Static pressure port device and static pressure port system for an aircraft

Abstract

The present invention relates to a static pressure port device for an aircraft, comprising a first static pressure port part which is fixedly arranged relative to a skin of the aircraft, a second static pressure port part which comprises one end facing the outside of the aircraft and another end inside the skin and facing the first static pressure port part, the second static pressure port part being provided at its one end with a pilot hole for sensing the outside static pressure and being releasably attached to the skin and being connected at its other end to the first static pressure port part. By employing a two-piece static pressure port part, quick disassembly outside the static pressure port device (from the outside) can be achieved, thereby reducing maintenance or replacement costs and saving time. The present invention also relates to a static pressure port system.

Description

Technical Field

[0001] This invention relates to the field of aircraft avionics. Specifically, it relates to a hydrostatic orifice device for aircraft, particularly a combined hydrostatic orifice device. Furthermore, the invention also relates to a hydrostatic orifice system including such an orifice device. Background Technology

[0002] The function of an aircraft's static pressure port (or barometric pressure orifice) is to obtain the static pressure of the outside atmosphere. Based on this atmospheric static pressure, the pilot can calculate the aircraft's barometric altitude. Specifically, aircraft altitude measurement is accomplished using a barometric altimeter, which operates by using the static pressure orifice to measure altitude. Therefore, the static pressure orifice accurately senses atmospheric static pressure, ensuring the accuracy of the barometric altimeter, and is a key parameter for flight control, navigation, and environmental control systems.

[0003] The basic principle of aircraft static pressure inlets is based on calculations using the static pressure equation, which states that in a steady fluid, the local pressure when the fluid is at rest is called static pressure. The static pressure inlet device senses the static pressure in the surrounding environment and then transmits it through pipes to a pressure gauge located in the cockpit.

[0004] Currently, the static pressure port devices used on aircraft mainly come in the following forms: full static pressure probes, which can be arranged on the side wall of L-shaped probes. The disadvantage is that because the static pressure port is located far from the fuselage, it is easily affected by airflow disturbances; fuselage static pressure ports, which adopt an integrated design. The disadvantage is that there are internal fuselage operation steps during installation, which makes them inconvenient.

[0005] For static pressure orifice devices, replacement is sometimes necessary after installation, which may be due to the following three reasons:

[0006] First, the static pressure orifice (or air duct) can become clogged. When the orifice is clogged, the static pressure is trapped within the orifice assembly and remains constant. During an aircraft climb, the static pressure should decrease, but it doesn't, resulting in a lower indicated airspeed; conversely, during a descent, the static pressure should increase, but it doesn't, resulting in a higher indicated airspeed. This leads to errors in altitude and airspeed indications; airspeed becomes unreliable, and altitude readings are also inaccurate. Therefore, the static pressure orifice assembly needs to be removed to clear any blockages in the air duct or any internal flow channels, or it needs to be replaced with a new one.

[0007] Secondly, the static pressure port device is also equipped with an anti-icing heating element to prevent icing from occurring inside the device due to excessively low temperatures during aircraft flight. The anti-icing heating element may include a heating resistor, but the resistor sometimes needs to be replaced or repaired for various reasons.

[0008] Furthermore, the air vents of the static pressure port device are usually flush with the aircraft skin. However, due to various conditions that may occur during flight or testing, the static pressure port device may be damaged, thus compromising the flatness between it and the skin. Therefore, the static pressure port device also needs to be replaced.

[0009] In addition, current integrated static pressure hole devices are usually equipped with multiple conformal plates to control the installation step difference, which makes disassembly and assembly inconvenient.

[0010] Therefore, there has always been a need in the field of aircraft avionics equipment for quick and easy external disassembly and assembly when static pressure port devices need to be replaced or repaired. Summary of the Invention

[0011] The present invention relates to a static pressure port device for an aircraft, the static pressure port device comprising: a first static pressure port component, which may be fixedly disposed relative to the skin of the aircraft; and a second static pressure port component, which may include one end facing the outside of the aircraft and another end located inside the skin and facing the first static pressure port component, the second static pressure port component may have an air duct for sensing external static pressure at one end and be releasably attached to the skin, and may be connected to the first static pressure port component at the other end.

