Abstract
This paper proposes an integral sliding mode guidance law with the constraints of the line-of-sight angle and its rate for the interception of a non-cooperative maneuvering target. The analytical guidance law is derived using an integral sliding mode control and an inertial delay control allowing for unknown uncertainties. The guidance law is further advanced to achieve exponential convergence and high terminal guidance accuracy with autopilot lag. This is accomplished by applying dynamic surface control and fractional order filters. Finally, the finite-time stability of the guidance law with and without missile autopilot lag is demonstrated. In addition to its robustness and precision, there are other benefits of this proposed guidance law. First, the proposed guidance law can effectively attenuate an abrupt change in guidance commands during the terminal homing phase in the presence of uncertainties without prior information. Second, the design parameters in the inertial delay control are decoupled with the integral sliding mode control. This decoupling supplies more degrees of freedom to regulate the performance of guidance commands. Third, the finite-time convergence of the proposed guidance law is guaranteed while accounting for the approximated second-order dynamics and uncertainties of the missile autopilot. Theoretical analysis and numerical simulations were conducted to demonstrate the efficiency of the proposed guidance law.
Highlights
The interception of a non-cooperative maneuvering target during the terminal homing phase using a defense missile is a unique challenge due to the high engagement speed and limited engagement time
An inertial delay control (IDC) was proposed to improve the estimation performance when system uncertainty bounds are unknown in advance [15], [16]
These sliding mode control (SMC)-based guidance laws have shown their effectiveness of achieving a high terminal miss distance accuracy subject to impact angle constraints and uncertainties
Summary
The interception of a non-cooperative maneuvering target during the terminal homing phase using a defense missile is a unique challenge due to the high engagement speed and limited engagement time. An inertial delay control (IDC) was proposed to improve the estimation performance when system uncertainty bounds are unknown in advance [15], [16] These SMC-based guidance laws have shown their effectiveness of achieving a high terminal miss distance accuracy subject to impact angle constraints and uncertainties. If the missile autopilot lag is considered, the abruptly changing guidance commands cannot be effectively tracked This significantly deteriorates the guidance law’s overall performance, especially in the case of short engagement time. A new ISM-type guidance law to intercept a non-cooperative maneuvering target subjected to terminal LOS angle constraints and autopilot dynamics is proposed. Compared with the previous work of the present authors ([21] and [22]), the proposed guidance law dramatically improves the robustness and guidance accuracy for a maneuvering target when unknown uncertainties exist in the closed-loop system. The reference guidance commands are precisely tracked throughout the terminal homing phase
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