Hydraulic system, hydraulic device, aircraft, aircraft device and method for testing hydraulic system

Abstract

The invention relates to a hydraulic system, a hydraulic device, an aircraft, an aircraft device and a method for testing a hydraulic system. In one aspect, the invention provides a hydraulic system (14) for incorporation in an aircraft (10) and for supplying hydraulic power to one or more hydraulic components (16) of the aircraft (10) by means of an operating fluid, the hydraulic system (14) comprises system pumping means (26) for introducing an operating fluid from a system inlet (24) of the hydraulic system (14) and for pumping the operating fluid into the hydraulic system (14).

Description

Technical Field

[0001] The invention relates to a hydraulic system for incorporation in an aircraft. The invention also relates to a hydraulic device, an aircraft, an aircraft device and a method for testing such a hydraulic system. Background Art

[0002] Conventional ground maintenance concepts for hydraulic systems rely on the use of airport-based ground support equipment, such as hydraulic ground vehicles. The procurement, logistics and use of these ground vehicles are very important to airport operators. Maintenance personnel are often required to maintain ground vehicles and intervene during certain maintenance procedures. During common maintenance of ground vehicles, hydraulic pumps and their controllers may be replaced. Different procedures can be used to manually perform further maintenance tasks. However, if there is no ground vehicle available at the location of the aircraft, delays may result. Summary of the invention

[0003] It is an object of the present invention to provide an improved or alternative method for testing or maintaining a hydraulic system for an aircraft.

[0004] To achieve this object, the invention provides a hydraulic system integrated in an aircraft according to a first main aspect of the application. A hydraulic device, an aircraft, an aircraft device and a method for testing such a hydraulic system are the subject of the concurrent main aspects of the application.

[0005] Advantageous embodiments of the invention are the subject matter of dependent aspects of the present application.

[0006] In one aspect, the present invention provides a hydraulic system for incorporation in an aircraft and for supplying hydraulic power to one or more hydraulic components of the aircraft with the aid of an operating fluid, the hydraulic system comprising a system pumping device for introducing the operating fluid from a system inlet of the hydraulic system and for pumping the operating fluid into the hydraulic system.

[0007] Preferably, the system pumping device is configured for introducing and pumping operating fluid at a variable pressure and / or flow rate within the hydraulic system.

[0008] Preferably, the hydraulic system further comprises control means for controlling the pressure and / or flow inside the hydraulic system by means of the system pumping means in the test mode.

[0009] Preferably, the hydraulic system further comprises a system degassing device for releasing gas from inside the hydraulic system.

[0010] Preferably, the hydraulic system further comprises a fluid filtering device for filtering the operating fluid inside the hydraulic system.

[0011] Preferably, the hydraulic system is configured for pumping the operating fluid to a system outlet of the hydraulic system and for draining the operating fluid from the hydraulic system.

[0012] In another aspect, the present invention provides a hydraulic device comprising a hydraulic system according to any of the preceding embodiments and a hose for conveying an operating fluid and for connecting to a system inlet and / or a system outlet of the hydraulic system.

[0013] Preferably, the hose comprises hose pumping means for pumping the operating fluid to the system pumping means when the hose is connected to the system inlet.

[0014] Preferably, the hydraulic device further comprises a removable reservoir for the operating fluid, the hose being configured for fluidly connecting the removable reservoir with a system inlet and / or a system outlet of the hydraulic system.

[0015] In another aspect, the invention provides an aircraft comprising a hydraulic system according to a combination of any of the preceding embodiments.

[0016] In another aspect, the invention provides an aircraft device comprising a hydraulic device according to any of the preceding embodiments and an aircraft, the hydraulic system of the hydraulic device being integrated in the aircraft.

[0017] In another aspect, the invention provides a method for testing a hydraulic system, the hydraulic system being incorporated in an aircraft and being used to supply hydraulic power to one or more hydraulic components of the aircraft by means of an operating fluid, the method comprising:

[0018] a) providing a removable reservoir for containing the operating fluid;

[0019] b) fluidly connecting the removable reservoir to a system inlet of the hydraulic system; and

[0020] c) Introducing the operating fluid from a system inlet of the hydraulic system through the hydraulic system and pumping the operating fluid into the hydraulic system.

[0021] Some aspects of preferred embodiments of the present invention can be summarized as follows:

[0022] The concept of the preferred embodiment of the present invention is to replace hydraulic ground support equipment, such as hydraulic ground vehicles, at an airport, final assembly line (FAL) and / or maintenance hangar. The preferred embodiment utilizes a motor pump unit mounted on the aircraft and corresponding controls and monitors. With this enhanced functionality of the aircraft hydraulic system, external devices may not be required and the task is automated, which can result in reduced maintenance time and costs.

