This chapter outlines the typical industrial practice for static aeroelasticity and flutter calculations. The certification requirements covering the issues are seen primarily in CS/AMC 25.629 under Subpart D, Design and Construction. The certification specifications require that the aircraft be adequately controllable over the flight envelope so that there is adequate effectiveness at the boundary of the flight envelope. There are two approaches for control effectiveness/reversal calculations. In the first approach, the structural model is fully constrained at the wing root and then an aileron control surface rotation is applied. In the second approach, the aircraft model is unconstrained and allowed to roll at a constant rate with linear downwash effects due to roll motion included. An important issue to address for an aircraft is the relationship between the ‘jig shape’ and the symmetric ‘flight shape’ that is desired at an optimal cruise flight condition.


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    Title :

    Static Aeroelasticity and Flutter


    Contributors:


    Publication date :

    2014-12-02


    Size :

    6 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English