Continuous Low Thrust Trajectory Design For Space Maneuver

With the advancement of science and technology,the human deep space exploration,including the Lunar exploration,planetary exploration of the solar system and the asteroid exploration missions have been the research hotspots.The continuous low thrust orbital maneuvering technology is the basis of these tasks,which is an essential topic.The research on the orbital maneuver using the advanced propulsion technology has been a hot issue in the field of the research at home and abroad.According to China's manned space flight and deep space exploration mission development plan,the application of the advanced propulsion technology to achieve a wide range of space maneuvering for the manned lunar mission and Mars exploration mission become a key technology.Based on the space maneuver of the spacecraft,the thesis studies the theory and technology of the orbit maneuver and the orbit design of the spacecraft under continuous low thrust.A novel orbital maneuver method has been proposed for the two-body problem and the three-body dynamics model respectively.Then its orbital characteristics and its potential applications have been studied.Several new mission orbits are proposed,which provide a new technical reserve for the track design under continuous thrust.The main research work of the thesis is summarized as follows:(1)The analytical solutions for the low thrust orbital transfer are studied.In case of the initial orbit is circular,the spacecraft orbital transfer in the circumferential thrust,radial thrust and the normal thrust are investigated.The analytical solutions of the orbital transfer have been developed,and the efficiency of orbital maneuver using circumferential thrust and tangential thrust for the orbital escape form the earth's gravitational field.Then the shape-based method for the low thrust has been studied,and an orbital maneuver example is proposed.In case of eccentric orbital transfer case,a novel method for orbital transfer is proposed,and the GTO to GEO orbital transfer case is applied to testify the method.(2)A novel virtual gravity field method for the low thrust orbital transfer is investigated.Considered the constraints of the existing analytical methods for the low thrust orbital transfer,a novel concept of virtual gravity field is presented.And mathematic model of the low thrust orbital transfer using the virtual gravity field method is developed.The proposed method is applied in the Earth-Mars low-thrust transfer mission and the near earth asteroid interception trajectory design to testfy the efficiency of the proposed method.(3)Application of low thrust transfer trajectory design for the near earth asteroids orbital transfer mission using the virtual gravity field method is studied.And the model of hybrid low thrust systems is developed.The orbital transfer trajectory optimization using the hybrid low thrust systems is investigated.(4)The semi-analytical formulation of third-body perturbation for the low thrust orbit transfer is studied.The semi-analytical formulation of the third-body perturbation for the orbital elements is developed,and the optimal orbital transfer considered the third-body perturbation is studied using the proposed method.(5)The concept of virtual three-body gravity is proposed.The artificial Lagrangian points and period orbits is studied,and the mathematic model of orbital transfer using the virtual three-body gravity field method is developed,then the RCD solar sail is considered to applied for the novel displaced orbit in the virtual three-body system.Finally,the Earth polar observation mission is utilized to testify the proposed method.