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The non-minimum phase feature of tail-controlled missile airframes is analyzed.Three selection strategies for desired performance indexes are presented.An acceleration autopilot design methodology based on output feedback and optimization is proposed.Performance and robustness comparisons between the two-loop and classical three-loop topologies are made.Attempts to improve the classical three-loop topology are discussed.Despite the same open-loop structure,the classical three-loop autopilot shows distinct characteristics from a two-loop autopilot with PI compensator.Both the two-loop and three-loop topologies can stabilize a static unstable missile.However, the finite actuator resource is the crucial factor dominating autopilot function.
The non-minimum phase feature of tail-controlled missile airframes is analyzed. Three selection strategies for desired performance indexes are presented. An acceleration acceleration test design methodology based on output feedback and optimization is proposed. Performance and robustness comparisons between the two-loop and classical three-loop topologies are made. Attempts to improve the classical three-loop topology are discussed. Yet the same open-loop structure, the classical three-loop autopilot shows distinct characteristics from a two-loop autopilot with PI compensator. loop and three-loop topologies can stabilize a static unstable missile. Even though, the finite actuator resource is the crucial factor dominating autopilot function.