[0023] Thus, preferred embodiments of the present invention provide hydraulic systems, hydraulic equipment, software including monitoring / control strategies and maintenance strategies designed and / or adapted to perform ground maintenance. Preferred embodiments may also include the ability to control hydraulic motor-pump-units similar to ground vehicles but from an aircraft. This operation preferably overrides current functionality, applies predetermined settings for planned maintenance and allows for fully independent control.

[0024] The embodiments of the present invention preferably have the following advantages and effects:

[0025] By introducing this ground vehicle functionality into the onboard hydraulic system, one, several, or all of the following advantages may be achieved:

[0026] 1. Significantly reduce costs for airport maintenance operators (less personnel, procurement, logistics);

[0027] 2. Ground maintenance is more flexible (no need to use ground vehicles, maintenance can be carried out at an outstation);

[0028] 3. Different aircraft will not have the same malfunction due to contamination of ground vehicles;

[0029] 4. More flexibility in the case of alternative hydraulic fluids (fluids dedicated only to the aircraft and not to common maintenance points such as ground vehicles);

[0030] 5. Improve the safety of ground handling (using all control and monitoring devices installed on the aircraft);

[0031] 6. Reduced probability of failure (due to autonomous maintenance procedures);

[0032] 7. More flexibility in case of alternative maintenance procedures (use of hydraulic pumps allows full functionality of the aircraft operating cycle); and / or

[0033] 8. No increase in aircraft weight: This can be a benefit to every operator, eliminating the need for hydraulic ground vehicles and thus increasing maneuverability. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Embodiments of the present invention will now be explained in more detail with reference to the accompanying drawings, in which:

[0035] Figure 1 An embodiment of an aircraft and a mobile hydraulic power unit is shown, the aircraft including a first embodiment of a combined hydraulic system;

[0036] Figure 2 schematically illustrates a second embodiment of a combined hydraulic system; and

[0037] Figure 3 An embodiment of an aircraft arrangement is shown. DETAILED DESCRIPTION

[0038] Figure 1 An embodiment of an aircraft 10 and a mobile hydraulic power unit 12 external to the aircraft 10 is shown.

[0039] The aircraft 10 comprises a first embodiment of an integrated hydraulic system 14 configured to operate a plurality of hydraulic components 16 of the aircraft 10 by means of an operating fluid or hydraulic fluid. The operating fluid may, for example, comprise water and / or oil.

[0040] The hydraulic power unit 12 comprises a unit inlet 18, a unit reservoir 20 for operating fluid, and a unit outlet 22. The unit inlet 18 and the unit outlet 22 are fluidly connected to the integrated hydraulic system 14 of the aircraft 10, respectively.

[0041] The hydraulic power unit 12 is configured to supply hydraulic power to a plurality of hydraulic components 16. To this end, the hydraulic power unit 12 includes a unit pumping device for pumping operating fluid from a unit outlet 22 into the hydraulic system 14. In addition, the hydraulic power unit 12 may be configured for introducing or sucking operating fluid from the hydraulic system 14 via a unit inlet 18.

[0042] Figure 2 A second embodiment of a hydraulic system 14 for incorporation into an aircraft 10 is schematically shown.

[0043] The hydraulic system 14 is configured to supply hydraulic power to a plurality of hydraulic components 16 of the aircraft 10 via an operating fluid.

[0044] The hydraulic system 14 includes a system inlet 24 , a system pumping device 26 , and a system outlet 28 .

[0045] The system inlet 24 may include an opening and / or closing device for fluidly opening and / or closing the system inlet 24. Furthermore, the system outlet 28 may include such an opening and / or closing device for opening and / or closing the system outlet 28.

[0046] The system pumping device 26 is configured for introducing operating fluid from the system inlet 24 and for pumping the operating fluid into the hydraulic system 14. Preferably, the system pumping device 26 is configured for introducing and pumping the operating fluid at a variable pressure and / or flow rate within the hydraulic system 14. Such pressure and / or flow rate may be in the range of 0 psi to 5000 psi or 0 gpm to 60 gpm, respectively.

[0047] The hydraulic system 14 may further include a monitoring and / or sensing device 30 for monitoring and / or sensing pressure and / or flow within the hydraulic system 14 .

[0048] The hydraulic system 14 may further include a system purge device 34. The system purge device 34 is configured to release gas or air from inside the hydraulic system 14. The system purge device 34 may, for example, include an air release valve.

