An on-orbit micro-thrust measurement simulation system of electrostatically suspended accelerometer

Abstract

The application relates to an on-orbit micro-thrust measurement simulation system of an electrostatic suspension accelerometer, and belongs to the technical field of high-precision acceleration measurement simulation. The system comprises an on-orbit parameter simulation device and an electrostatic suspension accelerometer output measurement device; wherein the on-orbit parameter simulation device is used for simulating an on-orbit simulation environment of the electrostatic suspension accelerometer, and comprises acceleration simulation, noise simulation and satellite attitude simulation; and the electrostatic suspension accelerometer output measurement device is used for processing the output of the electrostatic suspension accelerometer, and the processing result is divided into two paths, one of which is used as primary non-conservative force acceleration data measured by the accelerometer and is fed back to the electrostatic suspension accelerometer, and the other of which is used as electrostatic force acceleration of a mass block after the mass block is subjected to electrostatic force and is used for measuring the electrostatic suspension accelerometer.

Description

TECHNICAL FIELD

[0001] The application relates to an on-orbit micro-thrust measurement simulation system of an electrostatic suspension accelerometer, and belongs to the technical field of high-precision acceleration measurement simulation. BACKGROUND

[0002] The electrostatic suspension accelerometer (hereinafter referred to as an accelerometer) is a quasi-steady, micro-precision acceleration measurement device, which can measure the non-conservative force perturbation (including solar radiation pressure, earth albedo and radiation pressure perturbation, micro-vibration and micro-thrust) received by a satellite during on-orbit operation with high precision (better than 1 ng), and can provide real-time non-conservative force data for on-orbit precise orbit determination of the satellite, and has important uses in the fields of gravity field measurement, navigation model optimization, precise orbit determination, satellite drag-free control, gravitational wave detection and space inertial reference technology, and is an important symbol of the advancement of space technology.

[0003] The accelerometer adopts a high-precision differential capacitance detection method to measure the displacement between a mass block and an electrode cage with a measurement precision of pm order, then takes the displacement detection value as a bias value, inputs a PID controller for calculation, and applies a feedback control voltage to the electrode plate through a feedback driving circuit, so that the mass block is stably positioned at the center of the electrode cage under the action of the electrostatic force. In the closed-loop control state, the feedback readout voltage is combined with a scale factor to represent the non-conservative force acting on the satellite, and the measurement resolution is better than ng level. The measurement principle of a single channel of the electrostatic suspension accelerometer is as shown in the figure. Figure 1

[0004] In the case of ignoring the influence of nonlinear factors, the measurement result of the electrostatic suspension accelerometer is expressed by the following formula:

[0005] a el =B+G P V f

[0006] Wherein, a el is the measurement value of the electrostatic suspension accelerometer; B is the measurement bias value; V f is the feedback voltage; and G P is the sensitivity coefficient.

[0007] With the development of space technology, the users have higher and higher requirements for the orbit control of the satellite, and the orbit determination accuracy develops from meter level to centimeter level and millimeter level. With the improvement of the orbit accuracy index, various non-conservative forces received by the satellite on orbit have an increasingly important influence on the orbit. Therefore, accurately measuring the non-conservative force received by the satellite on orbit and the micro-thrust received by the satellite during attitude and orbit control becomes the basis for precise orbit determination and high-precision autonomous navigation. The electrostatic suspension accelerometer is the most mature and reliable device for measuring the non-conservative force acceleration of the satellite. The on-orbit environment of the satellite is complex, and platform micro-vibration, temperature fluctuation and satellite attitude are the main factors affecting the measurement accuracy of the accelerometer.​ SUMMARY

[0008] Therefore, the application aims at the real scene simulation problem of accelerometer measuring satellite micro-thrust in complex background environment, and provides an on-orbit micro-thrust measurement simulation system of electrostatic suspension accelerometer.

[0009] The application is implemented by the following technical solutions.

[0010] An on-orbit micro-thrust measurement simulation system of electrostatic suspension accelerometer comprises an on-orbit parameter simulation device and an electrostatic suspension accelerometer output measurement device, wherein

[0011] The on-orbit parameter simulation device is used for simulating and generating an on-orbit simulation environment of electrostatic suspension accelerometer, including acceleration simulation, noise simulation and satellite attitude simulation.

