High-altitude long-endurance (HALE) unmanned aerial vehicles (UAVs) are used for high flight altitudes, which enable low drag and fast flight with minimal fuel consumption. Two-stage turbocharging is necessary to sustain sea-level power at high flight altitudes. In this study, the limitations of two-stage turbocharging at high flight altitudes typical for HALE UAVs are analyzed for the first time. The obtained results show that the minimum available engine power increases as the altitude rises. This will limit the ability of the aircraft to descend rapidly. Furthermore, at high altitudes, if a lower operating point is required for a fast descent, further recovery to full power for climbing or cruising could be unavailable. In the latter cases, a lower altitude must be reached before full power would be available again. A basic algorithm for the assessment and analysis of the limitations of UAV engines with two-stage turbochargers operating at high altitudes is suggested.


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    Title :

    Limitations of Two-Stage Turbocharging at High Flight Altitudes


    Additional title:

    Sae Int. J. Engines


    Contributors:

    Published in:

    Publication date :

    2018-09-17


    Size :

    14 pages




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Two-stage turbocharging

    Mueller,R. / BBC,Baden,CH | Automotive engineering | 1978


    Two-stage turbocharging

    Meier, E. | Engineering Index Backfile | 1965



    Two-Stage Turbocharging

    Muller,R. / BBC,Baden,CH | Automotive engineering | 1978