| 摘要 |
The present invention relates to a method of controlling an aircraft in flight and in particular, yet not exclusively, to a method of attenuating wake vortices that are generated behind the aircraft. The method of controlling an aircraft in flight comprises the steps of: controlling aircraft engines so as to gather desired propulsion and a predetermined speed with respect to air, and adjusting high-lift elements (2) and control surfaces so that the aircraft follows a desired trajectory. In order to prevent wake turbulences or to mitigate these turbulences so as to render them less harmful for aircrafts that follow the generating aircraft or intersect its trajectory it is suggested to determine a wake vortex parameter as a function of a spoiler setting angle, and subsequently to adjust said spoiler setting angle to an optimum (6) at which the impact of the spoilers on aircraft performance takes a minimum and takes a maximum on wake vortex parameters.
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