ATTITUDE reorientation is a process of controlling the attitude of a rigid spacecraft to the desired orientation. It plays an important role in guaranteeing the success of on-orbit space missions, such as Earth observation [1], laser communications [2], and so on. In these applications, an essential objective is to achieve reliable and high-performance attitude control. Additionally, per safety concerns, attitude maneuvers are subject to some physical constraints. One arises from the angular velocities of the spacecraft, due to measurement saturation restrictions of the rate gyros [3]. The other two are limited driving torques and rotational speeds caused by reaction wheel assembly (RWA)[4]. Unexpected constraint violations may lead to the loss of pointing accuracy or even mission failure. Meanwhile, note that RWA is a typical momentum exchange device that consumes electrical power. However, electrical power is a valuable orbit resource, especially for downsized spacecraft with strict power budgets [5]. Therefore, it is practically significant to ensure satisfactory attitude performance and safe operation while aiming for electricity optimization.

Research efforts focusing on the constrained attitude control problem have been carried out extensively. In [6], a sliding mode controller incorporating with potential functions was proposed for rest-to-rest attitude reorientation with angular velocity limits. Aided by explicit reference governors, an attitude reorientation issue was