Sand prevention device for aircraft

Abstract

The invention relates to an aircraft sand prevention device which comprises a first panel, a second panel and a third panel, the first panel and the second panel are arranged along a first face, a cavity is defined by the third panel and the first panel and the second panel, separation assemblies are evenly arranged between the first panel and the second panel, and the sand prevention device further comprises a discharging assembly. And a part of the separating assembly and a part of the discharging assembly respectively act on the cavity to realize sand prevention. According to the sand removal device, the separation assembly is arranged, sand in air is subjected to inertia separation through the first guide part and the second guide part and enters the cavity, the power part is arranged in the second pipe, the power part can act while air flows through the second pipe, and then the sand in the cavity is discharged; and the separated sand can be discharged to the external environment through the discharging assembly.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to an aircraft sand prevention device. Background Art

[0002] Helicopters are often used to perform various special tasks, such as transportation, patrol, search and rescue, etc., due to their good maneuverability and flexibility. These tasks often need to be carried out in harsh natural environments such as sand, dust, salt spray, rain, etc. Especially when flying in dusty environments, if there is no effective sand prevention device, a large amount of sand and dust will enter the engine, causing serious wear and tear of the internal parts of the engine, and even causing failures. Therefore, sand prevention devices are of great significance to ensure the safe flight of helicopters in harsh environments. Summary of the invention

[0003] In view of the above-mentioned shortcomings of the prior art, an object of the present invention is to provide an aircraft sand control device to solve one or more problems in the prior art.

[0004] To achieve the above object, the technical solution of the present invention is as follows: An aircraft sand control device includes a first panel and a second panel arranged along a first aspect, and a third panel enclosed with the first panel and the second panel to form a chamber, separation components are evenly arranged between the first panel and the second panel, and the sand control device also includes a discharge component, and the separation component and a part of the discharge component act on the chamber respectively to achieve sand control.

[0005] Furthermore, the separation component includes a first tube, a protrusion is arranged on the surface of the first tube, the protrusion is respectively matched with the first panel and the second panel, a first guide member is arranged inside one end close to the first panel, the first guide member has a first arc surface and a second arc surface, and a depression is formed at the intersection of the first arc surface and the second arc surface.

[0006] Furthermore, a second guide is provided near the first panel on the first tube, the second guide is coaxially arranged with the first tube, and the end face diameter of the second guide near the first panel is smaller than the end face diameter of the first tube near the first panel.

[0007] Furthermore, the second guide member is connected to the first guide member, and the second guide member has a third arc surface, and the third arc surface matches the first arc surface.

[0008] Furthermore, a partition and a second tube coaxially arranged with the first tube are connected inside the first tube, the second tube is respectively connected to the first guide member and the partition, and the second tube has a fourth curved surface near the second panel.

[0009] Furthermore, a first hole is opened in the depression where the first arc surface and the second arc surface meet, the first guide member, the partition plate and the second tube together form a cavity, and the first hole leads to the cavity.

[0010] Furthermore, the wall of the second tube is evenly provided with power parts in the cavity area, and the power parts include a first blade, a second blade and a linkage shaft connecting the first blade and the second blade, and the linkage shaft passes through the wall of the second tube, the first blade is located in the second tube, and the second blade is located in the cavity.

[0011] Furthermore, the first tube is evenly provided with second holes on the surface of the cavity area.

[0012] Furthermore, the discharge assembly includes a third tube and a fourth tube, the fourth tube is symmetrically arranged at the intersection of the third tube and the fourth tube, and injection parts are evenly arranged on the surface of the fourth tube.

[0013] Furthermore, a fifth tube is arranged near the injection member, the fifth tube and the injection member are arranged coaxially, the diameter of the fifth tube increases from one end close to the injection member to one end away from the injection member, and the fifth tube is inclined relative to the second direction and arranged in the opposite direction.

[0014] Compared with the prior art, the beneficial technical effects of the present invention are as follows: The present invention sets a separation component, wherein the first guide member and the second guide member perform inertial separation on the sand in the air and allow the sand to enter the cavity, and sets a power member in the second tube, so that the power member can be activated while the gas flows through the second tube, thereby discharging the sand in the cavity, and then the separated sand can be discharged to the external environment through the discharge component. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 A schematic structural diagram of an aircraft sand prevention device according to an embodiment of the present invention is shown.

[0016] Figure 2 A schematic structural diagram of a separation assembly of an aircraft sand prevention device according to an embodiment of the present invention is shown.

[0017] Figure 3 An axonometric view of a separation assembly of an aircraft sand control device according to an embodiment of the present invention is shown.

[0018] Figure 4 A schematic cross-sectional structure diagram of a separation component of an aircraft sand prevention device according to an embodiment of the present invention in the AA direction is shown.

[0019] Figure 5A schematic structural diagram of a discharge assembly of an aircraft sand control device according to an embodiment of the present invention is shown.