[0012] The electrostatic suspension accelerometer output measurement device is used for processing the output of the electrostatic suspension accelerometer, and the processing result is divided into two paths, one of which is the primary non-conservative force acceleration data measured by the accelerometer and is fed back to the electrostatic suspension accelerometer, and the other is the electrostatic force acceleration of the mass block after being subjected to the electrostatic force and is used for measuring the electrostatic suspension accelerometer.

[0013] Further, the on-orbit parameter simulation device comprises a micro-thruster input module, a non-conservative force model and background noise input module, a high-frequency micro-vibration sensor measurement and preprocessing module and a center-of-mass deviation related acceleration processing module.

[0014] The micro-thruster input module is used for outputting the measured data or simulation data of satellite thrust acceleration to the electrostatic suspension accelerometer.

[0015] The non-conservative force model and background noise input module comprises an atmospheric drag model module, a light pressure model module and an accelerometer background noise module; the atmospheric drag model module is used for simulating the atmospheric drag acceleration of the satellite at different orbital altitudes and outputting the atmospheric drag acceleration to the electrostatic suspension accelerometer; the light pressure model module is used for simulating the solar light pressure acceleration of the satellite at different orbital altitudes and outputting the solar light pressure acceleration to the electrostatic suspension accelerometer; and the accelerometer background noise module is used for simulating the accelerometer background noise level and outputting the accelerometer background noise level to the electrostatic suspension accelerometer.

[0016] The high-frequency micro-vibration sensor measurement and preprocessing module comprises a high-frequency vibration acceleration data module and a high-pass filtering processing module; the high-frequency vibration acceleration data module is used for simulating the micro-vibration level of a satellite platform, and outputs the micro-vibration acceleration data obtained in simulation or experiment to the high-pass filtering processing module; the high-pass filtering processing module is used for filtering out low-frequency noise in the micro-vibration experimental data caused by device temperature drift and earth pulsation, and outputs the acceleration data close to the actual micro-vibration level of the satellite platform in orbit to the electrostatic suspension accelerometer;

[0017] The centroid deviation related acceleration processing module comprises a satellite centroid fluctuation over time module and a satellite attitude sensor attitude data processing module; the satellite centroid fluctuation over time module is used for simulating the change of the satellite centroid over time, and outputs to the electrostatic suspension accelerometer; the satellite attitude sensor attitude data processing module is used for simulating the change of the attitude angular velocity and angular acceleration of the satellite in orbit, and outputs to the electrostatic suspension accelerometer.

[0018] Further, the electrostatic suspension accelerometer output measurement device comprises a displacement detection module, an electronic displacement detection end temperature measurement module, an electronic driving amplification circuit temperature measurement module, an accelerometer output data preprocessing module, and a sensor physical feedback and temperature influence processing module; wherein,

[0019] The displacement detection module is used for detecting the differential capacitance value output by the accelerometer, and inputting the displacement detection result to the electronic displacement detection end temperature measurement module;

[0020] The electronic displacement detection end temperature measurement module is used for simulating the influence of the temperature change in orbit on the displacement detection circuit, and outputs the displacement detection voltage value containing the temperature influence to the sampling module;

[0021] The sampling module is used for sampling the output displacement detection voltage value, and outputs the sampling result to the PID control module;

[0022] The PID control module is used for generating a feedback control voltage taking the displacement detection voltage value as an error control object, and outputs to the electronic driving amplification circuit temperature measurement module;

[0023] The electronic driving amplification circuit temperature measurement module is used for outputting the driving amplification voltage to the low-pass filter after amplification according to the initial voltage value output by the PID control module;

[0024] The low-pass filter is used for low-pass filtering the output driving amplification voltage, and outputs the filtering result to the accelerometer output data preprocessing module and the sensor physical feedback and temperature influence processing module;

[0025] The accelerometer output data pre-processing module is used for correcting the accelerometer output bias value and filtering, and outputs scientific measurement data of the accelerometer meeting the technical requirements, and the output result is primary non-conservative force acceleration data obtained by the accelerometer measurement, and after ground data processing, non-conservative force acceleration data of the satellite is obtained.

[0026] The sensor physical feedback and temperature influence processing module is used for obtaining corresponding control acceleration according to the feedback driving voltage, and outputting electrostatic force acceleration of the mass block after being subjected to the electrostatic force.

[0027] Beneficial effects:

[0028] Firstly, by respectively accurately simulating the main non-conservative force acceleration of the satellite in orbit, combining the electrostatic suspension accelerometer system simulation model, and performing fusion processing of different sensor data, the single-axis measurement of the satellite micro thruster in orbit is simulated in a real scene. By comparing different types of accelerometers, the key design parameters of the accelerometer meeting the actual control requirements can be obtained, and a simulation foundation for subsequent autonomous flight and precise orbit determination of the satellite in the navigation denial situation is laid.

