SSTO

Grade . sensitivity analysis of SSTO vehicle parameters

单级入轨飞行器参数灵敏度分析

Computational Study on an Aerodynamic Configuration for SSTO Vehicles

单级入轨运载器气动布局研究

Optimal Analysis of Hydrogen - Oxygen Engine for SSTO

氢氧发动机实现单级入轨的优化分析

Optimal control analysis on gradual tripropellant engine for SSTO

渐变式三组元发动机实现单级入轨的最优控制

All changed variable mixture ratio and tripropellant rocket for SSTO

变混合比及三组元发动机用于单级入轨

The parameter of tripropellants engine for SSTO is optimized on the basis of performance calculation with respect to dry mass of launcher .

针对可重复使用的天地往返运载器运载任务，以三组元发动机的性能计算、分析为基础，以运载器的结构干质量为优化目标，对三组元发动机参数进行了优化分析。

Advised on hypersonic activities for other divisions , the High Speed Civil Transport , sonic boom , ozone environment , and rocket SSTO concepts .

建议对其他部门，高速民用运输，爆音，臭氧环境，和火箭的单级入轨概念的超音速活动。

Gradual engine can meet the needs of specific impulse and density specific impulse of single stage to orbit ( SSTO ) because the propulsion combination was changed gradually .

通过对推进剂组分进行连续控制，渐变式三组元发动机能够很好地满足单级入轨对比冲和密度比冲的要求。

By using a general flight trajectory analysis method , the feasibility and characteristic of horizontal takeoff single stage to orbit ( SSTO ) vehicle with ground launch assist were shown .

采用飞行弹道分析方法，说明地面助推水平起飞单级入轨运载器方案的可行性及特点。

Domestic and international study results of staged combustion cycle engines and turbopumps of single-stage-to-orbit ( SSTO ) engines are analyzed . According to these analysis results , range limits and requirements of tripropellant turbopump performance parameters are derived .

本文通过对国内外分级燃烧循环发动机和有关单级入轨发动机涡轮泵研究结果的分析，提出了三组元涡轮泵性能参数的限制范围与要求。