Water-blocking device and landing gear equipped with the water-blocking device

Abstract

This utility model relates to a water-blocking device, comprising: a first mounting part (1), one end of which is mounted on the landing gear; a connecting rod (3), one end of which is connected to the other end of the first mounting part (1); an adaptive adjustment component (4), one end of which is connected to the other end of the connecting rod (3); a water deflector (5), which is rotatably connected to the other end of the adaptive adjustment component (4) so ​​that the water deflector (5) is located on the rear side of the landing gear in the direction of flight of the aircraft; and a second mounting part (2), one end of which is connected to the water deflector (5), and the other end of which is mounted on the wheel axle of the landing gear. This water-blocking device can be used on aircraft with a tail-mounted engine layout and can effectively block the splashing water of the "chicken tail" jet.

Description

Technical Field

[0001] This utility model relates to the field of aircraft structure, specifically to a water deflector for aircraft landing gear, and more specifically, to a water deflector for aircraft landing gear with a tail-mounted engine layout. Background Technology

[0002] When an aircraft taxis on a runway covered in water or snow, water splashed from the tires can enter the engines on both sides of the aircraft, potentially causing a decrease in engine thrust, surge, stall, and performance degradation, directly affecting the aircraft's stability and safety. This impact is particularly severe for aircraft with tail-mounted engine layouts.

[0003] The water splash generated by the aircraft landing gear mainly includes the "bow wave," "lateral plume," and "tail flow." When the aircraft is taxiing, under the condition that the runway water depth remains constant, at lower aircraft speeds, the "bow wave" in front of the landing gear is the primary splash, while less splash occurs on the sides of the landing gear. As speed increases, the intensity of the "bow wave" gradually decreases and stabilizes, while the intensity of the "lateral plume" and "tail flow" continuously increases and their splash positions rise. Therefore, in practice, it is usually not necessary to block the "bow wave." When the aircraft speed approaches its skidding speed, the intensity of the "lateral plume" and "tail flow" reaches its maximum, at which point the water splash intensity also reaches its maximum and its highest position. For tail-mounted engines, the "chicken tail" jet formed between the nose landing gear wheels is usually blocked by the fuselage. However, the "chicken tail" jet formed between the main landing gear wheels may enter the engine's air intake. Compared to "lateral plumes," the formation and shape of "chicken tails" are more complex, with larger water volume, greater splash intensity, and higher height, which may cause more serious harm to aircraft safety.

[0004] In existing technologies, the main measure to solve the water splash problem is to install water deflectors on the landing gear or wheels to suppress the water flow and prevent it from entering the engine. Several types of water deflectors exist in the prior art. One type involves adding water deflectors to the sides and rear of the wheels. While this type of water deflector can effectively block the splashing water from the "lateral plume," its complex structure and heavy weight make it unsuitable for some small and medium-sized aircraft.

[0005] Another existing water-blocking device is the lateral guide vane installed on the side of the landing gear. This vane, with its outward tilt, guides and blocks the splashing water from the "lateral plume." However, this water-blocking structure only improves the splashing of the "lateral plume" and does not provide effective blocking of the "tail jet." The "tail jet" is formed by the convergence of water flows between the landing gears. Compared to the "bow wave" and "lateral plume," it has a more complex shape, greater splash intensity, and higher height. Typically, the "tail jet" formed by the nose landing gear wheels can be blocked by the fuselage, but the "tail jet" formed by the main landing gear wheels on both sides may enter the engine. Therefore, for engines with a tail-mounted layout, the "tail jet" formed by the main landing gear wheels is more critical to block.

[0006] Another type of water-blocking device exists in the prior art, which involves installing a baffle plate on the axle between the wheels to block the splashing water generated between the wheels. Although this arrangement of baffle plates can block the splashing water of the "chicken tail flow" to a certain extent, it cannot adaptively adjust the angle of the baffle plate according to the actual usage scenario to effectively block splashing water under different conditions.

[0007] In summary, there is an urgent need for a water deflector with a simple structure that can be applied to aircraft with tail-mounted engine layouts, effectively blocking the splashing water from the "chicken tail" and having the function of adaptively adjusting the angle of the deflector according to the intensity of the splashing water. Utility Model Content

[0008] This invention was made in view of the above-mentioned problems, and its purpose is to provide a water-blocking device for aircraft landing gear, which has a simple structure and can more effectively block the splashing water of "chicken tail stream".

