A Full Mission Summary (1997-2017) of the Attitude Control Performance during Orbit Trim Maneuvers Performed by the Cassini-Huygens Spacecraft

2018 ◽  
Author(s):  
Todd S. Brown
Keyword(s):  
Attitude Control ◽  
Control Performance

Testing, modeling and estimation of Taiji-1’s in-orbit magnetic parameters

2021 ◽  
pp. 2140023
Author(s):  
Xingjian Shi ◽  
Zhiming Cai ◽  
Keyword(s):  
Magnetic Property ◽  
Magnetic Moment ◽  
Attitude Control ◽  
Optimization Method ◽  
Noise Model ◽  
Control Performance ◽  
Global Optimization Method ◽  
Magnetic Parameters ◽  
The Magnetic Field ◽  
Reference Sensor

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.

Analytical results of BSE beam pointing and attitude control performance

1984 ◽  
Vol 21 (1) ◽  
pp. 113-119 ◽  
Author(s):  
Sachio Shimoseko ◽  
Hidetoshi Murakami ◽  
Ryo Mochizuki ◽  
Seiki Yokoyama ◽  
Makoto Kajikawa ◽  
...  
Keyword(s):  
Attitude Control ◽  
Control Performance ◽  
Analytical Results

Nano-Sat Scale Electric Propulsion for Attitude Control-Performance Analysis

2019 ◽  
Author(s):  
Jeffery King ◽  
Jonathan Kolbeck ◽  
Jin S. Kang ◽  
Michael Sanders ◽  
Michael Keidar
Keyword(s):  
Performance Analysis ◽  
Attitude Control ◽  
Electric Propulsion ◽  
Control Performance

The Attitude Control Performance of the BSE and its Influence on the Received Television Signal Strengths on the Ground

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

scholarly journals Terminal Sliding Mode Control with Unidirectional Auxiliary Surfaces for Hypersonic Vehicles Based on Adaptive Disturbance Observer

2015 ◽  
Vol 2015 ◽  
pp. 1-11 ◽  
Author(s):  
Naibao He ◽  
Changsheng Jiang ◽  
Bin Jiang ◽  
Qian Gao
Keyword(s):  
Attitude Control ◽  
Disturbance Observer ◽  
Sliding Mode ◽  
Robust Adaptive Control ◽  
Hypersonic Vehicles ◽  
Control Performance ◽  
External Disturbances ◽  
Terminal Sliding Mode ◽  
Control Scheme ◽  
Observer Model

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.

scholarly journals Reliability Approach to Optimal Thruster Configuration Design for Spacecraft Attitude Control Subsystem

2020 ◽  
Author(s):  
Mahdi Ghobadi ◽  
Maziar Shafaee ◽  
Mahdi Jafari Nadoushan
Keyword(s):  
Fuel Consumption ◽  
Attitude Control ◽  
Optimal Configuration ◽  
Configuration Design ◽  
Control Performance ◽  
Spacecraft Attitude Control ◽  
Control Subsystem ◽  
Redundancy Level ◽  
Minimum Number ◽  
Maximum Reliability

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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