Finite Thrust Orbit Design For Manned Lunar Prospecting Series Mission Using Inverse Dynamics Method

Research on series missions design and simulation of manned lunar prospecting can achieve the decoupling design of multiple flight stages,reduce the mission scales,and improve the success rate of the mission,which is the critical to our manned lunar landing plan.The study is focused on the lunar space station based series lunar prospecting mission,and the main research results are listed as below:Pseudo-equinoctial finite Fourier series method was proposed.The inverse dynamics method was utilized to establish the inverse model of the modified equinoctial elements perturbation equations.The novel method was then proposed to solve the problem for coplanar multi-revolutions of circle orbits transfer problems and the deep space transfer problems.In order to solve the Earth-Moon three-body transfer problems,the pseudo-equinoctial finite Fourier series method was combined with the curve-patched method.The combined method could be utilized as an effective tool for time unlimited Earth-Moon transfer orbit design.High-fidelity inverse simulation design of Finite-thrust free return orbit was proposed.A new set of pseudo parameters representing for the perilune motion states was defined at first,and based on which a hybrid multi-conic method was then proposed to design the free return orbit for manned spacecraft.The new method was more accurate than the traditional double patched-conic method,and it can thus produce initial value which has higher converge speed for high precision trajectory iteration design.Then,a fast and high precision inverse simulation method for fixed-thrust trajectory was proposed based on the impulses solutions,and the gravity loss of the impulse-thrust transfer was analyzed.The general characters and launch window of the free return orbit,and the reachable domain of pseudo-perilune parameters were analyzed with the hybrid multi-conic method.The results would be the theoretical base for further mission design.A high-fidelity finite-burn inverse simulation methodology for fixed-point return orbit was developed based on the reachable domain analysis in this paper.The geometric properties of the general return orbits were analyzed through the reachable domains of the trans-Earth injection points and the vacuum perigees.Then,with the existence criterion derived from geometric properties,a novel hybrid orbit transfer method was proposed to design the multi-impulses fixed-point return orbit.The desired orbit was substituted into the inverse simulation architecture as inputs of the finite-burn trajectory to calculate the high-fidelity direction of the finite-thrust and the switching time.Multiple time-scale window iteration design method for manned lunar prospecting series missions was proposed.Various flight modes of the mission based on the lunar space station were analyzed and the mission design process was decoupled.Then the multiple time-scale window iteration design method for manned lunar prospecting series missions was proposed.To testify the unmanned lunar circus,manned lunar circus,manned lunar landing,and lunar space station establishment,the flexible and reliable simulation architecture was established for lunar space station based series mission.In this paper,by the study of finite thrust orbit design for manned lunar prospecting series mission using inverse dynamics method,the low-thrust transfer orbit,limited thrust free return orbit,and the high-fidelity fixed-point return orbit was designed.Combined these orbit design methods with the multiple time-scale window iteration design method,the series mission was finally designed and simulated on the common simulation system.These methods and the conclusions obtained in this paper could be the theoretical support,important tool,and strategy references for further manned lunar landing study,mission planning,and index discussion.