Aerodynamic Simulation and Control Analysis of an Aircraft Emergency Tailplane System

This study proposes an improved solution to the issue of aircraft tailplane elevator jamming by designing a spare tail wing system. This system incorporates a deployable, foldable spare tail wing that can be extended in emergency situations, offering additional pitch moment to the aircraft, thus providing supplementary pitch control. Both tailplanes utilize the classic NACA0012 airfoil, with the Spalart-Allmaras turbulence model employed, and a free-stream Mach number of 0.6. Fluid simulations of the tailplane system were conducted under conditions of horizontal tailplane jamming using a dynamic mesh approach. The results demonstrate that the deployment and deflection of the spare tail wing to an optimal angle can generate additional pitch moment, effectively mitigating the loss of control caused by horizontal tailplane failures.