초록 ▼

A hydraulic drive for an aircraft includes: a gear, a first hydraulic pump and a second hydraulic pump, wherein the gear is installed in a gear housing and wherein the first hydraulic pump and the second hydraulic pump in each case are installed in a pump housing that is affixed to the gear housing,

A hydraulic drive for an aircraft includes: a gear, a first hydraulic pump and a second hydraulic pump, wherein the gear is installed in a gear housing and wherein the first hydraulic pump and the second hydraulic pump in each case are installed in a pump housing that is affixed to the gear housing, or the two together are installed in a pump housing that is affixed to the gear housing; a hydraulic supply device including a first and a second hydraulic system for operating actuators of the aircraft; and a monitoring and drive device, with the hydraulic supply device including a first hydraulic drive for coupling the latter to a first engine, and a second hydraulic drive for coupling the latter to a second engine, wherein each hydraulic drive includes: a gear drive shaft for coupling the respective hydraulic drive to an engine output shaft of the respective associated engine; two hydraulic pumps that are coupled to a gear output shaft, in each case with a connection device for connecting the hydraulic pump to the pressure line and to the suction line of a hydraulic system; an aircraft comprising such a hydraulic supply device; as well as a method for configuring a hydraulic supply device.

대표청구항 ▼

1. An aircraft, comprising: a first and a second engine,an aircraft system,a fail-safe hydraulic supply device being driven by the engines and comprising a first and a second hydraulic system for operating actuators of the aircraft system and a monitoring and drive device for controlling the hydraul

1. An aircraft, comprising: a first and a second engine,an aircraft system,a fail-safe hydraulic supply device being driven by the engines and comprising a first and a second hydraulic system for operating actuators of the aircraft system and a monitoring and drive device for controlling the hydraulic supply device, the hydraulic supply device including:a first hydraulic drive that is coupled to a gear drive shaft of the first engine, the first hydraulic drive comprising: a first hydraulic pump coupled to the first hydraulic line system and having a first hydraulic-pump drive shaft coupled to the gear drive shaft of the first engine and a second hydraulic pump coupled to the second hydraulic line system and including a second hydraulic-pump drive shaft coupled to the gear drive shaft of the first engine,a gear comprising the gear drive shaft for rotary coupling to an engine output shaft of the first engine and with a gear driven shaft,a coupling device for rotary coupling of the gear driven shaft and at least a first shaft on a gear end and a second shaft on the gear end rotary coupled thereto,a clutch coupling device for rotary coupling and decoupling of the respective one of the first shaft and the second shaft on the gear end and the respective one of the first and second hydraulic-pump drive shafts of the first or second hydraulic pump, wherein the clutch coupling device comprises at least one clutch which is designed as an operable clutch, each of the first and second hydraulic pump drive shafts rotary coupled with each other and each of the first and second hydraulic pump drive shafts decoupled or coupled to the gear drive shaft of the first engine with the at least one clutch,a second hydraulic drive coupled to a second gear drive shaft of the second engine and the second hydraulic drive comprises: a first hydraulic pump coupled to the first hydraulic line system having a first hydraulic-pump drive shaft coupled to the gear drive shaft of the second engine and a second hydraulic pump coupled to the second hydraulic line system having a second hydraulic-pump drive shaft coupled to the gear drive shaft of the second engine, the first and the second hydraulic-pump drive shafts rotary coupled with each other and the first and the second hydraulic-pump drive shafts are decoupled or coupled to the gear drive shaft of the second engine by at least one clutch, andthe monitoring and drive device which respectively is coupled with the clutch coupling device and the monitoring and drive device based on a signal from a flight control function that indicates a cruising operating state outputs a command signal to switch off one of the first hydraulic pump and the second hydraulic pump of the first hydraulic drive and to switch off one of the first hydraulic pump and the second hydraulic pump of the second hydraulic drive,wherein the command signal switches off one of the first hydraulic pump and the second hydraulic pump coupled to the gear drive shaft of the first engine and one of the first hydraulic pump and the second hydraulic pump coupled to the gear drive shaft of the second engine. 2. The aircraft according to claim 1, wherein the monitoring and drive device is functionally connected to each hydraulic pump and comprises a function by means of which the monitoring and drive device can transmit a drive signal to each clutch, based on which the respective hydraulic pump is decoupled. 3. The hydraulic supply device according to claim 1, wherein the two hydraulic pumps of a hydraulic supply system, which pumps have been switched off due to the signal due to the cruising operating state, are switched on again as soon as a flight phase with increased energy requirements and safety requirements is initiated or attained. 4. The aircraft of claim 1, wherein: the first engine and the second engine are each affixed to an engine pylon; andthe first hydraulic drive is arranged on the engine pylon and behind an engine burst region of the first engine. 5. The aircraft according to claim 4, wherein the engine burst region is located at a centre of a rearmost turbine wheel of the engine and extends outward at an angle of 10 degrees creating a cone-like shape, wherein the cone is directed rearward along a longitudinal axis of the aircraft.