Numerical Analysis of Porpoising Stability Limit of a Blended-Wing–Body Aircraft During Ditching

Abstract

The ditching processes of a blended-wing–body (BWB) aircraft under different initial speeds and pitch angles are simulated by numerically solving the unsteady Reynolds-averaged Navier–Stokes equations and the realizable [Formula: see text] turbulence model using the finite volume method. The volume-of-fluid model is adopted to capture the water–air interface. The six-degree-of-freedom model is employed to couple fluid dynamics and aircraft rigid-body kinematics. The global moving mesh is used to deal with the relative motion between the aircraft and the water. It is found that the plane composed of initial speed and pitch angle can be divided into two regions by a stability limit line, that is, the porpoising motion region (the aircraft takes coupled oscillatory motion between heaving and pitching) with large initial speeds and pitch angles and the stable motion region with low initial speeds and pitch angles. When the initial speed is large, the aircraft’s pitch-up moment peak and heaving amplitude are enhanced. Hence the aircraft carries out the porpoising motion. For the large initial pitch angle, the water entry depth of the aircraft increases and the waterline moves forward, which produces a more significant pitch-up moment peak and overload peak. As a result, the aircraft conducts the porpoising motion. The porpoising stability of the BWB configuration is obviously worse than the conventional and flying wing configurations. When the BWB aircraft ditches on water, the pilots should reduce the initial speed and pitch angle as much as possible to avoid the dangerous porpoising motion.

Numerical Simulations of Seaplane Ditching on Calm Water and Uniform Water Current Coupled with Wind

“…Bouncing phenomena were observed when the seaplane landed on the wave. Zheng et al [16] studied the motion of porpoising and the stability of a blended wing body plane ditching on water, which can be caused by a higher initial speed or pitch angle before slamming. The performance of a fixedwing multi-rotor Unmanned Aerial Vehicle (UAV) with different control parameters was parametrically studied by Benmoussa and Gamboa [17].…”