Displacement mode drag-free control dynamics coordination condition determination method

Abstract

A displacement mode drag-free control dynamics coordination condition determination method belongs to the technical field of satellite drag-free control, and comprises the following steps: assuming that a negative stiffness force zero position coincides with a measurement zero position, so as to establish a displacement mode single-degree-of-freedom drag-free control dynamics equation, a simplified general dynamics equation for each axis, and a degenerated switching dynamics equation; enabling three parameters of the maximum thrust acceleration, the negative stiffness coefficient and the mechanical limit of the displacement mode drag-free control system to meet a constraint relational expression, and the constraint relational expression is a basic dynamics coordination condition which should be met by the system; forming an allowable initial state prismatic area by solving four asymptotes of a switching kinetic equation in a phase trajectory diagram, and a displacement mode drag-free control yielding kinetic coordination condition when the maximum thrust of the drag-free thruster is insufficient is vividly given.

Description

technical field [0001] The invention relates to a method for determining dynamic coordination conditions of a displacement mode drag-free control, and belongs to the technical field of satellite drag-free control. Background technique [0002] Drag-free control technology is a key technology in the field of gravity field measurement satellites, gravitational wave detection satellites and equivalent principle test satellite control technology. According to different control objectives, no-drag control can be divided into acceleration mode no-drag control and displacement mode no-drag control. [0003] The no-drag control in displacement mode requires the thruster with continuously adjustable thrust to control the inspection quality in the on-board inertial sensor within a small variation range near the nominal position in the electrode cage. The acceleration corresponding to the displacement of the test mass relative to the nominal position is the result of the joint action ...

AI Technical Summary

Problems solved by technology

For example, if the maximum value of the thrust is too small, the transition time of the relative displacement control response will be too long, and it may not even have the ability to control the inspection mass back to the nominal position from some harsh initial conditions

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