The system comprises a main wing (3) with deflected flap (5), a blowing arrangement (1) with a number of nozzles located in front of the deflected flap (5) along the trailing edge of the main wing (3), static pressure sensors (4) fastened to the deflected flap (5), flight sensors (7) for measuring aircraft flight parameters, activating device for activating the blowing arrangement (1), and a control unit (6) connected to the sensors and activating device. The each nozzle is in the form of triple mini nozzle (2) with one inlet channel (10), streamlined collection chamber (9) and three outlet channels (11). wherein the outlet openings of the outlet channels (11) are located on the trailing edge of the main wing (3) above the axis of rotation of the flap (5) and the static pressure sensors (4) are located on the upper surface of the deflected flap (5), close to the flap trailing edge.
Autonomous active flow control system
Autonomes aktives Flusssteuerungssystem
Système de commande de flux actif autonome
2015-12-16
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
ACTIVE SEATING SYSTEM CONTROL BY AN AUTONOMOUS VEHICLE
Europäisches Patentamt | 2024
|