近期以來，脈衝爆震引擎（PDE）被認為是有發展性的推進技術，其在熱力循環效率，結構的簡單性和操作使用的可擴展性方面具有潛在的優勢。本文目的為針對實際應用較少的爆震引擎進行文獻的回顧與整理，並且建構基礎的模擬模型以利日後發展其相關的分析與評估。在數值模擬的部分，我們探討了三個不同計算模型所產生的不同差異性以及引擎內部的大致流體特性，其模型分別為利用不同算則計算之無黏性的冷流以及無黏性氫氧燃燒化學反應模型。以上模型皆能成功模擬出相似的物理現象，並在之後的研究加以應用。

The Pulse Detonation Engine (PDE) has been considered a developmental propulsion technology with advantages in thermal efficiency, simple in structure, and widely of operational application. The purpose of this paper is to review the literature for a detonation engine, and to construct a basic simulation model to facilitate the development of its analysis and evaluation. In the numerical simulation, we used the different variations of the three different computational models to simulate the approximate fluid properties inside the engine. The models are the inviscid cold flow with two different scheme and the first-order inviscid chemical reaction model. All of the above models can successfully simulate mostly physical phenomena and apply them in later studies.

Nomenclature	v
List of Figure	vi
1. Introduction	1
1.1. Background	1
1.3. Literature Review	6
1.4. Cycle Operation of PDE	15
1.4.1 Filling Process	16
1.4.2 Detonation Process	17
1.4.3 Purging Process	17
1.4.4 Rarefaction or Blowdown Process	18
1.5. Detonation Theory	18
1.5.2 ZND Model	34
2. Governing Equation	39
3. Numerical Results	40
3.1 The Numerical Results	45
3.2. Enlarged View	53
3.2.1 Nozzle	53
3.2.2 Throat	55
3.3. Distributions along Centerline	57
3.5 Result Discussion	58
4. Conclusions	62
5. Future Works	63
6. References	64
Figure 1.1 Specific impulse vs. Mach number regimes of various propulsion systems (Ma, 2008)	3
Figure1.2 Comparsion of PDEs with other engines (Ma, 2008)	5
Figure 1.3 Cycle Operation of PDE (Ma, 2008)	16
Figure 1.5 Schematic of Rayleigh lines and Hugoniot curve (Lee, 2008)	20
Figure 1.4 Steady planar detonation wave in a tube (Ma, 2008)	21
Figure 1.6 Schematic of pressure profile for a ZND detonation propagation in a tube (Ma, 2008)	34
Figure 1.7 Comprparison of Brayton and Humphrey cycle	35
Figure 3.1 Geometry (Ma, 2008)	41
Figure 3.2 Time evolution of Mach number field during the first cycle of operation. (Ma, 2008)	42
Figure 3.3 Time evolution of and density-gradient field during the first cycle of operation. (Ma, 2008)	43
Figure3.4 Time evolution of Mach number field and density-gradient field during the first cycle of operation. At t=1.33ms, 1.59 ms, 1.84ms, 2.25 ms, 3.08 ms, 3.83ms.	47
Figure3.5 Time evolution of Mach number field and density-gradient field during the first cycle of operation. At t= 0.6ms, 0.67ms, 0.8ms, 0.94ms, 1.22ms, 1.68ms.	50
Figure3.7 Enlarged views of pressure contour by CE/SE at 0.65 ms (2003, Ma)	53
Figure3.8 Enlarged views of cold flow pressure contour by AUSMD at time= 1.92ms	53
Figure3.9 Enlarged views of cold flow pressure contour by Fluent at time= 0.81ms	54
Figure3.10 Enlarged views of inviscid chemical reaction flow pressure contour by Fluent at time= 0.59ms	54
Figure3.11 Enlarged views of pressure contour by CE/SE (2003, Ma)	55
Figure3.12 Enlarged views of cold flow pressure contour by AUSMD at time= 1.44ms	55
Figure3.13 Enlarged views of cold flow pressure contour by Fluent at time= 0.62ms	56
Figure3.14 Enlarged views of inviscid chemical reaction flow pressure contour by Fluent at time= 0.44ms	56
Figure 3.15 Case cold flow (left) and chemical reaction (right) pressure and Mach number distributions along centerline during first cycle of operation at t=0.67 ms	57
Figure 3.16 Case cold flow (left) and chemical reaction (right) pressure and Mach number distributions along centerline during first cycle of operation at t=0.96 ms	57
Figure 3.17 Case cold flow (left) and chemical reaction (right) pressure and Mach number distributions along centerline during first cycle of operation at t=1.18 ms	58
Figure 3.18. Effect of valve close-up time on specific impulse	62

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