Butt joint structure of engine and air inlet channel of unmanned aerial vehicle

Abstract

The utility model discloses a butt joint structure of an unmanned aerial vehicle engine and an air inlet channel, and belongs to the field of unmanned aerial vehicle body structures. The structure comprises a butt-joint frame, an air inlet flange is installed on the front side of the butt-joint frame, and an engine flange is installed on the rear side of the butt-joint frame. A petal type annular inner groove is formed in the matching surface of the butt joint frame and the engine flange side, and a petal type annular sealing gasket matched with the inner groove in shape is embedded in the inner groove. An annular limiting boss is formed between the inner groove and the air passing hole of the butt joint frame to limit the sealing gasket. A pressing plate is installed on the outer edge of each petal lug of the sealing gasket and used for fixing the sealing gasket. And a plurality of through holes matched with the mounting holes of the butt-joint frame are uniformly distributed in the circumference of the sealing gasket, and first bolts for connecting the air inlet channel flange and the engine flange penetrate through the through holes. The sealing gasket adopts a pressing plate and bolt matched connection mode, so that the mounting reliability is ensured; the sealing gasket is limited by the annular limiting boss, so that the sealing gasket is prevented from being compressed and deformed to enter the air passing hole to influence the air inflow.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) airframe structure, specifically relating to a UAV engine and air intake docking structure. Background Technology

[0002] Currently, for small and medium-sized UAVs, piston engines with relatively low thrust are more commonly used due to cost considerations, while turbojet engines with relatively high thrust are less common. For UAVs with high performance requirements that use turbojet engines, the engines are generally installed along the flight path, and the air intake and engine are connected in two ways: on-frame docking and off-frame docking, with on-frame docking being more common.

[0003] The frame-mounted docking involves installing the intake flange in front of the docking frame (facing the UAV's heading forward) and the engine flange behind it. The docking frame has an air vent that connects the intake duct and the engine. Multiple mounting holes are evenly distributed around the air vent for bolts to pass through, enabling bolted connections between the engine flange, docking frame, and intake flange, forming the engine's intake passage. Considering the engine flange installation design compensation and the engine's expansion along its heading during operation, a sealing gasket is typically glued to the mating surface between the engine flange and the docking frame. However, this glued gasket may detach over long-term use, and it can deform under compression from the engine flange, allowing a small amount of sealant to enter the effective space of the intake duct, thus affecting the intake volume. Summary of the Invention

[0004] The technical problem to be solved:

[0005] To avoid the shortcomings of the prior art, the present invention provides a docking structure between a drone engine and an air intake, which solves the problem of the air intake volume of the air intake affected by the delamination of the sealing gasket and the compression deformation of the existing frame docking structure.

[0006] The technical solution of the present invention is: a docking structure for a drone engine and an air intake, including a docking frame, an air intake flange installed on the front side of the docking frame, and an engine flange installed on the rear side of the docking frame;

[0007] The mating frame has a petal-shaped annular groove on the side facing the engine flange, located at the mating surface of the two. Multiple radially arranged concave lugs are evenly distributed along the outer diameter of the groove to form the petals of the groove. The groove is used to embed and install a petal-shaped annular sealing gasket that matches the groove shape. An annular limiting boss is formed between the groove and the air passage of the mating frame to limit the sealing gasket. A pressure plate is installed at the outer edge of each lug of the sealing gasket, and the lug of the sealing gasket is sandwiched between the bottom surface of the groove of the mating frame and the pressure plate. The pressure plate is screwed to the mating frame. Multiple through holes matching the mounting holes of the mating frame are evenly distributed around the sealing gasket for the passage of the first bolt connecting the intake flange and the engine flange.

[0008] A further technical solution of the present invention is: the main body of the docking frame is plate-shaped, and an annular boss is provided on the side of the docking frame facing the air intake port, coaxial with the air intake port. The mounting holes of the docking frame are evenly distributed on the annular boss, which are used to pass through the first bolt to connect the air intake port flange and the engine flange on both sides of the docking frame.

[0009] A further technical solution of the present invention is: the two opposite edges of the docking frame facing the air intake are provided with flanges of the same height as the annular boss; the annular boss is provided with multiple longitudinally and transversely arranged reinforcing ribs around its perimeter, each reinforcing rib extending from the outer ring of the annular boss to the outer edge of the docking frame; the flanges, reinforcing ribs and annular boss together reinforce the docking frame.

