This two-parts article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part B of this article explains the performance sizing of the propulsion set designed in part A. Evaluating the performance of the propulsion, computer programs are written for all major components of the both master engine and ancillary thruster. The intake, compressor, detonation process, diffusers, axial turbine, and exit nozzle are modeled under certain flight conditions, and their performances are revealed and analyzed. The flight conditions are considered from the static condition at the sea level up to flight Mach number 5 at an altitude of 20,000 m. The performance of the propulsion set is also compared with some aircraft propulsions modeled by similar studies in all important aspects.

这篇由两部分组成的文章介绍了一种基于 DEA 压缩机的新型混合推进系统。该系统包含一个脉冲爆震 TurboDEA 作为主发动机，它提供几个称为 DEAThruster 的全电动辅助推进器。该系统称为推进装置，可根据设计任务和辅助推进器的数量归类为分布式推进系统。本文的 B 部分解释了 A 部分设计的推进装置的性能大小。评估推进性能，为主发动机和辅助推进器的所有主要组件编写了计算机程序。进气、压气机、爆震过程、扩压器、轴流式涡轮和出口喷嘴在特定飞行条件下建模，并揭示和分析它们的性能。飞行条件考虑从海平面的静态条件到 20,000 m 高度的 5 马赫飞行。推进装置的性能也在所有重要方面与类似研究建模的一些飞机推进装置进行了比较。