Three-dimensional impact angle guidance with coupled engagement dynamics

Abstract

This paper proposes three-dimensional impact angle control guidance laws based on a sliding mode control technique. Unlike the usual approach of decoupling the engagement dynamics into two mutually orthogonal two-dimensional planes, the guidance laws are derived using coupled engagement dynamics. By using this approach, the control effort required to achieve the objective reduces and the performance of the guidance law is improved. The derivations of guidance laws are done using both conventional as well as nonsingular terminal sliding mode control, which guarantees asymptotic and finite time convergence, respectively, to the desired impact angle. In order to derive the guidance laws, multi-dimensional switching surfaces are used. The stability of the system, with selected switching surfaces, is demonstrated using Lyapunov stability theory. Numerical simulation results are presented to validate the proposed guidance laws for constant speed, as well as a realistic interceptor model with given aerodynamic properties. The simulations show the advantage of using coupled dynamics. The robustness of the proposed guidance laws, with respect to the interceptor's system lag, is also investigated.

Three-dimensional impact angle guidance law based on robust repetitive control

“…As demonstrated in Fig. 2a, all the three methods enable successful interceptions, and it should be noted that the two methods named RRCGL and ILCGL [11] cost less interception time than NTSMGL [15] method. From Fig.…”

“…Let d and d be the desired final LOS angles in elevation and azimuth, respectively. By accepting the concept that zeroing the LOS angle rate will lead a perfect interception and taking the terminal angle constraint into consideration, the control object is to design a guidance law in such a way that → d , → d , ̇→ 0,̇→ 0 can be fulfilled asymptotically [15].…”

Range-Aware Impact Angle Guidance Law With Deep Reinforcement Meta-Learning

“…The forces acting on missile include thrust , drag , zero-lift drag and induced drag . With missile mass denoted by , and missile acceleration denoted by and , the dynamics of missile motion can be expressed as follows [28]:…”

Near-Optimal Guidance with Impact Angle and Velocity Constraints Using Sequential Convex Programming

“…Now, the energy optimization problem can be rewritten as follows: Problem 1. Minimize equation (8) subject to equations (4)-(7).…”

“…Li et al [5] used graph theory to derive the impact angle and time constraint guidance law. Sliding mode theory [6][7][8][9] and proportional navigation [10][11][12] have been introduced to achieve the desired impact angle. Optimal control theory has also been implemented to solve optimal guidance law problems under an impact angle constraint [13][14][15][16][17][18], but a limit has not been set on the terminal velocity owing to the complicated form of the aerodynamic coefficients.…”