Analysis of application specifics of a reaction wheel with intrinsic disturbing moments compensation

Electrical Engineering

Electrical engineering complexes and systems


Аuthors

Balkovoy N. N.

Scientific & Industrial Center Polyus, 56v, Kirova av., Tomsk, 634050, Russia

e-mail: balkovoy.nn@gmail.com

Abstract

Inertial electromechanical actuators in the form of reaction wheels (RW) found widespread occurrence as actuators of spacecraft attitude control system. The RWs task consists in forming a dynamic controlling moment proportionally to a control signal. This task is reduced to the RW acceleration control.

The article suggests the RW classification, describes advantages and disadvantages peculiar to each of the types. Amid all varieties of the units, reactions wheels with intrinsic disturbing moments' compensation (RWMC) are outlined as one of the most prospective types. The presented work is devoted to the study of these units application possibilities and comparing them with classical ones, where control is performed only by the electromagnetic moment.

To study dynamic and accuracy characteristics of a spacecraft equipped with the RWMC under study, its mathematical model was developed. Analysis of the RWMC dynamic moment development transient was performed. It revealed that transfer functions of compensating and basic (electromagnetic moment control) loops may be represented with high accuracy by the aperiodic link. The time constants of these links were also obtained while the RWMC experimental testing.

The model of the controlled rotational motion accounts for the RWMC static and dynamic imbalances values, as well as the number of RWMC nonlinearities, such as saturation, associated with attaining the limiting angular speed by the rotor and the dead zone while the rotor passes the zero angular speed (for a model without disturbances compensation) etc. Modeling of the spacecraft control system operation in stabilization mode in conditions of ideal measuring of angular position and angular speed was performed to study the effect of the unit specifics on the control system operation.

The spacecraft attitude control system with RWCM was compared to classical RW. In both cases, the control system loop was closed by the PID-regulator, since external disturbances, affecting the stabilization static error value, impact the spacecraft together with disturbing moments.

The simulation results showed that RWCMs has higher accuracy and dynamic characteristics compared to the classical RW. This type of units appears more preferable for developing precise spacecraft attitude control systems, since it allows reduce the “dead zone” of control, as well as oscillation in stabilization transient, especially in the area of near-zero angular rotation speeds of the RW rotor.

Keywords:

reaction wheel, intrinsic disturbing torques compensation, reaction wheels classification

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