Ground test method for spaceflight high-precision acceleration sensor in orbit environment adaptability

Abstract

The application provides a spaceflight high-precision acceleration sensor on-orbit environment adaptability ground test method, comprising the following steps: S1, primary calibration of the sensor; S2, vibration test of the sensor; S3, precision test of the sensor; S4, impact test of the sensor by applying an impact power spectrum; S5, normal-pressure temperature change test of the sensor; S6, hot-vacuum temperature change test of the sensor; S7, irradiation test of the sensor; S8, calibration of the sensor, compared with the primary calibration, if the error of the two calibrations is within the tolerance, the sensor is considered to pass the environment test verification. The scheme of the application can test the high-precision acceleration sensor for spaceflight environment through the ground test method, and screen out the acceleration sensor capable of meeting the requirements of high-precision spacecrafts such as space telescopes, high-resolution remote sensing satellites, laser communication satellites and the like.

Description

Technical Field

[0001] This invention belongs to the field of environmental testing of accelerometers, specifically relating to ground testing methods for the on-orbit environmental adaptability of high-precision aerospace accelerometers. Background Technology

[0002] With the vigorous development of aerospace technology, various types of spacecraft have emerged one after another. In order to meet the long-term on-orbit operation of spacecraft, a batch of reliable acceleration sensors that meet the needs of spaceflight and can measure acceleration are required.

[0003] With the improvement of key performance aspects such as imaging quality and pointing accuracy of high-precision spacecraft such as space telescopes, high-resolution remote sensing satellites, and laser communication satellites, a batch of high-precision accelerometers capable of measuring minute accelerations are needed. Compared with the previous sensors that only needed to meet the impact conditions during the ascent phase, the high-precision accelerometers with increased accuracy will have their impact resistance, adaptability to temperature alternation environments, and electromagnetic interference resistance affected.

[0004] However, the existing equipment reserves are insufficient to directly select an accelerometer sensor to meet the high-precision acceleration measurement requirements of aerospace. This makes it imperative to use experimental methods to screen out a high-precision accelerometer sensor that can meet the requirements of aerospace.

[0005] To ensure the on-orbit performance of the accelerometer, a separate adaptability test verification of the high-precision accelerometer needs to be carried out during the development process. The test includes impact test during the ascent phase, temperature alternation test during on-orbit operation, thermal vacuum test, electromagnetic radiation test, and irradiation test.

[0006] Currently, there is no ground-based testing method for high-precision accelerometers designed for aerospace environments. Summary of the Invention

[0007] This invention aims to provide a ground test method for the on-orbit environmental adaptability of high-precision accelerometers, to meet the on-orbit operation requirements of my country's new generation of ultra-large spacecraft.

[0008] To solve the above problems, the present invention adopts the following technical solution:

[0009] This invention provides a ground-based test method for the on-orbit environmental adaptability of a high-precision aerospace accelerometer, comprising the following steps:

[0010] S1: Perform initial calibration of the sensor. When the sensor passes the calibration test, proceed to the next step.

[0011] S2: Conduct a vibration test on the sensor. If the vibration test requirements for spacecraft are met, proceed to the next step.

[0012] S3: Perform an accuracy test on the sensor. If the accuracy meets the spacecraft requirements, the sensor is deemed to meet the requirements, and proceed to the next step.

[0013] S4: Apply an impact power spectrum to the sensor and conduct an impact test under spacecraft qualification-level conditions. If the sensor can work normally after the impact test, it is determined that the sensor has passed the impact test and proceeds to the next step.

[0014] S5: Perform an ambient pressure temperature change test on the sensor. If no abnormal signal is detected, the sensor has passed the ambient pressure temperature change test. Proceed to the next step.

[0015] S6: Perform a thermal vacuum temperature change test on the sensor. If no abnormal signal is detected, the sensor can be determined to have passed the thermal vacuum temperature change test. Proceed to the next step.

