This paper presents a semi-empirical approach to estimate the flight dynamics and stability derivatives of in-flight morphed platforms. Morphing can be a result of either planned design choices to optimize performance during the different phases of flight, or unplanned events such as wing damage induced from MANPADS or from a midair collision. Mass, mass center, stiffness, and shape changes caused by morphing do not always allow vehicle symmetry to be preserved, therefore a new semi-empirical approach is developed that includes effects of asymmetry. This new approach, and the additional stability derivatives formulated in this research, should prove useful and must be included in the accurate evaluation of in-flight morphing vehicles and in development of flight simulations.

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