A New Analytical Approach in Determination of Nonlinear Optimal Guidance Law for Satellite Injection Mission
Publish place: The 8th Conference of Iranian Aerospace Society
Publish Year: 1388
نوع سند: مقاله کنفرانسی
زبان: English
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شناسه ملی سند علمی:
AEROSPACE08_475
تاریخ نمایه سازی: 5 شهریور 1388
Abstract:
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.
Authors
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