液体火箭发动机对单级入轨运载器的影响  

EFFECT OF LIQUID ROCKET ENGINE ON THE SINGEL-STAGE-TO-ORBIT VEHICLE

作　　者：黄卫东[1] 王克昌[1] 陈启智[1] 

机构地区：[1]国防科技大学航天技术系,长沙410073

出　　处：《推进技术》1997年第6期19-22,共4页Journal of Propulsion Technology

摘　　要：对给定的飞行任务，计算了推进系统采用国外现有、改型以及新型液体火箭发动机时，主推进系统发动机的组成方式对单级入轨运载器干质量的影响。对推进系统采用改进SSME的单级入轨运载器，计算了在运载器起飞质量不变的情况下，发动机比冲和质量对运载器有效载荷的影响，以及在有效载荷不变的情况下，发动机比冲和质量对运载器子质运的影响。计算结果表明，推进系统采用双燃料双膨胀发动机的单级入轨运载器具有最小的干质量。On the assumption that the foreign existing and new liquid propellant rocket engines are adopted as propulsion system, the effects of the main proPuIsion system on the dry mass of the single-stage vehicle are calculated for a given flight mission' For the SSME-derivative engines powered single-stage vehicle, the effect of the engine specific impulse and engine mass on the payload are calculated with the fixed gross lift-off mass, and the effects of the engine specific impulse and engine mass on the vehicle dry mass are also calculated with the same paylcad. It is shown by the calculation results that the single-stage vehicle with dual-fuel, dual-expander englnes has the minimum dry mass.

关 键 词：单级入轨 液体推进剂 火箭发动机 运载器 

分 类 号：V475[航空宇航科学与技术—飞行器设计] V434