Lu Y.,Xi'an Jiaotong University |
Li J.,Xi'an Jiaotong University |
Li H.,State Key Laboratory of Astronautic Dynamics ADL |
Che Z.,State Key Laboratory of Astronautic Dynamics ADL |
Yang Y.,University of Electronic Science and Technology of China
2014 IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014 | Year: 2015
This paper discussed the problem of low-energy transfer orbit optimization based on the patched manifolds and homotopic method with multi-body environment. A new integrative optimization method is proposed in this article. As a typical example, the Earth-Mars transfer orbit design is discussed in detail. The design process of the final orbit is composed of two steps. First is optimizing the parameters that describe the patching manifolds in circular restricted three-body problems until the least total absolute velocity increment has been got. Second is optimizing the low-thrust control laws of the transfer orbit employing the homotopic method with multi-body environment that transfers the fuel optimization problem to more easier solved one of energy optimization problem. The results showed that the parameters that describe the patching manifolds could be optimized by the genetic algorithm with a relatively high speed, the homotopic method with multi-body environment could get the optimal value that meet the first order optimality conditions, and the final fuel cost is much less than the optimal transfer in two-body problem(about 1.57km/s less of the total Δv). Therefore, the method proposed in this paper could effectively solve the low-energy optimal control problem in multi-body environment for the future deep space explorations. © 2014 IEEE.
Huang A.,State Key Laboratory of Astronautic Dynamics ADL |
Huang A.,Xian Satellite Control Center |
Xie X.,State Key Laboratory of Astronautic Dynamics ADL |
Xie X.,Xian Satellite Control Center |
And 3 more authors.
Cehui Xuebao/Acta Geodaetica et Cartographica Sinica | Year: 2015
Based on the principle and observation model of the same beam interferometry measurement, observation equations of differential time delay and time delay rate for targets on lunar surface are proposed. Restriction of appointed height and digital lunar height model is introduced and a Kalman filter with restriction to determine the relative position is put forward. By data simulation, the arithmetic is then validated and evaluated, which could fleetly and accurately determine the relative position between rover and lander. Low precision of the lander's position is required in the calculation. ©, 2015, SinoMaps Press. All right reserved.