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Air drag effects on the missile trajectories
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نویسنده
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abd el-salam f.a.
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منبع
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journal of applied mathematics - 2011 - دوره : 2011 - شماره : 0
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چکیده
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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 bo,2π - e bo],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. © copyright 2011 f. a. abd el-salam.
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آدرس
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department of mathematics,faculty of science,taibah university,al-madinah al-munawarah,saudi arabia,department of astronomy,faculty of science,cairo university, Egypt
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Authors
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