A self-checking device, system, and method for a sensor for satellite propulsion polarity testing

Abstract

The application discloses a kind of self-checking device, system and method of sensor for satellite propulsion polarity test, the self-checking device includes base, wind speed generator, air duct cylinder, air volume adjusting assembly, the air volume adjusting mechanism of air volume adjusting assembly is formed with the air outlet hole of adjustable aperture, air duct cylinder is connected with the self-checking hole for sensor clamping fixture connection and is set apart with the self-checking hole and the air outlet hole, and the self-checking system includes self-checking device and self-checking equipment, and the self-checking equipment has power module, control module and control and processing software, the application overcomes the influence that wind speed sensor self-checking is susceptible to environmental airflow interference, and the limitation that self-checking condition is harsh, forms a kind of system and method capable of quickly constructing self-checking scene, and self-checking is completed fully automatically, effectively reduces time cost, improves test accuracy, reliability, and the application is suitable for satellite factory and launch site stage propulsion polarity test sensor to carry out relevant test work before self-checking and health status check.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of automation testing, in particular to a self-checking device, system and method for a sensor for satellite propulsion polarity testing. BACKGROUND

[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 powered to collect the wind speed emitted by the corresponding thruster nozzle of the satellite propulsion subsystem attitude control or orbit control. The temperature change caused by the airflow carrying away the heat of the hot wire affects the resistance value, and the resistance change is converted into an electrical signal, thereby measuring the airflow speed information of the thruster nozzle. The electrical signal is input into the propulsion polarity testing equipment in the form of a serial port and completes data logic interpretation, realizing the detection of the satellite propulsion polarity relationship.

[0003] As an important means of judging the health status of the polarity testing equipment before the propulsion polarity test, the self-checking work of the equipment is particularly important, especially the self-checking of the sensor. At present, the self-checking of the sensor for satellite propulsion polarity testing can only be performed by using a fan as a wind source for simple function checking, i.e. checking whether there is a measurement value. However, the thermal wind speed sensor has high sensitivity to temperature, airflow and other external conditions, the impact and fluctuation of the fan are large, and the test distance, wind speed and other factors are not easy to control, so the self-checking data cannot match the precision requirements in the actual use process of the sensor. Although a wind tunnel equipment with higher airflow stability and uniformity can obtain high-quality self-checking data, it has a large size and a complex installation and debugging process, and is not suitable for the requirements of the satellite propulsion polarity testing equipment in different test scenarios, rapid completion of equipment setup, equipment self-checking and product testing on board. SUMMARY

[0004] To solve the technical problems existing in the prior art, the purpose of the present application is to provide a self-checking device, system and method for a sensor for satellite propulsion polarity testing, which overcomes the many restrictions of the self-checking conditions and environment of the sensor for satellite propulsion polarity testing, solves the problem of complex self-checking process, and realizes the purposes of rapid setup of self-checking environment and automation of self-checking process.

[0005] To achieve the above-mentioned application purposes, the present application provides a self-checking device for a sensor for satellite propulsion polarity testing, comprising:

[0006] a base, one end of which is sealingly connected with a wind speed generator;

[0007] A duct cylinder is installed at the end of the base far from the wind speed generator, and a wind volume adjusting assembly is installed at the end of the base, and the wind volume adjusting assembly has a wind volume adjusting mechanism, and a wind outlet hole with adjustable aperture is formed in the middle of the wind volume adjusting mechanism;

[0008] The self-checking hole is arranged at intervals with the wind outlet hole, so that the wind outlet hole and the wind speed sensor probe in the sensor clamping device form a detection distance.

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

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

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

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

[0013] Further, the duct cylinder forms a surplus section for extending the duct cylinder at the side far from the self-checking hole, and a wind outlet is formed at the end of the surplus section.

[0014] Further, the sensor clamping device is arranged perpendicular to the axis of the duct cylinder, and the sensor hot-wire wind speed sensor probe is placed on the geometric center position of the duct cylinder through the sensor clamping device.

