초록 ▼

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

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.

대표청구항 ▼

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, anda pair of movably held add-on bodies arranged

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, anda 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, andwherein 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. 2. The lift arrangement of claim 1, wherein the aerodynamic lift body is a tail unit. 3. The lift arrangement of claim 1, wherein the aerodynamic lift body is a wing assembly. 4. The lift arrangement of claim 1, wherein the add-on bodies form a gap to the aerodynamic lift body. 5. The lift arrangement of claim 1, wherein the add-on bodies are arranged on a leading edge of the aerodynamic lift body. 6. The lift arrangement of claim 5, wherein the add-on bodies are held at a leading edge of the aerodynamic lift body and are rotatable on the leading edge of the aerodynamic lift body. 7. The lift arrangement of claim 1, wherein the aerodynamic lift body is at least in some sections held so as to be pivotable on an axis at least partly extending radially to the aircraft fuselage section. 8. The lift arrangement of claim 1, wherein each add-on body comprises a shape selected from a group of geometric shapes, with the group consisting of: a triangular shape,an ogival shape,a delta plan view with a polynomial leading edge,a delta plan view with a leading edge in the shape of a partial circular arc,a partial circular arc, andany combination of these geometric shapes. 9. The lift arrangement of claim 1, wherein the drive means is coupled to the trimmable horizontal stabilizer actuator by a mechanical push rod assembly. 10. The lift arrangement of claim 1, wherein the add-on body in a neutral position of the add-on body extends from an outside of the aircraft fuselage section into the aircraft fuselage section. 11. The lift arrangement of claim 1, wherein the add-on body in a neutral position of the add-on body conforms to the aircraft fuselage section so as to be flush on the surface. 12. The lift arrangement of claim 11, wherein the aircraft fuselage section comprises an indentation for accommodating the add-on body. 13. An aircraft, comprising an aircraft fuselage with at least one lift arrangement 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, anda 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 means of a trimmable horizontal stabilizer actuator, andwherein 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 at least one activation position takes place.