Device and method for increasing the aerodynamic lift of an aircraft

摘要

A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.

主权项

1. A lift arrangement for an aircraft, comprising:
an aircraft fuselage section with an outside, an aerodynamic lift body attached to the outside of the aircraft fuselage section and extending from the aircraft fuselage section outwardly, a drive means, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body, wherein the add-on bodies are connected to the drive means and are configured to be moved to a neutral position wherein the add-on bodies finish off so as to be flush with the outside of the aircraft fuselage section and to be moved to at least one activation position wherein the add-on bodies extend from the outside of the aircraft fuselage section outwardly, wherein the add-on bodies comprise an aerodynamically effective surface and are equipped in the at least one activation position with airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body, wherein the aerodynamic lift body is a moveable horizontal stabilizer attached to the aircraft fuselage section and is moveable by a trimmable horizontal stabilizer actuator, and wherein the drive means is coupled to the trimmable horizontal stabilizer actuator in such a manner that when the horizontal stabilizer is moved from a neutral position to a desired adjustment position, movement of the add-on bodies from the neutral position to the activation position takes place.