Patent Application
20250171163
This application incorporates by reference and claims priority to European patent application 23211830.7, filed Nov. 23, 2023.
The invention relates to a hydraulic system for integrating in an aircraft. The invention further relates to a hydraulic arrangement, an aircraft, an aircraft arrangement, and a method for testing such a hydraulic system.
Conventional on-ground maintenance concepts for hydraulic systems rely on the usage of airfield-based ground support equipment, such as hydraulic ground carts. Procurement, logistics, and usage of these ground carts are significant for airfield operators. Maintenance personnel usually need to serve the ground cart and intervene during certain maintenance procedures. During common maintenance with ground carts, the hydraulic pump and its control may be replaced. Different procedures are available to manually perform further maintenance tasks. However, if the ground cart is not available at the aircraft location, delays may be the result.
The invention may be embodied to provide an improved or alternative method for testing or maintaining a hydraulic system for an aircraft.
In one aspect, the invention provides a hydraulic system for integrating in an aircraft and for supplying hydraulic power to one or more hydraulic components of the aircraft by means of an operating fluid, the hydraulic system comprising a system pumping device for priming operating fluid from a system inlet of the hydraulic system and for pumping operating fluid thereinto.
The system pumping device may be configured for priming and pumping operating fluid at a variable pressure and/or flow rate inside the hydraulic system.
The hydraulic system may further comprise a controlling means for controlling the pressure and/or flow rate inside the hydraulic system by means of the system pumping device in a test mode.
The hydraulic system may further comprise a system deaeration device for releasing gas from inside the hydraulic system.
The hydraulic system may further comprise a fluid filtering device for filtering operating fluid inside the hydraulic system.
The hydraulic system may be configured for pumping operating fluid to a system outlet of the hydraulic system and for discarding operating fluid therefrom.
In another aspect, the invention may provide a hydraulic arrangement, comprising a hydraulic system according to any of the preceding embodiments and a hose for conducting operating fluid and for connecting to the system inlet and/or the system outlet of the hydraulic system.
The hose may include a hose pumping device for pumping operating fluid to the system pumping device when the hose is connected to the system inlet.
The hydraulic arrangement may further comprise a mobile reservoir for operating fluid, the hose being configured for fluidly connecting the mobile reservoir with the system inlet and/or the system outlet of the hydraulic system.
In another aspect, the invention may provide an aircraft, comprising an integrated hydraulic system according to any of the preceding embodiments.
In another aspect, the invention may provide an aircraft arrangement, comprising a hydraulic arrangement according to any of the preceding embodiments and the aircraft, the hydraulic system of the hydraulic arrangement being integrated in the aircraft.
In another aspect, the invention may provide a method for testing a hydraulic system integrated in an aircraft and for supplying hydraulic power to one or more hydraulic components of the aircraft by means of an operating fluid, the method comprising: providing a mobile reservoir containing operating fluid; fluidly connecting the mobile reservoir with a system inlet of the hydraulic system; and by the hydraulic system, priming operating fluid from the system inlet of the hydraulic system and pumping operating fluid thereinto.
Some aspects of embodiments of the invention may be summarized as follows:
The invention may be embodied to substitute hydraulic ground support equipment, such as hydraulic ground carts, on airfields, in the final assembly line (FAL), and/or in maintenance hangars. Preferred embodiments make use of an on-aircraft installed motor-pump unit and the respective control and monitoring. By this enhanced functionality of the aircraft hydraulic system, external means may not be needed and tasks are automated which may lead to a reduction of maintenance time and cost.
The invention may provide a hydraulic system, a hydraulic equipment, software including monitoring/control and maintenance strategies that are designed and/or adjusted to perform on-ground maintenance. Preferred embodiments may also include the ability to control the hydraulic motor-pump-unit similarly to a ground cart, but from the aircraft. The operation preferably goes beyond current functionalities, applying pre-defined settings for scheduled maintenance and allowing a fully independent control.
Embodiments of the invention may have the following advantages and effects:
By introducing this ground cart functionality into the on-board hydraulic system, one, several, or all of the following advantages may be achieved:
Embodiments of the invention are now explained in more detail with reference to the accompanying drawings of which
The aircraft 10 includes a first embodiment of an integrated hydraulic system 14 that is configured for operating a plurality of hydraulic components 16 of the aircraft 10 by means of an operating or hydraulic fluid. The operating fluid may be a liquid such as water or oil. The hydraulic components 16 may be all of the components in the aircraft that are driven or powered by the operating fluid.
The hydraulic power unit 12 includes 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 respectively fluidly connected with the integrated hydraulic system 14 of the aircraft 10.
