The invention discloses an aircraft tail. According to the technical scheme, for a vertically taking-off and landing fixed-wing aircraft of Application No. 2015203521439, the aircraft tail aims at reducing resistance during rotary flight, accurately adjusting a aircraft landing point and adjusting the aircraft stability during rotary takeoff and landing. The aircraft tail consists of a full-automatic vertical tail, a full-automatic vertical tail strengthening beam or full-automatic vertical tail strengthening sheet, a full-automatic vertical tail rotation shaft, a full-automatic vertical tail server, an auxiliary horizontal tail, an auxiliary horizontal tail rotation shaft and an auxiliary horizontal tail server, wherein the full-automatic vertical tail can have a function of performing forward and reverse 180-degree rotation around the straight line parallel to the vertical axis of the aircraft under the control of the full-automatic vertical tail server, and the auxiliary horizontal tail can have a function of performing forward and reverse 90-degree rotation around the straight line parallel to the longitudinal axis of the aircraft under the control of the auxiliary horizontal tail server.
Aircraft tail
09.12.2015
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Aircraft tail and aircraft comprising such aircraft tail
Europäisches Patentamt | 2024
|SAE Technical Papers | 1984