将图论及一种新的数学分析工具——矩阵的半张量积(semi-tensor product of matrices,STP),作为研究工具,通过研究图的k内稳定集的充分必要条件,研究了k轨道任务分配问题的可解性条件.定义了图的顶点子集的特征向量,利用STP方法得到图的...将图论及一种新的数学分析工具——矩阵的半张量积(semi-tensor product of matrices,STP),作为研究工具,通过研究图的k内稳定集的充分必要条件,研究了k轨道任务分配问题的可解性条件.定义了图的顶点子集的特征向量,利用STP方法得到图的k内稳定集新的若干充分必要条件.基于这些新的充分必要条件,建立了能够搜索出图的所有k内稳定集的两种算法.进而将上述结果应用到k轨道任务分配问题,得到了该问题可解性的两个充分必要条件.此外,通过这些充分必要条件,也发现了一些有趣的现象.例如,完全最优方案(completely optimal schedules)的存在.展开更多
The asteroid exploration opportunities are searched and calculated with launch dates in 2006 to2010, and with asteroid Ivar 1627 as the target, the spacecraft and its subsystems are designed and analyzed,and the trans...The asteroid exploration opportunities are searched and calculated with launch dates in 2006 to2010, and with asteroid Ivar 1627 as the target, the spacecraft and its subsystems are designed and analyzed,and the transfer trajectory is designed using △VEGA technology for the asteroid rendezvous. The design resultssatisfied the energy requirements for small explorers.展开更多
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...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.The Moon departure mission for the lunar probe is the focus of this paper.The possibility of the spacecraft orbiting the Moon to escape the Moon's gravitational pull is analyzed.The trajectory design for the Earth-Moon system libration point mission is studied in a full ephemeris dynamical model,which considers the non-uniform motion of the Moon around the Earth,the gravity of the Sun and planets and the finite thrust of the onboard engine.By applying the Particle Swarm Optimization algorithm,the trajectory design for the transfer from the Moon-centered orbit to the L1 halo orbit,the station-keeping strategies for the Earth-Moon halo orbit and the construction of homoclinic and heteroclinic orbits are investigated.Taking the tracking conditions and engineering constraints into account,two feasible schemes for the Moon departure libration point mission for the lunar probe are presented.展开更多
基金Supported by Key Scientific Research Program of the Higher Education Institutions of Henan Educational Committee(15A416005)2015 Science Foundation of Henan University of Science and Technology for Youths(2015QN016)+1 种基金National Natural Science Foundation of China(61573199)Sub-project of National Key Research and Development Program(2016YFD0700103–2)
文摘将图论及一种新的数学分析工具——矩阵的半张量积(semi-tensor product of matrices,STP),作为研究工具,通过研究图的k内稳定集的充分必要条件,研究了k轨道任务分配问题的可解性条件.定义了图的顶点子集的特征向量,利用STP方法得到图的k内稳定集新的若干充分必要条件.基于这些新的充分必要条件,建立了能够搜索出图的所有k内稳定集的两种算法.进而将上述结果应用到k轨道任务分配问题,得到了该问题可解性的两个充分必要条件.此外,通过这些充分必要条件,也发现了一些有趣的现象.例如,完全最优方案(completely optimal schedules)的存在.
文摘The asteroid exploration opportunities are searched and calculated with launch dates in 2006 to2010, and with asteroid Ivar 1627 as the target, the spacecraft and its subsystems are designed and analyzed,and the transfer trajectory is designed using △VEGA technology for the asteroid rendezvous. The design resultssatisfied the energy requirements for small explorers.
基金supported by the National Natural Science Foundation of China (Grant Nos. 10832004 and 11072122)
文摘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.The Moon departure mission for the lunar probe is the focus of this paper.The possibility of the spacecraft orbiting the Moon to escape the Moon's gravitational pull is analyzed.The trajectory design for the Earth-Moon system libration point mission is studied in a full ephemeris dynamical model,which considers the non-uniform motion of the Moon around the Earth,the gravity of the Sun and planets and the finite thrust of the onboard engine.By applying the Particle Swarm Optimization algorithm,the trajectory design for the transfer from the Moon-centered orbit to the L1 halo orbit,the station-keeping strategies for the Earth-Moon halo orbit and the construction of homoclinic and heteroclinic orbits are investigated.Taking the tracking conditions and engineering constraints into account,two feasible schemes for the Moon departure libration point mission for the lunar probe are presented.