The hydraulic power unit 12 is configured for supplying hydraulic power to the plurality of hydraulic components 16. For this, the hydraulic power unit 12 includes a unit pumping device for pumping operating fluid from the unit outlet 22 into the hydraulic system 14. Additionally, the hydraulic power unit 12 may be configured for priming or sucking in operating fluid from the hydraulic system 14 via the unit inlet 18.
The hydraulic system 14 is configured for supplying hydraulic power to the plurality of hydraulic components 16 of the aircraft 10 by the operating fluid.
The hydraulic system 14 provides the operating fluid, e.g., a hydraulic liquid, to each of the hydraulic components.
The hydraulic system 14 includes a system inlet 24, a system pumping device 26, and a system outlet 28. The system pumping device 26 may be a pump configured to pump hydraulic liquid.
The system inlet 24 may include an opening and/or closing device for fluidly opening and/or closing the system inlet 24. Also, the system outlet 28 may include such opening and/or closing devices for opening and/or closing the system outlet 28.
The system pumping device 26 is configured for priming operating fluid from the system inlet 24 and for pumping operating fluid into the hydraulic system 14. Preferably, the system pumping device 26 is configured for priming and pumping operating fluid at variable pressure and/or flow rate inside the hydraulic system 14. Such pressure and/or flow rate may be in a range of 0 to 5000 psi (pounds per square inch) or 0 to 60 gpm (gallons per minute), respectively.
The hydraulic system 14 may further include a monitoring and/or sensing device 30 for monitoring and/or sensing the pressure and/or flow rate inside the hydraulic system 14.
The hydraulic system 14 may further include a system deaeration device 34. The system deaeration device 34 is configured for releasing gas or air from inside the hydraulic system 14. The system deaeration device 34 may, for example, include an air relief valve.
The hydraulic system 14 may further include a fluid filtering device 36. The fluid filtering device 36 is configured for filtering operating fluid inside the hydraulic system 14.
The hydraulic system 14 further includes a controlling system 32 for controlling the pressure and/or flow rate inside the hydraulic system 14 by the system pumping device 26. For this, the controlling system 32 may be controller with a data connection with the monitoring and/or sensing device 30.
The controlling system 32 may further be configured for controlling the opening and/or closing device of the system inlet 24 or the system outlet 28, respectively. The controlling system 32 may further be configured for controlling the system deaeration device 34. The controlling system 32 may further be configured for controlling and/or monitoring the fluid filtering device 36.
The aircraft arrangement 38 includes a hydraulic arrangement 40 and another embodiment of the aircraft 10. The hydraulic arrangement 40 may be ground based and positioned near the aircraft while the aircraft is stationary in an airport.
The hydraulic arrangement 40 includes the hydraulic system 14 according to the second embodiment as shown in
The hydraulic arrangement 40 further includes a first hose 42 and a second hose 44 respectively for conducting operating fluid. 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 includes a hose pumping device 46 for pumping operating fluid from the hydraulic arrangement 40 to the system pumping device 26.
The hydraulic arrangement 40 further includes a first mobile reservoir 48 and a second mobile reservoir 50 respectively for operating fluid. The first mobile reservoir 48 and/or the second mobile reservoir 50 may respectively be configured as a barrel or any kind of other suitable container. The first mobile reservoir 48 contains a suitable amount of operating fluid, while the second mobile reservoir 50 provides a suitable volume for operating fluid. In other words, the first mobile reservoir 48 stores “fresh fluid”, e.g., the liquid an operator wants to use for filling the aircraft hydraulic system 14. The second mobile reservoir 50 is meant to collect the fluid that is drained/removed from the aircraft hydraulic system 14. Typically, this is “used” fluid and the second mobile reservoir 50 prevents the fluid from being spilled into the environment. The first and second mobile reservoirs 48, 50 may be ground based and mounted on a mobile vehicle that is moved into position next to the aircraft.
The first hose 42 and the second hose 44 respectively fluidly connect the first mobile reservoir 48 and the second mobile reservoir 50 with the system inlet 24 and the system outlet 28.
For the aircraft arrangement 38, the controlling system 32 may control the pressure and/or flow rate inside the hydraulic system 14 in a test or maintenance mode. The test mode is configured for testing or maintaining the hydraulic system 14 and/or the hydraulic components 16 of the aircraft 10. The test mode is to be performed when the aircraft 10 is on the ground.
In the test mode, the controlling system 32 may initiate one or more test processes by means of the system pumping device 26. The test processes may include one, several, or all of the following:
One, several, or all of the test processes may be performed sequentially or simultaneously and/or automatically.
The priming operating fluid from the system inlet 24 is performed by conducting operating fluid from the first mobile reservoir 48 via the first hose 42 to the system inlet 24. It is performed by the hose pumping device 46 and the system pumping device 26. Additionally, it may be supported by gravity and/or the principle of communicating vessels. Alternatively, the hose pumping device 46 in the first hose 42 may be omitted and the system pumping device 26 may prime operating fluid from the first mobile reservoir 48 alone and/or supported by gravity and/or the principle of communicating vessels.
