Design And Optimization Of Gravity-Assist For Multicelestial Rendezvous

Aerospace technology has now become a stage for competition among various aerospace powers.As one of the core technologies,deep space exploration orbit design is the research focus of scholars from various countries.For the detection of long-distance celestial bodies,the direct transfer method is not feasible due to the insufficient emission energy,and the flying technology that can effectively reduce energy consumption becomes particularly important.Therefore,as my country continues to explore the field of deep space exploration,the development of leveraging flight orbit technology will inevitably become an indispensable part.This article is aimed at this demand,and mainly focuses on the design of multi-celestial planets in the solar system by leveraging flight orbits.Part of the research is carried out,and on this basis,for example,the optimization of the flight trajectory design with the aid of force,and the feasibility of the algorithm is verified by a calculation example,and the optimization algorithm for the design of the flight trajectory of the multi-planetary planet in the solar system is given.The details are as follows:Firstly,model the borrowed flight trajectory,and use the conic splicing method to divide the borrowed flight trajectory into two parts for discussion: the interplanetary transfer orbit section and the borrowed flight overflight section.The Lambert problem solving method is used for the interplanetary transfer orbit section,and the flyover section of the borrowing force is divided into two types,power flyover and unpowered flyover,and the speed and speed of the probe before and after the borrowing force are respectively given.The position change relationship.Subsequently,the design of the multi-celestial body’s flight trajectory is analyzed in a step-by-step manner:(1)First,analyze a single borrowing to fly by borrowing.The energy contour map method is mainly used to search the launch window,and the calculation example "EVM" is simulated.(2)Analyzed the orbits of the same planets when multiple celestial bodies meet but did not use the same force repeatedly,and proposed a hybrid optimization method,that is,firstly use the global optimization method for preliminary search,and then use the local optimization method for precise search and global optimization.Partially compared the optimization results of genetic algorithm and differential evolution algorithm.The local optimization method chooses the sequential quadratic programming method to optimize.Finally,the "EVEJU" Uranus exploration leverage sequence is simulated.(3)Finally,analyze the borrowed flight trajectory containing the same planet with repeated borrowings.The resonance orbit design method is mainly used,the principle of resonance orbit is analyzed,and the method of resonance orbit design is deduced,and the "EVEEJ" and "EVEJ" are analyzed.The two calculation examples were compared and simulated.Aiming at the problem of the optimization design of the borrowed flight trajectory of the multi-celestial planetary sequence in the solar system,this paper proposes a complete search algorithm,which can provide a reference for the design of the deep space exploration orbit and the optimization of the borrowed flight.