[0049] The hydraulic system 14 may further include a fluid filter device 36. The fluid filter device 36 is configured to filter the operating fluid within the hydraulic system 14.

[0050] The hydraulic system 14 further comprises a control device 32 for controlling the pressure and / or flow rate within the hydraulic system 14 by means of the system pumping device 26. For this purpose, the control device 32 can be in data connection with the monitoring and / or sensing device 30.

[0051] The control device 32 may also be configured to control the opening and / or closing means of the system inlet 24 or the system outlet 28, respectively. The control device 32 may also be configured to control the system degassing device 34. The control device 32 may also be configured to control and / or monitor the fluid filtering device 36.

[0052] Figure 3 An embodiment of an aircraft arrangement 38 is shown.

[0053] The aircraft device 38 includes a hydraulic device 40 and another embodiment of the aircraft 10 .

[0054] The hydraulic device 40 includes a Figure 2 The hydraulic system 14 of the second embodiment is shown in FIG. The hydraulic system 14 is integrated in the aircraft 10 .

[0055] The hydraulic device 40 further comprises a first hose 42 and a second hose 44 for conveying operating fluid, respectively. The first hose 42 is connected to the system inlet 24, while the second hose 44 is connected to the system outlet 28. The first hose 42 comprises a hose pumping device 46 for pumping the operating fluid to the system pumping device 26.

[0056] The hydraulic device 40 further comprises a first removable reservoir 48 and a second removable reservoir 50, respectively, for operating fluid. The first removable reservoir 48 and / or the second removable reservoir 50 can be configured as a bucket or any other suitable container of any kind, respectively. The first removable reservoir 48 contains a suitable amount of operating fluid, while the second removable reservoir 50 provides a suitable volume for the operating fluid. In other words, the first removable reservoir 48 stores "fresh fluid", i.e., fluid that the operator wants to use to fill the aircraft hydraulic system 14. The second removable reservoir 50 is intended to collect fluid that is discharged / removed from the aircraft hydraulic system 14. Typically, this is the "used" fluid, and the second removable reservoir 50 prevents the fluid from spilling into the environment.

[0057] The first hose 42 and the second hose 44 fluidly connect the first removable reservoir 48 and the second removable reservoir 50 with the system inlet 24 and the system outlet 28, respectively.

[0058] For aircraft installations 38, control device 32 may control pressure and / or flow within hydraulic system 14 in a test or maintenance mode. Test mode is configured for testing or maintaining hydraulic system 14 and / or hydraulic components 16 of aircraft 10. Test mode is performed while aircraft 10 is on the ground.

[0059] In the test mode, the control device 32 can initiate one or more test processes with the help of the system pumping device 26. The test process may include one, several or all of the following:

[0060] - changing the pressure and / or flow rate inside the hydraulic system 14;

[0061] - Introducing the operating fluid from the system inlet 24;

[0062] - pumping the operating fluid into the hydraulic system 14;

[0063] - pumping the operating fluid to the system outlet 28;

[0064] - draining the operating fluid from the hydraulic system 14;

[0065] - opening and / or closing the system inlet 24 and / or the system outlet 28;

[0066] - venting the hydraulic system 14; and / or

[0067] - Filtering of the operating fluid inside the hydraulic system 14 .

[0068] One, several or all test processes can be executed sequentially or simultaneously and / or automatically.

[0069] The introduction of the operating fluid from the system inlet 24 is performed by conveying the operating fluid from the first removable reservoir 48 to the system inlet 24 via the first hose 42. This is performed by the hose pumping device 46 and the system pumping device 26. In addition, it can be supported by the principle of gravity and / or a communicating vessel. Alternatively, the hose pumping device 46 in the first hose 42 can be omitted, and the system pumping device 26 can introduce the operating fluid only from the first removable reservoir 48, and / or introduce the operating fluid by the principle of gravity and / or a communicating vessel.

[0070] The draining of the operating fluid from the hydraulic system 14 is performed by conveying the operating fluid from the system outlet 28 via the second hose 44 to the second removable reservoir 50. It can be performed solely by gravity and / or the principle of a communicating vessel. In addition, the draining of the operating fluid from the hydraulic system 14 can be supported by means of the system pumping device 26.

[0071] The introduction of operating fluid and the discharge of operating fluid can be performed simultaneously and / or automatically. In this case, the operating fluid in the hydraulic system 14 can be exchanged. In addition, the introduction of operating fluid and / or the discharge of operating fluid can be performed simultaneously and / or automatically with the exhaust of the hydraulic system 14 and / or the filtering of the operating fluid inside the hydraulic system 14.