[0016] S7: Conduct an irradiation test on the sensor. During the irradiation test, set the irradiation dose and irradiation time according to the spacecraft qualification test conditions, and do not supply power to the sensor.

[0017] S8: The sensor is calibrated. If the error between the two calibrations is within the tolerance, the sensor is considered to have passed the environmental test verification.

[0018] Furthermore, in step S1, if the sensor fails to meet the accuracy requirements of the spacecraft, the sensor is determined to be non-compliant.

[0019] Furthermore, in step S2, the vibration test includes a sinusoidal test and a random test.

[0020] Furthermore, in step S4, during the impact test, the sensor is only powered and no signal is collected.

[0021] Furthermore, in step S5, during the ambient pressure temperature change test, the temperature range and temperature change rate are set according to the spacecraft qualification test conditions. During the temperature change test, the sensor is powered on and sensor data is collected in real time to monitor the temperature change test process in real time. Any abnormal signals that may occur during the measurement can be mutually verified by several sensors.

[0022] Furthermore, in step S6, during the thermal vacuum temperature change test, the temperature range and holding time are set according to the spacecraft qualification-level test conditions. During the temperature change test, the sensor is powered on and sensor data is collected in real time to monitor the thermal vacuum temperature change test process in real time. At the same time, any abnormal signals that may occur during the measurement can be mutually verified by several sensors.

[0023] Beneficial effects—The advantages of this invention compared to the prior art are:

[0024] Using the solution of this invention, high-precision accelerometers in the space environment can be tested through ground-based testing methods to screen out accelerometers that can meet the requirements of high-precision spacecraft, including space telescopes, high-resolution remote sensing satellites, and laser communication satellites. Attached Figure Description

[0025] Figure 1 This is a flowchart of the high-precision acceleration sensor adaptability test in an embodiment of the present invention. Detailed Implementation

[0026] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be described in detail below with reference to the accompanying drawings. The description in this part is only exemplary and explanatory, and should not be used to limit the scope of protection of the present invention in any way.

[0027] High-precision accelerometers primarily serve the on-orbit operation of spacecraft. Therefore, the sensors need to meet both launch and on-orbit conditions. Launch testing requires verification through shock tests; on-orbit testing requires atmospheric pressure temperature change tests, thermal vacuum temperature change tests, and irradiation tests. For high precision, calibration is required before and after testing, with the error between the two calibrations within the permissible tolerance range. Furthermore, since shock testing is destructive, it is placed first. The damage caused by shock to the sensor accumulates as the testing progresses; therefore, when conducting adaptability tests on accelerometers, shock testing is performed first, followed by subsequent tests.

[0028] like Figure 1 This implementation plan takes a certain model as an example to introduce the test method for adaptability of aerospace high-precision accelerometers.

[0029] S001 First, the high-precision accelerometer is calibrated. If the sensor does not meet the calibration conditions, it is determined that the sensor does not meet the requirements. When the sensor passes the calibration test, proceed to step S002.

[0030] S002 For sensors that have passed the calibration test, a vibration test (including a sinusoidal test and a random test) is performed. If the vibration test is passed, proceed to step S003.

[0031] S003 For sensors that have passed the vibration test, an accuracy test is performed. When the noise floor of the sensor in the required frequency band is less than the specified maximum value, the sensor is deemed to meet the requirements and proceed to step S004.

[0032] S004 For sensors that meet the accuracy requirements, an impact power spectrum test is performed. During the impact test, the sensor is only powered and no signal is collected. During the impact test, the sensor is impacted three times in each of the X, Y, and Z directions. After each impact, the sensor's operation is checked. If the sensor can work normally, it is determined that the sensor has passed the impact test and proceeds to step S005.

