Nonlinear Dynamic Inversion Flight Control Design for Guided Projectiles-Reference-Cited by-同舟云学术

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Nonlinear Dynamic Inversion Flight Control Design for Guided Projectiles

Published:2020-05 Issue:5 Volume:43 Page:975-980
ISSN:1533-3884
Container-title:Journal of Guidance, Control, and Dynamics
language:en
Short-container-title:Journal of Guidance, Control, and Dynamics

Author:

Tipàn Steven¹,Theodoulis Spilios¹,Thai Sovanna¹,Proff Michael¹

Affiliation:

1. ISL, French–German Institute of Saint-Louis, 68300 Saint-Louis, France

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering

Reference11 articles.

1. Robust gain-scheduled autopilot design for spin-stabilized projectiles with a course-correction fuze

2. Observer-based adaptive sliding mode backstepping output-feedback DSC for spin-stabilized canard-controlled projectiles

3. Neural Network-Based Adaptive Control Design of Dual-Spin Projectile with Rotating Canards

4. Missile Autopilot Designs Using H8 Control with Gain Scheduling and Dynamic Inversion

Cited by 19 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Minimum-Data-Driven Guidance for Impact Angle Control;Aerospace;2024-05-08

2. Flight control design for a hypersonic waverider configuration: A non-linear model following control approach;CEAS Space Journal;2024-04-25

3. Nonlinear Model and Ballistic Impact of Body Aerodynamics for Canard Dual-Spin Aircraft;2024

4. Feedforward Compensation Enhanced Disturbance Rejection Control for a Spin-Stabilized Guided Projectile Subject to Actuator Rate Limit;Lecture Notes in Mechanical Engineering;2023-12-20

5. A guidance and control design with reduced information for a dual-spin stabilized projectile;Defence Technology;2023-07

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