Optimization Design And Performance Of Solar Thermal Micro Propulsion System

At present,the research development direction of the power plant used in small satellite is solar thermal micro-propulsion technology.Instead of using complex power management system,solar thermal micro-propulsion system can make full use of gathered solar radiation energy to produce thrust by heating the gas,which makes the total energy utilization rate reach 60% ~ 70%.Solar thermal micro-propulsion system can be widely used in different mission requirements of various spacecraft.Compared with most of the traditional propulsions,it is economical and has the advantage of small pollution and small propellant consumption.Solar thermal micro-propulsion technology is a new direction for the engine sustainable development.In order to use this technology better,the optimization research of existing solar thermal micro-propulsion system is indispensable.In this paper,condenser subsystem,thruster subsystem and the solar thermal micro-propulsion system based on space missions are defined as the research objects.After constructing the physical model and mathematical model,the work of simulation and optimization analysis are done to achieve the target.Also,the validity of the model is verified by experiment.First of all,the mathematical model of condenser system is constructed in this paper.Consider the sun-light collection efficiency and the mass of condenser system as performance evaluation criterion of optimization model,and realize multi-objective optimization by use NCGA and NSGA-? genetic algorithm respectively.Secondly,in the thruster subsystem,the physical model of laminate gas flow unit and nozzle are constructed and the fluid movement is simulated by CFD.The effect of key parameters including thickness of the flow unit,hole diameter,laminate circumferential diameter on the heating efficiency is analyzed.By using DOE method,integrated design with nozzle,a set of structure parameters of heat exchanger core that can optimize the heating efficiency can be derived.And then,in order to validate the correctness of the model,in this paper,the thrust of solar thermal micro-propulsion system is tested respectively under the condition of normal temperature and high temperature.Finally,synthesize the research result of condenser subsystem,thruster subsystem and the experiment.Give the mathematical model of solar thermal micro-propulsion system used in small satellite.Carry out the optimization research by using advanced genetic algorithm with the goal of specific impulse for thruster,propulsive efficiency and weigh for entire system.As the micro-spacecraft increasingly applied in various fields such as formation flight,military reconnaissance and scientific experiments,solar thermal micro-propulsion system will have more develop space and play a more and more important role.The research results obtained in this paper will not only improve the overall performance of solar thermal micro-propulsion system,but also has reference significance for the future design.