Optimal Ascent Trajectories and Feasibility of Next-Generation Orbital Spacecraft

被引：0
|
作者：
A. Miele
S. Mancuso
机构：
[1] Aero-Astronautics Group,Aerospace Sciences, and Mathematical Sciences
[2] Rice University,undefined
[3] Aero-Astronautics Group,undefined
[4] Rice University,undefined
来源：
Journal of Optimization Theory and Applications | 1998年 / 97卷
关键词：
Flight mechanics; astrodynamics; rocket-powered spacecraft; spacecraft design; single-stage-to-orbit spacecraft; two-stage-to-orbit spacecraft; optimal trajectories; ascent trajectories;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
This paper deals with the optimization of the ascent trajectories for single-stage-to-orbit (SSTO) and two-stage-to-orbit (TSTO) rocket-powered spacecraft. The maximum payload weight problem is studied for various combinations of initial thrust-to-weight ratio, engine specific impulse, and spacecraft structural factor. For TSTO rocket-powered spacecraft, two cases are studied: uniform structural factor and nonuniform structural factor between stages.
引用
收藏
页码：519 / 550
页数：31
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