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

[0016] The main body is provided with the wind volume adjusting mechanism;

[0017] The adjusting handle is placed outside the duct cylinder, and the outer wall of the duct cylinder is provided with a wind volume adjusting scale.

[0018] Further, the diameter of the wind outlet hole is adjusted in the range of 0-42mm.

[0019] Further, the self-checking device further comprises a base, and the base is fixedly connected to the base and the lower part of the duct cylinder, so that the self-checking device is placed horizontally through the base.

[0020] The self-checking system disclosed in the application comprises the self-checking device and the self-checking equipment of the sensor for testing the polarity of the satellite propulsion.

[0021] Further, the self-checking device comprises a power module, a control module and control and processing software;

[0022] The power module is used for receiving power supply control instructions of the control module and returning instruction execution condition information, and supplies power for the sensor, the wind speed generator and the control module.

[0023] The control module receives instructions of the control and processing software, outputs PWM signals with corresponding duty cycles according to the instructions, completes wind speed control of the wind speed generator, receives airflow speed information collected by the sensor and sends the information to the control and processing software.

[0024] The self-checking method disclosed in the application comprises the self-checking system described above, and comprises the following steps:

[0025] Step 1: debugging the control module, completing control voltage duty cycle parameter configuration corresponding to different wind speed control instructions;

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

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

[0028] Step 4: confirming that the self-checking device is placed horizontally and stably, the wind speed sensor probe for satellite propulsion polarity test is reliably connected with the self-checking device through the sensor clamping device, the wind speed sensor probe is placed at the geometric center position of the air duct cylinder, the probe polarity is ensured to be correct, and the wind speed sensor probe is perpendicular to the airflow direction;

[0029] Step 5: powering on the self-checking system, selecting the self-checking sequence corresponding to the wind speed sensor to be tested and running after confirming that the communication among the control and processing software, the control module and the power module is normal and the telemetry parameters are correct;

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

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

[0032] Step 8: After the wind speed data received by the control and processing software reaches 6 times, the automatic judgment is started, if the 6 wind speed data are all in the wind speed standard value range, the wind speed sensor is considered to meet the requirements at the wind speed self-checking point through the automatic judgment;

[0033] Step 9: According to the mode of steps 6-8, the self-checking sequence continues to send the next self-checking point wind speed control and carries out automatic judgment, until the self-checking of the corresponding 8 wind speed self-checking points of the thruster is completed;

[0034] Step 10: If the judgment result is abnormal, the self-checking is terminated and the problem is checked;

[0035] Step 11: If the state of the different types of thrusters is different, the above steps 3-10 are repeated.

[0036] In the above technical solution, the self-checking device, system and method of the sensor for satellite propulsion polarity test provided by the application have the following beneficial effects compared with the prior art:

[0037] 1) The self-checking device disclosed by the application provides a relatively stable, uniform and self-adjustable air flow environment, and the device is light, small, convenient to disassemble and assemble;

[0038] 2) The self-checking device disclosed by the application adopts a wind volume adjusting assembly, which can adjust the air volume according to the sizes of the nozzles of different types of thrusters, simulate the air flow state of the nozzle when the thruster is jetted, and create an ideal self-checking environment.

[0039] 3) The self-checking device disclosed by the application adopts a wind speed generator, which uses air multiplication technology to optimize the air flow, can generate natural wind with stable air flow, and overcomes the wind impact caused by the air cutting mode of the traditional blade fan, effectively improving the stability of sensor self-checking;

[0040] 4) The self-checking system disclosed by the application can control the wind speed generated by the wind speed generator in the self-checking device in real time, intelligently judge the collected air flow speed information, realize the automation of the self-checking process and the quantitative collection of self-checking data.