[0012] By using a two-piece (or combined) static pressure hole component, quick assembly and disassembly of the static pressure hole device can be achieved from the outside, thereby reducing maintenance or replacement costs and saving time.

[0013] Preferably, the static pressure orifice device may further include an intermediate connecting element for connecting the other end of the second static pressure orifice component to the first static pressure orifice component, so that fluid flowing in from the air guide hole can flow from the second static pressure orifice component to the first static pressure orifice component via the intermediate connecting element.

[0014] By using intermediate connecting elements, the connection between the first and second hydrostatic hole components can be simplified, reducing the requirements for the repositionability of their joints.

[0015] Advantageously, the intermediate connecting element can be configured to have a variable length so that the second hydrostatic hole component can change its position relative to the first hydrostatic hole component.

[0016] By incorporating a variable-length intermediate connecting element, the position of the second hydrostatic orifice component relative to the first hydrostatic orifice component can be easily changed. In particular, it allows for the rapid removal of the second hydrostatic orifice component from the first hydrostatic orifice component for maintenance or replacement, and its convenient return to its connected position with the first hydrostatic orifice component.

[0017] In particular, the intermediate connecting element can be configured as a retractable hose.

[0018] The above structure is highly flexible, reducing damage caused by the relative displacement between the first and second static pressure hole components. On the other hand, the structure itself is also very compact and low in cost (for example, compared to other foldable structures).

[0019] In addition, the second static pressure orifice component may include a venting conduit communicating with the venting orifice, the venting conduit being in fluid communication with the first static pressure orifice component, wherein the venting conduit may be configured to extend in the shape of the fastest curve converging toward the other end of the second static pressure orifice component.

[0020] By designing the air guide pipe in the form of the fastest curve, the hysteresis resistance of the fluid when passing through the pipe can be reduced, making it easier to obtain more accurate static pressure.

[0021] More preferably, the second static pressure hole component may also have an outwardly open mounting hole at one end for installing an airtight clamp.

[0022] By setting mounting holes, the airtight clamps can be easily fixed and connected during the test, thus solving the problems of easy air leakage and detachment of existing clamps.

[0023] Furthermore, the present invention also relates to a static pressure hole system, comprising: a static pressure hole device as described above; a mounting component including a first end near the skin and a second end toward the aircraft interior away from the skin, the mounting component being fixedly connected to the skin at its first end; wherein a first static pressure hole component is fixedly connected to the second end of the mounting component.

[0024] The static pressure hole system of the present invention allows for the fixed installation of one part of the static pressure hole device from the skin towards the aircraft interior, while the other part can be releasably connected to the skin, enabling rapid assembly and disassembly from the outside of the device with a very compact connection structure. Furthermore, since the first and second static pressure hole components are two-piece structures, their relative positions are variable, significantly reducing the requirement for conformal components to overcome step differences.

[0025] In particular, the hydrostatic orifice system may also include a conformal member for adjusting the step difference, the conformal member being fixedly connected to a first end of the mounting member, and a second hydrostatic orifice member being releasably attached to the conformal member at one end thereto.

[0026] By using conformal components, the static pressure orifice step can be precisely adjusted to meet the requirements of civil aircraft. Furthermore, these conformal components can be connected to both the mounting components and the second static pressure orifice component, resulting in a compact arrangement within the static pressure orifice system.

[0027] Preferably, the mounting component is configured as a cylinder, including a bottom disposed at its second end, the bottom including an opening through which a first hydrostatic orifice component can be placed and at least a portion thereof extends through the opening.

[0028] The cylindrical mounting component facilitates the placement of the first static pressure hole component, and the through opening at its bottom makes it easy to connect the first static pressure hole component to other external interfaces.

[0029] The first static pressure orifice component includes an external pipeline connector and / or an external electrical connector in its portion passing through the opening.

[0030] Various connectors exposed from the bottom of the mounting component facilitate fluid and / or electrical connections between the first static pressure orifice component and other components for subsequent static pressure testing.

