Practical guidance law controlling impact angle

Abstract

Impact angle is defined as the angle between the velocity vectors of a missile and a target at the instance of interception. The objective of the impact angle control guidance (IACG) law is to guide the missile into a collision course with a specified impact angle. In this paper, a new IACG law considering practical implementation is proposed. By selecting parameters properly, the proposed guidance law can be applied to various engagement situations such as the rear-chase case and the face-to-face case. On the basis of the backstepping control approach, the proposed guidance law only requires information about the impact angle, the line-of-sight rate, and the estimated time-to-go. These features improve the applicability of the proposed guidance law to the real systems. To verify the performance of the proposed guidance law, two-dimensional engagement problem is considered. Numerical simulation results demonstrate that the proposed guidance law is effective for controlling the impact angle.

Sliding mode based impact angle guidance law considering actuator fault

“…M a n u s c r i p t 16 The parameter  is chosen as 0 while  and K are set as 1 and 40, respectively.…”

“…With the development nonlinear control theory, some novel impact angle constraint guidance laws have also been designed based on Lyapunov function [15], backstepping methodology [16], state dependent Riccati equation (SDRE) method [17], sliding mode control (SMC) theory [18][19][20]. Among them, SMC is a well-known and extensively researched robust control theory due to its disturbances and model uncertainties rejection performance.…”

Lyapunov-based impact time control guidance laws against stationary targets

“…A bank-to-turn guidance law was proposed by introducing nonzero effort miss using Lyapunov stability theory [4]. A sliding mode control scheme and a back-stepping controller were also applied to develop nonlinear guidance laws [5][6][7].…”

Polynomial Function Based Guidance for Impact Angle and Time Control

“…For decades, many impact angle control guidance laws have been proposed based on the optimal control theory or nonlinear control design methods, etc. [1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16]. The authors of [1] proposed a suboptimal guidance law with a terminal body attitude constraint for reentry vehicles.…”

“…They also proposed an guidance law by using the state-dependent Riccati equation (SDRE) technique [9]. In addition to the above guidance laws, other guidance laws to satisfy the terminal angle constraint have been developed: terminal body angle constrained guidance law based on the linear quadratic terminal control problem [10], impact angle controller for minimum flight time [11], impact angle control law derived by the backstepping control method [12], and optimal solution to a simple rendezvous problem which can be used to control the impact angle [15,16].…”