Balancing an Aircraft With Symmetrically Deflected Split Elevator and Rudder During Short Landing Run

Abstract

This article investigates methods for balancing aircraft during short straight-line landing run realized by employing split rudder and elevator as air-brakes after touchdown. For standard atmospheric and runway conditions, directional and longitudinal balance equations for aircraft of conventional configuration such as Il-86 are presented. Methods depend on operational and mechanical approaches, where the first requires manual or automatic trim of shortly peaking small pitching, yawing, and rolling moments using dynamic forces while the second suggest some re-design of elevator and rudder control channels to limit deflection angles. The paper describes in detail each method disadvantages and suggests the adoption of automatic operational approach due to less required system modifications and piloting skills.

Viewing electromagnetic scattering characteristics on air-brake of a stealth plane

“…The tailless aircraft has a flatter shape design, and the stealth effect caused by the opening air brake may be amplified (Zhou and Huang, 2021; Jiao et al , 2017; Zuo and Wang, 2010). For control surfaces such as split rudder, the panels opened up and down will form a more complex dihedral angle structure (Zuhair, 2019; Arunachaleswaran et al , 2020; Yao et al , 2017). Some advanced helicopters or unmanned helicopters use active trailing edges and other control surfaces to change the pulling force of the rotor blades (Konar et al , 2020).…”