| 摘要 |
There is disclosed an aircraft and method of the aircraft control. The aircraft includes a frame, a power unit, a flexible wing, which bearing part consists of keel, lateral and transverse beams, a control circuit, a control column, aircraft controls. The control circuit is made with formation of two control circuit, the control rods are interconnected by joints and connect the hingedly attached steering column with the keel beam of flexible wing with possibility to change the angle of attack of the wing, and flexible elements by one end are diametrically attached to the lateral surface of the body of rotation of control column, each flexible element is attached to the respective crossbeam of flexible wing. A control system is made in the form of kinematically connected control circuits, whereas the transfer element by one end is connected to the control system-control column, and by other end - with a keel beam, by means of which for imparting the desired pitch direction of flight the angle of attack of a flexible wing is changed. The ends of flexible transmission elements from one side between them and each other end of each flexible transmission element is connected to the respective cross beam of flexible wing. Change of the length of flexible transmission elements affects the systems: cross beams - side beams, with which the ratio of the areas of half-wing is changed relative to the longitudinal axis of the aircraft. |
