| 摘要 |
In order to avoid the high drag and the high weight of aircraft tail assemblies, the control and stabilisation functions are taken over by a plurality of small control vanes (which can be extended and withdrawn) having an aerofoil profile which are fitted at suitable points on the aircraft surface. Aerofoil profiles offer the best conceivable ratio of control force to drag. The magnitude of the drag is further reduced as the necessity for flightpath corrections reduces, for example flight in a low-turbulence air layer. If the control vanes are installed in pairs with opposing force effects, braking forces can be produced in a continuously variable manner by extending them simultaneously. As a rule, control vanes are controlled by an on-board computer. The manoeuvrability of the aircraft is improved. Safety questions relating to defective operation in the case of sensors, computers and control vanes are solved by redundancy. In the case of military aircraft, exiting from the aircraft using the ejector seat is simplified.
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