Stability derivatives

Flight Dynamics

Published in James DeLaurier, Aircraft Design Concepts, 2022

The crux of an aircraft's flight-dynamic analysis is the determination of the stability derivatives. The described methodologies are generally based upon the individual contributions of the components, which are then added together, accounting for mutual interference factors. This is similar to what was described in Chapter 2 for the derivation of the aircraft's static lift, drag and pitching-moment equations.

Integrated multiple-model adaptive fault identification and reconfigurable fault-tolerant control for Lead-Wing close formation systems

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Journal Information

Published in International Journal of Systems Science, 2018

Chun Liu, Bin Jiang, Ke Zhang

Here, the new stability derivatives and of changes in Wing’s drag, lift and side force resulting from perturbations need to be determined for the Mach hold, Heading hold, and Altitude hold autopilot, respectively (Pachter et al., 2001). where and are lift coefficient of Lead and Wing UAV. and are the nominal locations in the formation geometry. aw and avt denote the lift curve slope of the wing and vertical tail, respectively. AR represents the aspect ratio of wing, η represents the aerodynamic efficiency factor of the tail, S denotes the surface area of elliptical wing, Svt denotes the area of vertical tail, b denotes the wing span, and hz denotes the height of the vertical tail. μ2 is the dimensionless correction in order to take the effects of physical viscosity into consideration and to make the mathematical deduction more precisely conform to the practical situation. It can be obviously calculated that the stability derivatives of and on x direction are zero.

Stability derivatives

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Flight Dynamics

Integrated multiple-model adaptive fault identification and reconfigurable fault-tolerant control for Lead-Wing close formation systems