Abstract: Abstract Electrostatic accelerometer offer high precision in measuring non-conservative forces and are increasingly being utilized in scientific and engineering fields related to space vehicles.To address the issue of spatial coupling accelerations in space applications,this paper derives relationships that express the influence of spatial dynamic perturbation factors,including the Sun,Moon,and other third-body bodies on accelerometer measurements.These factors encompass third body perturbation(Sun,Moon,etc.),the high order Earth gravity field and tidal force field,orbital and attitude variations of the spacecraft,installation position of the accelerometer,the spacecraft’s own gravitational field,and various spatial non-conservative forces.Based on these,a three dimensional perturbation algorithm for the output of the electrostatic accelerometer under various coupled perturbation sources in space is developed.A real time spatial coupled perturbation algorithm is implemented using MATLAB,and calculations on a geosynchronous orbit satellite are performed,yielding results consistent with expectations.The proposed algorithm can enhance the measurement accuracy of the electrostatic accelerometer and provide partial support for applications such as space vehicle inertial navigation and orbit determination.