Spacecraft Attitude Control Using Magnetic and Mechanical Actuation

Abstract

The aim of this paper is the analysis of simultaneous attitude control and momentum-wheel management of a spacecraft by means of magnetic actuators only. A proof of almost global asymptotic stability is derived for control laws that drive a rigid satellite toward attitude stabilization in the orbit frame, when the momentum-wheel is aligned with one of the principal axes of inertia. Performance of the proposed control laws is demonstrated by numerical simulations under actuator saturation. Robustness to external disturbances and model uncertainties is also evaluated. Nomenclature b Geomagnetic eld vector expressed in F B , T C D Spacecraft drag coecient e 1 ,ê 2 ,ê 3 Spacecraft principal axes of inertia F B Body-xed frame

Spacecraft Attitude and Reaction Wheel Desaturation Combined Control Method

“…The nonlinear model of (21) can be used to design control systems. One popular design method for nonlinear model involves Lyponuv stability theorem, which is actually used in [8,9]. A design based on this method focuses on stability but not on performance.…”

“…Since both attitude control and reaction wheel desaturation are performed at the same time using the same magnetic torque coils, the control system design should consider these two design objectives at the same time and some very recent research papers tackled the problem in this direction, for example, [8,9]. In [8], Tregouet et al studied the problem of the spacecraft stabilization and reaction wheel desaturation at the same time.…”

“…Moreover, their design is composed of two loops, which is essentially an idea of dealing with attitude control and wheel momentum management in separate considerations. In [9], a heuristic proportional controller was proposed and a Lyapunov function was used to prove that the controller can simultaneously stabilize the spacecraft with respect to the LVLH frame and achieve reaction wheel management. But this design method does not consider the the time-varying effect of the geomagnetic field in body frame.…”

Investigating the use of 3D printed soft magnetic PEEK‐based composite for space compliant electrical motors

“…1,2 Spacecrafts adopt BLDC electric motors in several subsystems such as attitude control, deployment mechanisms, and throttle valve control. 3 The basic structure of a BLDC motor consists of a rotating part that houses the permanent magnets plaques (the rotor) and a stationary core wrapped in electric coils (the stator). Traditionally, ferromagnetic cores are made in laminated electrical steel, Co-Fe alloys (preferred in aerospace applications) 4,5 and sintered powders of ferrites and other alloys.…”

Algorithms and Optimal Control for Spacecraft Magnetic Attitude Maneuvers

“…Magnetic rods are by far the cheapest, however their drawbacks include poor accuracy and even instantaneous under actuation [6]. Yet, they are widely studied for satellite attitude control as described in many references such as [6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25].…”