Pitch Autopilot Design for Agile Missiles with Uncertain Aerodynamic Coefficients

Kim Yoonsoo; Kim Byoung Soo

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Pitch Autopilot Design for Agile Missiles with Uncertain Aerodynamic Coefficients

机译：气动系数不确定的敏捷导弹的俯仰自动驾驶仪设计

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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 $H_infty$-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.

机译：这里提出的工作提出了两种针对敏捷导弹的俯仰自动驾驶仪设计，这些导弹在机动过程中会经历高俯仰角或攻角（AoA）。与高AoA有关的一个巨大挑战是，在常规风洞环境中无法精确预测空气动力学系数。为了直接解决这一挑战，建议的自动驾驶仪设计（基于积分器的反演和$ H_infty $-范数最小化）不需要精确了解此类空气动力学系数，因此具有很强的实用价值。仿真结果清楚地证明了这一实用价值。

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《Aerospace and Electronic Systems, IEEE Transactions on》 |2013年第2期|907-914|共8页
作者
Kim Yoonsoo; Kim Byoung Soo;
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Gyeongsang National University, Korea;

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正文语种 eng
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1. BTT autopilot design for agile missiles with aerodynamic uncer tainty [J] . Yueyue Ma, Jie Guo, Shengjing Tang 系统工程与电子技术（英文版） . 2015,第004期

机译：BTT自动驾驶仪设计敏捷导弹，空气动力学uncer娇小
2. Agile Missile Autopilot Design using Nonlinear Backstepping Control with Time-Delay Adaptation [J] . Chang-Hun Lee, Tae-Hun Kim, Min-Jea Tahk Transactions of the Japan society for aeronautical and space sciences . 2014,第1期

机译：时滞自适应非线性反推控制的敏捷导弹自动驾驶仪设计
3. Robust H_∞ autopilot design for agile missile with time-varying parameters [J] . Mahmood A., Kim Y., Park J. Aerospace and Electronic Systems, IEEE Transactions on . 2014,第4期

机译：具有时变参数的敏捷导弹的鲁棒H _{∞自动驾驶仪设计}
4. Autopilot design for agile missile with aerodynamic fin and side thruster [C] . Yong Seok Choi, Ho Chul Lee, Jae Weon Choi . 2003

机译：带有气动鳍和侧推力的敏捷导弹自动驾驶设计
5. A robust adaptive autopilot design for decomposed bank to turn missiles. [D] . Song, Kwang Sub. 2001

机译：一种强大的自适应自动驾驶仪设计，可用于分解银行以发射导弹。
6. Establishment of expanded and streamlined pipeline of PITCh knock-in – a web-based design tool for MMEJ-mediated gene knock-in PITCh designer and the variations of PITCh PITCh-TG and PITCh-KIKO [O] . Kazuki Nakamae, Yuki Nishimura, Mitsumasa Takenaga, 2017

机译：建立扩展和简化的PITCh敲入管道-一种基于Web的MMEJ介导的基因敲入设计工具PITCh设计器以及PITChPITCh-TG和PITCh-KIKO的变体
7. Integrated Design of Agile Missile Guidance and Autopilot Systems [O] . P. K. Menon, E. J. Ohlmeyer 2001

机译：敏捷导弹制导与自动驾驶系统的集成设计
8. Theoretical investigation of the stability at negative static margins of a supersonic missile with an autopilot sensitive to pitch angle and pitching velocity [R] . Cole, Henry, A , jr, Abramovitz, Marvin 1952

机译：具有对俯仰角和俯仰速度敏感的自动驾驶仪的超音速导弹负静态边缘稳定性的理论研究

Pitch Autopilot Design for Agile Missiles with Uncertain Aerodynamic Coefficients

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