[0072] However, the present invention also includes embodiments of the aircraft device 38 having a single hose 42 , 44 and / or a single removable reservoir 48 , 50 .

[0073] In the first case, the operating fluid may be introduced from the system inlet 24 by conveying the operating fluid from the removable reservoir 48, 50 to the system inlet 24 via the first hose 42. Simultaneously and / or automatically, the operating fluid may be discharged from the hydraulic system 14 by conveying the operating fluid from the system outlet 28 to the removable reservoir 48, 50 via the second hose 44. In this case, the operating fluid in the hydraulic system 14 may not be completely exchanged, but rather filtered simultaneously and / or automatically by the fluid filtering device 36.

[0074] In the second case, the operating fluid may be introduced from the system inlet 42 for filling / replenishing the hydraulic system 14 with the operating fluid, or the operating fluid may be discharged from the hydraulic system 14 for draining the operating fluid from the hydraulic system 14. The control device 32 may open and / or close the system inlet 24 and / or the system outlet 28 accordingly.

[0075] The preferred embodiments of the present invention can be summarized as follows:

[0076] To fill, drain and / or change the hydraulic fluid, embodiments preferably use on-board technology in conjunction with hydraulic fluid containers. These two types of existing infrastructure combined allow dedicated hydraulic ground equipment to be replaced.

[0077] This may be accomplished through enhanced hydraulic equipment foreseen in future aircraft applications and technical means of directly interconnecting hydraulic fluid reservoirs on the ground with the hydraulic system on the aircraft.

[0078] The preferred embodiment of the present invention aims to solve the problem that the system pumping device 26 or hydraulic pump in the aircraft 10 may not accept a height difference of several meters (ie, the height of the suction fluid may be limited). Therefore, there are preferably two possible concepts according to the embodiment of the present invention:

[0079] According to a first concept, a separate, continuously operated pump in the hose arrangement 40 can be used to pre-pressurize the suction hose 42 .

[0080] According to the second concept (hose introduction), an introduction pump can be used to build up pressure in the suction line until the system pumping device 26 has taken over the filling. The introduction pump only needs to be pre-pressurized under initial start-up conditions; it can be simpler than the hose device 40 according to the first concept.

[0081] According to a preferred embodiment of the present invention, these two concepts can be used alternately or together.

[0082] According to a second concept, a hose with an integrated pump is preferably used to push the hydraulic fluid from the container on the ground to the hydraulic system pump so that the hydraulic fluid can then be sucked into the hydraulic system without the need for additional air (hose introduction). A similar hose arrangement can be used to drain the spent hydraulic system fluid into a drain container. In this case, no dedicated pump is required.

[0083] By using this hardware and applying the proposed operating mode, a controlled fluid filling, changing, replenishing or draining of a hydraulic system can be achieved, preferably without the support of a hydraulic ground vehicle.

[0084] Fluid filling of a hydraulic system may include the following steps:

[0085] - transporting fluid containers to aircraft;

[0086] - connecting the fluid container to the hydraulic system at the foreseen connection point by means of a filling hose;

[0087] - Pumping the fluid from the container to the aircraft until the fluid reaches the hydraulic system pump (hose introduction);

[0088] - taking over the filling action with the hydraulic system pump inside the aircraft (flow and pressure controlled): this can be done automatically during a dedicated maintenance mode by the integrated aircraft hydraulic control means; and

[0089] - Automatic deflation during fluid filling is foreseen by means of a hydraulic system (reservoir bleed device).

[0090] Fluid changes in a hydraulic system can include the following steps:

[0091] - transporting full and empty fluid containers to the aircraft;

[0092] - connecting the full fluid container to the hydraulic system at the foreseen connection point by means of a filling hose;

[0093] - connecting the empty fluid container to the hose at the foreseen junction;

[0094] - Pumping the fluid from the container to the aircraft until the fluid reaches the hydraulic system pump (hose introduction);

[0095] - taking over the filling action with the hydraulic system pump inside the aircraft (flow and pressure controlled): this can be done automatically during a dedicated maintenance mode by the integrated aircraft hydraulic control means; and

[0096] -During the filling action, the used fluid will automatically drain into the empty container.

[0097] Replenishment of the hydraulic system can include the following steps:

[0098] -Partial increase of fluid volume to reach nominal reservoir level. Basically, same or similar procedure as fluid filling.

[0099] Bleeding a hydraulic system can include the following steps:

[0100] - transporting empty fluid containers to the aircraft;

[0101] - connecting the empty fluid container to the hose at the foreseen junction;

[0102] - Open the joint and drain the fluid by gravity;

[0103] - Alternatively, the internal aircraft hydraulic pump can actively support the discharge.