[0029] Secondly, in order to ensure that the accelerometer accurately measures the satellite micro thrust, the application simulates and processes multiple data sources, combines the accelerometer system simulation model, and performs a real scene simulation on the in-orbit measurement process of the satellite micro thrust acceleration, so as to obtain the key indicators of the accelerometer which can reduce the orbit error to within 1m. DETAILED DESCRIPTION

[0030] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0031] Figure 1 It is an acceleration meter single channel measurement block diagram;

[0032] Figure 2 It is an electrostatic suspension accelerometer in-orbit micro-thrust measurement simulation system block diagram;

[0033] Figure 3 It is a 100mN thruster starting and whole process thrust simulation curve;

[0034] Figure 4 It is the simulated input satellite micro-vibration data, (a) is acceleration, (b) is frequency spectrum;

[0035] Figure 5 It is the simulated input satellite angular velocity;

[0036] Figure 6 for simulating input satellite angular acceleration;

[0037] Figure 7 for simulating input data of mass center change;

[0038] Figure 8 for simulating input data of solar pressure perturbation

[0039] Figure 9 for simulating input data of accelerometer noise floor; (a) is noise floor, (b) is frequency spectrum;

[0040] Figure 10 for simulating input data and system output data time domain comparison chart;

[0041] Figure 11 for simulating input data and system output data time domain comparison chart;

[0042] Figure 12 for simulating input data and system output data time domain comparison chart; DETAILED DESCRIPTION

[0043] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0044] It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict; and all other embodiments obtained by those skilled in the art based on the embodiments in the present disclosure without creative labor are within the scope of protection of the present disclosure.

[0045] It should be noted that the various aspects of the embodiments described below are within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms and that any specific structure and / or function described herein is merely illustrative. Based on the teachings herein one skilled in the art should appreciate that an aspect described herein can be implemented independently of any other aspects and that an aspect can be implemented both as any number of devices and / or as any number of methods. For example, an apparatus can be implemented using any number of the aspects described herein. In addition, an apparatus can be implemented using any number of the aspects described herein in combination with one another and / or in combination with other structures and / or functions described herein.

[0046] The on-orbit micro-thrust measurement simulation system of the electrostatic suspension accelerometer according to the embodiment of the present application comprises an on-orbit parameter simulation device and an electrostatic suspension accelerometer output measurement device; wherein,

[0047] The in-orbit parameter simulation device is used for simulating a simulation environment of the electrostatically suspended accelerometer in orbit, including acceleration simulation, noise simulation, and satellite attitude simulation.

[0048] The electrostatically suspended accelerometer output measurement device is used for processing the output of the electrostatically suspended accelerometer, and the processing result is divided into two paths, one of which is the primary non-conservative force acceleration data measured by the accelerometer and is fed back to the electrostatically suspended accelerometer, and the other is the electrostatic force acceleration of the mass block after being subjected to the electrostatic force and is used for measuring the electrostatically suspended accelerometer.

[0049] In the embodiment of the application, the in-orbit parameter simulation device includes a micro-thruster input module (1), a non-conservative force model and background noise input module (2), a high-frequency micro-vibration sensor measurement and preprocessing module (3), and a center-of-mass deviation related acceleration processing module (4); the electrostatically suspended accelerometer output measurement device includes a displacement detection module, an electronic displacement detection end temperature measurement module (5), an electronic driving amplification circuit temperature measurement module (6), an accelerometer output data preprocessing module (7), and a sensor physical feedback and temperature influence processing module (8).

[0050] The micro-thruster input module (1) is used for outputting measured data or simulation data of satellite thrust acceleration to the electrostatically suspended accelerometer.

[0051] The non-conservative force model and background noise input module (2) includes an atmospheric drag model module, a light pressure model module, and an accelerometer background noise module; the atmospheric drag model module is used for simulating atmospheric drag acceleration of the satellite at different orbital altitudes and outputting the atmospheric drag acceleration to the electrostatically suspended accelerometer; the light pressure model module is used for simulating solar light pressure acceleration of the satellite at different orbital altitudes and outputting the solar light pressure acceleration to the electrostatically suspended accelerometer; and the accelerometer background noise module is used for simulating the background noise level of the accelerometer and outputting the background noise level to the electrostatically suspended accelerometer.