[0031] The second hydrostatic bore component includes an axially extending conformal component mounting surface, through which the second hydrostatic bore component is connected to the conformal component by a threaded engagement or a form-fit engagement.

[0032] With the help of the specially designed conformal component mounting surface, the second hydrostatic hole component can be easily and quickly releasably installed onto the conformal component, so as to achieve the purpose of quick assembly and disassembly. Attached Figure Description

[0033] Figure 1 A schematic cross-sectional view of a hydrostatic orifice system according to an embodiment of the present invention is shown, wherein a first hydrostatic orifice component and a second hydrostatic orifice component connected to each other are shown;

[0034] Figure 2 An exploded perspective view of a hydrostatic hole system according to an embodiment of the present invention is schematically shown, wherein a conformal component, a mounting component, a first hydrostatic hole component, and a second hydrostatic hole component are shown.

[0035] List of reference numerals in the attached diagram:

[0036] 100 Skin;

[0037] 110 Rivets;

[0038] 200 mounting components;

[0039] 210 (for mounting components) flange;

[0040] 220 First hole;

[0041] 230 Second hole;

[0042] 240 Bottom;

[0043] 242 Through the opening;

[0044] 300 First static pressure hole component;

[0045] 310 External pipeline connector;

[0046] 320 External electrical connector;

[0047] 330 air passage;

[0048] 400 Second static pressure hole component;

[0049] 402 First end;

[0050] 404 Second End;

[0051] 410 Air vent;

[0052] 420 air delivery line;

[0053] 430 mounting holes;

[0054] 440 Conformal component mounting surface;

[0055] 500 intermediate connecting elements;

[0056] 600 Conformal components. Detailed Implementation

[0057] The present invention will be further described below with reference to specific embodiments and accompanying drawings, but this should not be construed as limiting the scope of protection of the present invention.

[0058] Firstly, this invention pertains to the field of aircraft avionics, primarily to a static pressure orifice device and system for aircraft. Although this invention is described in reference to an aircraft, particularly an aircraft fuselage, it should be understood that the static pressure orifice device of this invention is not limited to use on aircraft, but can be used on any equipment requiring static pressure measurement.

[0059] Secondly, the static pressure orifice device or system of the present invention may include components and structures not described in the text or shown in the drawings to enable various product functions of the static pressure orifice device, such as acquiring external atmospheric static pressure and providing feedback to subsequent devices (e.g., barometers). Furthermore, the various drawings of the present invention only schematically illustrate the basic connection relationships between the various components of the static pressure orifice system, and do not specifically show the internal structure and components of the static pressure orifice device, such as fluid elements or circuit elements (e.g., anti-icing heating elements).

[0060] Furthermore, using terms like "first" and "second" merely indicates differences, such as different positions or components, and does not imply any sequential relationship or difference in importance.

[0061] Finally, it is worth noting that the numerical values ​​given in the various embodiments are merely examples and are not intended to limit the scope of the invention.

[0062] The static pressure port device of the present invention can be installed on aircraft, particularly on the skin of the aircraft fuselage, to obtain external atmospheric static pressure. Unlike existing integrated static pressure port devices, the static pressure port device of the present invention comprises at least two components: a first static pressure port component and a second static pressure port component. These two components are not two parts of a single integrated component, but rather two different components that can be separated or manufactured separately.

[0063] The first static pressure port component 300 can be fixedly disposed relative to the aircraft skin 100. Preferably, the first static pressure port component 300 can be fixedly connected to the skin 100. However, it should be understood that such connection can be direct or indirect, for example, by means of mounting components described below. In this invention, the fixation of the first static pressure port component 300 relative to the skin 100 can be a fixation that remains stationary after the static pressure port device or system has been installed in place. For example, tools are required to loosen the fixation of the first static pressure port component 300. Therefore, in this invention, the first static pressure port component 300 can also be referred to as a fixing component or fixing end of the static pressure port device.

