Load Analysis In Yaw Maneuver: Evaluating Techniques, Airspeeds, And Con-Figurations Effects On Rotorcraft Structural Design

Abstract

Yaw maneuver is one of the design limit maneuvers, which contributes to structural sizing of tail boom and aft fuselage. This paper presents a comprehensive load analysis methodology for rotorcraft yaw maneuvers. Four different simulation techniques, which are the yaw committee's recommendations, are evaluated using a consistent FLIGHTLAB-based model. Each technique is applied across a range of airspeeds and mass configurations, including full-scale variation in weight and center of gravity (CG) configurations. Results demonstrate that the most severe loading conditions occur when high sideslip angles coincide with high airspeeds, particularly for forward CG locations. Among the techniques, three are shown to produce comparable results and may be used interchangeably in load prediction studies. The analysis provides practical insights for rotorcraft design teams and supports the refinement of regulatory guidance in FAR and CS 27/29.351.