[0041] 5) The self-checking method disclosed by the application solves the problem that the satellite propulsion polarity test equipment cannot quickly build a self-checking environment, realizes the goal that the equipment can also complete the self-checking work in the use link, in addition, the self-checking system and the self-checking method can improve the self-checking efficiency while ensuring the self-checking accuracy of the sensor. BRIEF DESCRIPTION OF DRAWINGS

[0042] In order to make the technical solutions in the embodiments of the present application or the prior art clearer, the accompanying drawings needed in the embodiments will be briefly introduced. Obviously, the accompanying drawings in the following description only show some embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort based on these drawings.

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

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

[0045] Figure 3 is a schematic diagram of the air volume adjusting assembly structure of the self-checking device disclosed in the present application;

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

[0047] Figure 5 is a flowchart of the self-checking method disclosed in the present application.

[0048] Explanation of reference signs:

[0049] 1, base; 2, wind speed generator; 3, air volume adjusting assembly; 4, air duct cylinder; 5, air volume adjustment scale; 6, sensor clamping device; 7, base; 8, base; 9, wind speed sensor probe;

[0050] 3.1, main body; 3.2, air volume adjusting mechanism; 3.3, adjusting handle. DETAILED DESCRIPTION

[0051] In order to make the technical solutions in the embodiments of the present application or the prior art clearer, the accompanying drawings needed in the embodiments will be briefly introduced. Obviously, the accompanying drawings in the following description only show some embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort based on these drawings.

[0052] Figure 1 is a schematic diagram of the overall structure of the self-checking device disclosed in the present application;

[0053] Figure 2 is a schematic diagram of the internal structure of the self-checking device disclosed in the present application;

[0054] The self-checking device for the sensor for satellite propulsion polarity test disclosed in the present application comprises:

[0055] The base 1 is sealedly connected with the wind speed generator 2 at one end;

[0056] The air duct cylinder 4 is installed at the end of the base 1 far from the wind speed generator 2, and the air duct cylinder 4 is installed at the end of the base 1 with the air volume adjusting assembly 3, and the air volume adjusting assembly 3 has an air volume adjusting mechanism 3.2, and the air volume adjusting mechanism 3.2 is formed with an air outlet hole with adjustable hole diameter, wherein the air duct cylinder 4 is also provided with a self-checking hole for connecting with the sensor clamping device 6, and the self-checking hole is arranged in a spaced manner with the air outlet hole, so that the air outlet hole and the wind speed sensor probe 9 in the sensor clamping device 6 form a detection distance.

[0057] Specifically, referring to Figure 1 As shown in the figure, in the structure, the base 1 is the basis of the entire self-checking device, used for connecting the wind speed generator 2 and the air volume adjusting assembly 3, and the base 1 is provided with a sealing ring at the interface, which can ensure the airtightness of the power section and the self-checking section of the self-checking device, and at the same time, the airflow direction is kept parallel to the axis of the entire self-checking device.

[0058] The wind speed generator 2 is installed on one side of the base 1, and the interface is designed to be sealed. The external air is sucked into the inside of the wind speed generator 2 through the turbine, flows out through the fine holes of the hollow tubular ring, and advances along the inner wall of the ring-shaped airfoil. The pressure difference formed in front of and behind the center of the ring generates a forward airflow. In this embodiment, the wind speed generator 2 used is a wind speed generator that can generate a continuous and stable airflow of 0-24 m / s in the prior art. The wind speed generator 2 is connected to the self-checking device through a special self-checking cable, and the self-checking device can control the wind speed generator 2 to generate wind of corresponding size.

[0059] The tasks performed by small satellites determine the differences in the type of thruster of the satellite propulsion system. The commonly used thrusters of the propulsion system can be generally divided into 1N, 5N, 10N, etc. according to the thrust size. The size of the thruster nozzle also increases with the increase of the thrust, and the diameter range is generally 15mm-40mm. As can be seen from the nozzle airflow velocity calculation formula v=(F-s*p) / m, the size of the wind speed v is not only determined by the values of the thrust F, the pressure p at the nozzle, and the mass flow m, but also related to the nozzle cross-sectional area s. Therefore, the self-checking device needs to have air volume adjusting capability to simulate the airflow injection width of nozzles of different size thrusters.

