Simulating a Missile flight using limited aerodynamic data by compensating with robust control

What is it about?

This study delves into the relationships between the missile aerodynamics model, two potential autopilot configurations, and the resulting closed-loop autopilot-airframe response to acceleration commands through flight simulation. The aerodynamic models are crucial since they predict the forces and moments applied to the missile throughout its flight. To save time and computational resources, the study uses multi-fidelity surrogate modeling techniques, which are simpler but may lead to some inaccuracies and instabilities. To address these potential issues, the research tests a more robust control system instead of the usual three-loop autopilot. The simulations, conducted at an altitude of 5 km and speeds of Mach 2.5 and Mach 4, showed that the robust control autopilot provided stable responses, while the traditional system was unstable under certain conditions. Future research should aim at improving these aerodynamic models and incorporating artificial intelligence to fine-tune the robust autopilot systems.

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Why is it important?

Aerodynamic forces and moments act on the vehicle throughout the flight and are the primary means of altering the velocity vector during critical phases such as target intercept. Therefore, accurate modeling of missile aerodynamics is a primary concern for simulating realistic missile trajectories. Another significant factor shaping the trajectory of a missile is the Guidance, Navigation, and Control (GNC) system, which generates acceleration commands and converts these commands into control surface deflections. In certain flight conditions, the GNC system may be able to enforce dynamic stability when the airframe is statically unstable.

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