Airbus Deutschland Gmbh

Airbus Operations Gmbh

Liebherr-aerospace Lindenberg Gmbh

Udo B Carl

Wolfgang Gleine

Knut Mau

Ben Holert

Marcus Gojny

Helge Sachs

Uwe Neumann

Axel Vötter

The present invention provides a device and a method for the residual analysis of a residuum to detect system errors in the system behavior of an aircraft. The device for the residual analysis of a residuum comprises an apparatus to generate the residuum at least dependent on the reference variable and the system output variable, a comparator unit to provide an analytical result by comparing the residuum to a given threshold, a first unit to provide a constant threshold portion, a second unit to provide an adaptive threshold portion at least dependent on the reference value, which can change over time, and a third unit to provide the threshold by linking the constant threshold portion to the adaptive threshold portion.

Device and method for the residual analysis of a residuum to detect system errors in the system behaviour of a system of an aircraft

The invention relates to a device for load limitation in a aircraft high lift system, said system comprising individual segments of landing flap systems and slat flap systems, and a drive unit. The inventive device for load limitation comprises a control unit that is connected to position sensors and is embodied in such a way as to process signals from the position sensors and to generate a signal for limiting the supplied drive power. The invention also relates to a method for load limitation. According to said method, signals from at least two position sensors are measured; at least one reference variable is calculated form the measured signals; each reference variable is compared with a corresponding threshold value pre-determined from a maximum authorized load; and a control signal is generated for limiting the drive power, when at least one of the reference variables reaches or exceeds the threshold value.

Method for load limiting in drive systems for aircraft high lift systems

An apparatus is described for the adjustment of horizontal stabilizers for aircraft in relation to the aircraft axis with mechanical power transmission from two drives to the horizontal stabilizer. The apparatus may include two differential transmissions coupled via a connection shaft that drive the horizontal stabilizer via a mechanical transmission, such as a respective spindle and a spindle nut.

Apparatus for the adjustment of horizontal stabilizers for aircraft

An elastically expandable hollow displacement element is secured to the rear surface of an aircraft wing slat. When the displacement element is contracted, the slat may be retracted onto the wing's leading edge. When the slat is extended, the displacement element is expanded to protrude convexly from the slat, thereby preventing vortex formation in the slat air gap and reducing aero-acoustic noise. A pressure control system for inflating and deflating the displacement element includes a bleed air line connected from the aircraft engine bleed air system to the displacement element, a shut-off valve and a pressure control valve interposed in series in the bleed air line, and a slat contour controller connected by respective signal lines to the valves, which control the quantity and the pressure of the bleed air supplied into the displacement element, for properly inflating the same.

Pressure control system for a pressure-expandable displacement element

A hollow expandable and contractible displacement element is secured onto the concave rear surface of a slat facing the leading edge of an aircraft wing. A bleed air line supplies engine bleed air into the hollow displacement element to selectively expand or contract the displacement element, which is preferably elastically expandable. When the slat is extended, the displacement element is expanded to fill-out the concave cavity on the rear surface of the slat so as to prevent formation of a vortex in the slat air gap and thereby to reduce aero-acoustic noise. When the slat is retracted, the displacement element is contracted to be conformingly accommodated in the sickle-shaped space between the slat and the leading edge of the wing.

Growing community of inventors

Hamburg, Germany

Udo B Carl