Abstract
This paper proposed a robust autopilot design for air to air guided missile and a Hardware-in-the-Loop (HIL) simulation which is based on the derived missile-control transfer functions and the 6DOF simulation model. The introduced autopilot is implemented within the 6DOF simulation to check its robustness against non-modeled dynamics and nonlinearities. The nonlinear 6DOF equations of motions are solved together to obtain the pitch and yaw transfer functions. The missile equations are described in the form of modules programmed within the C++ environments to form the baseline for subsequent design and analysis. Furthermore, a comparison between both our previous work, i.e. classical and robust autopilot, are justified via HIL simulation. The simulation results demonstrated the robustness capability in presence disturbance and noise.
Highlights
The great developments in mathematics and computational capabilities facilitate the design and implementation of control
Noise Sensitivity Applying a white Gaussian noise to the tracker output yields the control effort shown in Figure 10, which clarifies that C1 has lower infinity norm ǁωtTǁ∞ = 0.2378 than C2 ǁωtTǁ∞ = 0.5623 which has an indication of the stability of the robust controller and it is less sensitive to additive noise compared to other controllers
The flight path evaluation considering the software environment reveals that the designed robust autopilot has a successful flight path trajectory against different types of disturbance and noise, as well as it has acceptable miss-distance
Summary
The great developments in mathematics and computational capabilities facilitate the design and implementation of control. The design and analysis of an autopilot to satisfy the ever-increasing performance requirements necessitates the availability of the guided missile system model that consists of the different equations representing its spatial motion in space These equations consist of nonlinear differential equations in addition to geometrical relations and the guidance law. The main objective of this paper is to utilize the 6DOF and transfer functions obtained from previous work [8] for autopilot design using robust control and to evaluate its performance against different sources of uncertainty complemented with the HIL evaluation.
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
