Research on Intercepting Algorithm Non-Maneuvering Target for Hypersonic Aircraft Based on Robust Control Theory

In response to the numerous issues in precise guidance for hypersonic aircraft, this paper focuses on the design of a terminal guidance law to establish a guidance model suitable for theoretical analysis. By employing the differential equations of missile-target spatial motion, a model for guidance law design is derived. Furthermore, nonlinear robust control is introduced into the design and analysis of forward interception guidance law. Through the design, analysis, and simulation of sliding mode guidance law to intercept non-naneuvering target, the effectiveness and feasibility of robust guidance law design for forward interception are validated.