[0052] The high-frequency micro-vibration sensor measurement and preprocessing module (3) includes a high-frequency vibration acceleration data module and a high-pass filtering processing module; the high-frequency vibration acceleration data module is used for simulating the micro-vibration level of the satellite platform and outputting micro-vibration acceleration data obtained in simulation or experiment to the high-pass filtering processing module; and the high-pass filtering processing module is used for filtering low-frequency noise caused by device temperature drift, ground pulsation, etc. in the micro-vibration experimental data and outputting acceleration data close to the actual micro-vibration level of the satellite platform in orbit to the electrostatically suspended accelerometer.

[0053] The centroid deviation related acceleration processing module (4) comprises a satellite centroid fluctuation over time module and a satellite attitude sensor attitude data processing module; the satellite centroid fluctuation over time module is configured to simulate the change of the satellite centroid over time and output to the electrostatic suspension accelerometer; the satellite attitude sensor attitude data processing module is configured to simulate the change of the satellite in-orbit attitude angular velocity and angular acceleration and output to the electrostatic suspension accelerometer.

[0054] A displacement detection module is configured to detect the differential capacitance value output by the accelerometer and input the displacement detection result to the electronic displacement detection end temperature measurement module (5);

[0055] The electronic displacement detection end temperature measurement module (5) comprises a displacement detection circuit temperature influence coefficient and coupling module, which is configured to simulate the influence of the in-orbit temperature change on the displacement detection circuit, output the displacement detection voltage value containing the temperature influence to the sampling module;

[0056] A sampling module is configured to sample the output displacement detection voltage and output the sampling result to the PID control module;

[0057] The PID control module is realized by a PID algorithm, and outputs the feedback control voltage taking the displacement detection voltage value as the error control object to the electronic driving amplifier circuit temperature measurement module (6);

[0058] The electronic driving amplifier circuit temperature measurement module (6) comprises a driving amplifier circuit temperature influence coefficient and coupling module, which is configured to output the driving amplifier voltage to the low-pass filter after amplification according to the initial voltage value output by the PID control module;

[0059] A low-pass filter is configured to low-pass filter the driving amplifier voltage output by (6) and output the filtering result to the accelerometer output data preprocessing module (7) and the sensor physical feedback and temperature influence processing module (8);

[0060] The accelerometer output data preprocessing module (7) comprises an output data offset correction and filtering output module, which is configured to correct the accelerometer output offset and perform filtering, and output the scientific measurement data of the accelerometer meeting the technical requirements; the output result of (7) is the primary non-conservative force acceleration data obtained by the accelerometer measurement, and the non-conservative force acceleration data received by the satellite can be obtained after later data processing;

[0061] The sensor physical feedback and temperature influence processing module (8) comprises a sensor temperature influence coefficient and coupling module, which is configured to obtain the corresponding control acceleration according to the feedback driving voltage, and output the electrostatic force acceleration of the mass block after being subjected to the electrostatic force.

[0062] Each module in the embodiment will be described in detail as follows:

[0063] (1) Micro-thrust input module

[0064] This module is constructed according to the measured parameters of 100 mN ion thrust, combined with the satellite mass, and the micro-thrust acceleration module output is constructed as shown in Figure 3 .

[0065] (2) High-frequency micro-vibration sensor measurement and preprocessing module

[0066] The main activity mechanisms of the satellite in orbit include momentum wheels and other attitude holding mechanisms, SADA, etc., which cause high-frequency signals above several hertz. According to the measurement data of a certain in-orbit quartz flexible accelerometer, 1Hz high-pass filtering is performed to remove the low-frequency quantities outside the measurement bandwidth. The simulated input on-board micro-vibration data is shown in Figure 4 .

[0067] (3) Centroid deviation related acceleration processing module

[0068] The deviation of the accelerometer mass center from the satellite centroid and the satellite angular velocity angular acceleration coupling will cause the related acceleration bias value:

[0069]

[0070] The first term is the centrifugal acceleration, the second term is the angular acceleration influence, is the satellite angular velocity, is the satellite angular acceleration. The simulated satellite angular velocity change curve is shown in Figure 5 , and the simulated satellite angular acceleration is shown in Figure 6 .

[0071] (4) Satellite centroid fluctuation over time module

[0072] The satellite centroid is related to factors such as satellite on-orbit fuel consumption, periodic temperature changes causing deformation, etc. According to the centroid change peak-to-peak value ±1mm, the change period is simulated as shown in Figure 7 .

