Analytical results of BSE beam pointing and attitude control performance

1982 ◽  
1984 ◽  
Vol 21 (1) ◽  
pp. 113-119 ◽  
Author(s):  
Sachio Shimoseko ◽  
Hidetoshi Murakami ◽  
Ryo Mochizuki ◽  
Seiki Yokoyama ◽  
Makoto Kajikawa ◽  
...  

Author(s):  
Xingjian Shi ◽  
Zhiming Cai ◽  

Taiji-1’s in-orbit magnetic property is significant for the improvement of the satellite’s attitude-control performance and the acceleration noise model of gravitational reference sensor. Test data of satellite drifts have been used to construct the model including interaction among the magnetic field; remnant magnetic moment and induced magnetic moment so as to estimate the satellite’s magnetic property. Using the global optimization method, the remnant magnetic moment of Taiji-1 is estimated to be (-1.42 -0.19 -0.06) Am2.


Author(s):  
Jeffery King ◽  
Jonathan Kolbeck ◽  
Jin S. Kang ◽  
Michael Sanders ◽  
Michael Keidar

1982 ◽  
Vol BC-28 (4) ◽  
pp. 150-156 ◽  
Author(s):  
Sachio Shimoseko ◽  
Hidetoshi Murakami ◽  
Ryo Mochizuki ◽  
Seiki Yokoyama ◽  
Makoto Kajikawa ◽  
...  

2015 ◽  
Vol 2015 ◽  
pp. 1-11 ◽  
Author(s):  
Naibao He ◽  
Changsheng Jiang ◽  
Bin Jiang ◽  
Qian Gao

A novel flight control scheme is proposed using the terminal sliding mode technique, unidirectional auxiliary surfaces and the disturbance observer model. These proposed dynamic attitude control systems can improve control performance of hypersonic vehicles despite uncertainties and external disturbances. The terminal attractor is employed to improve the convergence rate associated with the critical damping characteristics problem noted in short-period motions of hypersonic vehicles. The proposed robust attitude control scheme uses a dynamic terminal sliding mode with unidirectional auxiliary surfaces. The nonlinear disturbance observer is designed to estimate system uncertainties and external disturbances. The output of the disturbance observer aids the robust adaptive control scheme and improves robust attitude control performance. Finally, simulation results are presented to illustrate the effectiveness of the proposed terminal sliding mode with unidirectional auxiliary surfaces.


Author(s):  
Mahdi Ghobadi ◽  
Maziar Shafaee ◽  
Mahdi Jafari Nadoushan

An optimal thruster configuration for attitude control subsystem of a spacecraft is presented in this paper. The optimal configuration is designed according to minimum number of required thrusters for satisfying desired reliability with specific redundancy level. The genetic algorithm is employed for optimization process and feasibility of the results is evaluated using algebraic and geometry methods. The main feature of the proposed configuration among feasible configuration with minimum number of required thrusters, which has held to optimal configuration, is that this configuration has maximum reliability and minimum fuel consumption. In addition to feasibility, attitude control performance of some configurations is also examined through the simulation. The results of simulation confirm that the proposed configuration has desirable performance. It is noteworthy to mention that the configuration with maximum number of required thrusters, which is a conventional configuration such that each thruster belongs to only one control channel, has less fuel consumption than optimal configuration. However, the total mass of optimal configuration is less than that of conventional configuration due to a smaller number of thrusters.


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