A framework of trajectory design and optimization for the hypersonic gliding vehicle

2020 ◽  
Vol 106 ◽  
pp. 106110 ◽  
Author(s):  
Kai An ◽  
Zhen-yun Guo ◽  
Xiao-ping Xu ◽  
Wei Huang
Author(s):  
Chong Sun ◽  
Jianping Yuan ◽  
Qun Fang ◽  
Yao Cui ◽  
Mingxiao Wang ◽  
...  

a novel spacecraft trajectory design method using hybrid low thrust system is proposed in this paper. The hybrid system is constituted with a solar sail propulsion thruster and a solar electric propulsion thruster. In proposed method, the former one provides radical thrust and circumferential thrust to from a virtual gravity, while the later one provides a tangential thrust. In this way, the spacecraft is virtually motioned by constant tangential thrust in a virtual gravity field. Using proposed method, the thrusting trajectory can be parameterized, and a large number of feasible trajectories for circle to circle rendezvous problem can be obtained. To the end the steering law to minimize the fuel cost is found using Matlab optimization tools Fmicon function, and the result is compared with traditional pure solar electric propulsion method in terms of payload mass fraction. The simulation results show that the proposed method can reduced propellant consumption significantly compared with the pure SEP system.


2020 ◽  
Vol 316 ◽  
pp. 04009
Author(s):  
Ke Yi ◽  
Si-hong She ◽  
Shun Zhang ◽  
Bang-ya Hu ◽  
Meng Liu

In order to enhance the penetration ability of the rocket and the damage degree of the target, the trajectory design and optimization of the rockets are carried out, and the cooperative strategy of multiple rockets is designed. Firstly, the particle motion model of rocket is established, and the power and guidance scheme are given. Then, a cooperative attack strategy based on different launch points for multiple rockets is proposed, which transforms the cooperative attack into the optimization of launch points. The optimization model of the launch point under the expected attack time is established, and the model is solved by the cultural algorithm. The distribution of the launch point under different attack time is obtained and fitted as curves under corresponding conditions. Finally, aiming at the problem of multiple rockets cooperative combat, using the obtained curves, three kinds of cooperative strategies which are suitable for different attack time requirements are proposed and verified by simulation.


2019 ◽  
Vol 1325 ◽  
pp. 012031
Author(s):  
Jin Zhang ◽  
Zhongsheng Wang ◽  
Jianyong Zhou

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