Volume 32 Issue 10
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Aircraft/engine performance integrated analysis on combined cycle engine[J]. Journal of Aerospace Power, 2017, 32(10): 2498-2508. doi: 10.13224/j.cnki.jasp.2017.10.024
Citation: Aircraft/engine performance integrated analysis on combined cycle engine[J]. Journal of Aerospace Power, 2017, 32(10): 2498-2508. doi: 10.13224/j.cnki.jasp.2017.10.024
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Aircraft/engine performance integrated analysis on combined cycle engine

doi: 10.13224/j.cnki.jasp.2017.10.024
  • Received Date: 2016-07-06
  • Publish Date: 2017-10-28
    Abstract
  • Two cases of combined cycle engines（case 1:turbine engine/ramjet/dual mode scramjet, case 2:turbine engine/ejector ramjet/dual mode scramjet）were comparatively studied by using aircraft/engine performance integrated analysis method. Constraint analysis and mission analysis were conducted based on a given mission of the hypersonic vehicle capable of Mach number of 65 cruise. The optimal thrust loading and wing loading satisfying the constraint were obtained, and the corresponding takeoff gross mass and sealevel takeoff thrust were further obtained. Results indicated that under the condition of completing the mission of hypersonic vehicle, case 1 had a comparable takeoff mass with case 2. The takeoff mass of case 1 was 26% lower than case 2, and the takeoff thrust of case 1 was 103% higher than case 2. Considering the stateoftheart of turbine engines, two 129kNthrust turbine engines and two 119kNthrust turbine engines were used for case1 and case 2, respectively. In addition, the takeoff mass increased shapely with the cruise distance. The takeoff masses will be about 85t for both cases when the cruise distance is 4000km.

     

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