基于ESO的可重复使用飞行器积分滑模控制器设计

doi:10.3969/j.issn.1674-1579.2016.01.006

›› 2016, Vol. 42 ›› Issue (1): 31-36.doi: 10.3969/j.issn.1674-1579.2016.01.006

Previous Articles Next Articles

ESOBased Integral Sliding Mode Control Design for Reusable Launch Vehicle

LIU He-Long, HE Ying-Zi, LIU Gao-Tong, CHEN Shang-Shang

1.Beijing Institute of Control Engineering, Beijing 100190, China;
2.Science and Technology on Space Intelligent Control Laboratory, Beijing 100190, China;
3.Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China

Online:2016-02-20 Published:2016-03-04

Abstract

CLC Number:

TP273

LIU He-Long, HE Ying-Zi, LIU Gao-Tong, CHEN Shang-Shang. ESOBased Integral Sliding Mode Control Design for Reusable Launch Vehicle[J]., 2016, 42(1): 31-36.

0
/ / Recommend

Add to citation manager EndNote|Reference Manager|ProCite|BibTeX|RefWorks

URL: http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/10.3969/j.issn.1674-1579.2016.01.006

http://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/Y2016/V42/I1/31

［1］田栢苓．高超声速飞行器再入轨迹设计与制导控制方法研究［D］．天津大学．2011. ［2］SHTESSEL Y, HALL C, JACKSON M. Reusable launch vehicle control in multipletimescale sliding modes［J］. Journal of Guidance Control and Dynamics, 2000, 23(6):1013-1020. ［3］TIAN B, FAN W, ZONG Q, et al. Nonlinear robust control for reusable launch vehicles in reentry phase based on timevarying high order sliding mode［J］. Journal of The Franklin Institute, 2013, 350(7): 1787-1807. ［4］TIAN B, FAN W, ZONG Q. Integrated guidance and control for reusable launch vehicle in reentry phase［J］. Nonlinear Dynamics, 2015, 80(1-2): 397-412. ［5］SHAO X L, WANG H L. Active disturbance rejection based trajectory linearization control for hypersonsic reentry vehicle with bounded uncertainties［J］. ISA Transaction, 2015, 54: 27-38. ［6］SONG J, WANG L, CAI G, et al. Nonlinear fractional order proportionintegralderivative active disturbance rejection control method design for hypersonic vehicle attitude control［J］. Acta Astronautica, 2015, 111: 160-169. ［7］ZHENG Q, GAO L Q, GAO Z Q. On stability analysis of active disturbance rejection control for nonlinear timevaring plant with unknown dynamics［C］//Proceedings of the 46th IEEE Conference on Decision and Control. New York: IEEE, 2007: 3501-3506. ［8］YANG X X, HUANG Y. Capabilities of extended states observer for estimating uncertainties［C］//American Control Conference. Hyatt Regency Riverfront, 2009: 3700-3705. ［9］BAHM C, BAUMANN E, MARTIN J, et al. The X43A hyperX mach 7 flight 2 guidance, navigation and control overview and flight test results［C］//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies. Washington D.C: AIAA, 2005: 1-23. ［10］JEE G, SHARMA K K, RAO K K, et al. Evolution of attitude control law of an Indian reentry launch vehicle［J］. International Journal of Advances in Engineering Sciences and Applied Mathematics, 2014, 6(34): 148-157. ［11］TIAN B, ZONG Q. Optimal guidance for reentry vehicles based on indirect Legendre pseudospectral method［J］.Acta Astronautica, 2011,68(6):1176-1184.

[1]	LIU Zhiyong1,2, HE Yingzi1,2. Integral Sliding Mode Control with Adaptive Parameters for Flying around Slowly Rotating Target [J]. , 2009, 35(4): 22-26.
[2]	GUO Tingrong^1;2onclick="searchArc('2(1.Beijing','%e8%8b%b1%e6%96%87%e4%bd%9c%e8%80%85')"> . Variable Structure Output Feedback Control with Disturbance Compensation for Flexible Spacecraft [J]. , 2008, 34(5): 41-44.

ESOBased Integral Sliding Mode Control Design for Reusable Launch Vehicle

PDF (PC)

Like

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 2

Metrics

Comments

Recommended 0