Design of nonlinear terminal guidance/autopilot controller for missiles with pulse type input devices

Abstract

This investigation addresses a nonlinear terminal guidance/autopilot controller with pulse-type control inputs for intercepting a theater ballistic missile in the exoatmospheric region. Appropriate initial conditions on the terminal phase are assumed to apply after the end of the midcourse operation. Accordingly, the terminal controller seeks to minimize the distance between the commanded missile and the target missile to ensure a hit-to-kill interception. In particular, a 3D terminal guidance law is initially developed to eliminate the so-called "sliding velocity," thus, constraining the relative motion between the missile and the target along the line of sight. Sliding mode control is adopted to design stable pulse-type control systems. Then, a quaternion-based attitude controller is used to orient appropriately the commanded missile, taking into account the fact that the missile is a rigid body, to realize interceptability. The stability of the overall integrated terminal guidance/autopilot system is then analyzed thoroughly, based on Lyapunov stability theory. Finally, extensive simulations are conducted to verify the validity and effectiveness of the integrated controller with the pulse type inputs developed herein.

Research on Integrated Guidance and Control of Distributed Cooperation of Multi-Interceptor with State Coupling

“…In existing papers, most of them were designed in a single channel [21,22], regardless of the coupling between channels. The authors in [23,24] designed IGC algorithms in three dimensions, but designing the controller is difficult when establishing the model with a high order.…”

Robust adaptive control for a class of cascaded nonlinear systems with applications to space interception

“…ROBUST ADAPTIVE CONTROL FOR A CLASS OF CASCADED NONLINEAR SYSTEMS 2049 1. On the one hand, from a practical point of view, this kind of nonlinear systems can capture the dynamic behavior of many practical systems such as active suspension systems [17][18][19], missile guidance=autopilot systems [20,21], spacecraft rendezvous, and lunar soft landing [22]. Take the spacecraft rendezvous, for example, the relative translational dynamics of two adjacent spacecraft can be described by a linear system known as C-W equations [23], whereas the attitude dynamics of the pursuer spacecraft is a highly nonlinear system.…”

Integrated Game Based Guidance with Nonlinear Autopilot Design for Maneuvering Target Interception

“…A comparison between PPN and TPN was then made by Shukla and Mahapatra [5]. In addition to PN guidance, other formulations of the guidance laws also have been proposed in recent years, such as the 3-D modeling method [6][7][8][9], and differential geometric method [10,11]. In this paper, we apply game theory in the design of guidance law.…”