New methods are currently being investigated to perform certification of future electric Vertical Take-Off and Landing (VTOL) aircraft. Due to the expected mission requirements, classical certification methods do not lend themselves to this type of vehicle. One aspect being investigated is a new approach to evaluate Handling Qualities (HQs) as means of compliance demonstration. The EUROCAE Working Group 112 has proposed new Flight Test Manoeuvres (FTM) that could be used for this purpose. These FTMs are scaled based on vehicle geometry. This paper presents first results obtained from a flight campaign to test a set of the proposed FTMs. The flight tests were performed with a coaxial ultralight helicopter and conducted at airport Obermehler (EDCO) in Germany. One pilot flew seven proposed FTMs. Pilot feedback and analysis of results are used to propose modifications to the FTMs.
In this paper, the Blade Element Momentum Theory (BEMT) hast been applied to setup a nonlinear model structure for a coaxial helicopter with a maximum take-off weight (MTOW) of 600kg. The model includes unknown aerodynamic parameters, which are estimated using flight test data. An extensive flight test campaign, with a fully instrumented CoAx 600 helicopter has been carried out to generate the required flight test data for parameter estimation. In this study, we use the maneuvers performed in the vicinity of the hover flight condition for system identification. The nonlinear model can be trimmed and linearized for the analysis of the system dynamics and control design. This has been done for one trim point in the study and the corresponding pole plan has been provided.
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