Thermodynamic vent system with accurate temperature response and control method thereof

Abstract

The invention discloses a thermodynamic vent system with accurate temperature response and a control method thereof. The thermodynamic vent system is characterized in that a plurality of groups of temperature sensors are arranged in a storage tank; electromagnetic valves are arranged on all nozzles; a data collector collects data of the temperature sensors and transmits the data to a computer; the computer controls on-off of the nozzles through logical operation; when the equivalent temperature of the local area exceeds the critical saturation temperature, the corresponding nozzle is opened, the low-temperature fluid flows out of the nozzle to cool the corresponding area, and point-to-point accurate temperature control and pressure control are achieved; and the temperatures of the inner wall faces of the storage tank at different positions are obtained, different temperature response strategies are adopted according to the temperature difference, and on-off of all the nozzles is controlled, so that the work needed by a low-temperature circulating pump for pumping a propellant is reduced, the circulating flow and the exhaust loss of the low-temperature propellant are reduced, and accurate response to a high-temperature area in the storage tank is achieved.

Description

technical field [0001] The invention relates to a thermodynamic exhaust system, in particular to a thermodynamic exhaust system with precise temperature response and a control method thereof. Background technique [0002] Cryogenic propellants have the characteristics of high fuel performance, non-toxicity, and large specific impulse, which can well meet the requirements of spacecraft payload and energy density. Cryogenic liquids represented by liquid hydrogen, liquid oxygen, and liquid methane are still the first choice for future space vehicle propellants. However, low temperature conditions put forward more stringent requirements for the insulation of on-orbit tanks. Even with a well-insulated low-temperature storage system, the heat leakage of the space thermal environment is less than 5W / m 2 , will still cause the local temperature of the low-temperature propellant in the storage tank to rise, causing the liquid to evaporate or even boil, thereby causing the pressure ...

AI Technical Summary

Problems solved by technology

However, the traditional TVS system still has the following problems: the fluid sprayed by the spray rod flows out from all nozzles, but only a few or even one nozzle plays a leading role in cooling the high temperature area, resulting in a decrease in pump efficiency and an increase in discharge, resulting in Unnecessary energy loss and propellant loss

Images