The discarding of operating fluid from hydraulic system 14 is performed by conducting operating fluid from the system outlet 28 via the second hose 44 to the second mobile reservoir 50. It may be performed only by gravity and/or the principle of communicating vessels. Additionally, the discarding of operating fluid from the hydraulic system 14 may be supported by means of the system pumping device 26.
The priming operating fluid and the discarding of operating fluid may be performed simultaneously and/or automatically. In this case, the operating fluid in the hydraulic system 14 may be exchanged. Also, the priming operating fluid and/or the discarding of operating fluid may be accompanied simultaneously and/or automatically with the de-airing of the hydraulic system 14 and/or the filtering of operating fluid inside the hydraulic system 14.
The invention may comprise embodiments of the aircraft arrangement 38 with a single hose 42, 44 and/or a single mobile reservoir 48, 50.
In a first case, operating fluid may be primed from the system inlet 24 by conducting operating fluid from the mobile reservoir 48, 50 via the first hose 42 to the system inlet 24. Simultaneously and/or automatically, operating fluid may be discarded from hydraulic system 14 by conducting operating fluid from the system outlet 28 via the second hose 44 to the mobile reservoir 48, 50. In this case, the operating fluid in the hydraulic system 14 may not be exchanged completely, but simultaneously and/or automatically filtered by the fluid filtering device 36.
In a second case, operating fluid may either be primed from the system inlet 42 for filling/topping up the hydraulic system 14 with operating fluid or operating fluid may be discarded from the hydraulic system 14 for draining operating fluid from the hydraulic system 14. The controlling system 32 may open and/or close the system inlet 24 and/or the system outlet 28 accordingly.
Embodiments of the invention may be summarized as follows:
For filling, draining, and/or changing hydraulic fluid, embodiments preferably use technology on aircraft in combination with hydraulic fluid containers. These both types of already existing infrastructure are combined so that dedicated hydraulic ground equipment can be substituted.
This can be achieved with enhanced hydraulic equipment foreseen on future aircraft applications, and a technical device that interconnects the hydraulic fluid container on ground directly with the hydraulic system on the aircraft.
The invention may be embodied to aim to tackle the problem, that the system pumping device 26 or the hydraulic pump in the aircraft 10 may not accept several meters of differential height (i.e., a sucking fluid height may be limited). Therefore, there are preferably two possible concepts according to embodiments of the invention:
According to a first concept, a separate, continuously operating pump in the hose arrangement 40 may be used for pre-pressurizing the suction hose 42.
According to a second concept (hose priming), a primer pump may be used for building up a pressure in the suction line until the system pumping device 26 has taken over the filling. The primer pump would only be needed for pre-pressurization for an initial starting condition; it may be simpler than the hose arrangement 40 according to the first concept.
Both concepts may be used alternatively or together according to preferred embodiments of the invention.
According to the second concept, a hose with an integrated pump is preferably used to push the hydraulic fluid from the container on ground to the hydraulic system pump so that it can then be sucked without the addition of air (hose priming) into the hydraulic system. A similar hose device can be taken for draining used hydraulic system fluid into a drain container. In this case, a dedicated pump would not be needed.
By using this hardware and applying the proposed operational modes, a controlled fluid filling, changing, topping up or drainage of the hydraulic system may be achieved preferably without support of a hydraulic ground cart.
The fluid filling of the hydraulic system may comprise the following steps:
The fluid changing in the hydraulic system may comprise the following steps:
The topping-up of the hydraulic system may comprise the following step:
The draining of the hydraulic system may comprise the following steps:
In case of fluid filling, fluid changing, draining, and topping up, but also for other maintenance purposes, hydraulic deaeration may be needed.
A hydraulic deaeration may be performed by using a proper hydraulic fluid flow plus opening means in the hydraulic system that are able to relieve accumulated air to ambient.
To achieve this, preferred embodiments may use the capabilities of the proposed hydraulic system (controllable flow and pressure, air relief valve, enhanced control functions) by applying a dedicated maintenance mode so that filling, fluid changing, draining, topping up and possibly deaeration after invasive maintenance can be supported automatically.
The proposed hydraulic system can be operated by setting specific pressures and flows. Additionally, by applying the proposed procedures and making use of a fluid connecting device from a fluid container to the hydraulic system, the existing ground support equipment may be substituted. The different operational modes may be performed automatically using the hydraulic system inherent data/functionality and combining logics.
While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both, unless the disclosure states otherwise. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.
| Number | Date | Country | Kind |
|---|---|---|---|
| 23211830.7 | Nov 2023 | EP | regional |
