Velocity-Free Attitude Reorientation of a Flexible Spacecraft with Attitude Constraints

Simple model-free attitude control design for flexible spacecraft with prescribed performance

“…Theorem 1. Consider the flexible spacecraft attitude control system (5) and the error transformation (19). If the virtual angular velocity x d and the controller u are given as equations (21) and 22, then the transformed error " li is uniformly bounded, and the attitude error e li satisfies the performance constraint equation 7.…”

“…The common way to achieve the objectives in engineering is to give a desired attitude trajectory before designing a controller to track it. [16][17][18][19] However, the actual control effect mostly relies on the controller design and the control gain selection. Furthermore, there is no systematic procedure, which can obtain the required control behaviors by a prior selection of some certain parameters.…”

Spacecraft Attitude Control With Nonconvex Constraints: An Explicit Reference Governor Approach

“…Potential field methods generate a suitable control law by constructing an artificial potential field that has a minimum at the target reference and high values around the exclusion zones. This field is then used as either a Lyapunov function to which techniques from nonlinear control are applied [17]- [22] or as a cost function to which techniques from optimal control [23] are applied. Potential field methods are typically computationally inexpensive, and thus suitable for onboard implementation.…”

“…, (18)-(19), and (21)-(22), the set {(q, ω)|∆(q, ω) ≥ 0} is forward-invariant for any constant v andthere exists > 0 such that v ∈ R δ implies ∆(v, 0) > . As a result,(16)satisfies the requirements of [30, Definition 1].…”

Finite‐time disturbance observer based integral sliding mode control for attitude stabilisation under actuator failure

“…And much attention has been paid by academic and industrial communities to their development, to ensure that the expected control system performance indices are achieved. Many control methods have been applied to achieve the attitude control missions, such as feedback control, non‐linear control, optimal control, adaptive control, sliding mode control, robust control, and their integrations [1–7]. However, it may result in unsatisfactory performance even instability when unexpected malfunctions or catastrophic failures occur in actuating mechanisms.…”