[0009] This utility model provides a water-blocking device, which is installed on an aircraft landing gear and includes:

[0010] A first mounting part, one end of which is mounted on the landing gear;

[0011] A connecting rod, one end of which is connected to the other end of the first mounting part;

[0012] An adaptive adjustment component, one end of which is connected to the other end of the linkage;

[0013] A water deflector, the other end of which is rotatably connected to the adaptive adjustment assembly so that the water deflector is positioned rearward on the landing gear in the direction of flight; and

[0014] The second mounting part has one end connected to the water deflector and the other end mounted on the landing gear wheel axle.

[0015] In another embodiment of this invention, preferably, the adaptive adjustment component can also be implemented as a hydraulic cylinder assembly, which includes a hydraulic cylinder and a hydraulic rod. One end of the hydraulic cylinder assembly is connected to one end of a connecting rod, and the other end of the hydraulic cylinder assembly is connected to a baffle plate in a rotatable manner.

[0016] In another embodiment of this invention, the baffle plate is configured such that its thickness gradually decreases from its center to its edge. Preferably, the baffle plate is configured as a spatial curved surface shape that protrudes relative to the second mounting portion in a direction away from the second mounting portion.

[0017] The present invention also provides a landing gear, which may include the water-blocking device as described in any of the foregoing embodiments, wherein the water-blocking device is connected to the landing gear strut via a first mounting portion and the water-blocking device is connected to the landing gear wheel axle via a second mounting portion.

[0018] In another embodiment of the landing gear of this invention, the water deflector is arranged to cover the space between a pair of wheels located on the rear side of the landing gear in the direction of flight of the aircraft.

[0019] Preferably, the width of the water deflector plate of the water deflector in the transverse direction of the aircraft's travel is approximately 40% to 60% of the distance between a pair of wheels.

[0020] In summary, the water-blocking device of this invention has a simple structure and light weight, meeting the water-blocking requirements of small and medium-sized aircraft and offering economic benefits. It effectively blocks "tail-spray" water and is suitable for aircraft with tail-mounted engine layouts, preventing water from entering the engine due to "tail-spray." Furthermore, because the water-blocking device incorporates an adaptive adjustment component, namely a hydraulic cylinder assembly, this component can effectively adjust the angle of the water-blocking plate based on ground undulations and the intensity of the splash, thus coping with "tail-spray" water of varying intensities. Additionally, the simple structure and modular design of this water-blocking device facilitate disassembly and replacement during assembly or maintenance. Attached Figure Description

[0021] The accompanying drawings are provided only to further illustrate the present invention and constitute a part of this specification. They are used to explain the principles of the present invention and do not constitute a limitation thereof.

[0022] In the diagram:

[0023] Figure 1 This is a schematic diagram of a water-blocking device in the prior art;

[0024] Figure 2 This is a schematic diagram of another water-blocking device in the prior art;

[0025] Figure 3 This is a schematic diagram of another water-blocking device in the prior art;

[0026] Figure 4 This is a schematic diagram of a water-blocking device according to an embodiment of the present invention;

[0027] Figure 5 This is a schematic diagram of a landing gear equipped with a water-blocking device according to the present invention.

[0028] List of reference numerals

[0029] 1. First Installation Department;

[0030] 2. Second Installation Section;

[0031] 3-link system;

[0032] 4. Adaptive adjustment component;

[0033] 41. Hydraulic cylinder;

[0034] 42. Hydraulic rod;

[0035] 5. Water baffles;

[0036] 51 arms;

[0037] 52 mounting brackets;

[0038] 100 Water-blocking device;

[0039] W represents the width of the water-retaining plate. Detailed Implementation

[0040] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present application.

[0041] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such terms can be used interchangeably where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion.

[0042] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate directions or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated devices, elements, or components to having a specific orientation, or to be constructed and operated in a specific orientation.

[0043] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in certain circumstances to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application according to the specific circumstances.

[0044] Furthermore, the terms "installation," "setting," "arrangement," "equipped with," "connection," and "socketing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral structure; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediary medium; or they can refer to the internal communication between two devices, components, or parts. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0045] The following explanations are needed for some of the terms used in this utility model.