[0060] Figure 3 The structure of the air volume adjusting assembly of the self-checking device is shown in the figure.

[0061] Referring to Figure 2 , 3 As shown in the figure, the air volume adjusting assembly 3 is installed on the other side of the base 1, and the air volume adjusting assembly 3 is built-in at the air inlet end of the air duct cylinder 4. The plane of the air volume adjusting assembly 3 is parallel to the cross section of the wind speed generator 2, so that the airflow flows into the air duct cylinder 4 in the direction consistent with the axis of the air duct cylinder 4. The air volume adjusting assembly 3 comprises: a main body 3.1, an air volume adjusting mechanism 3.2, and an adjusting handle 3.3.

[0062] The main body 3.1 is the basis of the air volume adjusting assembly 3, the air volume adjusting mechanism 3.2 is installed on the main body 3.1, and the adjusting handle 3.3 is installed on the air volume adjusting mechanism 3.2. The size of the air outlet is adjusted by controlling the opening and closing of the air baffle of the air volume adjusting mechanism 3.2 through the adjusting handle 3.3, so as to achieve the purpose of adjusting the air volume according to the jet state of different types of satellite thrusters. Specifically, as shown in Figure 3 The air volume adjusting mechanism 3.2 can complete the free adjustment of the air outlet diameter under the control of the adjusting handle 3.3. Preferably, the air outlet diameter adopts a design with a minimum diameter of 0 mm and a maximum diameter of 42 mm, which can adapt to the jet states of the nozzles (diameter 15 mm-40 mm) of the three commonly used types of thrusters on existing small satellites, and also has the self-checking compatibility requirement of the thruster nozzles of smaller micro-nano satellites or batch-produced small satellites;

[0063] Referring to Figure 1 It is shown that:

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

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

[0066] In addition, considering the influence of the air flow environment of the air speed generator 2 and the air volume adjusting assembly 3, the air duct 4 is increased by 20 cm of pipe length allowance. Preferably, the air duct 4 is formed with an allowance section for lengthening the air duct 4 on the side away from the air outlet hole of the self-checking hole, and the allowance section is formed with an air outlet hole at the end;

[0067] Specifically, the air duct 4 adopts a 32 cm long, 6 cm inner diameter, 0.4 cm thickness, smooth inner wall acrylic round pipe. The air volume adjusting assembly is installed at the pipe length 9 cm of the air duct 4, and the self-checking hole is opened at the pipe length 12 cm of the air duct 4 and is connected with the sensor clamping device 6. This structure effectively guarantees the stable and uniform flow of the self-checking airflow;

[0068] The air volume adjustment scale 5 is arranged on the air duct cylinder 4 and cooperates with the air volume adjustment assembly 3, and is used for indicating different jet states of the thrustor corresponding to the opening and closing sizes of the air volume adjustment mechanism, and the numbers 0-8 correspond to eight scales respectively, which represent the hole diameter sizes of the air volume adjustment mechanism from small to large, i.e. 0mm for the hole diameter, 5mm for the hole diameter, 10mm for the hole diameter, and 40mm for the hole diameter, and the self-checking can be carried out according to the jet size state of the satellite thrustor to be measured, and the air volume adjustment scale 5 provides a standard scale basis for the air volume adjustment assembly 3.

[0069] The sensor for testing the polarity of the small satellite propeller is designed in a cylindrical structure with a length of 95mm and a diameter of 14mm, and the front 15mm part is a sensor head embedded with a metal heating film. When measuring the wind speed, the metal film is basically maintained at a constant temperature by using the current change through the metal film, i.e. the resistance is basically constant. At different wind speeds, the current wind speed value can be measured by the function relationship between the heat loss power of the metal film and the wind speed. The sensor needs to be measured according to the wind direction of the polarity mark.

