Integrated Autopilot Guidance Based on Angular Rate Feedback Structure
Author:
Affiliation:
1. Incheon National University,Department of Mechanical Engineering,Incheon,Republic of Korea
2. Chungbuk National University,School of Mechanical Engineering,Cheongju,Republic of Korea
Funder
National Research Foundation
Publisher
IEEE
Link
http://xplorestaging.ieee.org/ielx7/9828005/9828007/09828280.pdf?arnumber=9828280
Reference7 articles.
1. Sliding-Mode Control for Integrated Missile Autopilot Guidance
2. Connections Between Linear and Nonlinear Missile Autopilots via Three-Loop Topology
3. Integrated guidance and control of dual missiles considering trade-off between input usage and response speed
4. Integrated Sliding Mode Autopilot-Guidance for Dual-Control Missiles
5. Continuous-Time Predictive Control-Based Integrated Guidance and Control
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