Assessment of engine׳s power budget for hydrogen powered hybrid buoyant aircraft

Propulsion and Power Research

Ashraf A. Omar¹  Erwin Sulaeman²  Waqar Asrar²  Anwar U. Haque²  J.S. Mohamed Ali² 

[1] Department of Aeronautical Engineering, University of Tripoli, P.O. Box 81507, Tripoli, Libya;Department of Mechanical Engineering, International Islamic University Malaysia, 50728 Kuala Lumpur, Malaysia;

关键词: Hybrid buoyant aircraft;    Ballonet׳s inflation;    Operator׳s constrains;    Engine selection;    Power budget;   

DOI  :  10.1016/j.jppr.2016.01.008

来源: DOAJ

【 摘 要 】

It is well known that hydrogen has less undesirable exhaust emissions as compared with other types of liquid fuels. It can be used as an alternative fuel for a hybrid buoyant aircraft in which half of the gross takeoff weight is balanced by the aerostatic lift. In the present study, weight advantage of liquid hydrogen as an ideal fuel has been explored for its further utilization in such aircraft. Existing relationships for the estimation of zero lift drag of airship is discussed with special focus on the utilization of such analytical relationships for the aircraft whose fuselage resembles with the hull of an airship. Taking the analytical relationship of aircraft and airship design as a reference, existing relationships for estimation of power budget are systematically re-derived for defined constraints of rate of climb, maximum velocity and takeoff ground roll. It is perceived that when the propulsion sizing for liquid hydrogen is required, then the presented framework for estimation of its power budget will provide a starting point for the analysis. An example for estimation of the power requirement is also presented as a test case.

【 授权许可】

Unknown