Research And Simulation Of Utility Oriented Service Flight Planning Method

From the development trend of the aerospace industry,we can know that the design principles of spacecraft have changed,the mode of idea changed from function to pursue comprehensive balance of efficiency,cost and performance.Based on this development trend,the optimal design of flight planning becomes very complex but critical.This paper aims at the problem of spacecraft long-range guided orbit transfer.First of all,I solving Lambert Orbit Intercepting Pulse Strategy and Multi-Pulse Long-Guided Orbit Transfer Strategy by improved genetic algorithm.Secondly,I convert the pulse quantity to the limited thrust on the thrust arc at the pulse point,this method realizes the conversion of multi-pulse long-range guided orbit transfer to long-range guided orbit transfer under limited thrust.Next,I revised the direction of speed increment of the limited thrust orbit transfer strategy.The main work content is as follows:(1)The article introduces pulse orbit transfer theory and research history,and analyzes research status,respective advantages and disadvantages of four kinds optimization algorithm for Orbit Transfer under Limited Thrust;(2)The article researched time system and conversion,spatial coordinate system and transformation,the method of describe the position of space objects,and established kinetic model of limited-thrust orbit transfer under different coordinate systems;(3)The article explains principle of Lambert Orbital Interception,principle of special point orbit transfer.Moreover,the article given the convert method from pulse strategy to limited-thrust strategy and the correction method of the engine thrust;(4)The article improves the selection and crossover operations in genetic algorithms,determine the individual's pros and cons according to the level of fitness value,and selectdominant individuals to inherit to the next generation;(5)The article determine the best position for orbit transfer and initial transfer orbit by solves the fuel-optimized Lambert orbit interception strategy,and continue to re-plan the transfer track between spacecraft and target location.Until the required speed increment is 0,the engine stopped working.The track spacecraft flying freely along the current transfer orbit,and reach the target position within the specified time;(6)The article constructs the non-coplanar orbit transfer speed increment matrix and non-coplanar orbit transfer time matrix by solving fuel optimal coplanar orbit transfer strategy.In addition,the article construct a non-coplanar orbit transfer utility matrix by the weighting method,this approach achieves the transformation of the multi-objective orbit transfer strategy problem into a single-objective optimal control problem.Finally,convert the obtained orbit transfer pulse strategy to orbit transfer strategy under different thrusts.The research results of this article have a good application prospect in the limited-thrust orbit transfer optimization research.The research content and results meet the expected requirements.The article can provide a certain technical method reference and theoretical knowledge reference for the design of future track transfer in China.