[0104] Degassing of hydraulic system:

[0105] Hydraulic degassing may be required in the case of fluid filling, fluid changing, draining and replenishing, but also for other maintenance purposes.

[0106] Hydraulic deaeration can be performed by using an appropriate flow of hydraulic fluid in addition to an opening device in the hydraulic system that is able to release accumulated air into the surrounding environment.

[0107] To achieve this, a preferred embodiment may utilize the capabilities of the proposed hydraulic system (ability to control flow and pressure, air release valve, enhanced control functionality) by applying a dedicated maintenance mode so that filling, fluid changes, draining, replenishment and possible degassing can be automatically supported after invasive maintenance.

[0108] The proposed hydraulic system can be operated by setting specific pressure and flow. In addition, by applying the proposed procedure and utilizing the fluid connection device from the fluid container to the hydraulic system, it can replace the existing ground support equipment. Different operation modes can be automatically executed using the data / functions and combination logic inherent in the hydraulic system.

[0109] Reference numerals list

[0110] 10 Aircraft

[0111] 12 Hydraulic power unit

[0112] 14 Combined hydraulic system

[0113] 16Hydraulic components

[0114] Unit 18 entrance

[0115] 20 unit reservoir

[0116] Unit 22 Exit

[0117] 24 System Entrance

[0118] 26 system pumping device

[0119] 28 System Exit

[0120] 30 Monitoring and / or sensing devices

[0121] 32 control devices

[0122] 34 System degassing device

[0123] 36Liquid filtration device

[0124] 38 Aircraft Devices

[0125] 40 Hydraulic device

[0126] 42 First Hose

[0127] 44 Second hose

[0128] 46 Hose Pumping Device

[0129] 48 first removable storage

[0130] 50 Second removable storage

Claims

1. A hydraulic system (14) for incorporation in an aircraft (10) and for supplying hydraulic power to one or more hydraulic components (16) of the aircraft (10) by means of an operating fluid, the hydraulic system (14) comprising a system pumping device (26) for introducing the operating fluid from a system inlet (24) of the hydraulic system (14) and for pumping the operating fluid into the hydraulic system (14).

2. The hydraulic system (14) according to claim 1, characterized in that The system pumping device (26) is configured to introduce and pump operating fluid within the hydraulic system (14) at a variable pressure and / or flow rate.

3. The hydraulic system (14) according to claim 2, further comprising control means (32) for controlling the pressure and / or flow inside the hydraulic system (14) by means of the system pumping device (26) in a test mode.

4. The hydraulic system (14) according to any one of the preceding claims, further comprising a system degassing device (34) for releasing gas from inside the hydraulic system (14).

5. The hydraulic system (14) according to any one of the preceding claims, further comprising a fluid filtering device (36) for filtering operating fluid inside the hydraulic system (14).

6. The hydraulic system (14) according to any of the preceding claims, the hydraulic system (14) being configured for pumping operating fluid to a system outlet (28) of the hydraulic system (14) and for discharging operating fluid from the hydraulic system (14).

7. A hydraulic device (40) comprising a hydraulic system (14) according to any one of the preceding claims and a hose (42, 44) for conveying operating fluid and for connection to a system inlet (24) and / or a system outlet (28) of the hydraulic system (14).

8. The hydraulic device (40) according to claim 7, characterized in that The hose (42) includes a hose pumping device (46) for pumping operating fluid to the system pumping device (26) when the hose (42) is connected to the system inlet (24).

9. The hydraulic device (40) according to claim 7 or 8, further comprising a removable reservoir (48, 50) for operating fluid, the hose (42, 44) being configured to fluidically connect the removable reservoir (48, 50) to a system inlet (24) and / or a system outlet (28) of the hydraulic system (14).

10. An aircraft (10) comprising a combined hydraulic system (14) according to any one of claims 1 to 6.

11. An aircraft installation (38) comprising a hydraulic device (40) according to any one of claims 7 to 9 and an aircraft (10), the hydraulic system (14) of the hydraulic device (40) being integrated in the aircraft (10).

12. A method for testing a hydraulic system (14) for incorporation in an aircraft (10) and for supplying hydraulic power to one or more hydraulic components (16) of the aircraft (10) by means of an operating fluid, the method comprising: a) providing a removable reservoir (48) containing an operating fluid; b) fluidly connecting the removable reservoir (48) to a system inlet (24) of the hydraulic system (14); and c) introducing operating fluid from a system inlet (24) of the hydraulic system (14) through the hydraulic system (14) and pumping the operating fluid into the hydraulic system (14).

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