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中文摘要：
脉冲爆震火箭发动机是一种利用脉冲式爆震波产生高温、高压燃气发出的冲量来产生推力的新型推进系统。与常规液体火箭发动机相比，脉冲爆震火箭发动机具有更高的性能，并且结构更简单。本文应用特征线法给出一维爆震波在爆震管内的传播过程的解析解。对爆震波到达爆震管口后发动机的非定常排气流动过程进行了二维数值模拟，并对比了无喷管和带3种不同形式喷管（收敛喷管、收敛扩张喷管和扩张喷管）对发动机推力等性能参数的影响。
英文摘要：
A pulse detonation rocket engine （PDRE） is a new propulsion system that generates thrust by using high-temperature and high-pressure air produced by pulse detonation waves. It has better perform- ance ar：d simpler construction compared with a conventional steady state liquid rocket engine. The paper used the characteristics line method to calculate the one-dimensional detonation wave propagation process inside a detonation tube. It also conducted a two-dimensional numerical simulation of the unsteady blowdown process after the detonation wave reaches the exit of the detonation tube. Furthermore, it contrasted the influence of nozzles, convergence nozzles, convergence-divergence nozzles and divergence nozzles on the performance parameters of PDRE.
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