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

[0071] Referring to Figure 1 As shown in the figure, the self-checking device further includes a base 7 and a base 8, the base 7 is connected with the air duct cylinder 4, and the base 8 is connected with the base 1, so that the self-checking device can be placed horizontally and stably.

[0072] The self-checking device has a small and light appearance, and the weight is about 260g. Through reasonable design, the self-checking device is easy to assemble and has good operability. Moreover, the self-checking device can build a relatively stable, uniform and adjustable fluid gas field environment for the sensor, and also completes the limiting and fixing installation of the sensor.

[0073] Figure 4 The self-checking system is composed of the self-checking device and the self-checking equipment of the sensor for testing the polarity of the satellite propeller.

[0074] The self-checking system disclosed by the application includes the self-checking device and the self-checking equipment of the sensor for testing the polarity of the satellite propeller, and the self-checking equipment is connected with the wind speed sensor and the wind speed generator 2 of the self-checking device through a special self-checking cable.

[0075] The self-checking equipment includes a power module, a control module and control and processing software.

[0076] The power module receives the power control instructions of the control module and returns instruction execution information, and supplies power for the sensor, the wind speed generator 2 and the control module.

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

[0078] The small satellite propulsion system is generally composed of a propulsion tank, a propulsion pipeline, a self-locking valve, an electromagnetic valve, a thruster and the like. According to the relevant test requirements of the satellite, the propulsion tank needs to store a certain amount of test gas, and the pressure of the tank is generally set at 0.2 MPa. Since the nozzle pressure of the thruster is affected by many factors such as the pressure of the propulsion tank, the length of the propulsion pipeline, the state of the self-locking valve, the state of the electromagnetic valve and the like, the wind speed generated by the nozzle of the thruster also has certain differences. Therefore, multiple self-checking points need to be selected to cover the wind speed range generated by the nozzle of the thruster during self-checking. According to the test experience, the wind speed generated by the small satellite thruster is generally concentrated in the range of 1.5 m / s to 10 m / s. Therefore, 8 wind speed self-checking points of 1.5, 2.5, 4, 6, 8, 10, 7.5 and 3 are set in turn, which are represented by N1, N2,..., N8 respectively, and the interpretation error range of each self-checking point is ±0.5 m / s.

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

[0080] The control and processing software pre-compile self-checking instruction sequence according to the 8 self-checking points of the wind speed sensor. In the self-checking sequence of each self-checking point, the test instruction is sent to the control module to control the control module to set the working gear of the wind speed generator 2, and the collected wind speed information and the wind speed control gear information are automatically interpreted to obtain the self-checking result.

[0081] Figure 5 The self-checking method flow chart

[0082] The application also discloses a self-checking method using the above self-checking system, which comprises the following steps:

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

[0084] Step 2: According to the type of thruster, the control and processing software writes a test instruction sequence, which 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. The threshold range is set according to the reading error. Specifically, there are three kinds of test sequences prepared and used, corresponding to 1N, 5N and 10N thrusters respectively. Taking the 1N thruster as an example, the self-checking steps of the wind speed self-checking point N1 (1.5 m / s) are described below.

[0085] Step 3: According to the nozzle size of the satellite thruster to be tested (1N, 5N, 10N), adjust the air volume adjusting assembly 3 so that the adjusting handle 3.3 is at the corresponding air volume adjusting scale 5. For example, if the current thruster to be tested is 1N, its nozzle diameter is 15mm, then the adjusting handle 3.3 is adjusted to the scale position of the number 3.

[0086] Step 4: Confirm that the self-checking device is placed horizontally and stably. The wind speed sensor probe 9 for satellite propulsion polarity test is reliably connected to the self-checking device through the sensor clamping device 6, so that the wind speed sensor probe 9 is placed at the geometric center position of the air duct cylinder 4, ensuring that the probe polarity is correct and the sensor probe inlet is perpendicular to the airflow direction.

[0087] Step 5: Power on the self-checking system. After confirming 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, select the self-checking 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-checking sequence, controls the wind speed generator 2 of the self-checking device, and generates standard airflow at wind speed N1 (1.5 m / s).

