Component subjected to pressure with a pressure sensor that can be stopped

Abstract

The present invention relates to a pressure-sensitive component, for example a shock absorber, preferably for an aircraft, particularly an airplane, with a pressure sensor (3), it being understood that fluid communication (4) between the pressure sensor (3) and a pressure chamber (2) of the component can be reversibly stopped by means of a shut-off device. Furthermore, the invention relates to a method for replacing and / or maintaining a pressure sensor (3) of such a pressure-sensitive component, and to the use of such a component for manufacturing and / or maintaining an aircraft, particularly an airplane.

Description

Title of the invention: Component subjected to pressure with a pressure sensor that can be stopped

[0001] The present invention relates to a component subjected to the action of pressure, for example a shock absorber, an actuator or a valve block, preferably for an aircraft, in particular for an airplane, with a pressure sensor, it being understood that a fluidic communication between the pressure sensor and a pressure chamber of the component can be stopped reversibly by means of a stopping device.

[0002] Today, the pressure sensors used are directly and / or fluidically inseparable from the component / shock absorber in the case of components subjected to pressure, for example, shock absorbers. If a sensor needs to be replaced, the pressure must consequently be released from the shock absorber and, possibly, the fluid must also be drained from the shock absorber.

[0003] Consequently, the workload required for replacing the sensor is traditionally considerable, especially when it also involves releasing the pressure from the entire shock absorber assembly and even draining the fluid. Furthermore, in certain circumstances, it is necessary to use new oil or a different fluid, as the old oil becomes contaminated during drainage.

[0004] In this context, the present invention aims to mitigate the drawbacks of the prior art or even eliminate them entirely. In particular, the present invention aims to create a simplified maintenance method for a pressure sensor.

[0005] This objective is achieved through the subject matter of the independent claims. Advantageous improvements are the subject of the sub-claims.

[0006] Consequently, a component subjected to the action of pressure, preferably for an aircraft, in particular for an airplane, is provided with a pressure sensor, it being understood that fluid communication between the pressure sensor and a pressure chamber of the component can be stopped reversibly by means of a stopping device.

[0007] This point is explained in the same way as a shock absorber as a component subjected to pressure. In the present case, the invention makes it possible to replace a pressure sensor connected to the shock absorber, for example, of a running gear, without thereby releasing the pressure from the shock absorber, which reduces the labor time and resources required to replace the sensor.

[0008] The shut-off device preferably reduces the workload during sensor replacement, since it allows the sensor to be separated from the (main) pressure chamber. Thus, neither lowering the pressure in the main chamber nor removing the fluid is necessary.

[0009] The invention can be applied to pressure sensors in all modules in which a pressurized fluid can be monitored, for example, shock absorbers, actuators, and valve blocks. While the invention is explained below using the example of a shock absorber, its interpretation should not be limited to this example.

[0010] The invention offers the advantage of reducing the time and workload required when replacing the pressure sensor. No refilling of the shock absorber is necessary. The aircraft thus remains grounded for less time while the sensor is being replaced.

[0011] The stop device may have a stop element that can be moved by translation, preferably in the form of a slide, which can preferably be moved between a stop position, in which the fluidic communication between the pressure sensor and the pressure chamber is stopped, and an open position, in which the fluidic communication between the pressure sensor and the pressure chamber is opened.

[0012] The stop element can be moved by means of a threaded mesh automatically, for example by a correspondingly designed control unit, and / or manually.

[0013] The stop element can be mounted in a sealed manner in a housing so that preferably an intermediate space existing in the radial direction between the stop element and the housing is sealed by means of a metal-on-metal sealing gasket or by means of a separate sealing element.

[0014] For a particularly reliable closure of the fluidic communication, the stop element may have, on its end facing the pressure chamber, a preferably convex geometry, which is designed to provide a tight seal against a corresponding, preferably concave, geometry of a pressure chamber housing. For example, the end of the stop element may be arched, and the curvature may conform to a corresponding cone of the housing.

[0015] To limit the translational displacement of the stopping element, the component may be equipped with at least one limiting element, which limits the translational displacement of the stopping element in at least one direction. The limiting element may be configured as a stop, a locking lug, or as a retaining arm.

[0016] The component may be a shock absorber, an actuator, a valve block, or any component with a pressure chamber. The shut-off device may be a valve.

[0017] Another aspect of the present invention relates to a method for replacing and / or maintaining a pressure sensor of a component subjected to the action of pressure, preferably of a shock absorber, with the steps of: stopping a fluidic communication between the pressure sensor and a pressure chamber of the component by means of a stopping device, replacing and / or maintaining a pressure sensor, and opening the fluidic communication between the pressure sensor and a pressure chamber of the component by means of the stopping device.

[0018] The traditional operating procedure for replacing or servicing a shock absorber pressure sensor includes the following steps: immobilizing the aircraft, removing nitrogen from the landing gear shock absorber, removing oil from the landing gear shock absorber, replacing the sensor, refilling the landing gear shock absorber with new oil, refilling the landing gear shock absorber with new nitrogen, and returning the aircraft to service.

