Pitch Autopilot Design for Agile Missiles with Uncertain Aerodynamic Coefficients
Pitch Autopilot Design for Agile Missiles with Uncertain Aerodynamic Coefficients
- New search for: Yoonsoo Kim,
- New search for: Byoung Soo Kim,
- New search for: Yoonsoo Kim,
- New search for: Byoung Soo Kim,
The work presented here proposes two pitch autopilot designs for agile missiles which experience high pitch angles or angles of attack (AoA) during their manoeuvres. One great challenge pertaining to high AoA is that aerodynamic coefficients cannot be precisely predicted in a conventional wind tunnel environment. To directly address this challenge, the proposed autopilot designs (based on the integrator backstepping and H∞-norm minimization) do not require precise knowledge of such aerodynamic coefficients and so has a strong practical merit. Simulation results clearly testify this practical merit.
Document information
Pitch Autopilot Design for Agile Missiles with Uncertain Aerodynamic Coefficients
IEEE Transactions on Aerospace and Electronic Systems ; 49 , 2 ; 907-914
2013-04-01
2011288 byte
Article (Journal)
Electronic Resource
English
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