result.

[0081] Figure 5 Flow chart of the self-test method

[0082] The present invention also discloses a self-checking method, which utilizes the self-checking system and comprises the following steps:

[0083] Step 1: Debug the integrated control module and complete the control voltage duty cycle parameter configuration corresponding to different wind speed control instructions;

[0084] Step 2: Write a test instruction sequence in the control and processing software according to the thruster type. The test sequence is composed of different wind speed control instructions. The wind speed value collected by the wind speed sensor is used as the post-instruction judgment of the wind speed control instruction, and the judgment threshold range is set according to the accompanying reading error. There are three specific test sequences compiled and adopted by this method, corresponding to 1N, 5N, and 10N thrusters respectively. The following takes the 1N thruster as an example to explain the self-check steps of the wind speed self-check point N1 (1.5m / s);

[0085] Step 3: According to the nozzle size (1N, 5N, 10N) of the satellite thruster to be tested, adjust the air volume adjustment component 3 so that the position of the adjustment handle 3.3 corresponds to the corresponding air volume adjustment scale 5. If the current thruster to be tested is 1N and its nozzle diameter is 15mm, then the adjustment handle 3.3 is adjusted to the scale position of number 3;

[0086] Step 4: Confirm that the self-test device is placed horizontally and properly, and the wind speed sensor probe 9 for satellite propulsion polarity test is reliably connected to the self-test device through the sensor clamp 6, so that the wind speed sensor probe 9 is placed at the geometric center of the wind duct tube 4, and the polarity of the probe is correct, and the air inlet of the sensor probe is perpendicular to the airflow direction;

[0087] Step 5: Power on the self-test system, confirm that the communication between the control and processing software, the integrated control module, and the power module is normal, and the telemetry parameters are correct, then select the self-test sequence corresponding to the wind speed sensor to be tested and run it;

[0088] Step 6: The integrated control module receives the wind speed N1 (1.5 m / s) control instruction in the self-test sequence, controls the wind speed generator 2 of the self-test device, and generates a standard airflow according to the wind speed N1 (1.5 m / s);

[0089] Step 7: After the self-check point is adjusted and stabilized for 2 minutes, the integrated control module receives the wind speed collection instruction in the self-check sequence, controls the wind speed sensor to collect wind speed information at a frequency of 6 times / minute, and sends the received serial port wind speed information to the control and processing software;

[0090] Step 8: After the control and processing software receives wind speed data for 6 times, it starts to make automatic judgments. If the 6 wind speed data are all within the wind speed range of N1±0.5m / s, it can be automatically judged that the performance of the wind speed sensor at the wind speed self-check point N1 meets the requirements;

[0091] Step 9: In the same manner as in steps 6 to 8, the self-check sequence continues to send wind speed N2 (2.5 m / s) control and automatically reads it until the self-check of the eight wind speed self-check points (N1 to N8) corresponding to the corresponding thruster is completed;

[0092] Step 10: If the result is abnormal, terminate the self-test and troubleshoot the problem;

[0093] Step 11: For different types of thruster states, repeat the above steps 3 to 10. After the self-test is completed, the self-test system records the measurement data, cuts off the power, and ends the test.

[0094] In summary, the self-test device, system and method of the satellite propulsion polarity test sensor disclosed in the present invention generate a controllable uniform standard airflow through the self-test system. After the polarity test wind speed sensor installed in the self-test device collects airflow information, the airflow information, wind speed control information, self-test threshold, etc. are logically interpreted by the self-test device, thereby forming a self-test result of the sensor. The self-test system is composed of a self-test device and a self-test device. The base, wind speed generator, air volume adjustment component, air duct tube, air volume adjustment scale, sensor positioner, base and other parts are combined to form a wind speed sensor self-test device; the self-test device includes an integrated control module, a power supply module, and control and processing software. The present invention overcomes the limitations that the wind speed sensor self-test is easily affected by the interference of environmental airflow and the harsh self-test conditions, and forms a system and method that can quickly build a self-test scene and automatically complete the self-test, effectively reducing the time cost and improving the test accuracy and reliability. The present invention is suitable for self-test and health status inspection of propulsion polarity test sensors before carrying out related testing work in satellite factories and launch sites.

[0095] The above description is only an illustrative embodiment of the present application and is not intended to limit the scope of the present application. Any equivalent changes, modifications and combinations made by any technician in the field without departing from the concept and principle of the present application shall fall within the scope of protection of the present application.

Claims

1. A self-test device for a sensor for satellite propulsion polarity testing, characterized in that: include: A base (1) having one end sealedly connected to a wind speed generator (2); An air duct cylinder (4) is installed at the end of the base (1) away from the wind speed generator (2), and the air duct cylinder (4) is installed with an air volume adjustment component (3) at the end of the base (1), the air volume adjustment component (3) has an air volume adjustment mechanism (3.2), and an air outlet hole with an adjustable aperture is formed in the middle of the air volume adjustment mechanism (3.2); The air duct tube (4) is also provided with a self-checking hole for connecting with the sensor retainer (6), and the self-checking hole is spaced apart from the air outlet, so that a detection distance is formed between the air outlet and the wind speed sensor probe (9) in the sensor retainer (6).

