On-orbit micro-thrust measurement simulation system of electrostatic suspension accelerometer

Abstract

The invention 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 and generating an on-orbit simulation environment of the electrostatic suspension accelerometer, and the on-orbit simulation environment comprises acceleration simulation, noise simulation and satellite attitude simulation; the electrostatic suspension accelerometer output measuring device is used for processing the output of an electrostatic suspension accelerometer, the processing result is divided into two paths, one path serves as primary non-conservative force acceleration data measured by the accelerometer and is fed back to the electrostatic suspension accelerometer, and the other path serves as secondary non-conservative force acceleration data. And the other path is used as the electrostatic force acceleration after the mass block is subjected to the electrostatic force effect and is used for measuring the electrostatic suspension accelerometer.

Description

Technical Field

[0001] The invention relates to an on-orbit micro-thrust measurement simulation system of an electrostatically suspended accelerometer, belonging to the technical field of high-precision acceleration measurement simulation. Background Art

[0002] The electrostatically suspended accelerometer (hereinafter referred to as "accelerometer") is a quasi-steady-state, small acceleration precision measurement device that can measure with high precision (better than 1ng) the non-conservative force perturbations to which the satellite is subjected during its in-orbit operation, including solar pressure, earth reflection and radiation pressure perturbations, micro-vibrations, micro-thrusts, etc. It can provide real-time non-conservative force data for the satellite's in-orbit precise orbit determination. It has important uses in the fields of gravity field measurement, navigation model optimization, precise orbit determination, satellite drag-free control, gravitational wave detection, space inertial reference technology, etc., and is an important symbol of the advancement of space technology.

[0003] The accelerometer uses a high-precision differential capacitance detection method to measure the displacement between the mass block and the electrode cage with a measurement accuracy of the order of pm. The displacement detection value is then used as the deviation value and input into the PID controller for calculation. The feedback control voltage is applied to the electrode plate through the feedback drive circuit to stabilize the mass block at the center of the electrode cage under the action of the electrostatic force. In the closed-loop control state, the non-conservative force acting on the satellite is characterized by the feedback readout voltage combined with the scale factor. The measurement resolution is better than the ng level. The measurement principle of the single-channel electrostatic suspension accelerometer is as follows: Figure 1 shown.

[0004] Ignoring the influence of nonlinear factors, the measurement results of the electrostatic suspension accelerometer are expressed by the following formula:

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

[0006] Among them, a el Electrostatic suspension accelerometer measurement value; B measurement bias; V f Feedback voltage; G P Sensitivity coefficient.

[0007] With the development of aerospace technology, users have higher and higher requirements for satellite orbit control, and the orbit determination accuracy has developed from meter level to centimeter level and millimeter level. With the improvement of orbit accuracy indicators, the impact of various non-conservative forces on the orbit of satellites on orbit is becoming increasingly important. Therefore, accurately measuring the non-conservative forces on satellites in orbit and the micro-thrust on satellites during attitude and orbit control has become the basis for precise orbit determination and high-precision autonomous navigation. Electrostatic suspension accelerometers are currently the most mature and reliable equipment for measuring satellite non-conservative force acceleration. The satellite on-orbit environment is complex, and platform micro-vibration, temperature fluctuations, and satellite attitude are the main factors affecting the measurement accuracy of accelerometers. Summary of the invention

[0008] In view of this, the present invention provides an on-orbit micro-thrust measurement simulation system of an electrostatically suspended accelerometer, aiming at the problem of quasi-real-scene simulation of measuring satellite micro-thrust by an accelerometer in a complex background environment.

[0009] The present invention is achieved by the following technical solutions:

[0010] An on-orbit micro-thrust measurement simulation system for an electrostatically suspended accelerometer includes an on-orbit parameter simulation device and an electrostatically suspended accelerometer output measurement device; wherein:

[0011] The on-orbit parameter simulation device is used to simulate and generate an on-orbit simulation environment of an electrostatically suspended accelerometer, including acceleration simulation, noise simulation, and satellite attitude simulation;

[0012] The electrostatic suspension accelerometer output measurement device is used to process the output of the electrostatic suspension accelerometer. The processing result is 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, and the other is used as the electrostatic force acceleration after the mass block is acted upon by the electrostatic force, which is used to measure the electrostatic suspension accelerometer.

[0013] Furthermore, the on-orbit parameter simulation device of the present invention includes 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 implicated acceleration processing module;

[0014] A microthruster input module is used to output the measured data or simulated data of the satellite thrust acceleration to the electrostatic suspension accelerometer;

[0015] The non-conservative force model and background noise input module include 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;

[0016] 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 the 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 level of micro-vibration of the on-orbit satellite platform to the electrostatic suspension accelerometer;

[0017] The center of mass deviation-involved 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 the 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 satellite's attitude angular velocity and angular acceleration changes in orbit and output them to the electrostatic suspension accelerometer.