[0020] Markings in the accompanying drawings: 1, first panel; 2, second panel; 3, separation component; 301, first tube; 3011, protrusion; 3012, second hole; 302, first guide member; 3021, first arc surface; 3022, second arc surface; 3023, first hole; 303, second guide member; 3031, third arc surface; 304, partition; 305, second tube; 3051, fourth arc surface; 306, cavity; 307, power member; 3071, first blade; 3072, second blade; 3073, linkage shaft; 4, third panel; 5, discharge component; 501, third tube; 502, fourth tube; 503, injection member; 504, fifth tube. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solution and advantages of the present invention clearer, the following is a further detailed description of an aircraft sand control device proposed by the present invention in combination with the accompanying drawings and specific embodiments. According to the following description, the advantages and features of the present invention will be clearer. It should be noted that the accompanying drawings are in a very simplified form and all use non-precise proportions. The terms "center", "lateral", "length", "width", "height", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "side" and the like indicate the orientation or position relationship based on the orientation or position relationship shown in the accompanying drawings, rather than indicating or implying that the aircraft sand control device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention, but only to facilitate and clearly assist in explaining the purpose of the embodiments of the present invention. In order to make the purpose, features and advantages of the present invention more obvious and easy to understand, please refer to the accompanying drawings.

[0022] It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings in this specification are only used to match the contents disclosed in the specification so as to facilitate understanding and reading by persons familiar with this technology, and are not used to limit the conditions for the implementation of the present invention. Therefore, they have no substantive technical significance. Any modification of the structure, change in the proportion relationship or adjustment of the size shall still fall within the scope of the technical contents disclosed in the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0023] The specific structure of an aircraft sand control device is described below: See also Figure 1 and Figure 5The aircraft sand prevention device of this embodiment includes a first panel 1 and a second panel 2 arranged along a first direction, and a third panel 4 enclosed with the first panel 1 and the second panel 2 to form a chamber. The first direction in this embodiment is perpendicular to the first panel 1 and the second panel 2 and is a direction from the first panel 1 to the second panel 2.

[0024] Please continue reading Figure 2 and Figure 3 Furthermore, corresponding slots are evenly provided on the surfaces of the first panel 1 and the second panel 2, and a separation component 3 is evenly arranged between the first panel 1 and the second panel 2. The separation component 3 includes a first tube 301, and a protrusion 3011 is arranged on the surface of the first tube 301. In the present embodiment, two protrusions 3011 are arranged, and the protrusions 3011 are respectively matched with the first panel 1 and the second panel 2 to fix the separation component 3.

[0025] Please continue reading Figure 4 A first guide member 302 is provided at one end near the first panel 1. The first guide member 302 has a first curved surface 3021 and a second curved surface 3022. A depression is formed at the intersection of the first curved surface 3021 and the second curved surface 3022. A second guide member 303 is also provided near the first panel 1 of the first tube 301. The second guide member 303 is connected to the first guide member 302. The second guide member 303 is coaxially arranged with the first tube 301. The end face diameter length of the second guide member 303 near the first panel 1 is smaller than the end face diameter length of the first tube 301 near the first panel 1.

[0026] Furthermore, the second guide member 303 has a third curved surface 3031, and the third curved surface 3031 is matched with the first curved surface 3021. Air enters the first tube 301 along the first curved surface 3021 and the third curved surface 3031 from the gap between the first guide member 302 and the second guide member 303 along the first direction, and under the acceleration provided by the first curved surface 3021 and the third curved surface 3031, sand in the air is separated from the airflow under the action of inertia and then falls into the concave where the first curved surface 3021 and the second curved surface 3022 meet.

[0027] Furthermore, a partition 304 and a second tube 305 coaxially arranged with the first tube 301 are connected to the first tube 301, and the second tube 305 is respectively connected to the first guide member 302 and the partition 304. The second tube 305 also has a fourth curved surface 3051 near the second panel 2. By setting the second tube 305 and the fourth curved surface 3051, the airflow after the sand is separated flows in the second tube 305 along the first direction, diffuses through the fourth curved surface 3051 and then enters the engine compartment.

[0028] Furthermore, a first hole 3023 is opened in the depression where the first curved surface 3021 and the second curved surface 3022 meet, and the first guide member 302, the partition plate 304 and the second tube 305 enclose a cavity 306. The first hole 3023 leads to the cavity 306, so that the sand deposited in the depression where the first curved surface 3021 and the second curved surface 3022 meet enters the cavity 306. By forming the cavity 306, the sand is effectively prevented from being scattered everywhere.

