Effect of autopilot structure on proportional navigation guidance

Qun Li Xia; Yi Ying Liu; Zai Kang Qi

Effect of autopilot structure on proportional navigation guidance

Qun Li Xia^*
, Yi Ying Liu
, Zai Kang Qi

^*此作品的通讯作者

空天科学与技术学院

Beijing Institute of Technology

科研成果: 期刊稿件 › 文章 › 同行评审

摘要

The dynamic characteristics of acceleration autopilot and attitude autopilot are discussed in detail. Also, a comparison study was made between these two different types of control schemes for guidance loop. By means of simulation, it is concluded that the guidance accuracy is mainly determined by the slowest subsystem among different system dynamics. For air-to-ground missiles, with limited terminal guidance time, the control scheme of acceleration autopilot combined with proportional navigation guidance (PNG) law is the better choice.

源语言	英语
页（从-至）	177-181
页数	5
期刊	Journal of Beijing Institute of Technology (English Edition)
卷	16
期	2
出版状态	已出版 - 6月 2007

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引用此

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title = "Effect of autopilot structure on proportional navigation guidance",

abstract = "The dynamic characteristics of acceleration autopilot and attitude autopilot are discussed in detail. Also, a comparison study was made between these two different types of control schemes for guidance loop. By means of simulation, it is concluded that the guidance accuracy is mainly determined by the slowest subsystem among different system dynamics. For air-to-ground missiles, with limited terminal guidance time, the control scheme of acceleration autopilot combined with proportional navigation guidance (PNG) law is the better choice.",

keywords = "Autopilot, Guidance accuracy, Guidance and control, Guidance law",

author = "Xia, \{Qun Li\} and Liu, \{Yi Ying\} and Qi, \{Zai Kang\}",

year = "2007",

month = jun,

language = "English",

volume = "16",

pages = "177--181",

journal = "Journal of Beijing Institute of Technology (English Edition)",

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publisher = "Beijing Institute of Technology",

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T1 - Effect of autopilot structure on proportional navigation guidance

AU - Xia, Qun Li

AU - Liu, Yi Ying

AU - Qi, Zai Kang

PY - 2007/6

Y1 - 2007/6

N2 - The dynamic characteristics of acceleration autopilot and attitude autopilot are discussed in detail. Also, a comparison study was made between these two different types of control schemes for guidance loop. By means of simulation, it is concluded that the guidance accuracy is mainly determined by the slowest subsystem among different system dynamics. For air-to-ground missiles, with limited terminal guidance time, the control scheme of acceleration autopilot combined with proportional navigation guidance (PNG) law is the better choice.

AB - The dynamic characteristics of acceleration autopilot and attitude autopilot are discussed in detail. Also, a comparison study was made between these two different types of control schemes for guidance loop. By means of simulation, it is concluded that the guidance accuracy is mainly determined by the slowest subsystem among different system dynamics. For air-to-ground missiles, with limited terminal guidance time, the control scheme of acceleration autopilot combined with proportional navigation guidance (PNG) law is the better choice.

KW - Autopilot

KW - Guidance accuracy

KW - Guidance and control

KW - Guidance law

UR - https://www.scopus.com/pages/publications/34447342535

M3 - Article

AN - SCOPUS:34447342535

SN - 1004-0579

VL - 16

SP - 177

EP - 181

JO - Journal of Beijing Institute of Technology (English Edition)

JF - Journal of Beijing Institute of Technology (English Edition)

IS - 2

ER -

Effect of autopilot structure on proportional navigation guidance

摘要

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