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2011 Air Drag Effects on the Missile Trajectories
F. A. Abd El-Salam
J. Appl. Math. 2011: 1-19 (2011). DOI: 10.1155/2011/871304


The equations of motion of a missile under the air drag effects are constructed. The modified TD88 is surveyed. Using Lagrange's planetary equations in Gauss form, the perturbations, due to the air drag in the orbital elements, are computed between the eccentric anomalies of the burn out and the reentry points [ E b o , 2 π - E b o ] , respectively. The range equation is expressed as an infinite series in terms of the eccentricity e and the eccentric anomaly E. The different errors in the missile-free range due to the drag perturbations in the missile trajectory are obtained.


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F. A. Abd El-Salam. "Air Drag Effects on the Missile Trajectories." J. Appl. Math. 2011 1 - 19, 2011.


Published: 2011
First available in Project Euclid: 15 March 2012

zbMATH: 1330.70070
MathSciNet: MR2844118
Digital Object Identifier: 10.1155/2011/871304

Rights: Copyright © 2011 Hindawi


Vol.2011 • 2011
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