Spacecraft attitude control using explicit model predictive control

Abstract

In this paper, an explicit model predictive controller for the attitude of a satellite is designed. Explicit solutions to constrained linear MPC problems can be computed by solving multi-parametric quadratic programs (mpQP), where the parameters are the components of the state vector. The solution to the mpQP is a piecewise affine (PWA) function, which can be evaluated at each sample to obtain the optimal control law. The on-line computation effort is restricted to a table-lookup, and the controller can be implemented on inexpensive hardware as fixed-point arithmetics can be used. This is useful for systems with limited power and CPU resources. An example of such systems is micro-satellites, which is the focus of this paper. In particular, the explicit MPC (eMPC) approach is applied to the SSETI/ESEO micro-satellite, initiated by the European Space Agency (esa). The theoretical results are supported by simulations.

1-Bit processing based model predictive control for fractionated satellite missions

“…Such methods are further developed by other efforts such as Spjøtvold, et al, 2004) and many applications e.g. (Hegrenaes, et al, 2005). A recent survey of EMPC methods is given in (Alessio and Bemporad, 2009).…”

“…The EMPC algorithm is also proposed for spacecraft attitude control in (Hegrenaes , et al, 2005) as one of the few practical studies for the spacecraft attitude control system using MPC.…”

“…(Quevedo, et al, 2003), (Hegrenaes, et al, 2005). The OBMPC inherits the benefits of the MPC algorithm for the WCS, in which the prediction data can be used to produce backup information in case of packet loss or a large time delay occurrence.…”

Model predictive control application to spacecraft rendezvous in mars sample return scenario

“…A linearized quaternion-based prediction model [13] extended to consider the elliptical orbital dynamics is used for the relative attitude control. The attitude reference frame used for control is chosen depending on the direction of approach, and the attitude setpoint in the inertial frame to avoid the predicted trajectory crossing the discontinuity at ±180 • in the quaternion representation [33].…”

Cascade-Based Controlled Attitude Synchronization and Tracking of Spacecraft in Leader-Follower Formation

“…It should be noted that we apply (10) and its derivative to the generated reference rather than the dynamical equation to keep a simple control law structure compared to [38]. The second controller is designed as a synchronizing controller to make the states q f (t) and ω f b i, f b (t) converge towards q l (t) and ω f b i,lb (t).…”