Optimal Control with Aerospace Applications by James M. Longuski José J. Guzmán & John E. Prussing

Author:James M. Longuski, José J. Guzmán & John E. Prussing
Language: eng
Format: epub
Publisher: Springer New York, New York, NY

2.If f < g, then there is insufficient thrust. The solutions for θ are in the third and fourth quadrants, corresponding to non-physical cases of falling below ground level.

7.2.2 The Optimal Trajectory

Once θ has been calculated, we solve for the state at from the integrated equations of motion, Eqs. (7.59a)–(7.59d). Thus, the optimal trajectory is given (parametrically) as:

(7.64)

for 0 ≤ t ≤ T. Equations (7.64) indicate that the rocket travels along a straight line during thrusting, given by the flight path angle γ (see Fig. 7.8).

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