[0029] Furthermore, the wall of the second tube 305 is evenly provided with power members 307 in the region of the cavity 306, and the power members 307 include a first blade 3071, a second blade 3072, and a linkage shaft 3073 connecting the first blade 3071 and the second blade 3072, the linkage shaft 3073 passes through the wall of the second tube 305, the first blade 3071 is located in the second tube 305, the second blade 3072 is located in the cavity 306, and the first tube 301 is evenly provided with second holes 3012 on the surface of the region of the cavity 306. When the airflow after separating the sand flows through the second tube 305 along the first direction, the first blade 3071 is driven to rotate at the same time, and then under the action of the linkage shaft 3073, the second blade 3072 is driven by the rotation of the first blade 3071, and the sand falling into the cavity 306 is discharged into the cavity through the second hole 3012 under the action of the second blade 3072.

[0030] Please continue reading Figure 5 The sand control device further comprises a discharge assembly 5. A part of the separation assembly 3 acts on the chamber to separate the sand, and a part of the discharge assembly 5 acts on the chamber to discharge the sand. The discharge assembly 5 comprises a third pipe 501 and a fourth pipe 502. The fourth pipe 502 is symmetrically arranged at the intersection of the third pipe 501 and the fourth pipe 502. One end of the third pipe 501 is fitted in the chamber to suck and discharge the separated sand in the chamber.

[0031] Furthermore, the surface of the fourth tube 502 is evenly provided with injection parts 503, and a fifth tube 504 is also provided near the injection parts 503. The fifth tube 504 and the injection parts 503 are coaxially arranged, and the diameter of the fifth tube 504 increases from the end close to the injection parts 503 to the end away from the injection parts 503, so that the sand in the chamber is diverted from the third tube 501 to the fourth tube 502, and then ejected from the injection parts 503 and discharged to the external environment through the fifth tube 504. The fifth tube 504 is inclined and reversely arranged relative to the second direction, and the second direction in this embodiment is the direction of flight of the aircraft, so as to avoid the discharged sand from falling into the suction range of the separation component 3 again.

[0032] The technical features of the above-described embodiments can be combined arbitrarily. In order to make the description concise, all possible combinations of the technical features in the above-described embodiments are not described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification. The above-described embodiments only express several implementation methods of the present invention, and their descriptions are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that for ordinary technicians in this field, without departing from the concept of the present invention, several variations and improvements can be made, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be based on the attached claims.

Claims

1. An aircraft sand control device, comprising a first panel and a second panel arranged along a first aspect, and a third panel enclosed with the first panel and the second panel to form a chamber, characterized in that: Separation components are evenly arranged between the first panel and the second panel, and the sand control device also includes a discharge component. The separation component and a part of the discharge component act on the chamber respectively to realize sand control.

2. The aircraft sand control device according to claim 1, characterized in that: The separation component includes a first tube, a protrusion is arranged on the surface of the first tube, the protrusions are respectively matched with the first panel and the second panel, a first guide is arranged inside one end close to the first panel, the first guide has a first arc surface and a second arc surface, and a depression is formed at the intersection of the first arc surface and the second arc surface.

3. An aircraft sand control device according to claim 2, characterized in that: The first tube is further provided with a second guide member near the first panel. The second guide member is coaxially arranged with the first tube. The end surface diameter length of the second guide member near the first panel is smaller than the end surface diameter length of the first tube near the first panel.

4. An aircraft sand control device as claimed in claim 3, characterized in that: The second guide member is connected to the first guide member, and the second guide member has a third arc surface, and the third arc surface matches the first arc surface.

5. An aircraft sand control device according to claim 4, characterized in that: The first tube is also connected with a partition and a second tube coaxially arranged with the first tube. The second tube is respectively connected to the first guide member and the partition. The second tube also has a fourth curved surface near the second panel.

6. An aircraft sand control device according to claim 5, characterized in that: A first hole is provided at a depression where the first arc surface and the second arc surface meet. The first guide member, the partition plate and the second tube together form a cavity. The first hole leads to the cavity.

7. An aircraft sand control device according to claim 6, characterized in that: The second tube wall is evenly provided with power parts in the cavity area, and the power parts include a first blade, a second blade and a linkage shaft connecting the first blade and the second blade. The linkage shaft passes through the second tube wall. The first blade is located in the second tube, and the second blade is located in the cavity.

8. An aircraft sand control device according to claim 7, characterized in that: The first tube is evenly provided with second holes on the surface of the cavity area.

9. The aircraft sand control device according to claim 1, characterized in that: The discharge assembly includes a third tube and a fourth tube. The fourth tube is symmetrically arranged at the intersection of the third tube and the fourth tube. Injection pieces are evenly arranged on the surface of the fourth tube.

10. An aircraft sand control device according to claim 9, characterized in that: A fifth tube is also arranged near the injection member. The fifth tube and the injection member are arranged coaxially. The diameter of the fifth tube increases from one end close to the injection member to one end away from the injection member. The fifth tube is inclined relative to the second direction and arranged in the opposite direction.

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