[0064] The second static pressure port component 400 may be releasably or easily detachably attached to the skin 100. The second static pressure port component 400 may include one end facing the outside of the aircraft and another end located inside the skin 100 and facing the aforementioned first static pressure port component 300. In this invention, one end and the other end of the second static pressure port component 400 can be understood as its two axial ends, where axial refers to a direction substantially perpendicular to the skin 100. Furthermore, the expression "inside the skin" means the inner side in the direction from the skin (or outside) towards the aircraft interior. In other words, the first static pressure port component 300 is positioned closer to the aircraft interior than the second static pressure port component 400, while the second static pressure port component 400 is closer to the aircraft exterior than the first static pressure port component 300.

[0065] To obtain external atmospheric static pressure, the second static pressure orifice component 400 has a vent 410 at its outward-facing end. Preferably, the vent 410 is annular when viewed from the outside. More preferably, the vents 410 of the second static pressure orifice component 400 are distributed in two concentric rings, inner and outer. In particular, the annular distribution of the vents 410 can be such that the center of the ring is located at the center of the surface at that end of the second static pressure orifice component 400. The surface at that end of the second static pressure orifice component 400 can also be a circular surface, for example, see [reference needed]. Figure 2 .

[0066] In some embodiments, the second static pressure hole component 400 is releasably attached to the skin 100 at one end. Although the second static pressure hole component 400 can be directly attached to the skin 100, it is preferred to connect it indirectly to the skin 100 via other components to provide various possibilities for detachable connection thereto. For example, the second static pressure hole component 400 can be connected to the skin 100 via a conformal member, which will be detailed below. Therefore, in this invention, the second static pressure hole component 400 can also be referred to as a moving part or moving end of the static pressure hole device. Although the term "moving" is used, it should be understood that it is not arbitrarily moving when installed in place or in operation, but should remain stationary relative to the skin 100.

[0067] The second static pressure orifice component 400 can be connected to the first static pressure orifice component 300 at its opposite end facing the first static pressure orifice component 300. Advantageously, the second static pressure orifice component 400 is not directly connected to the first static pressure orifice component 300, although this is also feasible, but it places higher demands on the joint structure of the corresponding connection points of the first and second static pressure orifice components 300. Preferably, the connection between the second static pressure orifice component 400 and the first static pressure orifice component 300 is accomplished by means of an intermediate connecting element 500, that is, the mutually facing ends (or joint portions) of the second static pressure orifice component 400 and the first static pressure orifice component 300 are connected by the intermediate connecting element 500. It is understood that, in order to maintain the function of the static pressure orifice device itself, fluid (generally atmosphere) flowing in from the vent 410 of the second static pressure orifice component 400 can flow from the second static pressure orifice component 400 into the first static pressure orifice component 300 via this intermediate connecting element 500. For this purpose, the intermediate connecting element 500 includes the necessary communication portions or structures.

[0068] In some embodiments, the intermediate connecting element 500 may be configured to have a variable length so that the second hydrostatic orifice component 400 can change its position relative to the first hydrostatic orifice component 300. For example, the intermediate connecting element 500 may be in its first configuration when the hydrostatic orifice device is installed, and in its second configuration when the hydrostatic orifice device is being disassembled for maintenance or replacement. Advantageously, in the first configuration, the length of the intermediate connecting element 500 is minimized, i.e., the distance between the second hydrostatic orifice component 400 and the first hydrostatic orifice component 300 is shortest, while in the second configuration, the length of the intermediate connecting element 500 can be lengthened or extended to increase the distance between the second hydrostatic orifice component 400 and the first hydrostatic orifice component 300.

[0069] More preferably, the intermediate connecting element 500 can be configured as a retractable flexible hose. Alternatively, the intermediate connecting element 500 can also be a foldable telescopic element (which may be non-flexible). In this invention, the expression "change of position" is primarily used to indicate a relative positional change along the axial direction, but does not exclude relative positional changes other than the axial direction, such as lateral or arbitrary positional changes. For example, when the intermediate connecting element 500 is a flexible hose, although the main stretching direction is axial (i.e., generally perpendicular to the surface of the skin 100), there may be relative positional displacements in various directions (between the second hydrostatic hole component 400 and the first hydrostatic hole component 300).

