Orbital Design And Optimization Of Mars Probe

With the development of China’s space engineering and technology, theexploration of Mars has been another significant development area of spacetechnology, after afterwards China Manned space. The trajectory design is the coretechnology of the mission to Mars, which concerns the proceeding, success orfailure of this mission. According to the requirement of Mars exploration, taking theengineering application problems as the core, this thesis researches the directtransfer orbit design of Mars exploration, midcourse correction and assisted orbitaltransfer. The content is as follows:Aimed at solving the direct transfer orbit of Mars exploration, we simplify thisorbit to “Lambert” based on two-body mode and derivate the solution procedure ofuniversal variables. Moreover, we use the combination of “GA” and “SQP” tosearch the minimum energy launch window of the Mars exploration in2013, whichtakes the launch and flight time as variables. The heliocentric transfer orbit and theescape orbit are designed by optimum solution. Then we select the launch azimuth.At last, the STK visual simulation is taken on the basis of those above-mentionedstarters.Aimed at the transfer orbit optimization problems of Mars exploration, theauthor researches the State Transition Matrix of this system and carries out thetheoretical analyses on the errors occur during the transfer orbit.“B-plane”parameters are used to describe the terminal parameter of the Mars orbit plane.Meanwhile, a rapid differential corrections process is deduced to design the orbitsaccurately, which is more suitable for navigation calculation and error analysiscompared with the conventional method. At length, the author makes correctionsrepeatedly in the process of heliocentric transfer orbit and makes theoreticalanalyses for correction time by “Space Ratio Strategy”. All above-mentioned resultshave huge reference value. The terminal position precision of the probe in certainprobability is given via fixed error source, investigation of the relationship betweencorrected speed with terminal errors and “Monte Carlo” simulation followingcorrection time selection.First, the author presents the progress of direct brake and aero-assisted orbit trapping methods, then compares the task time and fuel consumption factors ofthese two methods. In practical projects, we should confirm the trapping method inthe light of the actual conditions. Then, the Gravity-assist trajectories are researched.The change of explore speed, orbit parameters and energy that leaped eight planetsare inferred. Finally, according to the hard energy matching problem during theunpowered swingby, the author designs one powered swingby orbit and analyses itsprinciple. This powered swingby orbit can increase the launch window considerablyand save fuel consumption. The results of this research have high practical valuethat can provide references for Mars autonomous exploration in our future.