Output Measurement Equations for Flexible Aircraft Flight Dynamics

Grauer, Jared A ; Boucher, Matthew J

关键词: FLEXIBLE WINGS;    AERODYNAMIC STABILITY;    DYNAMIC STRUCTURAL ANALYSIS;    FLIGHT TEST INSTRUMENTS;    AIRCRAFT INSTRUMENTS;    OUTPUT;    PROVING;    EQUATIONS OF MOTION;    MATHEMATICAL MODELS;    ELASTIC DEFORMATION;    AEROELASTICITY;    AIR FLOW;    AIRSPEED;    STRAIN GAGES;    STRUCTURAL VIBRATION;   

RP-ID  :  NASA/TM-2018-220102,L-20956,NF1676L-31027

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

A summary of output measurement equations for onboard sensors used in flight testing of flexible aircraft is presented. These equations include the effects of structural flexibility and are considerably more complex than the standard equations for rigid-body aircraft. The output equations discussed include accelerations from linear accelerometers, strains, angular rates, angular accelerations, Euler angles, true airspeed, and air flow angles. The output equations are derived in full form and then simplified in some cases. Linearized output equations, suitable for state-space or transfer function models, are also developed. Example flight test data from the X-56A subscale aeroelastic demonstrator is discussed, for reference.