[0070] Thus, as described above, by using a two-piece (or combined) static pressure hole component, quick assembly and disassembly can be achieved from the outside of the static pressure hole, thereby reducing maintenance or replacement costs and saving time.

[0071] The second static pressure orifice component 400 may include an internal air guide pipe 420 communicating with the aforementioned air guide hole 410. This air guide pipe 420 should be in fluid communication with the first static pressure orifice component 300. If an intermediate connecting element 500 is provided between the second static pressure orifice component 400 and the first static pressure orifice component 300, the fluid in the air guide pipe 420 first flows into the intermediate connecting element 500 and then into the first static pressure orifice component 300. It is understood that the term "air guide pipe" can refer to an air guide channel formed by the second static pressure orifice component 400 itself, or it can be a separate air guide pipe inserted into the main structure of the second static pressure orifice component 400, as long as it enables fluid communication to the first static pressure orifice component 300.

[0072] Preferably, the venting conduit 420 can be configured to converge from near one end of the second static pressure orifice component 400 toward the other end. For example, from Figure 1 It can be seen that the distance between the air guide pipe 420 and the axial central axis of the second static pressure orifice component 400 at the end where the air guide hole 410 is located is greater than that at the other end. More preferably, when the air guide holes 410 of the second static pressure orifice component 400 are arranged in two concentric circles, the air guide pipes are also arranged in two concentric circles (each air guide pipe 420 preferably corresponds to one air guide hole 410). For example, both concentric circles of air guide pipes 420 can converge toward the other end of the second static pressure orifice component 400 (in Figure 1 (This is most clearly shown in the cross-sectional view).

[0073] In a particularly advantageous embodiment, the air guide 420 can be configured to extend in the shape of a brachistochrone curve converging towards the other end of the second static pressure orifice 400. Here, the term "brachistochrone curve" is a geometric concept, namely, the line that takes the shortest time for a frictionless particle to travel from one point to another in a vertical plane under the influence of gravity. Designing the air guide 420 in the form of a brachistochrone curve can reduce the hysteresis resistance of the fluid as it passes through the guide. In the prior art, the air guide 420 is generally straight or L-shaped (first vertically downward toward the first static pressure orifice 300, then inward toward the axial central axis of the second static pressure orifice 400 to reach the interface position of the second static pressure orifice 400 facing the first static pressure orifice 300).

[0074] In addition, an airtightness test is required to evaluate the static pressure orifice device. This test involves fixing a clamp onto the device. Current technology often uses suction cup-type airtight clamps for installation, but this can lead to problems such as air leakage and detachment during and after installation.

[0075] In some embodiments of the present invention, the second static pressure orifice component 400 may also have an outwardly open mounting hole 430 at one end for mounting an airtight clamp, so as to facilitate the fixed connection of the airtight clamp and thus improve work efficiency. This mounting hole 430 is typically spaced sufficiently from the air guide hole 410. Preferably, the mounting hole 430 may be located at the center of the surface of that end of the second static pressure orifice component 400, such as... Figure 1 As shown in the image.

[0076] In addition to the aforementioned static pressure orifice device, which is mainly used to obtain the static pressure of the external atmosphere, the present invention also relates to a static pressure orifice system including such a device. This static pressure orifice system, in addition to the device, also includes other means or components for mounting the device on the skin 100 or for performing other functions.

[0077] The static pressure port system may include a mounting component 200 for securing the skin 100 to the first static pressure port component 300. Specifically, the mounting component 200 may include a first end 402 near the skin 100 and a second end 404 extending inwards from the skin 100. The mounting component 200 is secured to the skin 100 at its first end 402 and to the first static pressure port component 300 at its second end 404. Thus, the first static pressure port component 300 can be fixed at a position spaced apart from the skin 100 (within the skin or inwards), which helps to provide sufficient space for the placement of the second static pressure port component 400. On the other hand, it also allows the second static pressure port component 400, as the "moving end," to be located outside the static pressure port assembly, while the first static pressure port component 300, as the "fixed end," is located inside the static pressure port assembly. In other words, maintenance or replacement operations can be performed without involving the first static pressure port component 300 located at a certain distance inside the skin 100.