[0018] Furthermore, the electrostatic suspension accelerometer output measurement device of the present invention 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,

[0019] The displacement detection module is used to detect the differential capacitance value output by the accelerometer and input the displacement detection result to the temperature measurement module of the electronic displacement detection end;

[0020] The temperature measurement module of the electronic displacement detection end is used to simulate the influence of on-track temperature change on the displacement detection circuit, and output the displacement detection voltage value including the temperature influence to the sampling module;

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

[0022] A PID control module is used to generate a feedback control voltage with a displacement detection voltage value as an error control object, and output it to the temperature measurement module of the electronics drive amplifier circuit;

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

[0024] A low-pass filter, used for performing low-pass filtering on the output drive amplified voltage, and outputting the filtering result to the accelerometer output data preprocessing module and the sensor physical feedback and temperature impact processing module;

[0025] The accelerometer output data preprocessing module is used to correct the accelerometer output bias and filter it to output the accelerometer scientific measurement data that meets the 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 received by the satellite is obtained.

[0026] 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.

[0027] Beneficial effects:

[0028] First, by accurately simulating the main non-conservative force acceleration of the satellite on orbit, combined with the electrostatic suspension accelerometer system simulation model, the fusion processing of different sensor data is carried out, and the single-axis measurement of the satellite microthruster on orbit is simulated in a quasi-realistic manner. By comparing different types of accelerometer designs, the key design parameters of the accelerometer that meet the actual control requirements can be obtained, and the simulation foundation for the subsequent autonomous flight and precise orbit determination of satellites under navigation denial conditions can be laid.

[0029] Second, in order to ensure that the accelerometer can accurately measure the satellite microthrust, the present invention simulates a variety of data sources, combines the accelerometer system simulation model, and performs a quasi-real-scene simulation of the on-orbit measurement process of the satellite microthrust acceleration, and obtains the key indicators of the accelerometer that can reduce the orbit error to within 1m. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0031] Figure 1 This is the block diagram of single channel measurement of accelerometer;

[0032] Figure 2 This is the block diagram of the on-orbit micro-thrust measurement simulation system of the electrostatically suspended accelerometer;

[0033] Figure 3 It is the 100mN thruster startup and full process thrust simulation curve;

[0034] Figure 4 The on-board micro-vibration data for simulation input, (a) is acceleration, (b) is spectrum;

[0035] Figure 5 The satellite angular velocity is the input for the simulation;

[0036] Figure 6 The satellite angular acceleration is input for simulation;

[0037] Figure 7 Input data for center of mass change simulation;

[0038] Figure 8 Input Data for Solar Pressure Perturbation Simulation

[0039] Fig. 9 Input data for accelerometer background noise simulation; (a) is background noise, (b) is spectrum;

[0040] Fig.10 It is a time domain comparison diagram of simulation input data and system output data;

[0041] Fig.11 Comparison chart of low-pass filtering of different frequencies for accelerometer simulation output data;

[0042] Fig.12 Velocity error and displacement error caused by accelerometer measurement error under different measurement bandwidths, (a) velocity residual, (b) displacement residual. DETAILED DESCRIPTION

[0043] The embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0044] It should be noted that the following embodiments and features in the embodiments may be combined with each other in the absence of conflict; and, based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in the field without making any creative work are within the scope of protection of the present disclosure.

[0045] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein may be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present disclosure, it should be understood by those skilled in the art that an aspect described herein may be implemented independently of any other aspect, and two or more of these aspects may be combined in various ways. For example, any number of aspects described herein may be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein may be used to implement this device and / or practice this method.

[0046] The embodiment of the present application provides an on-orbit micro-thrust measurement simulation system of an electrostatically suspended accelerometer, comprising an on-orbit parameter simulation device and an electrostatically suspended accelerometer output measurement device; wherein:

[0047] The on-orbit parameter simulation device is used to simulate and generate an on-orbit simulation environment of an electrostatically suspended accelerometer, including acceleration simulation, noise simulation, and satellite attitude simulation;

[0048] The electrostatic suspension accelerometer output measurement device is used to process the output of the electrostatic suspension accelerometer. The processing result is 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, and the other is used as the electrostatic force acceleration after the mass block is acted upon by the electrostatic force, which is used to measure the electrostatic suspension accelerometer.

[0049] The on-orbit parameter simulation device in the embodiment of the present application comprises 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 electrostatic suspension accelerometer output measurement device comprises a displacement detection module, an electronics displacement detection end temperature measurement module (5), an electronics drive amplifier circuit temperature measurement module (6), an accelerometer output data preprocessing module (7) and a sensor physical feedback and temperature influence processing module (8).

