Mission Optimization Of Gso Orbital Mission With Multiple Server And Multiple Target

With the development of aerospace technology and the burgeoning demand for space exploration,High-orbit spacecraft occupies important and limited orbital resources and play an important role in all aspects of society.At the same time,in the process of increasing systemization of space equipment,high-orbit spacecraft are often located at the top of the information chain of the spacecraft system.The medium and low orbit spacecraft in the system often rely on various types of information provided by the high orbit spacecraft to perform their work.Because of the above reasons,the number of high-orbit spacecraft operating in orbit is increasing,the technology used is becoming more advanced,and the types of missions are becoming more abundant.Therefore,the on-orbit service mission optimization technology of high-orbit spacecraft has gradually become one of the research hotspots of on-orbit service technology.From the perspective of orbit,the high-orbit service mission can be divided into three stages: mission planning,orbit transfer,and short-range relative orbit control.Among them,mission planning must be based on the evaluation and calculation of the orbit transfer cost,so although it is ahead of the orbit transfer in the task sequence,it is necessary to analyze the optimization and cost calculation of the orbit transfer during the research.When the service spacecraft completes the orbit transfer and moves to the vicinity of the target,a certain orbit control is required to meet the effective working conditions of the service payload in orbit.The main research contents of this paper are as follows:This article investigates the high-orbit spacecraft,analyzes its mission attributes,orbital characteristics,platform capabilities,load capacity characteristics,etc.,explains the necessity of carrying out the research of this article,and provides data that combines actual mission scenarios and requirements for the design of algorithms support.In addition,this paper also conducts a detailed investigation on orbit forecasting methods and mission planning methods.First of all,the space-time system required for this study is established,and on this basis,an ideal orbit model and a high-precision orbit dynamics model for subsequent algorithm design and mission simulation are established.In order to solve the requirements of the high-speed orbit prediction method in the optimization process of a large number of missions,a simplified recursive formula with J2 term based on the mean orbit element is derived.For the solution of the optimal dual-pulse lambert orbit change strategy,considering the constraints of fuel,service time,sun light,moon reflected light and earth shadow.The initial orbit operation time,the transfer orbit operation time,and the lambert circle are used as optimization variables,and the time and fuel are comprehensively optimized.Prior to this,this article conducted a modeling analysis of the sun and moon’s illumination constraints for nearEarth spacecraft during the functional time of optical service payload.For the many-to-many on-orbit service task optimization algorithm,this paper considers the target and multiple possible service requirements.The service spacecraft has the initial conditions of multiple service loads.The task assignment is based on the matching relationship between service loads and service requirements,and is based on the previously established Oneto-one optimal dual-pulse lambert trajectory change strategy,with the maximum reachable phase screening,phase difference inverse sequence number screening,proximity principle screening,etc.for different task schemes(including task allocation,service order,service type,etc.)The traversal optimization of the screening mechanism.Finally,for the relative orbit control that needs to be performed at the end of each orbit service mission period,a closed-loop orbit control algorithm based on a straight-line approach to the formation vector is designed.