[0073] (5) Solar pressure model module

[0074] According to the solar pressure calculation formula (photon full absorption):

[0075]

[0076] Where c is the speed of light, W is the radiant flux, i.e. the energy per unit time per unit area; R1 is the distance of the object from the sun, L s = 3.84 x 10 26 W is the solar irradiance, i.e. the total energy of light radiation emitted by the sun per unit time.

[0077] The distance between the satellite orbit and the sun is about 1 astronomical unit, and the pressure caused by the solar radiation pressure is 4.55 x 10 -6 Pa, and the solar radiation pressure value in the total reflection case is twice that of the total absorption, about 9.11 x 10 -6 Pa, the satellite irradiation area is 50 m 2 Analysis, in the case of total absorption, the acceleration caused is about 7.7 x 10 -8 m / s 2 , in the case of total reflection, the acceleration caused is about 1.5 x 10 -7 m / s 2 , take the intermediate state, the solar radiation pressure acceleration is about 1 x 10 -7 m / s 2 Analysis, and changes with the orbit period, Figure 8 is the solar radiation pressure simulation data of 1200s.

[0078] (6) Atmospheric drag model module

[0079] The atmospheric drag force acting on the satellite in orbit is mainly concentrated in the direction of the satellite flight, and the atmospheric drag acceleration calculation formula is as follows:

[0080]

[0081] In the above formula, C d is the drag coefficient, taken = 2.2, p is the atmospheric density of the orbit, taken 1 x 10 -15 kg / m 3 , S is the satellite windward area, taken 15 m 2 , v is the satellite orbit speed (6.89 x 10 3 m / s), M is the satellite mass.

[0082] The atmospheric drag acceleration in the direction of the satellite flight is about 7.6 x 10 -9 m / s 2 , and the solar radiation pressure perturbation acceleration is much larger than the atmospheric drag effect.

[0083] (7) Accelerometer background noise module

[0084] According to the background noise distribution characteristics of the accelerometer, the input accelerometer background noise and spectrum of the simulation analysis are given as follows Figure 9 The background noise

[0085] Simulation process:

[0086] The non-conservative force acceleration and the accelerometer background noise are substituted into the system model, the system simulation input data is compared with the system output data, and the output curve is obtained as shown in the following Figure 10

[0087] After the accelerometer system model, the high-frequency interference signal is greatly attenuated. Figure 11 The output curves obtained by respectively performing 5Hz, 1Hz, 0.6Hz and 0.3Hz low-pass filtering on the measurement output data, and the output filtering frequency is reduced to better distinguish the micro-thrust effect, as shown in the following Figure 11

[0088] Figure 12 The velocity error and displacement error caused by the accelerometer measurement error under different measurement bandwidths. It can be seen that by using the accelerometer to directly measure the micro-thrust acceleration, the measurement bandwidth is designed near 1Hz, and the 3-hour micro-thrust action can be controlled to within 2cm from the 83m (micro-thrust error 5mN) calculation error.

[0089] The application can realize performance simulation of different performance electrostatic suspension accelerometers in measuring satellite micro-thrust on orbit, and is used for researching application mode of the electrostatic suspension accelerometer in satellite micro-thrust measurement, and can also be used for analyzing response of the electrostatic suspension accelerometer to various disturbance factors of the platform, and simulation analysis in autonomous navigation, satellite on-orbit high-precision real-time precise orbit determination, silent flight, navigation denial and the like.

[0090] Through the on-orbit micro-thrust measurement simulation system of the electrostatic suspension accelerometer, the full-process simulation of the accelerometer in measuring the satellite micro-thrust in a complex environment can be realized, and the simulation result has important significance for application of the actual electrostatic suspension accelerometer in satellite autonomous navigation, micro-thrust measurement, precise orbit determination and the like.

[0091] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any change or replacement within the technical range disclosed by the application can be easily thought by those skilled in the art, and should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.​​