[0050] A micro-thruster input module (1) is used to output measured data or simulated data of satellite thrust acceleration to an electrostatically suspended accelerometer;

[0051] The non-conservative force model and background noise input module (2) comprises 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;

[0052] The high-frequency micro-vibration sensor measurement and preprocessing module (3) comprises 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 the low-frequency noise caused by device temperature drift, ground pulsation, etc. in the micro-vibration experimental data and output acceleration data close to the actual level of the micro-vibration of the on-orbit satellite platform to the electrostatic suspension accelerometer;

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

[0054] A displacement detection module, used for detecting the differential capacitance value output by the accelerometer, and inputting the displacement detection result into the electronic displacement detection end temperature measurement module (5);

[0055] The electronic displacement detection end temperature measurement module (5) includes a displacement detection circuit temperature influence coefficient and a coupling module, which is used to simulate the influence of on-track temperature changes on the displacement detection circuit, and output a displacement detection voltage value including the temperature influence to the sampling module;

[0056] A sampling module, used for sampling the output displacement detection voltage and outputting the sampling result to the PID control module;

[0057] The PID control module is implemented by the PID algorithm, and outputs a feedback control voltage with the displacement detection voltage value as the error control object, which is given to the temperature measurement module (6) of the electronics drive amplifier circuit;

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

[0059] A low-pass filter, used for performing low-pass filtering on the driving amplified voltage output by (6), and outputting 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) includes an output data bias correction and filtering output module, which is used to correct the accelerometer output bias, filter, and output accelerometer scientific measurement data that meets technical requirements. The output result of (7) is used as the primary non-conservative force acceleration data measured by the accelerometer. After subsequent data processing, the non-conservative force acceleration data received by the satellite can be obtained.

[0061] The sensor physical feedback and temperature influence processing module (8) includes a sensor temperature influence coefficient and a coupling module, and is used to obtain a 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.

[0062] Each module in this embodiment is described in detail below:

[0063] (1) Micro-thrust input module

[0064] This module is based on the measured parameters of 100mN ion thrust and the satellite mass. The output structure of the micro-thrust acceleration module is as follows: Figure 3 shown.

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

[0066] The main active mechanisms of the satellite on orbit include attitude holding mechanisms such as momentum wheels and SADA, which cause high-frequency signals of several Hz or above. Based on the measurement data of a quartz flexible accelerometer on orbit, a 1Hz high-pass filter is performed to remove the low-frequency components outside the measurement bandwidth. The simulated input micro-vibration data on the satellite is as follows: Figure 4 shown.

[0067] (3) Center of mass deviation-related acceleration processing module

[0068] The deviation between the center of mass of the accelerometer and the center of mass of the satellite Angular velocity of satellite Angular acceleration Coupling will cause the acceleration bias:

[0069]

[0070] Among them, the first term is the centrifugal acceleration, and the second term is the angular acceleration effect. is the satellite angular velocity, is the satellite angular acceleration. is the satellite angular velocity change curve of a certain satellite simulation, and is the angular acceleration change curve. Figure 5 The satellite angular velocity of the simulation input is shown as Figure 6 The satellite angular acceleration is the input for the simulation.

[0071] (4) Satellite center of mass fluctuation module over time

[0072] The satellite center of mass is related to factors such as satellite fuel consumption on orbit and deformation caused by periodic temperature changes. The simulation is performed according to the peak-to-peak value of the center of mass change of ±1mm and the change period of 10000s. Figure 7 shown.

[0073] (5) Solar pressure model module

[0074] According to the solar light pressure calculation formula (total absorption of photons):

[0075]

[0076] In the formula, c is the speed of light, W is the radiation flux, that is, the energy passing through a unit area per unit time; R1 is the distance of the object from the sun, L s =3.84×10 26 W is the solar intensity, that is, 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. When all photons are absorbed by the satellite, the pressure caused by the sun's light pressure is 4.55×10 -6 Pa, the solar pressure value under total reflection is twice that of total absorption, about 9.11×10 -6 Pa, the satellite illumination area is calculated as 50m 2 Analysis shows that the acceleration caused by full absorption is 7.7×10 -8 m / s 2 , the acceleration caused by full launch is about 1.5×10 -7 m / s 2 , take the middle state, and adjust the solar pressure acceleration to 1×10 -7 m / s 2 analysis, and changes with the orbital period, Figure 8 To capture 1200s of solar pressure simulation data.

[0078] (6) Atmospheric drag model module

[0079] The atmospheric drag force on the satellite in orbit is mainly concentrated in the direction of the satellite's flight. The calculation formula for the atmospheric drag acceleration is as follows:

[0080]

[0081] In the above formula, C d is the drag coefficient, taken as = 2.2, ρ is the orbital atmospheric density, taken as 1×10 -15 kg / m 3 , S is the satellite windward area, take 15m 2 , v is the satellite orbital velocity (6.89×10 3 m / s), M is the satellite mass.

