The flap rudder layout for enhancing the rolling-control capability of a hypersonic aircraft is a layout form applied to a spherical-conical-cylindrical axisymmetric hypersonic aircraft, and the aircraft obtains a control moment through flap rudder deflection so as to control the flight attitude. The flap rudder is designed into a flat plate structure and is mounted at the bottom of the aircraft through a rudder shaft. The designed installation angle of the flap type rudder remarkably improves the rolling-control capacity of the aircraft, and effective distribution of pitching, yawing and rolling control efficiency of the aircraft is achieved.
一种增强高超声速飞行器滚控能力的襟翼舵布局,是应用在球‑锥‑柱型轴对称高超声速飞行器上的布局形式,飞行器通过襟翼舵偏转获得控制力矩,从而控制飞行姿态。襟翼舵设计为平板构型,通过舵轴安装于飞行器底部。襟翼舵设计安装角显著提升了飞行器的滚转控制能力,且实现了对飞行器俯仰、偏航和滚转控制效率的有效分配。
Flap rudder layout for enhancing rolling-control capability of hypersonic aircraft
一种增强高超声速飞行器滚控能力的襟翼舵布局
2020-09-25
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung |
Aerial rudder active cooling system of hypersonic aircraft
European Patent Office | 2025
|Tema Archive | 1986
Heatproof device for leading edge of rudder (wing) of hypersonic aircraft
European Patent Office | 2024
|