[0046] Based on the landing gear, the direction of water splash is divided into forward, lateral, and aft. According to the different directions of water splash, the types of water splash include "bow wave", "lateral plume", and "tail flow".

[0047] Bow wave: also known as the pre-wheel plume, specifically refers to the splashing water formed when the forward compression of the aircraft wheels causes water accumulated on the runway to be squeezed in front of the aircraft wheels.

[0048] Lateral plume: Specifically refers to the splashing water formed when water on the runway is squeezed to the side of the aircraft's wheels due to the lateral compression of the wheels.

[0049] Chicken tail flow: also known as "intermediate feather flow", specifically refers to the splashing water generated by the interaction between the landing gear and the aircraft wheels due to the structure of the landing gear.

[0050] A pair of wheels: also known as a "set of wheels" or "wheel assembly," consists of two separate wheels. Aircraft typically have three pairs of wheels: one pair mounted on the nose landing gear and two pairs mounted on the main landing gear. Figure 1 and Figure 3 As shown, each example depicts a pair of wheels.

[0051] Figure 4 This is a schematic diagram of a water-blocking device 100 according to an embodiment of the present invention. The water-blocking device 100 includes a first mounting part 1, a connecting rod 3, an adaptive adjustment component 4, and a water-blocking plate 5. One end of the first mounting part 1 is sleeved on the landing gear strut, and the other end is rotatably connected to one end of the connecting rod 3. The other end of the connecting rod 3 is connected to one end of the adaptive adjustment component 4. The other end of the adaptive adjustment component 4 is rotatably connected to the water-blocking plate 5 via a mounting seat 52 provided on the water-blocking plate 5. The water-blocking device 100 also includes two opposingly arranged second mounting parts 2. The water-blocking plate 5 has two opposingly arranged support arms 51 on its longer sides, and these two support arms 51 extend in the direction from the water-blocking plate 5 to the second mounting parts 2. The two support arms 51 are respectively rotatably connected to one end of the two opposingly arranged second mounting parts 2. The other ends of the two opposingly arranged second mounting parts 2 are respectively connected to the wheel axles of the landing gear. Figure 4 As shown, the adaptive adjustment component 4 can be implemented as a hydraulic cylinder 41 assembly, which includes a hydraulic cylinder 41 and a hydraulic rod 42. The inner and outer surfaces of the baffle 5 are preferably arc-shaped curved surfaces, spatial curved surface shapes that bulge away from the second mounting portion 2. Of course, the inner and outer surfaces can also be implemented as planes. The baffle 5 is configured such that its thickness gradually decreases from its center to its edge.

[0052] like Figure 4 As shown, the width W of the water deflector 5 in the transverse direction of the aircraft's travel is mainly related to the distance between the wheels on the same side and the splash angle, and is preferably 40% to 60% of the distance between a pair of wheels.

[0053] Figure 5 This is a schematic diagram of a landing gear equipped with a water-blocking device 100 according to the present invention. The landing gear includes the water-blocking device 100 according to the present invention, wherein the water-blocking device 100 is connected to the landing gear via a first mounting part sleeved on the aircraft landing gear strut, and the water-blocking device 100 is further connected to the landing gear via two oppositely arranged second mounting parts rotatably connected to the landing gear wheel axles.

[0054] Figure 1 This is a schematic diagram of a prior art water-blocking device. The device includes side deflectors and a rear deflector. While this type of water-blocking device can effectively block splashes from "lateral plumes" and "tail jets," its complex structure and heavy weight make it unsuitable for use with small and medium-sized aircraft.

[0055] Figure 2This is a schematic diagram of another existing water-blocking device. This device includes side deflectors and primarily addresses water splashing from the sides of aircraft tires, i.e., "lateral plume" splashes. It is unsuitable for aircraft with tail-mounted engines because the main splash affecting this type of aircraft is the "tail-like" splash. Since the engines of tail-mounted aircraft are located in the middle and rear of the aircraft, the "tail-like" splash from the main landing gear can bypass the wings and enter the engine, thus affecting aircraft performance. Therefore... Figure 2 The existing technology device shown is also not applicable to aircraft with tail-mounted engine layouts.