[0082] The calculated atmospheric drag acceleration in the satellite's flight direction is about 7.6×10 -9 m / s 2 , the acceleration caused by solar pressure perturbation is much greater than the influence of atmospheric resistance.

[0083] (7) Accelerometer background noise module

[0084] According to the distribution characteristics of the accelerometer background noise, the accelerometer background noise and spectrum of the simulation analysis input are given as follows Fig. 9 As shown, the noise floor

[0085] Simulation process:

[0086] Substitute various non-conservative force accelerations and accelerometer background noise into the system model, and compare the system simulation input data with the system output data, as shown below Fig.10 shown.

[0087] After passing through the accelerometer system model, the high-frequency interference signal is greatly attenuated. Fig.11 The output curves obtained by low-pass filtering the measured output data at 5Hz, 1Hz, 0.6Hz, and 0.3Hz are shown in Figure 1. Reducing the output filter frequency can better distinguish the micro-thrust effect, such as Fig.11 shown.

[0088] Fig.12 The velocity error and displacement error are 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 and designing the measurement bandwidth around 1Hz, the orbit calculation error of 3 hours of micro-thrust can be controlled from 83m (micro-thrust error 5mN) to within 2cm.

[0089] The present invention can realize the performance simulation of on-orbit measurement of satellite micro-thrust by electrostatic suspension accelerometers with different performances, and is used to study the application mode of electrostatic suspension accelerometers in satellite micro-thrust measurement. It can also be used to analyze the response of electrostatic suspension accelerometers to various disturbance factors of the platform, as well as the simulation analysis of high-precision real-time precise orbit determination, silent flight, autonomous navigation under navigation denial conditions, etc. of satellites on-orbit.

[0090] Through the electrostatic suspension accelerometer on-orbit micro-thrust measurement simulation system, the full process simulation of the accelerometer's micro-thrust measurement of satellites in complex environments can be realized. The simulation results are of great significance to the actual application of electrostatic suspension accelerometers in satellite autonomous navigation, micro-thrust measurement, precise orbit determination, etc.

[0091] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. An on-orbit micro-thrust measurement simulation system for an electrostatically suspended accelerometer, characterized in that: It includes the on-orbit parameter simulation device and the electrostatic suspension accelerometer output measurement device; wherein, The on-orbit parameter simulation device is used to simulate and generate an on-orbit simulation environment of 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 result is 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, and the other is used as the electrostatic force acceleration after the mass block is acted upon by the electrostatic force, which is used to measure the electrostatic suspension accelerometer.

2. The on-orbit micro-thrust measurement simulation system of the electrostatic suspension accelerometer according to claim 1 is characterized in that: 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 preprocessing module, and a center of mass deviation implicated acceleration processing module; A microthruster 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 that the satellite is subjected to at different orbital altitudes and output it to the electrostatic suspension accelerometer; The accelerometer noise floor module is used to simulate the accelerometer noise floor 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 the 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 level of micro-vibration of the on-orbit satellite platform to the electrostatic suspension accelerometer; The mass center deviation implicated acceleration processing module includes a satellite mass center fluctuation module over time and a satellite attitude sensor attitude data processing module; The satellite mass center fluctuation module over time is used to simulate the change of satellite mass center over time and output it to the electrostatic suspension accelerometer; The satellite attitude sensor attitude data processing module is used to simulate the satellite's attitude angular velocity and angular acceleration changes in orbit and output them to the electrostatic suspension accelerometer.

3. According to claim 2, the electrostatic suspension accelerometer on-orbit micro-thrust measurement simulation system is characterized in that: 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 temperature measurement module of the electronic displacement detection end; The temperature measurement module of the electronic displacement detection end is used to simulate the influence of on-track temperature change on the displacement detection circuit, and output the displacement detection voltage value including the temperature influence to the sampling module; A sampling module, used for sampling the output displacement detection voltage value and outputting the sampling result to the PID control module; A PID control module is used to generate a feedback control voltage with a displacement detection voltage value as an error control object, and output it to the temperature measurement module of the electronics drive amplifier circuit; The electronic drive amplifier circuit temperature measurement module is used to output the drive amplifier voltage to the low-pass filter after amplification according to the initial voltage value output by the PID control module; A low-pass filter, used for performing low-pass filtering on the output drive amplified voltage, and outputting 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 filter it to output the accelerometer scientific measurement data that meets the 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 received by 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.

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

5. The on-orbit micro-thrust measurement simulation system of the electrostatic suspension accelerometer according to claim 2 is characterized in that: The satellite mass center fluctuation module over time is simulated according to the peak-to-peak value of the mass center change ±1mm and the change period of 10000s.

6. The on-orbit micro-thrust measurement simulation system of the electrostatic suspension accelerometer according to claim 2 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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