Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The present disclosure related to an apparatus 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. In accordance with the present disclosure, two differential transmissions coupled via a connection shaft drive the horizontal stabilizer via mechanical transmission means such as a respective spindle and a spindle nut.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A bi-directional power conversion system interconnects hydraulic and electrical power systems on-board a vehicle such as an air-craft, whereby the power conversion system can selectively convert available electrical power to needed hydraulic power or vice versa. The power conversion system includes a hydraulic machine (15) connected to the hydraulic system (10) of the vehicle, an electrical machine (20) connected to the electrical system (3) of the vehicle through a power converter and control unit (22), a rotational drive shaft (14) mechanically interconnecting the hydraulic machine (15) and the electrical machine (20), and a priority and safety control unit (26) that controls the operation of the system.

Abstract: A fly-by-wire control system for the elevator assemblies of an aircraft is quipped with a mechanical auxiliary control (8) and with a synchronizing coupling (10). The electrical control links connecting the controlling computers to the elevator drives are each equipped with an override mechanism (4,2). A mechanical cable link (9) of the auxiliary mechanical control (8) connects a pilot operated mechanical control member such as a pitch control wheel having a detent to the respective override mechanism. This combination makes sure that the pilot initiated control signals have performance priority over any other signals at all times. The synchronizing coupling (10) is arranged between the mechanical control links leading to the respective elevator flap drives to assure a symmetric flap deflection on both sides at high speed flight under failure conditions. Centering springs (12) assure a centered position of the flap if the respective flap side signal transmission linkage (4.

Abstract: An elevator control system especially for an aircraft such as an airplane, s equipped with an electrically controllable elevator flap drive system for the elevator flap on each side of the aircraft. Additionally, the system is equipped with a mechanically controlled auxiliary drive system which is responsive to a hand wheel operated by the pilot. A single hand wheel has mechanical connecting links to the elevator flaps on both sides of the aircraft. Monitoring features enable the pilot to test the auxiliary mechanical drive system without actually switching on that system. The auxiliary mechanically operated system is functional even if all other power systems failed, since a ram air turbine is provided for generating the hydraulic pressure for driving the auxiliary system.

Abstract: A vertical rudder control and drive system for an aircraft, such as an aiane, is equipped with electrically controllable vertical rudder drive systems on each side of the aircraft. Additionally, the control system is equipped with a mechanically controllable auxiliary drive system for the operation of the vertical rudder in response to foot pedals operated by the pilot when there should be a failure in the electrically controlled drive systems. A mechanical control signal transmitting link is provided between the foot pedals and the hydro-mechanical drive for the vertical rudder. Monitoring features enable the pilot to test the mechanical drive system without actually using that system in flight. Preflight tests may be performed.