A Composite Temperature Control System Combining Spacecraft Feedback Control and Feedback Compensation

Abstract

A composite temperature control system combining feedback control and feed-forward compensation, including a temperature deviation feedback module, an external heat flow and internal heat source feed-forward module, an electric heating drive module, a temperature measurement sensor, and a thermal control implementation module; the temperature measurement module analyzes the temperature measurement sensor value , to provide adjustment input for the temperature control cycle adjustment module, the temperature control cycle adjustment module and the heating control module together realize the calculation output of the electric heating drive signal, the distinguishable heating time setting module controls the minimum step size of the heating control module, and the external heat flow weighting module Provides external heat flow weighting to correct the output of the heating control module. The invention can reduce the error caused by the temperature control strategy and the control method, and close the known disturbance and control parameters in the operating environment of the spacecraft.

Description

technical field [0001] The invention belongs to the field of spacecraft temperature control and relates to a coincident temperature control system combining feedback control and feedforward compensation. Background technique [0002] The process of traditional spacecraft temperature control is a dynamic balance under the simultaneous action of active heat control and passive heat conduction. Active thermal control calculates and controls the off time of the electric heater within the scope of system computing resource capacity by sensing the deviation from the target temperature, so that the system temperature can be kept near the preset temperature point; while passive heat conduction is through reasonable Thermal cladding and insulation design to reduce system heat leakage. The combination of active thermal control and passive heat conduction is the result of the trade-offs made by the spacecraft to obtain stable temperature conditions under the condition of limited platf...

AI Technical Summary

Problems solved by technology

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, the present invention proposes a composite temperature control system for spacecraft that combines feedback control and feed-forward compensation, which reduces the temperature control accuracy error caused by the control method and solves the problem of environmental The problem of temperature control accuracy reduction caused by periodic fluctuations, and the thermal control parameter settings are realized according to the characteristics of the controlled channel, so as to reduce the error caused by the control strategy and control method, and improve the control accuracy

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