[0033] S005 Perform an atmospheric pressure temperature change test on the sensor that meets the impact requirements. In the atmospheric pressure temperature change test, set the temperature range T1 and the temperature change rate V1, and keep it at high and low temperatures for h1 hours. During the temperature change test, the sensor is powered on and the sensor data is collected in real time. The temperature change test process is monitored in real time. Any abnormal signals that may occur during the measurement can be verified by several sensors. If there are no abnormal signals, it can be determined that the sensor has passed the atmospheric pressure temperature change test. Proceed to step S006.

[0034] S006 Perform a thermal vacuum temperature change test on the sensor that meets the normal pressure temperature change test. During the thermal vacuum temperature change test, set the temperature range T2 and keep it at high and low temperatures for h2 hours. During the temperature change test, power the sensor and collect sensor data in real time. Monitor the thermal vacuum temperature change test process in real time. If any abnormal signals may occur during the measurement, they can be verified by several sensors. If there are no abnormal signals, it can be determined that the sensor has passed the thermal vacuum temperature change test. Proceed to step S007.

[0035] S007 Finally, an irradiation test was conducted on the sensor. During the irradiation test, the sensor was not powered, and the irradiation test dose rate and irradiation time T3 were set.

[0036] After the S008 irradiation test is completed, the sensor is calibrated. If the error between the two calibrations is within 10% of the allowable tolerance, the sensor can be considered to have passed the environmental test verification.

[0037] This article uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. The above descriptions are only preferred embodiments of the present invention. It should be noted that due to the limitations of textual expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of the present invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of the present invention.

Claims

1. A ground test method for the on-orbit environmental adaptability of a high-precision aerospace accelerometer, characterized in that, Includes the following steps: S1: Perform initial calibration of the sensor. When the sensor passes the calibration test, proceed to the next step. S2: Conduct a vibration test on the sensor. If the vibration test requirements for spacecraft are met, proceed to the next step. S3: Perform an accuracy test on the sensor. If the accuracy meets the spacecraft requirements, the sensor is deemed to meet the requirements, and proceed to the next step. S4: Apply an impact power spectrum to the sensor and conduct an impact test under spacecraft qualification-level conditions. If the sensor can work normally after the impact test, it is determined that the sensor has passed the impact test and proceeds to the next step. S5: Perform an ambient pressure temperature change test on the sensor. If no abnormal signal is detected, the sensor has passed the ambient pressure temperature change test. Proceed to the next step. S6: Perform a thermal vacuum temperature change test on the sensor. If no abnormal signal is detected, the sensor can be determined to have passed the thermal vacuum temperature change test. Proceed to the next step. S7: Conduct an irradiation test on the sensor. During the irradiation test, set the irradiation dose and irradiation time according to the spacecraft qualification test conditions, and do not supply power to the sensor. S8: The sensor is calibrated. If the error between the two calibrations is within the tolerance, the sensor is considered to have passed the environmental test verification.

2. The method according to claim 1, characterized in that, In step S1, if the sensor fails to meet the accuracy requirements of the spacecraft, it is determined that the sensor does not meet the requirements.

3. The method according to claim 1, characterized in that, In step S2, the vibration test includes a sinusoidal test and a random test.

4. The method according to claim 1, characterized in that, In step S4, during the impact test, the sensor is powered but no signal is collected.

5. The method according to claim 1, characterized in that, In step S5, during the ambient pressure temperature change test, the temperature range and temperature change rate are set according to the spacecraft qualification test conditions. During the temperature change test, the sensor is powered on and sensor data is collected in real time. The temperature change test process is monitored in real time. Any abnormal signals that may occur during the measurement can be mutually verified by several sensors.

6. The method according to claim 1, characterized in that, In step S6, during the thermal vacuum temperature change test, the temperature range and holding time are set according to the spacecraft qualification-level test conditions. During the temperature change test, the sensor is powered on and sensor data is collected in real time to monitor the thermal vacuum temperature change test process in real time. At the same time, any abnormal signals that may occur during the measurement can be mutually verified by several sensors.

Images