Hostname: page-component-848d4c4894-nr4z6 Total loading time: 0 Render date: 2024-05-04T14:54:51.463Z Has data issue: false hasContentIssue false
  • English
  • Français

Coning motion stability of spinning missiles with strapdown seekers

Published online by Cambridge University Press:  04 July 2016

S. He ,
D. Lin  and
J. Wang
S. He*
Affiliation:
School of Aerospace Engineering, Beijing Institute of Technology, BeijingP.R. China
D. Lin
Affiliation:
School of Aerospace Engineering, Beijing Institute of Technology, BeijingP.R. China
J. Wang
Affiliation:
School of Aerospace Engineering, Beijing Institute of Technology, BeijingP.R. China
*
shaoming.he.cn@gmail.com
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper investigates the problem of coning motion stability of spinning missiles equipped with strapdown seekers. During model derivation, it is found that the scaling factor error between the strapdown seeker and the onboard gyro introduces an undesired parasitic loop in the guidance system and, therefore, results in stability issues. Through stability analysis, a sufficient and necessary condition for the stability of spinning missiles with strapdown seekers is proposed analytically. Theoretical and numerical results reveal that the scaling factor error, spinning rate and navigation ratio play important roles in stable regions of the guidance system. Consequently, autopilot gains must be checked carefully to satisfy the stability conditions.

Keywords

Spinning MissileConing Motion StabilityStrapdown SeekerScaling Factor Error
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1232 , October 2016 , pp. 1566 - 1577
Copyright
Copyright © Royal Aeronautical Society 2016 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

1. Park, B.G., Kim, T.H. and Tahk, M.J. Optimal impact angle control guidance law considering the seeker's field-of-view limits, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2013, 227 (8), pp 1347–1364.Google Scholar
2. Kim, D., Ryoo, C.K., Kim, Y. and Kim, J. Guidance and control for missiles with a strapdown seeker, Proceedings of International Conference on Control, Automation and Systems (ICCAS), 2011, Gyeonggi-do, Korea, pp 969-972.Google Scholar
3. Willman, W.W. Effects of strapdown seeker scale-factor uncertainty on optimal guidance, J Guidance, Control, and Dynamics, 1988, 11 (3), pp 199–206.Google Scholar
4. Jang, S.A., Ryoo, C.K., Choi, K. and Tahk, M.J. Guidance algorithms for tactical missiles with strapdown seeker, Proceedings of SICE Annual Conference, the University Electro-Communications, 2008, Japan, pp 2616-2619.Google Scholar
5. Yun, J., Ryoo, C.K. and Song, T.L. Strapdown sensors and seeker based guidance filter design, Proceedings of International Conference on Control, Automation and Systems (ICCAS), 2008, Seoul, Korea, pp 468-472.Google Scholar
6. Kuhn, G.D., Nielsen, J.N. and Spangler, S.B. Theoretical study of vortex shedding from bodies of revolution undergoing coning motion, NASA Contractor Report, Nielson Engineering and Research Inc., Report number NEAR TR-14, 1969.Google Scholar
7. Platus, D.H. Missile and spacecraft coning instabilities, J Guidance, Control, and Dynamics, 1994, 17 (5), pp 1011–1018.Google Scholar
8. Murphy, C.H. Symmetric missile dynamic instabilities, J Guidance, Control, and Dynamics, 1981, 4 (5), pp 464–471.CrossRefGoogle Scholar
9. Liaño, G. and Morote, J. Roll-rate stability limits of unguided rockets with wraparound fins, J Spacecraft and Rockets, 2006, 43 (4), pp 757–761.CrossRefGoogle Scholar
10. Pechier, M., Guillen, P. and Cayzac, R. Magnus effect over finned projectiles, J Spacecraft and Rockets, 2001, 38 (4), pp 542–549.Google Scholar
11. Mao, X., Yang, S. and Xu, Y. Coning motion stability of wrap around fin rockets, Science in China Series E: Technological Sciences, 2007, 50 (3), pp 343–350.Google Scholar
12. Zhou, W., Yang, S. and Dong, J. Coning motion instability of spinning missiles induced by hinge moment, Aerospace Science and Technology, 2013, 30 (1), pp 239–245.Google Scholar
13. Koohmaskan, Y., Arvan, M.R., Vali, A.R. and Behazin, F. Dynamic stability conditions for a rolling flight vehicle applying continuous actuator, Aerospace Science and Technology, 2015, 42, pp 451–458.Google Scholar
14. Yan, X., Yang, S. and Zhang, C. Coning motion of spinning missiles induced by the rate loop, J Guidance, Control, and Dynamics, 2010, 33 (5), pp 1490–1499.CrossRefGoogle Scholar
15. Yan, X., Yang, S. and Xiong, F. Stability limits of spinning missiles with attitude autopilot, J Guidance, Control, and Dynamics, 2011, 34 (1), 278–283.CrossRefGoogle Scholar
16. Li, K., Yang, S. and Zhao, L. Stability of spinning missiles with an acceleration autopilot, J Guidance, Control, and Dynamics, 2012, 35 (3), 774–786.Google Scholar
17. Li, K., Yang, S. and Zhao, L. Three-loop autopilot of spinning missiles, Proceedings of the Institution of Mechanical Engineers, Part G: J of Aerospace Engineering, 2014, 228 (7), pp 1195–1201.CrossRefGoogle Scholar
18. Zipfel, P.H. Modeling and Simulation of Aerospace Vehicle Dynamics, 2nd ed., American Institute of Aeronautics and Astronautics, 2007, Reston, Virginia, US.Google Scholar
19. Zarchan, P. Tactical and Strategic Missile Guidance, 5th ed., American Institute of Aeronautics and Astronautics, 2007, Reston, Virginia, US.Google Scholar