国家自然科学基金(s10832004)

作品数：8被引量：39H指数：4
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Orbit control strategy for Lagrange point orbits based on an analytical method被引量：1
《Science China(Physics,Mechanics & Astronomy)》2013年第4期830-839,共10页Lü Jing LU QiShao WANG Qi 
supported by the National Natural Science Foundation of China (Grant Nos. 10832004 and 11102006);the Fan-Zhou Foundation (Grant No. 20110502)
The periodic or quasi-periodic orbits around collinear Lagrange points present many properties that are advantageous for space missions. These Lagrange point orbits are exponentially unstable. On the basis of an analy...
关键词：analytical method control strategy Lagrange point periodic or quasi-periodic orbit 
Opportunities search of transfer between interplanetary halo orbits in ephemeris model被引量：4
《Science China(Technological Sciences)》2013年第1期188-193,共6页WANG YaMin CUI PingYuan QIAO Dong 
supported by the National Basic Research Program of China ("973" Program) (Grant No. 2012CB720000);the National Natural Science Foundation of China (Grant Nos. 10832004 and 11102020)
In this paper,a two-level search method for searching transfer opportunities between interplanetary halo orbits,exploiting the invariant manifolds of the restricted three-body problem,is proposed.In the method,the fir...
关键词：ephemeris model halo orbit invariant manifold transfer opportunities search 
Analytic approach on geometric structure of invariant manifolds of the collinear Lagrange points
《Science China(Physics,Mechanics & Astronomy)》2012年第9期1703-1712,共10页LU Jing WANG Qi WANG ShiMin 
supported by the National Natural Science Foundation of China (Grant Nos. 10832004 and 11102006);the FanZhou Foundation (Grant No. 20110502)
An analytical method is proposed to find geometric structures of stable,unstable and center manifolds of the collinear Lagrange points.In a transformed space,where the linearized equations are in Jordan canonical form...
关键词：analytical method stable manifold unstable manifold center manifold geometric structure 
Trajectory design for the Moon departure libration point mission in full ephemeris model被引量：3
《Science China(Technological Sciences)》2011年第11期2924-2934,共11页CHEN Yang BAOYIN HeXi LI JunFeng 
supported by the National Natural Science Foundation of China (Grant Nos. 10832004 and 11072122)
The lunar probe may still have some remaining fuel after completing its predefined Moon exploration mission and is able to carry out some additional scientific or technological tasks after escaping from the Moon orbit...
关键词：Moon exploration trajectory design full ephemeris model libration point halo orbit 
Design and optimization of a trajectory for Moon departure Near Earth Asteroid exploration被引量：7
《Science China(Physics,Mechanics & Astronomy)》2011年第4期748-755,共8页CHEN Yang BAOYIN HeXi LI JunFeng 
supported by the National Natural Science Foundation of China(Grant Nos. 10832004 and 11072122)
The lunar probe often has some remaining fuel on completing the predefined Moon exploration mission and may carry out some additional tasks from the Moon orbit using the fuel.The possibility for the lunar probe to esc...
关键词：trajectory design full ephemeris model Near Earth Asteroid exploration Particle Swarm Optimization 
Fuel optimal low thrust rendezvous with outer planets via gravity assist被引量：8
《Science China(Physics,Mechanics & Astronomy)》2011年第4期756-769,共14页GUO TieDing JIANG FangHua BAOYIN HeXi LI JunFeng 
supported by the National Natural Science Foundation of China(Grant Nos. 10832004 and 11072122)
Low thrust propulsion and gravity assist (GA) are among the most promising techniques for deep space explorations.In this paper the two techniques are combined and treated comprehensively,both on modeling and numerica...
关键词：low thrust fuel optimal trajectory maximum principle homotopic technique gravity assist 
Optimal four-impulse rendezvous between coplanar elliptical orbits被引量：6
《Science China(Physics,Mechanics & Astronomy)》2011年第4期792-802,共11页WANG JianXia BAOYIN HeXi LI JunFeng SUN FuChun 
supported by the National Natural Science Foundation of China(Grant Nos. 10832004 and 11072122)
Rendezvous in circular or near circular orbits has been investigated in great detail, while rendezvous in arbitrary eccentricity elliptical orbits is not sufficiently explored. Among the various optimization methods p...
关键词：If the initial values are taken randomly it is difficult to converge to the optimal solution. elliptical orbit rendezvous primer vector fuel optimal 
Target selection and transfer trajectories design for exploring asteroid mission被引量：15
《Science China(Technological Sciences)》2010年第4期1150-1158,共9页CUI PingYuan1,QIAO Dong1,CUI HuTao2 & LUAN EnJie3 1 School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China 2 Harbin Institute of Technology,Harbin 150001,China 3 National Defense Science and Industry Bureau,Beijing 100048,China 
supported by the National Natural Science Foundation of China (Grant Nos 10832004 and 10672044)
Technique of target selection and profiles of transfer trajectory for Chinese asteroid exploring mission are studied systemically.A complete set of approaches to selecting mission targets and designing the transfer tr...
关键词：EXPLORING ASTEROID TARGET selection multiple flybys transfer TRAJECTORY 
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