Design and Simulation of Guidance Law for a Kind of Flight Test Missile

Abstract:

To reduce the miss distance of flight test missile, the midcourse guidance law is studied in this paper. The nonlinear projectile dynamic model is developed at first, and then designed the midcourse guidance law with the impact point prediction information. The guidance law was designed using the difference between predicting impact point and target point. To improve the guidance law’s performance, this research inducted the predicted impact point’s velocity information and integral term into guidance law command. At the end, the simulation was developed. The results of simulation show that the guidance law designed in this study is successful and it can satisfy the test missile’s flight mission requirements.

• Periodical: Advanced Materials Research (Volumes 538-541)
• Pages: 2887-2891
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.538-541.2887
• Online since: June 2012
• Authors: Yu Qian, Xiao Jun Xiang, Jun Li Yang
• Keywords: Flight Test Missile, Guidance Law, Impact Point Prediction

References

[1] Naidu, D. S., Journal of guidance, Control, and Dynamics, Vol. 24, No. 6, 2001, p.1057–1078.

[2] Zarchan, P., Tactical and Strategic Missile Guidance, 5th ed., Vol. 219,AIAA, Reston, VA, 1997, p.281–289.

[3] Kumar, P., Dwivedi, P. N., and Bhattacharya, A., 2006 AIAA Guidance, Navigation and Control Conference and Exhibit, Keystone, CO, AIAA Paper 2006-6783, 2006.

DOI: 10.2514/mgnc06

[4] Prasiddha Nath Dwivedi,Abhijit Bhattacharya.JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS Vol. 34, No. 3, May–June (2011)

[5] Leonard C. Hainz III,Mark Costello. Atmospheric Flight Mechanics Conference and Exhibit. AIAA 2004-4711

DOI: 10.2514/6.2004-4711

[6] Leonard C. Hainz III,Mark Costello. JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS. Vol. 28, No. 5, September–October (2005)