According to the research background of high thrust nuclear thermal propulsion, a 100 ton thrust nuclear thermal rocket engine with closed cycle scheme was proposed in this paper, and the overall system parameters were calculated. The results indicated that the propellant temperature in the nuclear reactor outlet was most significant to the specific impulse of engine. When the outlet hydrogen temperature of reactor was between 2500 K and 3000 K, the vacuum specific impulse was 8000 N·s/kg to 8800 N·s/kg correspondingly. For the main power system in the space transporta-tion, the nuclear thermal rocket and chemical rocket were compared and analyzed based on the pres-ent thermal rocket engine. In addition, the trajectory and carrying capacity of the nuclear thermal rocket were simulated, and the results showed that the nuclear thermal rocket had larger carrying co-efficient than the traditional chemical rocket due to its higher specific impulse.%根据大推力核热火箭发动机的背景要求,论证提出了一种百吨推力闭式循环核热火箭发动机系统方案,完成了系统参数的分析评估,计算结果表明,反应堆出口推进剂温度显著影响发动机比冲,当反应堆出口温度在2500 K~3000 K范围时,发动机真空比冲为8000 N·s/kg~8800 N·s/kg.在此基础上,针对航天运输主动力火箭方案,对比分析了核热火箭与化学火箭的差异,评估了核热火箭弹道仿真及运载能力,结果表明,核动力火箭由于其高比冲的特性,运载系数远高于传统动力火箭.
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