Research on Three-Dimensional Integrated Guidance and Control Design with Multiple Constraints

Abstract

In this paper, a fixed-time convergence-integrated guidance and control (IGC) method is proposed, which considers terminal line-of-sight (LOS) angle constraint, full-state constraints, and input saturation. Firstly, an IGC design model considering the full coupling of three channels is constructed, and a fixed-time convergence disturbance observer is used to estimate and compensate the unknown disturbances in the model. Secondly, based on the fixed-time stability theory, sliding mode control, and backstepping control, a novel IGC scheme is carried out, and the second-order instruction filter is used to restrict the system states and control instructions. Furthermore, the fixed-time stability of the close-loop system is proved and the expression of convergence time upper bound is given. Finally, comparison simulation and Monte Carlo simulation verify the effectiveness and superiority of the proposed IGC algorithm.

Full state‐constrained integrated guidance and control for aerial interceptors with tunnel prescribed performance using integral barrier Lyapunov function

“…To deal with the un‐differentiable problem of conventional saturation function $$$ Sat\left(\kern0.2em \right) $$$ at the corner point, inspired by Reference 31, the following piecewise smooth function is adopted in this paper $$$$ Sat\left({u}_i\right)=\left\{\begin{array}{l}\eta {u}_{i,\max }+\left({u}_{i,\max }-\eta {u}_{i,\max}\right)\tanh \left(\frac{u_i-\eta {u}_{i,\max }}{u_{i,\max }-\eta {u}_{i,\max }}\right),\kern1.2em if\kern2.2em {u}_i>\eta {u}_{\mathrm{max}}\\ {}{u}_i,\kern19em if\kern0.5em -\eta {u}_{i,\min}\le {u}_i\le \eta {u}_{i,\max}\\ {}-\eta {u}_{i,\min }+\left({u}_{i,\min }-\eta {u}_{i,\min}\right)\tanh \left(\frac{u_i+\eta {u}_{i,\min }}{u_{i,\min }-\eta {u}_{i,\min }}\right),\kern.8em if\kern2.2em {u}_i<-\eta {u}_{i,\min}\end{array}\right., $$$$ where $$$ i=1,2,3 $$$ and …”

“…To deal with this problem, a novel IGC schema combined with an integral barrier Lyapunov function (iBLF) was proposed in Reference 30 to constrain the flight states of STT missiles. In Reference 31, a fixed‐time convergence‐IGC method with full state constraints was carried out against a stationary target, where the system states were restricted by second‐order instruction filters.…”