[0078] In some embodiments, such as Figure 2 As shown, the mounting component 200 can be configured as a cylinder. This cylindrical structure can extend generally axially (i.e., inwardly from near the skin 100) and is open at least at its first end 402. Optionally, the cylindrical structure has a laterally extending flange 210 at its first end 402 for secure connection to the skin 100, for example, by means of a threaded fastener.

[0079] The cylindrical structure may include a bottom 240 located at its second end 404 (i.e., the second end 404 of the cylindrical structure is not fully open). Preferably, the bottom 240 may include an opening 242 on which the first static pressure orifice component 300 can be mounted, and at least a portion of the first static pressure orifice component 300 extends through the opening 242 (further away from the skin 100). For example, the portion of the first static pressure orifice component 300 extending through the opening 242 may include an external pipeline connector 310 and / or an external electrical connector 320, wherein the external pipeline connector 310 is used to connect to the aircraft's static pressure conduit (i.e., fluid flowing into the first static pressure orifice component 300 further flows into the static pressure conduit), and the external electrical connector 320 is used to receive power input to the anti-icing heating element or part of the static pressure orifice device. It is understood that the interior of the first static pressure orifice component 300 may also be provided with a venting passage 330 to allow fluid flowing into it to flow through the venting passage 330 to the external pipeline connector 310.

[0080] However, this is not mandatory. For example, the first hydrostatic orifice component 300 can also be substantially located inside the mounting component 200, without any portion extending out of the mounting component 200. In this case, however, an external connector is required to extend into the mounting component 200 for fluid and / or electrical connection with the first hydrostatic orifice component 300.

[0081] In theory, the outer surface of the static pressure orifice device should be completely flush with the outer surface of the aircraft skin 100. However, in practice, due to manufacturing errors, installation errors, and the coating on the outer surface of the skin, the outer surface of the static pressure orifice device may be higher or lower than the outer surface of the aircraft skin, i.e., there is a step difference, which causes static pressure error. This will result in errors in the subsequently calculated atmospheric parameters such as air pressure and altitude, greatly affecting the error of the altitude measurement system. To solve this problem, the static pressure orifice system of the present invention may include a conformal component 600 for adjusting the aforementioned step difference. The conformal component 600 may be constructed in the form of a conformal plate.

[0082] It is worth noting that since the first and second static pressure hole components of the static pressure hole device are designed as a two-piece structure, they are independent of each other; for example, their relative positions are variable. This significantly reduces the requirement to use conformal components to overcome the step difference. More specifically, the thickness of the conformal component (e.g., the external step difference) is only limited by the thickness of the skin, and as long as both maintain the same manufacturing tolerances, they can remain compatible. The second static pressure hole component does not affect the step difference because its connection as a "moving end" ensures that its outer surface is flush with the outer surface of the conformal component (as mentioned earlier, this can be achieved using threads, snaps, etc.). In contrast, in the prior art, adjustable shims, rubber shims, etc., need to be added between the outer surface of the aircraft skin and the conformal plate to achieve precise adjustment of the static pressure hole step difference, meeting the requirements of civil aircraft for static pressure hole step difference. These are not needed in this invention, yet the same accuracy requirements are achieved, which significantly reduces structural complexity and improves operational flexibility and ease of use.

[0083] exist Figure 2 In the illustrated embodiment, the conformal member is a conformal plate with an opening in the middle, but this is not a mandatory structure. The size and shape of the conformal member 600 are directly related to the skin 100 of the static pressure hole device mounting area. The conformal member 600 can be fixedly connected to the mounting member 200 at its first end 402, while the second static pressure hole member 400 can also be releasably attached to the conformal member 600 at one end. Thus, the second static pressure hole member 400 can be releasably attached to the skin 100.

