Review of Design Load Situation,
MESSERSCHMITT-BOELKOW-BLOHM G M B H MUNICH (GERMANY F R)
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The philosophy of the relevant design requirements and the essential load parameters for the manoeuvre load conditions, including the determination of the control displacements from MIL-A-8861 to MIL-A-008861 A is reviewed. These MIL-specifications have been applied firstly to an airplane with mechanical flight controls and secondly with a fly-by-wire system that has control laws integrated. After discussion of various influences due to damping modes on control input and on feedback of response parameters, some results for an aircraft with a Control and Stability Augmentation System are shown. Finally, an active controlled aircraft configuration is evaluated. To present an approach to a design load analysis, the time histories of control displacements have been varied.