Rapid design and optimization of low-thrust rendezvous/interception trajectory for asteroid deflection missions

2014 ◽  
Vol 53 (4) ◽  
pp. 696-707 ◽  
Author(s):  
Shuang Li ◽  
Yongsheng Zhu ◽  
Yukai Wang
2015 ◽  
Vol 42 ◽  
pp. 365-375 ◽  
Author(s):  
Haibin Shang ◽  
Shuai Wang ◽  
Weiren Wu

Author(s):  
Jackson Shannon ◽  
Martin Ozimek ◽  
Justin Atchison ◽  
Christine Hartzell

Micromachines ◽  
2019 ◽  
Vol 10 (11) ◽  
pp. 780 ◽  
Author(s):  
Myunggi Ji ◽  
Qiang Li ◽  
In Ho Cho ◽  
Jaeyoun Kim

Soft material-based pneumatic microtube actuators are attracting intense interest, since their bending motion is potentially useful for the safe manipulation of delicate biological objects. To increase their utility in biomedicine, researchers have begun to apply shape-engineering to the microtubes to diversify their bending patterns. However, design and analysis of such microtube actuators are challenging in general, due to their continuum natures and small dimensions. In this paper, we establish two methods for rapid design, analysis, and optimization of such complex, shape-engineered microtube actuators that are based on the line-segment model and the multi-segment Euler–Bernoulli’s beam model, respectively, and are less computation-intensive than the more conventional method based on finite element analysis. To validate the models, we first realized multi-segment microtube actuators physically, then compared their experimentally observed motions against those obtained from the models. We obtained good agreements between the three sets of results with their maximum bending-angle errors falling within ±11%. In terms of computational efficiency, our models decreased the simulation time significantly, down to a few seconds, in contrast with the finite element analysis that sometimes can take hours. The models reported in this paper exhibit great potential for rapid and facile design and optimization of shape-engineered soft actuators.


2019 ◽  
Vol 49 (8) ◽  
pp. 084509
Author(s):  
XuSheng WANG ◽  
YuMing PENG ◽  
Xi LU ◽  
WeiHuang SHI ◽  
Wei ZHANG ◽  
...  

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.


2012 ◽  
Vol 588-589 ◽  
pp. 335-339 ◽  
Author(s):  
Lei Fu ◽  
Min Xu ◽  
Xiao Min An ◽  
Xun Liang Yan

A low-thrust guidance scheme, which is weighted combined by taking the optimum strategy of thrust allocation and the target deficits value into consideration for each orbital element, is developed. The presented guidance scheme is predictive in nature and does not rely on a stored reference trajectory or reference controls. The orbit transfer problem is converted into parametric optimization and utilizing a hybrid genetic algorithm. The minimum-time orbit transfer is considered. The influence of the Earth’s oblateness is taken into consideration in the simulation of minimum-time. A conclusion is drawn that the designed method presented here turns out to be an autonomous scheme because the information of target orbit is considered in the transfer process.


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