A thermal control device for a fuel storage tank

Abstract

The invention provides a thermal control device for an engine fuel storage tank, comprising: a multi-layer structure, a thermal insulation gasket, a heater and a thermistor. It includes that the multi-layer structure is wrapped on the hemispherical surface and the column section of the fuel tank, the upper and lower sides of the tank mounting plate, and the corresponding surface of the tank support rod. The multi-layer structures are 10-unit, 5-unit, and 5-unit multi-layer heat insulation components respectively, and each multi-layer heat insulation unit is composed of double-sided aluminized polyester film and nylon net towel. According to the results of previous dynamic load satellite heat balance tests, combined with the staged consumption characteristics of propellant in orbit, in addition to heat insulation installation and all-layer coating, the present invention focuses on thermal compensation control on the lower ball section and installation area of ​​the storage tank to meet the Thermal control requirements for bipropellant tanks. It meets the high-precision temperature control requirements of satellite fuel storage tanks, and at the same time adapts to the temperature requirements of the transfer orbit section and the normal on-orbit section, with good reliability and flexible design.

Description

technical field The technical field of the aerospace and aviation of the present invention, in particular, relates to a thermal control device for a fuel storage tank. Background technique Bicomponent propulsion systems were first launched in the mid-1970s and were widely used by the 1980s. The engine module of this system is composed of a 490N two-component liquid apogee engine and 16-18 10N thrusters. They use the same pressure and propellant control system. The pipeline in front of the engine valve is divided into an apogee and an attitude control engine. It is characterized by high specific stroke and large payload. Through the multiple ignition performance of the liquid apogee engine, the accuracy of orbiting is greatly improved. Further, the propellant storage module of the propellant control system mainly includes 4 propellant storage tanks, 8 self-locking valves, 2 normally open electric explosion valves, 4 filling and discharging valves, 4 pressure sensors and se...

AI Technical Summary

Problems solved by technology

The purpose of the present invention is in order to solve the problem of the thermal control demand of bicomponent propellant storage tank, propose a kind of thermal control device of fuel storage tank, especially adapt to the engine of 490N

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