2. The self-test device of a sensor for satellite propulsion polarity testing according to claim 1, characterized in that: The ratio of the windward area of ​​the hot wire part of the wind speed sensor probe (9) in the sensor positioner (6) to the cross-sectional area of ​​the wind duct working section of the wind duct cylinder (4) is not greater than 5%; The detection interval l can be obtained by the formula l=0.25dˉ0.5d; The length L of the air duct tube (4) can be obtained by the formula L=2.0dˉ4.0d; Wherein, d is the inner diameter of the air duct tube (4).

3. A self-test device for a sensor for satellite propulsion polarity testing according to claim 1 or 2, characterized in that: The air duct tube (4) is located on the side of the self-inspection hole away from the air outlet and is formed with a surplus section for extending the air duct tube (4), and an air outlet is formed at the end of the surplus section.

4. The self-test device of a sensor for satellite propulsion polarity testing according to claim 1, characterized in that: The sensor positioner (6) is arranged perpendicular to the axis of the air duct cylinder (4), and the sensor thermal wind speed sensor probe (9) is placed against the geometric center position of the air duct cylinder (4) through the sensor positioner (6).

5. The self-test device of a sensor for satellite propulsion polarity testing according to claim 1, characterized in that: The air volume adjustment component (3) comprises a main body (3.1) installed in the air duct cylinder (4) and an adjustment handle (3.3) for adjusting the diameter of the air outlet hole of the air volume adjustment mechanism (3.2); The air volume adjustment mechanism (3.2) is installed on the main body (3.1); The adjustment handle (3.3) is placed outside the air duct cylinder (4), and an air volume adjustment scale (5) is provided on the outer wall of the air duct cylinder (4).

6. The self-test device of a sensor for satellite propulsion polarity testing according to claim 5, characterized in that: The adjustment range of the air outlet diameter is 0-42mm.

7. The self-test device of a sensor for satellite propulsion polarity testing according to claim 1, characterized in that: It also comprises a base, wherein the air duct cylinder (4) and the lower part of the base (1) are respectively fixedly connected with bases (7, 8), and the self-test device is placed horizontally through the base.

8. A self-checking system, characterized in that: It comprises a self-test device and a self-test equipment of a sensor for satellite propulsion polarity testing as described in any one of claims 1 to 7, wherein the self-test equipment is connected to the sensor and the wind speed generator (2) of the self-test device via a cable.

9. A self-checking system according to claim 8, characterized in that: The self-test equipment includes a power supply module, an integrated control module and control and processing software; The power supply module is used to receive the power supply control instruction of the integrated control module and return the instruction execution status information, so as to supply power to the sensor, the wind speed generator (2) and the integrated control module; The integrated control module receives instructions from the control and processing software, outputs a PWM signal with a corresponding duty cycle according to the instructions, completes the wind speed control of the wind speed generator (2), receives the air flow speed information collected by the sensor, and sends it to the control and processing software.

10. A self-test method, characterized in that: A self-checking system according to claim 8, the method comprising the following steps: Step 1: Debug the integrated control module and complete the control voltage duty cycle parameter configuration corresponding to different wind speed control instructions; Step 2: Write a test instruction sequence in the control and processing software according to the thruster type. The test sequence is composed of different wind speed control instructions. The wind speed value collected by the wind speed sensor is used as the post-instruction judgment of the wind speed control instruction, and the judgment threshold range is set according to the accompanying reading error; Step 3: According to the nozzle size of the satellite thruster to be tested, adjust the air volume adjustment component (3) so that the position of the adjustment handle (3.3) corresponds to the corresponding air volume adjustment scale (5); Step 4: Confirm that the self-test device is placed horizontally and properly, and the wind speed sensor probe (9) for satellite propulsion polarity test is reliably connected to the self-test device through the sensor clamp (6), so that the wind speed sensor probe (9) is placed at the geometric center of the wind duct tube (4), and while ensuring that the probe polarity is correct, the wind speed sensor probe (9) is perpendicular to the air flow direction; Step 5: Power on the self-test system, confirm that the communication between the control and processing software, the integrated control module, and the power module is normal, and the telemetry parameters are correct, then select the self-test sequence corresponding to the wind speed sensor to be tested and run it; Step 6: The integrated control module receives the wind speed control instruction in the self-test sequence and controls the wind speed generator (2) of the self-test device to generate a standard airflow at a preset wind speed; Step 7: After the self-check point is adjusted and stabilized for 2 minutes, the integrated control module receives the wind speed collection instruction in the self-check sequence, controls the wind speed sensor to collect wind speed information at a frequency of 6 times / minute, and sends the received serial port wind speed information to the control and processing software; Step 8: After the control and processing software receives wind speed data for 6 times, it starts to make automatic judgments. If all 6 wind speed data are within the standard wind speed value range, it can be automatically judged that the performance of the wind speed sensor at the wind speed self-test point meets the requirements; Step 9: In the same manner as steps 6-8, the self-test sequence continues to send the next self-test point wind speed control and automatically interprets it until the self-test of the 8 wind speed self-test points corresponding to the corresponding thruster is completed; Step 10: If the result is abnormal, terminate the self-test and troubleshoot the problem; Step 11: Repeat the above steps 3-10 for different types of thruster states.

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