Guidance Law for Near Space Interceptor based on Block Backstepping Sliding Mode and Extended State Observer

다국어 초록 (Multilingual Abstract)

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 (Table of Contents)

• Abstract
• 1. Introduction
• 2. Guidance model description of the NSI
• 3. Guidance law design and stability analysis
• 4. Simulation results
• 5. Conclusion
• References

참고문헌 (Reference)

1 Zhou, D., "laws with finite time convergence" 32 (32): 1838-1846, 2009

2 Zhang, Z., "Terminal guidance laws of missile based on ISMC and NDOB with impact angle constraint" 31 (31): 30-41, 2013

3 Zarchan, P., "Tactical and strategic missile guidance" American Institute of Aeronautics and Astronautics 2012

4 Liu, H., "Speed control for PMSM servo system using predictive functional control and extended state observer" 59 (59): 1171-1183, 2012

5 Sun, S., "Sliding mode guidance law with autopilot lag for terminal angle constrained trajectories" 34 (34): 69-78, 2013

6 Dai, J., "Research on nearspace hypersonic weapon defense system and the key technology" 21 (21): 58-61, 2010

7 Chen, B., "Nonlinear fuzzy H∞ guidance law with saturation of actuators against maneuvering targets" 10 (10): 769-779, 2002

8 Yang, C., "Nonlinear H∞ guidance law for homing missiles" 21 (21): 882-890, 1998

9 Zhou, D., "New guidance laws for homing missile" National Defense Industry Press 2002

10 Siouris, G., "Missile guidance and control systems" Springer-Verlag 2004

11 Li, S., "Generalized extended state observer based control for systems with mismatched uncertainties" 59 (59): 4792-4892, 2012

12 Swaroop, D., "Dynamic surface control for a class of nonlinear systems" 45 (45): 1893-1899, 2000

13 Xia, Y., "Compound control methodology for flight vehicles" Springer Science Business Media 2013

14 Zhang, Z., "Composite guidance laws based on sliding mode control with impact angle constraint and autopilot lag" 35 (35): 764-776, 2013

15 Hou, M., "Adaptive block dynamic surface control for integrated missile guidance and autopilot" 26 (26): 741-750, 2013

16 Han, J., "Active disturbance rejection control technique--the technique for estimating and compensating the uncertainties" National Defense Industry Press 2008

17 Qu, P., "A dimension reduction observerbased guidance law accounting for dynamics of missile autopilot" 227 (227): 1114-1121, 2013