[0056] Figure 3 This is a schematic diagram of another existing water-blocking device. This device is a water-blocking plate mounted on the axle between the landing gear wheels. While this water-blocking plate can block "tail spray" water to some extent and is suitable for aircraft with tail-mounted engines, it is fixed to the landing gear and cannot adaptively adjust its angle according to actual operating conditions or splash intensity to ensure effective water blocking. Functionally, this structure only changes the splash pattern from the landing gear and has no related water-guiding function. Structurally, this structure is installed by bolting it to the main landing gear's buffer strut at a certain angle, and it lacks active or adaptive adjustment components. In comparison, while this invention also solves the problem of water splashing in a "chicken tail" spray pattern, it still has the following differences. Firstly, functionally, while reducing the splash angle, the multi-curved surface design effectively guides the water flow away from the engine, thereby reducing the amount of water splashing into the engine intake. The hydraulic cylinder assembly allows for adjustment of the baffle's tilt angle to adapt to splashing conditions under different ground conditions and can also buffer the large load of splashing water to a certain extent, preventing component damage. Structurally, the water guiding mechanism is designed as a modular structure, facilitating disassembly, replacement, and maintenance.

[0057] In summary, the water-blocking device of this invention has a simple structure and low weight, meeting the water-blocking requirements of small and medium-sized aircraft without increasing takeoff weight, thus offering economic benefits. It effectively blocks "tail-spray" water and is suitable for aircraft with tail-mounted engine layouts, preventing water from entering the engine through the wing. Furthermore, the inclusion of an adaptive adjustment component, i.e., a hydraulic cylinder assembly, allows the water-blocking device to effectively adjust the angle of the deflector based on ground undulations and water splash intensity to cope with varying degrees of "tail-spray" water. Additionally, the simple structure and modular design of this water-blocking device facilitate disassembly and replacement during assembly or maintenance.

[0058] The implementation of this utility model is not limited to the embodiments described above, and can be adjusted and optimized according to different design requirements and usage environments. The scope of protection of this utility model should be determined by the content of the claims, and not limited to the embodiments described above. Although this utility model has been described through specific embodiments, any modifications, changes, and combinations made by those skilled in the art to various embodiments and implementation methods of this utility model without departing from the spirit of this utility model should be within the scope of protection of this utility model.

Claims

1. A water deflector device (100) for mounting to an aircraft landing gear, characterised in that, include: First mounting part (1), one end of the first mounting part (1) is mounted on the landing gear; Link (3), one end of which is connected to the other end of the first mounting part (1); An adaptive adjustment component (4) is provided, one end of which is connected to the other end of the connecting rod (3); A water deflector (5) is connected to the other end of the adaptive adjustment assembly (4) in a rotatable manner so that the water deflector (5) is located on the rear side of the landing gear in the direction of travel of the aircraft. as well as The second mounting part (2) is connected at one end to the water baffle (5) and at the other end to the landing gear wheel axle.

2. The water-blocking device (100) according to claim 1, characterized in that, The adaptive adjustment component (4) can be implemented as a hydraulic cylinder assembly, one end of which is connected to one end of the connecting rod (3), and the other end of which is connected to the baffle plate (5) in a way that allows relative rotation.

3. The water-blocking device (100) according to claim 1, characterized in that, The water baffle (5) is configured such that the thickness of the water baffle (5) gradually decreases from its center to its edge.

4. The water-blocking device (100) according to claim 1, characterized in that, The water baffle (5) is configured as a spatial curved surface shape that protrudes away from the second mounting part (2) relative to the second mounting part (2).

5. A landing gear comprising a strut and a wheel axle, characterized in that The landing gear is equipped with a water-blocking device (100) according to any one of claims 1 to 4, the water-blocking device (100) being connected to the strut of the landing gear via the first mounting part (1), and the water-blocking device (100) being connected to the wheel axle of the landing gear via the second mounting part (2).

6. The landing gear according to claim 5, characterized in that, The water-blocking device is arranged to cover the space between a pair of wheels on the rear side of the landing gear in the direction of travel of the aircraft.

7. The landing gear according to claim 5, characterized in that, The width (W) of the water deflector in the transverse direction of the aircraft's travel is approximately 40% to 60% of the distance between a pair of wheels.

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