[0089] Step 7: After the self-checking point is adjusted and stabilized for 2 minutes, the integrated control module receives the wind speed collection instruction in the self-checking sequence, controls the wind speed sensor to collect wind speed information at a frequency of 6 times per 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 6 wind speed data, it starts automatic judgment. If the 6 wind speed data are all within the range of wind speed N1 ± 0.5 m / s, it can pass the automatic judgment and consider that the performance of the wind speed sensor at this wind speed self-checking point N1 meets the requirements.

[0091] Step 9: According to the method of steps 6-8, the self-checking sequence continues to send wind speed N2 (2.5 m / s) control and perform automatic judgment until the self-checking of the corresponding 8 wind speed self-checking points (N1-N8) of the corresponding thruster is completed.

[0092] Step 10: If the judgment result is abnormal, terminate the self-checking and troubleshoot the problem.

[0093] Step 11: different type of thruster state, then repeat the above steps 3-10, after self-checking, the self-checking system records the measurement data, power off, end of detection.

[0094] In summary, the self-checking device, system and method for the sensor for satellite propulsion polarity test disclosed by the application, the controllable uniform standard airflow is generated by the self-checking system, after the airflow information is collected by the wind speed sensor for polarity test installed in the self-checking device, the self-checking equipment carries out logical interpretation on the airflow information, wind speed control information, self-checking threshold and the like, so as to form the self-checking result of the sensor, the self-checking system is composed of the self-checking device and the self-checking equipment, the base, the wind speed generator, the air volume adjusting assembly, the air duct cylinder, the air volume adjustment scale, the sensor clamping device, the base and the like are combined to form the wind speed sensor self-checking device; the self-checking equipment includes the comprehensive control module, the power module, the control and processing software, the application overcomes the influence of the wind speed sensor self-checking on the environmental airflow interference and the limitation of the harsh self-checking condition, forms a system and method capable of quickly constructing the self-checking scene and automatically completing the self-checking, effectively reduces the time cost, improves the test accuracy and reliability, and the application is suitable for the self-checking and health state checking of the sensor for satellite factory and launch site stage propulsion polarity test before carrying out the related test work.

[0095] The above description is merely illustrative of the specific embodiments of the application, and is not intended to limit the scope of the application. Any equivalent changes, modifications and combinations made by any person skilled in the art without departing from the concept and principle of the application shall fall within the scope of the application.

