Research On The Technology Of Trajectory Design And Correction For Deep Space Exploration Probe

Orbit design is the basis of deep space exploration. Selecting a reasonable orbit can save a lot of fuel, reduce flying time and the risk. In this paper, issues as launch window, deep space autonomous navigation, and orbit control involved in deep space exploration were studied; the effectiveness and feasibility of the method chosen in deep space exploration were verified through the simulation.First, to solve the problem of selecting the launch window problem in deep space exploration, using the genetic algorithm optimization theory, the launch time and flight time of optimization variables, the minimize of launch energy of objective function, to do the genetic search for the best launch window. By solving Lambert problem, the launch time and the target arriving velocity of the spacecraft were obtained, the escape orbit and heliocentric transfer orbit based on two-body problem were also designed.Then, aiming at deep space exploration autonomous navigation issue, the position of the spacecraft in the solar coordinate system for deep space exploration was confirmed. On the basis of time phase model of pulsar based on SSB coordinate system, and the conversion equation of detector measurement time to barycentric dynamical time(TDB), the navigation algorithm was designed based on linear model, using least square method for position and velocity estimation, and four pulsars were chosen for navigation simulation, and analyzing the simulation precision of different initial position error and time measurement error.Finally, based on orbit control problem of deep space probe, the orbit control method based on solar sail attitude adjustment was proposed. On the foundation of establishment of solar sail orbital dynamics, the mathematical relationships among the solar sail cone angle, rotation angle, orbit thrust and the probe attitude were derived. By translating target orbit elements into position and velocity, design the control law for feedback of position and velocity. In accordance with the requirements of orbit control, design attitude control law, to achieve the aid of orbit control by get the pressure of sunlight needed to control the orbit through adjusting the solar sail. Finally testify the efficiency of the method of control the orbit based on solar sail attitude adjustment through mathematical simulation.