Compound temperature control system with combination of spacecraft feedback control and feedforward compensation

Abstract

The invention discloses a compound temperature control system with combination of spacecraft feedback control and feedforward compensation. The compound temperature control system comprises a temperature deviation feedback module, an external heat flux internal heat source forwardfeed module, an electric heating driving module, a temperature measurement sensor, and a thermal control implementationmodule. A temperature measuring module analyzes the value of the temperature measurement sensor, and provides adjusting input for a temperature control period adjusting module. The temperature control period adjusting module and a heating control module achieve electric heating driving signal calculating output. Minimum step size of the heating control module is controlled by a distinguishable heating time setting module. An external heat flux weighting module provides external heat flux weighting, and modified the output of the heating control module. Error caused by a temperature control strategy and a control method can be reduced, and a closed loop of known disturbance and control parameters in the spacecraft operating environment is achieved.

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...

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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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