Dissertation
Dissertation > Aviation, aerospace > Aerospace ( Astronauts ) > Basic theory and experiments > Flight Mechanics > Spacecraft flight mechanics > The orbit of the spacecraft ( including satellites )

Optimal Orbit Design of Returning from Moon

Author LiLuoGang
Tutor CuiZuoTao
School Harbin Institute of Technology
Course Aircraft design
Keywords Lunar surface return Optimal orbit Maximum principle Months to transfer orbit Simulation
CLC V412.41
Type Master's thesis
Year 2010
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With the development of space science and technology , human exploration of the moon is deepening China 's lunar exploration program is also being orderly and smooth implementation . The lunar surface return technology is a key technology for lunar exploration , how to design a return to the track , and how to make the return process as small as possible to achieve fuel consumption , to become China 's lunar exploration project three issues must be addressed . Firstly, on the lunar surface return the power rising segment of the track to explore . The main return to power for the spacecraft lunar surface ascent fuel consumption , considering the moon 's rotation , the Coriolis force , establish a dynamic model of the spacecraft in three-dimensional space , the moon . Burnup optimal indicators , to utilize pontryagin maximum principle , the spacecraft returned on the lunar surface the power ascent stage engine thrust direction optimal open-loop control law . Consider the end position and speed of constraint solving conjugate variables initial value , and ultimately obtained a feasible optimal trajectory of the spacecraft . Analysis and design of the January transfer orbit characteristics . The first transfer orbit of the characteristics of the preliminary analysis of the three-dimensional model based on the lunar impact ball concept and months . Then the preliminary design method of the January the land transfer orbit track . Finally, after the analysis of the major role perturbation accurate dynamic model design of months to transfer orbit .

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