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Adaptive Nonlinear Attitude Control and Momentum Management of Spacecraft
1997
Journal of Guidance Control and Dynamics
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for the attitude control problem (without momentum management) with a full inertia matrix and without linearization of the system dynamics. ...
JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS Vol. 20, No. 5, September—October 1997
Adaptive Nonlinear Attitude Control and Momentum Management of Spacecraft
Scott J. Paynter* and Robert H. ...
doi:10.2514/2.4150
fatcat:k4mkua3bbjcgjpnne5oo7kbiya
Application of Model-Free Control to the Operation of Post-Capture Combined Spacecraft
2023
Aerospace (Basel)
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system for the attitude and orbital dynamics motions of post-capture combined spacecraft are presented. ...
The results show that the model-free control has a good control effect on the attitude and orbit of the post-capture combined spacecraft, even if the configuration of the spacecraft is time-varying. ...
Acknowledgments: We would like to thank the Shanghai Key Laboratory of Space Intelligent Control Technology for providing the data used in the model tests described in this paper. ...
doi:10.3390/aerospace10010090
fatcat:b63nndxs4ra5fn2bc57g44cz5a
Adaptive finite-time tracking control of 6DOF spacecraft motion with inertia parameter identification
2019
IET Control Theory & Applications
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Compared with the previous control designs, the proposed control strategy can realise inertia parameter identification together with tracking of command position and attitude in finite time, in the presence ...
This study deals with the problem of relative motion control with 6 degrees of freedom (6DOF) for spacecrafts without a priori knowledge of the inertia parameters. ...
Acknowledgments This work was supported by the Major Program of National Natural Science Foundation of China under grant nos. 61690210 and 61690212 and by Self-Planned Task (NO.SKLRS201716A) of State Key ...
doi:10.1049/iet-cta.2019.0245
fatcat:brdohw6zwnb6thx3jn52xxem5a
Indirect Robust Adaptive Fault -Tolerant Control for Attitude Tracking of Spacecraft
2008
Journal of Guidance Control and Dynamics
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., “Adaptive Asymptotic Tracking of Spacecraft Attitude Motion with Inertia Matrix Identification,” Journal of Guidance, Control, and Dynamics, Vol. 21, No. 5, 1998, pp. 684-691.
Servidia, P. ...
Adaptive Control for Attitude Tracking of Spacecraft.” ...
doi:10.2514/1.31158
fatcat:kzdq3a64a5c2zm6msc7j7fo7hm
Quaternion-based adaptive attitude tracking controller without velocity measurements
2001
Journal of Guidance Control and Dynamics
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., “Adaptive Asymptotic Tracking of Spacecraft Attitude Motion with Inertia Matrix Identification, Journal of Guidance, Control, and Dynamics, Vol. 21, No. 5, 1998, pp 684-69 |
"Hughes, P. ...
., “Globally Convergent Adaptive Control of Spacecraft Angular Velocity Without Inertia Modeling.” ...
doi:10.2514/3.22618
fatcat:cdlvf2debbh43nujcbudwlxp34
Quaternion-Based Adaptive Attitude Tracking Controller Without Velocity Measurements
2001
Journal of Guidance Control and Dynamics
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., “Adaptive Asymptotic Tracking of Spacecraft Attitude Motion with Inertia Matrix Identification, Journal of Guidance, Control, and Dynamics, Vol. 21, No. 5, 1998, pp 684-69 |
"Hughes, P. ...
., “Globally Convergent Adaptive Control of Spacecraft Angular Velocity Without Inertia Modeling.” ...
doi:10.2514/2.4837
fatcat:2yxy3bjpfbbplo67ao6t2wgwsm
Unscented Kalman Filtering for Hybrid Estimation of Spacecraft Attitude Dynamics and Rate Sensor Alignment
[chapter]
2011
Advances in Spacecraft Technologies
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Adaptive asymptotic tracking of spacecraft attitude motion with inertia matrix identification, Journal of Guidance, Control and Dynamics, Vol. 21, No. 5,
References Fig. 2 . 2 Body angular rate reference ...
as ω R ∈ is the body angular velocity, J is the mass moment of inertia matrix, and 3 u R ∈ is the external control input torque. ...
The final section contains eleven chapters that present a series of novel control methods for spacecraft orbit and attitude control. ...
doi:10.5772/14022
fatcat:puktkxj3xbcnlb2s4znjzubbfu
Designing a low-cost spacecraft simulator
2003
IEEE Control Systems
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This algorithm can also be used to estimate the inertia matrix for later use in attitude tracking and indirect adaptive control schemes. ...
