Coning motion instability of spinning missiles induced by the delay of strap-down seeker
Author:
Funder
National Natural Science Foundation of China
Publisher
Elsevier BV
Subject
Mechanical Engineering,Aerospace Engineering
Reference23 articles.
1. Control failure of the roll-isolated inertial navigation system under large pitch angle[J];Song;Chinese J Aero,2020
2. Angular motion of a Re-entering symmetric missile;Murphy;AIAA J,1965
3. Murphy CH. Free flight motion of symmetric missiles. Aberdeen Proving Ground. MD: Ballistic Research Lab; 1963. Report No.: 1216.
4. Stability of spinning missile with homing proportional guidance law;Hu;Aerosp Sci Technol,2017
5. Coning motion of spinning missiles induced by the rate loop;Yan;J Guid Control Dyn,2010
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1. Stability of Single-Channel Homing Rolling Aerospace Vehicle;Aerospace;2024-08-12
2. Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot;Asian Journal of Control;2022-07-10
3. Dynamic Estimation and Compensation of Time Delay for Missiles with Strapdown Seeker;Journal of Guidance, Control, and Dynamics;2021-11-22
4. Coupling analysis and dynamic stability boundary of spinning missiles considering actuator dynamics and autopilot;Aerospace Science and Technology;2021-04
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