Claims

1. An electrostatically suspended accelerometer on-orbit micro-thrust measurement simulation system, characterized in that: It includes an on-orbit parameter simulation device and an electrostatic suspension accelerometer output measurement device; wherein, The on-orbit parameter simulation device is used to simulate and generate an on-orbit simulation environment for an electrostatically suspended accelerometer, including acceleration simulation, noise simulation, and satellite attitude simulation; The electrostatic suspension accelerometer output measurement device is used to process the output of the electrostatic suspension accelerometer. The processing results are divided into two paths, one of which is used as the primary non-conservative force acceleration data measured by the accelerometer and fed back to the electrostatic suspension accelerometer. The other path is used as the electrostatic force acceleration after the mass block is subjected to the electrostatic force and is used to measure the electrostatic suspension accelerometer. The on-orbit parameter simulation device includes a micro-thruster input module, a non-conservative force model and background noise input module, a high-frequency micro-vibration sensor measurement and pre-processing module, and a center of mass deviation implicated acceleration processing module; The micro-thruster input module is used to output the measured data or simulated data of the satellite thrust acceleration to the electrostatic suspension accelerometer; The non-conservative force model and background noise input module includes an atmospheric drag model module, a light pressure model module, and an accelerometer background noise module; the atmospheric drag model module is used to simulate the atmospheric drag acceleration experienced by the satellite at different orbital altitudes and output it to the electrostatic suspension accelerometer; the light pressure model module is used to simulate the solar light pressure acceleration experienced by the satellite at different orbital altitudes and output it to the electrostatic suspension accelerometer; the accelerometer background noise module is used to simulate the accelerometer background noise level and output it to the electrostatic suspension accelerometer; The high-frequency micro-vibration sensor measurement and preprocessing module includes a high-frequency vibration acceleration data module and a high-pass filter processing module. The high-frequency vibration acceleration data module is used to simulate the micro-vibration level of the satellite platform and output the micro-vibration acceleration data obtained in the simulation or experiment to the high-pass filter processing module. The high-pass filter processing module is used to filter out low-frequency noise caused by device temperature drift and ground pulsation in the micro-vibration experimental data, and output acceleration data close to the actual micro-vibration level of the on-orbit satellite platform to the electrostatic suspension accelerometer. The center of mass deviation implicated acceleration processing module includes a satellite center of mass fluctuation module over time and a satellite attitude sensor attitude data processing module; the satellite center of mass fluctuation module over time is used to simulate the change of satellite center of mass over time and output it to the electrostatic suspension accelerometer; the satellite attitude sensor attitude data processing module is used to simulate the change of satellite attitude angular velocity and angular acceleration in orbit and output it to the electrostatic suspension accelerometer; The electrostatic suspension accelerometer output measurement device includes a displacement detection module, an electronic displacement detection end temperature measurement module, an electronic drive amplifier circuit temperature measurement module, an accelerometer output data preprocessing module, and a sensor physical feedback and temperature impact processing module; wherein, The displacement detection module is used to detect the differential capacitance value output by the accelerometer and input the displacement detection result to the electronic displacement detection end temperature measurement module; The temperature measurement module at the electronic displacement detection end is used to simulate the impact of on-track temperature changes on the displacement detection circuit and output the displacement detection voltage value including the temperature effect to the sampling module; A sampling module is used to sample the output displacement detection voltage value and output the sampling result to the PID control module; The PID control module is used to generate a feedback control voltage with the displacement detection voltage value as the error control object, and output it to the electronic drive amplifier circuit temperature measurement module; The electronic drive amplifier circuit temperature measurement module is used to output the drive amplified voltage to the low-pass filter after amplification based on the initial voltage value output by the PID control module; A low-pass filter, configured to perform low-pass filtering on the output drive amplified voltage, and output the filtering result to the accelerometer output data preprocessing module and the sensor physical feedback and temperature impact processing module; The accelerometer output data preprocessing module is used to correct the accelerometer output bias and perform filtering to output scientific accelerometer measurement data that meets technical requirements. The output result is used as the primary non-conservative force acceleration data measured by the accelerometer. After ground data processing, the non-conservative force acceleration data exerted on the satellite is obtained; The sensor physical feedback and temperature impact processing module is used to obtain the corresponding control acceleration according to the feedback driving voltage, and output the electrostatic force acceleration after the mass block is acted upon by the electrostatic force.

2. The electrostatically suspended accelerometer on-orbit micro-thrust measurement simulation system according to claim 1 is characterized in that: The microthruster input module is used to simulate the measured parameters of 100mN ion thrust.

3. The on-orbit micro-thrust measurement simulation system of the electrostatically suspended accelerometer according to claim 1 is characterized in that: The satellite mass center fluctuation module is simulated according to the peak-to-peak value of the mass center change ±1mm and the change period of 10000s.

4. The electrostatically suspended accelerometer on-orbit micro-thrust measurement simulation system according to claim 1 is characterized in that: The solar pressure model module converts the solar pressure acceleration into 1×10 -7 m / s 2 analysis, and varies with the orbital period.

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