Study Of Transfer Trajectory Design Method For Deep Space Exploration And Application To Small Body Exploration

With the supports of the Tenth Five-Year 863 Program'Autonomy Technology of Deep Space Exploration and Its Simulation and Demonstration System','Investigation on Entry Orbit Design and Optimization of Interplanetary Surperhighway', National Natural Science Foundation of China'Investigation on Mechanism and Optimal Method of transfer Trajectory for Deep Space Exploration', and the First Asteroid Exploration Program and Scenario of China, this dissertation deeply studies the transfer trajectory of deep space exploration and target selection and design of trajectory profiles for small body exploration. The main contents of this dissertation are as follows:For the'transfer Free-time'search problem of launch opportunity for interplanetary exploration, especially Large-Scale search of launch opportunity for small body exploration, combining Gauss Algorithm and Variational Theory, a search method with Global-Local Coordinated is presented. According to the requirments of exploration mission, it defines the target function and makes certain search domain. Then, it reduces the search dimension, combining Gauss Algorithm and ephemeris computation, obtains the necessary analytical partial derivatives by Variational Theory and boundary constraints, and solves this problem by using Global-Local Coordinated method. Compared with traditional method, the method proposed by this dissertation needs little compute time and becomes more efficient. On based of Primer Vector theory, a'transfer Fixed-time'search method of launch opportunity with multiple-impulsive transfer is proposed. In the method, combining the necessary condition of optimal transfer, it finds and judges the midcourse impulse by using history of Primer Vecotr magnitude. The method, which search launch opportunity with multiple-impulsive transfer, extends the investigation about search problem of launch opportunity with direct transfer to the multiple-impulsive fields.For design problem of transfer trajectory with multiple encounters for interplanetary mission, combining Tisserand theory, Prok-Chop plots with"soft matching"ideal, a hybrid method is presented. In this method, it determines flyby sequence by using P ? rpcurve, on base of Tisserand theory, and makes centain feasible domain and time sequence of design paremeter by using Prok-Chop plots, avoids the assumption of flyby sequence and intial trajectory segment by using traditional method. Then it finds the optimal design parameters by using"software matching"and penalty function strategies. Design and computation of transfer trajectory for Mars Mission with Venus Gravity assists and ROSETTA mission demonstrate the effectiveness of the method.For the gravity-assisted and its derivative technology, it proposes conditions of capture, escape and change of orbit type, developes the capture fields of powered swingby, presents the patching condition of aerogravity-assisted transfer trajectory. For gravity-assisted technology, based on CR3BP model, it studies implication relation between free parameters of gravity assist and orbit change with all phase angles, presents conditions of capture, escape and change of direct and retrograde orbit. Then it extends this investigation to ER3BP model, and puts the emphasis on the relation between phase angle, eccentricity of gravity-assisted body and trajectory. For the gravity-assisted derivative technology, it developes the possible capture fields of powered swingby, presents the patching conditions of aerogravity-assisted transfer. These relations and conditions will provide principle for designing transfer trajectory profile of interplanetary mission.For the design problem of interplanetary transfer trajectory, a design method of transfer trajectory with Libration point by using invariant manifold structures is presented. In this method, the five-dimension continuous systems can be reduced four-dimension discrete system by using PoincaréMapping. It uses the monodromy matrix to analyze this system for determinating the local subspace which involved in target periodic orbits. Local subpace will be extended to stable invariant manifold. Then the spacecraft transfers from parking orbit to target periodic orbits associated with librations point, and escapes from unstable invariant manifold associated with the system to achieve interplanetary flight with low energy. Application in the small body exploration mission demonstrates the potential predominance.For the First Asteroid Exploration Program and Scenario of China, combining the contents of this dissertation, systematical research and computation from target selection to design profiles of transfer trajectory is performed. A set of effectual method about target selection and transfer trajectory design of small body exploration is presented. Firstly, basing on evaluating accessibility method of global optimal two-impulsive and gravity-assisted, the possible target is evaluated and filtrated. 26 targets which involved in scientifically significant and technically feasible can be obtained. Then, according to constraints of the mission, it selects the 1627 Ivar asteroid as the target of the mission, the 3288 seleucus and 4660 Nereus asteroid as the possible candidates by using Large-Scale search method of launch opportunity. For the Ivar asteroid, it designs transfer trajectory profiles by using direct transfer and transfer with gravity-assisted and selects the 2:1ΔV-EGA transfer profile by comparison of several different profiles. This profile can decrease the launch energy and total velocity increments to satisfy with requirements of the mission. Finally, it extends the 2:1ΔV-EGA pofile to mulitple flybys pofile for Ivar asteroid exploration mission, achieves the mission to rendezvous with three target objects, and analyzes the trajectory characteristics assoicated with measure and control system of spacecraft to validate the feasible of the mission.