Abstract
In order to meet the needs of high-precision guidance for intercepting hypersonic targets, a novel head-pursuit guidance law considering the dynamic characteristics of a missile control system and the target mobility is presented via combining a fast power reaching law with backstepping sliding mode control in this paper. Initially, a three-dimensional head-pursuit system model of the missile and target is established. Subsequently, the system model is decomposed into a pitch plane system and lateral plane system, the control system dynamics are equivalent to second-order systems, and finite-time disturbance observers are introduced to estimate the target accelerations. On the basis of the previous work, the head-pursuit guidance laws of the vertical system and the lateral system which can stabilize the closed-loop system are designed separately and strict proofs of the methods are given. Finally, simulations are carried out to verify the effectiveness of this head-pursuit guidance law.
Highlights
Hypersonic vehicles have the characteristics of long flight distance, high flight speed, and high maneuverability, which has great military value and presents great challenges to the interception of such aircraft
In order to meet the actual requirements of intercepting hypersonic vehicles, this paper considers the dynamic characteristics of the control system, estimates the unknown target maneuver with a finite-time disturbance observer (FTDO), and designs three-dimensional head-pursuit guidance laws based on the backstepping sliding mode control theory
A head-pursuit guidance law based on the backstepping sliding model control theory and FTDO is proposed considering the autopilot dynamic characteristics, and its stability is proved using the Lyapunov stability theorem
Summary
Hypersonic vehicles have the characteristics of long flight distance, high flight speed, and high maneuverability, which has great military value and presents great challenges to the interception of such aircraft. The head-pursuit guidance law reduced the requirement of overload capacity and avoided the problem of aerodynamic ablation of interceptor warhead cover On this basis, literature [6] designed the head-pursuit guidance law based on sliding mode control theory and verified the advantages of this method. In order to meet the actual requirements of intercepting hypersonic vehicles, this paper considers the dynamic characteristics of the control system, estimates the unknown target maneuver with a finite-time disturbance observer (FTDO), and designs three-dimensional head-pursuit guidance laws based on the backstepping sliding mode control theory. The target maneuver is estimated by the FTDO and head-pursuit guidance laws which consider that the dynamic characteristics of the control system are designed and the stability of the closed-loop system is verified. The effectiveness and superiorities of the guidance laws designed in this paper are verified through the digital simulations
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