[0084] exist Figure 2In this design, the second static pressure hole component 400 may be located within or engage with the central opening of the conformal plate. Specifically, the second static pressure hole component 400 may include an axially extending conformal component mounting surface 440, through which the second static pressure hole component 400 may be connected to the conformal component 600 by means of a threaded engagement or other form-fitting engagement. Preferably, the engagement between the second static pressure hole component 400 and the conformal component 600 may be a threaded connection, a snap-fit ​​connection (e.g., snap-fit ​​quick-installation), a tenon connection, etc. Of course, the second static pressure hole component 400 may also include a non-axially extending surface to engage with a corresponding portion of the conformal component 600, but this is not shown in the drawings.

[0085] Next, let's use... Figure 2 The structural arrangement of the hydrostatic orifice system according to the present invention will be further explained.

[0086] exist Figure 2 In this embodiment, the skin 100 is exemplarily shown in the form of a generally flat disc-shaped element (but the invention is not limited to this shape), the central opening of which should be large enough to accommodate the hydrostatic orifice device and allow it to be exposed to the outside. Holes, such as rivet holes, are provided on the skin 100 for fixed connection with the mounting component 200.

[0087] The mounting component 200 may be generally cylindrical, having a length extending axially. A flange 210 is integrally formed at its first end 402, which is also generally flat and disc-shaped, and a first hole 220 is provided on the flange 210 corresponding to the position of the hole in the aforementioned skin 100. For example... Figure 2 As shown, the first hole 220 is located near the outer periphery of the flange 210 of the mounting member 200. A rivet 110 for securing the connection can pass through both the hole in the skin 100 and the first hole 220 of the mounting member 200. The mounting member 200 has a bottom 240 at its second end 404, on which an opening 242 (in...) is provided. Figure 2 (Not visible in the image). The size of the through opening 242 is smaller than the size of the opening at its first end 402 of the mounting component 200. The through opening 242 mainly facilitates the connection of various connectors of the first static pressure hole component 300, such as external electrical connector 320 and external pipeline connector 310, to components outside the static pressure hole device.

[0088] exist Figure 2In this invention, the first static pressure hole component 300 can be constructed in a generally plate-like shape (i.e., the thickness of the main body, excluding various connectors, is significantly smaller than its lateral dimension, for example, significantly smaller than its diameter dimension), but the invention is not limited to this shape. Holes, such as screw holes, are provided on this plate-like portion for connection with the mounting component 200. Here, an interface portion (or connector) for connection with the second static pressure hole component 400, or rather, with the intermediate connecting element 500, is formed at the end of the first static pressure hole component 300 opposite to the end where the external electrical connector 320 and external pipeline connector 310 are located.

[0089] Furthermore, the second static pressure orifice component 400 can be configured in a generally bowl-shaped or lotus-pod-shaped manner, with an air guide hole 410 at its outermost end, preferably distributed in an inner ring and an outer ring (see...). Figure 2 Specifically, the air guide hole 410 on the inner ring is at the same first distance from the axial central axis (not shown) of the second static pressure hole component 400, and the air guide hole 410 on the outer ring is at the same second distance from the axial central axis of the second static pressure hole component 400, wherein the first distance is less than the second distance. For connection with the conformal component 600, the outer contour of the second static pressure hole component 400 (e.g., bowl-shaped) has an axially extending contour portion at its first end 402, i.e., a non-curved contour portion, which is referred to as the conformal component mounting surface 440. The second static pressure hole component 400 has an interface (or connector) at its second end 404 for connection with the first static pressure hole component 300 or the intermediate connecting element 500.

[0090] exist Figure 2 In this design, the conformal member 600 can be constructed as a generally flat plate, and thus can be called a conformal plate. The conformal plate has multiple screw holes, which correspond to the positions of a second hole 230 located closer to the center of the flange 210 of the mounting member 200 (i.e., the second hole 230 is closer to the center of the mounting member 200 than the first hole 220), to securely connect the conformal plate to the mounting member 200 using fasteners. The central opening of the conformal plate is adapted to be releasably connected to the conformal member mounting surface 440 of the second hydrostatic hole member 400, for example, by threaded installation, snap-fit ​​installation (quick-release installation), tenon-and-mortise installation, adhesive bonding, etc. Typically, the outer dimension of the conformal member 600 is smaller than the outer dimension of the mounting member 200 (flange 210), while the outer dimension of the mounting member 200 is larger than the size of the central opening of the skin 100, but smaller than the outer dimension of the skin 100.

