Sizing Results For Continuous And Pulse Detonation Engines

For the evaluation of the different propulsion systems, structural concept 5, VDK CURRENT, at 21.0 kg/m2 was used. The propulsion systems (Figure 4.29) were installed in the appropriate configuration concept, and sized to the mission. Figure 4.31 presents the gross weight and OWE as a function of oxidizer-to-fuel ratio, and Figure 4.32 presents the gross weight and OWE as a function of weight ratio. Each of these presentations provides different perspectives of the sizing results and the characteristics of the propulsion systems. Whenever presenting results as a function of oxidizer-to-fuel ratio, Figure 4.31, there is always the discontinuity between the rockets and the airbreathing systems. For the rocket-derived systems, the all-rocket is not the top point, but the second from the top. The air augmented rocket is heavier than the all-rocket because the thrust increase and reduced oxidizer-to-fuel ratio does not offset the weight of the ejector system. In Figure 4.32 this is clearly

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