[0019] The operating method mentioned above can be simplified by using the present invention: closing the stop device, replacing the sensor, opening the stop device.

[0020] In a method according to the invention, the pressure in the pressure chamber is separated from the environment by a seal on the sensor interface and preferably a seal in a slide preferably when the stop device is open.

[0021] After the closing of the stop device, the pressure is preferably absorbed by the two sealing joints, in that a rounded end of the slide is pushed by a thread on a cone on the housing or the running gear, and the pressure is thus separated from the pressure sensor.

[0022] In a process according to the present invention, a pressure in the pressure chamber of the component may remain constant or substantially constant preferably during the execution of the process and / or no fluid is removed from or evacuated from the pressure chamber.

[0023] Furthermore, the present invention relates to an aircraft, in particular an airplane, with at least one component subjected to the action of pressure according to the present invention.

[0024] Furthermore, the present invention relates to the use of a component according to the present invention and / or a method according to the present invention for the manufacture and / or maintenance of an aircraft, in particular an airplane.

[0025] Furthermore, all the features of the invention described herein can be combined with each other in any way or are claimed in isolation from each other.

[0026] Further details and advantages of the invention are explained in more detail with reference to an exemplary embodiment shown in the figure. Identical reference numbers designate similar or identical components.

[0027] We can see: [Fig. 1]: a cross-section of a shock absorber according to the present invention, in which the stopping device is in the open position, and on [Fig.2]: the cross-section of [Fig.1], in which the stop device is in the stop position.

[0028] Figure 1 illustrates a shock absorber with a housing 1, in which a shock absorber chamber 2 subjected to pressure is disposed. The pressure in the shock absorber chamber 2 is measured by means of a pressure sensor 3, which is connected to the shock absorber chamber 2 via a passage 4.

[0029] The passage 4 can be stopped by means of a slide 5. The slide 5 is mounted so as to be able to slide axially in the housing 1 and an intermediate space between the slide 5 and the housing 1 is, in this example, sealed by a metal-on-metal seal 6. Alternative seals, such as an O-ring, are conceivable.

[0030] The slide 5 can be moved by means of a thread 7. The translational movement of the slide 5 is limited by means of a limiting element 8. In addition, a sealing gasket 9 is present. The limiting element 8 may also have a sealing element or is constructed as such. Besides the sealing gasket 9, the housing 1 forms a stop.

[0031] As can be seen in [Fig. 2], the slide 5 is in the stop position (is moved to the left in [Fig. 2]) so that passage 4 is stopped. The pressure or fluid in the shock absorber chamber 2 is hermetically sealed / locked in this position so that replacing the pressure sensor 3 no longer has any effect on the inside of the shock absorber chamber 2. [Fig. 2] also illustrates the sealing gasket 10 of the pressure sensor 3.

Claims

Demands

1. A component subjected to the action of pressure, preferably for an aircraft, in particular for an airplane, with a pressure sensor, wherein a fluidic communication (4) between a pressure sensor (3) and a pressure chamber (2) of the component can be reversibly stopped by means of a stopping device.

2. Component according to claim 1, characterized in that the stop device has a stop element that can be moved by translation, preferably in the form of a slide (5), which can be moved between a stop position, in which the fluidic communication between the pressure sensor (3) and the pressure chamber (2) is stopped, and an open position, in which the fluidic communication between the pressure sensor (3) and the pressure chamber (2) is opened.

3. Component according to claim 2, characterized in that the stop element can be moved automatically and / or manually by means of a threaded mesh (7).

4. Component according to any one of claims 2 or 3, characterized in that the stop element is hermetically mounted in a housing (1) such that an intermediate space existing in the radial direction between the stop element and the housing (1) is sealed preferably by means of a metal-on-metal seal (6) or by means of a separate sealing element.

5. Component according to any one of claims 2 to 4, characterized in that the stop element has on its end facing the pressure chamber (2) a preferably convex geometry, which is designed to come into tight contact with a corresponding geometry, preferably concave, of a housing (1) of the pressure chamber (2).

6. Component according to any one of claims 2 to 5, further having at least one limiting element (8), which limits the translational displacement of the stopping element in at least one direction.

7. Component according to any one of the preceding claims, characterized in that the component is a shock absorber, an actuator or a valve block.

8. A method for replacing and / or servicing a pressure sensor (3) of a component subjected to pressure, preferably of a component according to any one of the preceding claims, with the steps of: stopping fluid communication between the pressure sensor (3) and a pressure chamber (2) of the component by means of a stopping device, replacing and / or servicing a pressure sensor (3), and opening fluid communication (4) between the pressure sensor (3) and a pressure chamber (2) of the component by means of the stopping device.

9. A method according to claim 8, characterized in that a pressure remains constant or substantially constant in the pressure chamber (2) of the component during the execution of the method.

10. Aircraft, in particular airplane, with a component subjected to the action of pressure according to any one of claims 1 to 7.

11. Use of a component according to any one of claims 1 to 7 and / or of a method according to any one of claims 8 to 9, to manufacture and / or maintain an aircraft, in particular an airplane.

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