[0091] Although various embodiments of the invention are described in the accompanying drawings with reference to a hydrostatic hole system installed on the skin of an aircraft, it should be understood that embodiments of the pallet nut within the scope of the invention can be applied to applications on other vehicles with similar structures and / or functions.

[0092] The foregoing description has already given many features and advantages, including various alternative implementations, as well as details of the structure and function of the apparatus and methods. This document is intended to be exemplary and is not exhaustive or limiting.

[0093] It will be apparent to those skilled in the art that various modifications can be made within the full scope indicated by the broad superordinate meaning of the terms expressed in the appended claims, particularly in terms of structure, materials, elements, components, shapes, dimensions, and arrangements of components, including combinations of these aspects within the scope of the principles described herein. Such various modifications are intended to be included herein, provided they do not depart from the spirit and scope of the appended claims.

Claims

1. A static pressure orifice device for an aircraft, characterized in that, The static pressure orifice device includes: A first static pressure hole component (300) is fixedly disposed relative to the skin (100) of the aircraft; A second static pressure orifice component (400) includes one end facing the outside of the aircraft and another end located inside the skin (100) and facing the first static pressure orifice component (300). The second static pressure orifice component (400) has an air vent (410) at one end for sensing external static pressure and is releasably attached to the skin (100), and is connected to the first static pressure orifice component (300) at the other end. It also includes an intermediate connecting element (500) for connecting the other end of the second static pressure orifice component (400) to the first static pressure orifice component (300) so that fluid flowing in from the air vent (410) can flow from the second static pressure orifice component (400) to the first static pressure orifice component (300) via the intermediate connecting element (500). The intermediate connecting element (500) is configured to have a variable length so that the second static pressure orifice component (400) can change its position relative to the first static pressure orifice component (300).

2. The static pressure orifice device as described in claim 1, characterized in that, The intermediate connecting element (500) is configured as a retractable hose.

3. The static pressure orifice device as described in claim 1 or 2, characterized in that, The second static pressure orifice component (400) includes an air guide line (420) communicating with the air guide orifice (410), the air guide line (420) being in fluid communication with the first static pressure orifice component (300), wherein the air guide line (420) is configured to extend in the shape of a fastest curve converging toward the other end of the second static pressure orifice component (400).

4. The static pressure orifice device as described in claim 1 or 2, characterized in that, The second static pressure hole component (400) is also provided at one end with an outwardly open mounting hole (430) for installing an airtight clamp.

5. A static pressure orifice system, characterized in that, The static pressure orifice system includes: The static pressure orifice device as described in any one of claims 1 to 4; Mounting component (200) includes a first end (402) near the skin (100) and a second end (404) toward the interior of the aircraft away from the skin (100), the mounting component (200) being fixedly connected to the skin (100) at its first end (402). The first static pressure hole component (300) is fixedly connected to the second end (404) of the mounting component (200).

6. The hydrostatic orifice system as described in claim 5, characterized in that, It also includes a conformal component (600) for adjusting the step difference, the conformal component (600) being fixedly connected to the first end (402) of the mounting component (200), and the second hydrostatic hole component (400) being releasably attached to the conformal component (600) at one end thereto.

7. The hydrostatic orifice system as described in claim 5, characterized in that, The mounting component (200) is configured in a cylindrical shape and includes a bottom (240) disposed at its second end (404), the bottom (240) including a through opening (242) on which the first hydrostatic hole component (300) can be placed and at least a portion thereof extends through the through opening.

8. The hydrostatic orifice system as described in claim 7, characterized in that, The first static pressure hole component (300) passing through the opening (242) includes at least a portion of an external pipeline connector (310) and / or an external electrical connector (320).

9. The hydrostatic orifice system as described in claim 6, characterized in that, The second hydrostatic hole component (400) includes an axially extending conformal component mounting surface (440), through which the second hydrostatic hole component (400) is connected to the conformal component (600) by means of the conformal component mounting surface (440) via a threaded engagement or a form-fit engagement.

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