Identification of Moment of Inertia Matrix One way of calculating the moments of inertia (MOI) of the rigid spacecraft simulator is to use a CAD model. ...
doi:10.1109/mcs.2003.1213601
fatcat:7lzx7zrwevajdfp7huks44hyd4
Attitude Control of Spacecraft: Mixed H/H Approach
2001
Journal of Guidance Control and Dynamics
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'® In this paper, we deal with the adaptive mixed H,/H,. attitude control problem of the given spacecraft systems under unknown inertia matrix J and external disturbance T ,. ...
Conclusions
This paper presents an adaptive mixed H>/H., attitude control de- sign of the nonlinear spacecraft system with an external disturbance and uncertain inertia matrix. ...
doi:10.2514/2.4776
fatcat:p3xw5s3h75hnnmkpqumogwif3q
Recursive Star-Identification Algorithm using an Adaptive SVD-based Angular Velocity Estimator
[article]
2020
arXiv
pre-print
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This paper describes an algorithm obtained by merging a recursive star identification algorithm with a recently developed adaptive SVD-based estimator of the angular velocity vector (QuateRA). ...
First, a speed comparison is made with the state-of-the-art lost-in-space star identification algorithm, Pyramid. ...
In the recursive scenario, the attitude dynamic of a spacecraft is associated with a small angular velocity, and the star identification (Star-ID) was completed at some previous time such that the stars ...
arXiv:2003.11684v2
fatcat:hc2nrtdgmzehbgek4pqphaplje
Quaternion Observer-Based Model-Independent Attitude Tracking Control of Spacecraft
2009
Journal of Guidance Control and Dynamics
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., “Adaptive Asymptotic Tracking of Spacecraft Attitude Motion with Inertia Matrix Identification,’ Journal of Guidance, Control, and Dynamics, Vol. 21, No. 5, 1998, pp. 684-691. doi: 10.2514/2.4310 Krstié ...
Proposition 3: Consider a spacecraft with time-varying inertia matrix J, external disturbances, and attitude observer defined in Eqs. (4-6). ...
doi:10.2514/1.43029
fatcat:gvms5a7rznftjgmkb57oyccrki
Optimal Discrete-Time Design of Three-Axis Magnetic Attitude Control Laws
2010
IEEE Transactions on Control Systems Technology
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Index Terms-Attitude control, magnetic actuators, periodic optimal control, periodic systems, spacecraft control, static output feedback. ...
The problem of designing discrete-time attitude controllers for three-axis stabilization of magnetically actuated spacecraft is considered. ...
We will consider a spacecraft with inertia matrix , equipped with a single momentum wheel aligned with the body axis, with moment of inertia and angular velocity relative to the body frame. ...
doi:10.1109/tcst.2009.2024757
fatcat:o4pn4ycstrawxenfhuddb5bijy
Adaptive attitude control and momentum management for large-angle spacecraft maneuvers
1992
Journal of Guidance Control and Dynamics
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JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS Vol. 15, No. 4, July-August 1992
Adaptive Attitude Control and Momentum Management for Large-Angle Spacecraft Maneuvers
Alexander G. ...
This results in less complex control laws compared to alternate adaptive schemes requiring on- line identification. ...
doi:10.2514/3.20937
fatcat:ytyobs7vurfmzapugd6qwg7ngq
OPTIMAL DISCRETE-TIME MAGNETIC ATTITUDE CONTROL OF SATELLITES
2005
IFAC Proceedings Volumes
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The problem of designing discrete-time attitude controllers for magnetically actuated spacecraft is considered. ...
Several methods are discussed and a novel approach to the tuning of "projection based" controllers is proposed relying on periodic optimal output feedback control techniques. ...
of the attitude dynamics with respect to the nominal Earth pointing equilibrium. ...
doi:10.3182/20050703-6-cz-1902.01987
fatcat:77qzakbsifbgtmbj5p6q634la4
Adaptive Output Feedback Control for Spacecraft Rendezvous and Docking Under Measurement Uncertainty
2006
Journal of Guidance Control and Dynamics
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The actual mass of the chaser spacecraft is assumed to be 50 kg with the following true inertia matrix:
250 100 50 I=} 100 200 30 50 30 = 150
The chaser is assumed to be equipped with three momentum wheels ...
of the spacecraft translational and attitude dynamics to generate the pseudo-velocity-like signals. ...
doi:10.2514/1.17498
fatcat:b4jxxwdhjrbtvprgkw6qwqni6q
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