Energy optimal spacecraft attitude control subject to convergence rate constraints

Nadjim Horri, Phil Palmer, Mark Roberts

Research output: Contribution to journalArticle

13 Citations (Scopus)

Abstract

Attitude control of operational satellites is still predominantly performed by standard controllers such as Proportional plus Derivative (PD) control laws, which are still preferred for implementation to the computationally intensive nonlinear optimal control techniques, representing higher implementation complexity. In this paper, an inverse optimal control approach based on phase space geometry is presented, which is easy to implement and free from numerical and computational issues. The optimal control objective is to minimize a norm of the control torque subject to a rapidity constraint on the convergence rate of a Lyapunov function, under the effect of a benchmark controller. The proposed optimization method is shown to significantly enhance the torque-rapidity trade-off compared to the benchmark controller, chosen to be a PD law then a sliding mode controller. The inverse optimal control scheme is implemented on an air bearing table experimental platform.
Original languageEnglish
Pages (from-to)1297-1315
Number of pages19
JournalControl Engineering Practice
Volume19
Issue number11
Publication statusPublished - Nov 2011

Fingerprint

Attitude Control
Attitude control
Spacecraft
Convergence Rate
Controller
Optimal Control
Energy
Controllers
Torque
Benchmark
Nonlinear Optimal Control
Derivative
Bearings (structural)
Derivatives
Sliding Mode
Lyapunov Function
Torque control
Optimization Methods
Phase Space
Lyapunov functions

Keywords

  • Optimal
  • Attitude control
  • Geometric
  • Minimum norm
  • Lyapunov
  • Air bearing table

ASJC Scopus subject areas

  • Control and Systems Engineering

Cite this

Energy optimal spacecraft attitude control subject to convergence rate constraints. / Horri, Nadjim; Palmer, Phil; Roberts, Mark.

In: Control Engineering Practice, Vol. 19, No. 11, 11.2011, p. 1297-1315.

Research output: Contribution to journalArticle

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