Claims

1. A self-checking method, characterized by, The self-checking system comprises a self-checking device of a satellite propulsion polarity test sensor and a self-checking apparatus connected with the sensor and a wind speed generator (2) of the self-checking device through a cable; the self-checking device of the satellite propulsion polarity test sensor comprises: a base (1) having a wind speed generator (2) connected at one end thereof; a wind channel cylinder (4) installed at the end of the base (1) away from the wind speed generator (2), wherein a wind volume adjusting assembly (3) is installed at the end of the base (1), the wind volume adjusting assembly (3) has a wind volume adjusting mechanism (3.2) with an adjustable air outlet hole in the middle thereof; wherein a self-checking hole for connecting with a sensor clamping device (6) is further formed in the wind channel cylinder (4), the self-checking hole is arranged at intervals with the air outlet hole, so that the air outlet hole and a wind speed sensor probe (9) in the sensor clamping device (6) form a detection interval; the self-checking method comprises the following steps: Step 1: debugging the integrated control module to complete the control voltage duty cycle parameter configuration corresponding to different wind speed control instructions; Step 2: writing test instruction sequences in the control and processing software according to the type of the thruster, the test sequences are composed of different wind speed control instructions, the wind speed value collected by the wind speed sensor is used as the instruction after judgment of the wind speed control instruction, and a judgment threshold range is set according to the judgment error; Step 3: adjusting the wind volume adjusting assembly (3) according to the nozzle size of the satellite to be tested, so that the position of the adjusting handle (3.3) corresponds to the corresponding wind volume adjusting scale (5); Step 4: confirming that the self-checking device is placed horizontally and stably, the satellite propulsion polarity test wind speed sensor probe (9) and the self-checking device are reliably connected through the sensor clamping device (6), the wind speed sensor probe (9) is placed at the geometric center position of the wind channel cylinder (4), the wind speed sensor probe (9) is perpendicular to the airflow direction, and the polarity of the probe is correct; Step 5: powering on the self-checking system, selecting the self-checking sequence corresponding to the wind speed sensor to be tested and running after confirming 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; Step 6: the integrated control module receives the wind speed control instruction in the self-checking sequence, controls the wind speed generator (2) of the self-checking device to generate standard airflow at a preset wind speed; Step 7: after the self-checking point is adjusted and stabilized for 2 minutes, the integrated control module receives the wind speed collection instruction in the self-checking sequence, controls the wind speed sensor to collect wind speed information at a frequency of 6 times per 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 automatic judgment, if the 6 wind speed data are all within the wind speed standard value range, the wind speed sensor at the self-checking point is considered to meet the requirements through automatic judgment; Step 9: the next self-checking point wind speed control is sent and automatic judgment is performed in the self-checking sequence in the manner of steps 6-8, until the self-checking of 8 self-checking points corresponding to the corresponding thruster is completed. Step 10: If the interpretation result is abnormal, terminate the self-checking and troubleshoot the problem; Step 11: If the state of the different types of thrusters is different, repeat steps 3-10.

2. The self-checking method of claim 1, wherein the self-checking device comprises a power module, a control module, and control and processing software. The power module is used to receive power supply control instructions from the control module and return instruction execution information, and to supply power to the sensor, the wind speed generator (2), and the control module. The control module receives instructions from the control and processing software, outputs corresponding duty cycle PWM signals according to the instructions, completes wind speed control of the wind speed generator (2), receives airflow speed information collected by the sensor, and sends the information to the control and processing software.

3. The self-checking method of claim 1, wherein the ratio of the windward area of the hot wire part of the wind speed sensor probe (9) in the sensor clamping device (6) to the cross-sectional area of the working section of the wind tunnel cylinder (4) is not greater than 5%. The detection distance l can be obtained by the formula l = 0.25d~0.5d. The length L of the wind tunnel cylinder (4) can be obtained by the formula L = 2.0d~4.0d. Where d is the inner diameter of the wind tunnel cylinder (4).

4. The self-checking method of claim 1 or 3, wherein the wind tunnel cylinder (4) is located on the side of the self-checking hole away from the air outlet hole and forms a surplus section for extending the wind tunnel cylinder (4), and the surplus section forms an air outlet at the end.

5. The self-checking method of claim 1, wherein the sensor clamping device (6) is perpendicular to the axis of the wind tunnel cylinder (4), and the sensor hot-wire wind speed sensor probe (9) is placed on the geometric center of the wind tunnel cylinder (4) through the sensor clamping device (6).

6. The self-checking method of claim 1, wherein the air volume adjusting assembly (3) comprises a main body (3.1) installed in the wind tunnel cylinder (4) and an adjusting handle (3.3) for adjusting the diameter of the air outlet of the air volume adjusting mechanism (3.2). The main body (3.1) is provided with the air volume adjusting mechanism (3.2). The adjusting handle (3.3) is placed outside the wind tunnel cylinder (4), and the outer wall of the wind tunnel cylinder (4) is provided with an air volume adjustment scale (5).

7. The self-checking method of claim 6, wherein the diameter adjustment range of the air outlet is 0-42mm.

8. The self-checking method of claim 1, wherein the self-checking device of the sensor for testing the polarity of the satellite thruster further comprises a base, and the wind tunnel cylinder (4) and the base (1) are respectively fixedly connected with a base (7, 8), so that the self-checking device can be placed horizontally through the base. ​ ​ ​ ​ ​ ​ ​

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