Optimal Feedback Gains for Spacecraft Attitude Stabilization Using Magnetorquers Fabio Celani and Renato Bruni
Outline •
attitude stabilization problem
•
spacecraft model and stabilizing feedback
•
method for designing feedback gains based on minimization of settling time
•
case study
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Page 2
Attitude stabilization problem spacecraft with magnetorquers on a circular Low Earth Orbit Z
GeoCentric Inertial (GCI) frame
body frame X,
Y
objective: body frame aligned with GCI frame using magnetorquers only parametrize attitude of body frame with respect to GCI frame using quaternion vector part of body frame aligned with GCI frame Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Page 3
Spacecraft model attitude kinematics attitude dynamics
magnetorquers = three coils aligned with body axis vector of coils’ magnetic dipole moments geomagnetic field in body frame
spacecraft model
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Page 5
Design of feedback gains by optimization 1/2
fix initial state
to significant value
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Page 6
Design of feedback gains by optimization 2/2
fix initial state analytic expression of
to significant value in terms of
and
not available
Lipschitzian without Lipschitz constant optimization algorithm • does not need analytic expression of • just needs to compute at a number of points use simulations • requires feasible set be bounded rectangle determine
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Page 7
Case study 1/2
circular orbit
inclination 87°
altitude 450 km
€ • significant initial state • desired final state
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Page 8
Case study 2/2 design by trial-and-error
design by optimization
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Page 9
Conclusions •
method for designing gains of PD-like feedback that achieves attitude stabilization using magnetorquers
•
design based on minimization of settling time
•
proposed design more systematic than by trial-and-error
Fabio Celani and Renato Bruni 3rd IAA Conference on University Satellite Missions and CubeSat Workshop
Optimal Feedback Gains for Spacecraft Attitude ...
GeoCentric Inertial (GCI) frame body frame parametrize attitude of ... spacecraft with magnetorquers on a circular Low Earth Orbit body frame aligned with GCI ...
Jan 5, 2016 - Let Bi be the geomagnetic field at spacecraft expressed in inertial frame Fi. .... In order to simplify forthcoming expressions let us define â.
determined by length of measurement process (not a control design parameter) ... closed-loop dynamics given by sampled-data nonlinear time-varying system.
attitude control problem. ⢠model of spacecraft with magnetorquers. ⢠separation between measurement and actuation. ⢠design of piecewise-constant control. ⢠case study. Page 3. Attitude control problem. Fabio Celani. Sapienza University of R
The book documents the development of the important ... determination and control systems. It provides ... Spacecraft Systems Engineering (Aerospace Series).
of Bi(t), it is necessary to determine an expression for ri(t) which is the spacecraft's position vector resolved in Fi. Define a coordinate system xp, yp in the orbital's ...
Using a Lyapunov framework, a nonlinear output feed- back control ...... â4 rad/s. For this desired attitude trajectory, Ïrd and ËÏrd can be computed using (25).
vehicles [2], [10], the six-DOF rigid body dynamics and control problem for ... adaptive output feedback attitude tracking controller was developed in [12]. Finally ...
verse directional unit vectors expressed in the body frame. Thus, ..... u D W QT .QWQT /¡1 Lrp ... Note that according to the condition number of the matrix C, the.
signed for spacecraft attitude tracking using Variable Speed Control Moment Gyros ... (2). (3). (4) where the 's denote the values of at . The symbol denotes the ..... are not physically meaningful since they may not preserve the orthogonality of ...
Get the latest news and analysis in the stock market today including national and world stock market news business news financial news and moreOnline PDF ...
Administration/ Goddard Space Flight Center Extensiye work has been done for ... this book, prepared by the Computer Sciences Corporation under the able direction of Dr. James Wertz, ... who need information on spacecraft orientation and how it is de
A. Background. Spacecraft flying in ... Space technology, Narvik University College N-8515 Narvik, Norway. E- mail: {rayk ...... AIAA Education Series, Reston,.
2 Research Engineer, Autonomous Control Branch, Air Force Research Laboratory, Wright-Patterson AFB, OH. 45433 and ... 3 Professor, Electrical & Computer Engineering Department, Air Force Institute of Technology, Wright-Patterson ..... target assignm
a weighted sum-rate maximization at each scheduling instant. We show that such an .... station has perfect knowledge of the channel state m[t] in every time slot.
system to obtain a robust quasi optimal adaptive control law. Such an approach is used ..... therefore reduces to the tracking of the singular value xsing given by eq. (8). For the .... [7] I. Smets, G. Bastin, and J. Van Impe. Feedback stabilisation
Published online 23 May 2005 in Wiley InterScience ... 4 Graduate School of the Chinese Academy of Sciences, Beijing 100049, People's ... the degree of discretization and parameterization is very high, the work of computation stands out and ...
May 23, 2005 - of a population dynamics: viscosity solution approach ...... Seven different arbitrarily chosen control bi and the optimal feedback control bn.
Received: 6 April 2005 / Accepted: 6 December 2006 / Published online: 11 ... of the continuous casting process in the secondary cooling zone with water spray control ... Academy of Mathematics and System Sciences, Academia Sinica, Beijing 100080, ..
Graduate School of Engineering, Hiroshima University,. Japan. Supported in .... B are devoted to some technical estimates used in this paper. 3 ... order to give a rigorous meaning of the process characterized by (1.4), we employ the notion of ...
![[PDF BOOK] Fundamentals of Spacecraft Attitude ...](https://p.pdfkul.com/img/300x300/pdf-book-fundamentals-of-spacecraft-attitude-_5a18b5681723ddf1e0bf44ce.jpg)
