A New Analytical Approach in Determination of Nonlinear Optimal Guidance Law for Satellite Injection Mission

سال انتشار: 1388
نوع سند: مقاله کنفرانسی
زبان: انگلیسی
مشاهده: 2,549

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شناسه ملی سند علمی:

AEROSPACE08_475

تاریخ نمایه سازی: 5 شهریور 1388

چکیده مقاله:

In this paper an optimal terminal guidance approach for nonlinear injection to a final target orbit is presented to minimize control effort. This problem is formulated as an optimal control problem considering the thrust direction as a control variable. The final orbital states are expressed as terminal constraints. By considering the control effort as performance measure and using a new analytical technique the optimal trajectory and optimal control are obtained. By using the methods of calculus of variations and applying a trigonometric series for approximating the performance measure, the optimal thrust angle is determined. In the next, for computing optimal trajectory, the governing state-space equations should be transformed to a new differential equations expressing with respect to control variable. Finally by using the proposed analytical technique, the optimal trajectory and control could be obtained for injection problem in the exact form.

نویسندگان

H.H. Afshari

M.SC candidate, Aerospace Department, K.N.Toosi University OF Technology, Tehran, Iran

A. Mokhtari

Coressponding author, M.SC candidate, Aerospace Department, K.N.Toosi University OF Technology, Tehran, Iran

J. Roshanian

Associated professor, Aerospace Department, K.N.Toosi University OF Technology, Tehran, Iran

A.B. Novinzadeh

Assistant professor, Aerospace Department, K.N.Toosi University OF Technology, Tehran, Iran