Thermal Design and Validation for Monopropellant Propulsion Systems of Remote-Sensing Satellite

Abstract

Monopropellant propulsion systems with hydrazine are widely use for orbit and attitude control of remote-sensing satellite. Thermal design of the spacecraft propulsion system is very important to ensure its temperature in the range of 5–60 ℃. A thermal design method for remote-sensing satellite propulsion system is presented in the paper. Enhanced thermal insulation design is used to reduce the sensitivity of propulsion system to thermal environment. Heaters for the propulsion system are installed to prevent propellant from freezing. The heating power consumption of propellant lines and pipe valve is obtained through theoretical analysis. Taking remote sensing satellites in different descending node as examples, thermal design and on-orbit performance are discussed. The validity of thermal design for the propulsion system is proved by in-orbit data. The on-orbit thermal performance is well meet thermal requirements of propulsion systems. Impacts of propulsion system temperature are discussed.