Patent ID: 6161801
Filing Date: 2000-12-19
Classification: B64C,G05D,Y02T

Abstract:
A method of reducing the influence of a total load acting on the wings of an aircraft, wherein said total load includes a 1 g basis load and a variable wind gust load, wherein said wings each respectively include an outer wing portion and an inner wing portion, and wherein at least one of said inner and outer wing portions of each one of said wings has a variable lift geometry, said method comprising the following steps:flying said aircraft in a climb phase from take-off up to a cruising altitude, in a cruise phase substantially at said cruising altitude, and in a descent phase from said cruising altitude down to landing,adjusting said variable lift geometry of each one of said wings to a first configuration during at least a part of said climb phase and at least a part of said descent phase,adjusting said variable lift geometry of each one of said wings to a second configuration during a majority of said cruise phase, andexpressly excluding a step of sensing a vertical acceleration of said aircraft or said wings in connection with said adjusting of said variable lift geometry,wherein said first and second configurations in comparison to each other have respective different lift distributions on said inner and outer wing portions, wherein said outer wing portions provide a relatively lower lift in said first configuration and a relatively higher lift in said second configuration, and wherein a portion of said total load acting on said outer wing portions is lower in said first configuration than in said second configuration because a portion of said 1 g basis load acting on said outer wing portions is lower in said first configuration than in said second configuration.