지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 저널정보
- 한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.15 Number.2
- 발행연도
- 2014.6
- 수록면
- 163 - 172 (10page)
이용수
초록· 키워드
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This paper proposes a novel guidance law based on the block backstepping sliding mode control and extended state observer (ESO), which also takes into account the autopilot dynamic characteristics of the near space interceptor (NSI), and the impact angle constraint of attacking the maneuvering target . Based on the backstepping control approach, the target maneuvers and the parameter uncertainties of the autopilot are regarded as disturbances of the outer loop and inner loop, respectively. Then, the ESO is constructed to estimate the target acceleration and the inner loop disturbance, and the block backstepping sliding model guidance law is employed, based on the estimated disturbance value. Furthermore, in order to avoid the “explosion of complexity” problem, first-order low-pass filters are also introduced, to obtain differentiations of the virtual control variables. The stability of the closed-loop guidance system is also proven, based on the Lyapunov theory. Finally, simulation results demonstrate that the proposed guidance law can not only overcome the influence of the autopilot dynamic delay and target maneuvers, but also obtain a small miss distance.
목차
Abstract
1. Introduction
2. Guidance model description of the NSI
3. Guidance law design and stability analysis
4. Simulation results
5. Conclusion
References
참고문헌 (19)
참고문헌 신청
1. [학술지(정기간행물)] - Dai, J. / 2010 / Research on nearspace hypersonic weapon defense system and the key technology / Journal of the Academy of Equipment Command & Technology 21 (3) : 58 ~ 61
2. [단행본] - Zarchan, P. / 2012 / Tactical and strategic missile guidance / American Institute of Aeronautics and Astronautics
3. [단행본] - Siouris, G. / 2004 / Missile guidance and control systems / Springer-Verlag
4. [학술지(정기간행물)] - Zhang, Z. / 2013 / Composite guidance laws based on sliding mode control with impact angle constraint and autopilot lag / Transactions of the Institute of Measurement and Control 35 (6) : 764 ~ 776
5. [학술지(정기간행물)] - Qu, P. / 2013 / A dimension reduction observerbased guidance law accounting for dynamics of missile autopilot / Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227 (7) : 1114 ~ 1121
2. [단행본] - Zarchan, P. / 2012 / Tactical and strategic missile guidance / American Institute of Aeronautics and Astronautics
3. [단행본] - Siouris, G. / 2004 / Missile guidance and control systems / Springer-Verlag
4. [학술지(정기간행물)] - Zhang, Z. / 2013 / Composite guidance laws based on sliding mode control with impact angle constraint and autopilot lag / Transactions of the Institute of Measurement and Control 35 (6) : 764 ~ 776
5. [학술지(정기간행물)] - Qu, P. / 2013 / A dimension reduction observerbased guidance law accounting for dynamics of missile autopilot / Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227 (7) : 1114 ~ 1121
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UCI(KEPA) : I410-ECN-0101-2015-550-002914116