[0010] A further technical solution of the present invention is: the inner groove of the docking frame is set at the same depth, and six ears are provided at its ear pieces.

[0011] A further technical solution of the present invention is: the shape of the pressure plate is consistent with the shape of the lug of the sealing gasket, and the pressure plate, the lug of the sealing gasket and the docking frame are fixedly connected by a second bolt passing through them in sequence.

[0012] A further technical solution of the present invention is that the sealing gasket is a rubber sealing gasket with a compression amount of 15%-40% as compensation for the engine flange installation design.

[0013] A further technical solution of the present invention is that the docking frame is provided with a plurality of weight-reducing through holes for weight reduction.

[0014] A further technical solution of the present invention is that the docking frame is provided with multiple wire-passing holes for passing cables through.

[0015] Beneficial effects

[0016] The beneficial effects of this invention are as follows: By setting an inner groove on the mating frame facing the engine flange, a sealing gasket with the same structure as the inner groove is embedded and installed. The sealing gasket is fixed to the inner groove of the mating frame by bolts through multiple pressure plates, ensuring the reliability of the sealing gasket installation. Simultaneously, by setting an annular limiting boss between the inner edge of the inner groove and the air passage of the mating frame, the sealing gasket is limited, preventing deformation of the sealing gasket from extending into the air passage of the mating frame when squeezed by the engine flange, thus solving the problem of the sealing gasket compression deformation affecting the intake air volume.

[0017] This invention's docking frame employs a thin frame plate with annular bosses, reinforcing ribs, and two side flanges, along with multiple weight-reduction holes, achieving weight reduction while meeting support strength requirements. Furthermore, the equal-height design of the side flanges and annular bosses does not interfere with the installation of the docking frame and the intake flange. Additionally, the side flanges face the intake direction, ensuring reinforcement of the docking frame without affecting the engine flange installation. The overall docking structure design is reasonable, ensuring unobstructed space for the intake duct and engine installation.

[0018] The engine flange, docking frame, and intake flange docking structure of this invention, as well as the gasket mounting structure, are all designed as bolt-removable structures to meet the requirements of convenient disassembly and maintenance. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the docking structure between the UAV engine and the air intake duct of the present invention (viewed from the engine side);

[0020] Figure 2 This is a schematic diagram of the docking structure between the UAV engine and the air intake of the present invention (viewed from the side of the air intake);

[0021] Figure 3 This is a schematic diagram of the docking frame in this invention (showing the engine flange mounting side);

[0022] Figure 4 This is a schematic diagram of the docking frame in this invention (showing the intake flange mounting side);

[0023] Figure 5 This is a schematic diagram of the sealing gasket installation structure in this invention;

[0024] Figure 6 This is a schematic diagram of the sealing gasket structure in this invention;

[0025] Figure 7 This is a schematic diagram of the connection structure between the intake flange and the engine flange in this invention;

[0026] Figure 8 This is a schematic diagram of the connection cross-section of the sealing gasket in this invention;

[0027] Figure 9 This is a schematic diagram showing the installation positions of the main and auxiliary mounting sections of the engine.

[0028] Explanation of reference numerals in the attached figures:

[0029] 1. Docking frame, 1-1. Inner groove, 1-2. Limiting boss, 1-3. Air passage hole, 1-4. Annular boss, 1-5. Mounting hole, 1-6. Flanged edge, 1-7. Reinforcing rib, 1-8. Weight reduction through hole, 1-9. Cable passage hole, 2. Air intake, 2-1. Air intake flange, 3. Engine, 3-1. Engine flange, 4. Sealing gasket, 4-1. Lug of sealing gasket, 5. Pressure plate, 6. First bolt, 7. First nut, 8. First washer, 10. Second bolt, 11. Second nut, 12. Second washer, 13. Fuselage bulkhead, 14. Main mounting section, 15. Subsidiary mounting section. Detailed Implementation

[0030] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the invention, and should not be construed as limiting the invention.

[0031] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0032] This embodiment provides a docking structure for a drone engine and an air intake, mainly addressing the problems existing in the docking of existing drone turbojet engines and air intake frames, including the reliability of the sealing gasket connection and the problem of the air intake volume being affected by the compression and deformation of the sealing gasket. By improving the docking structure between the engine and the air intake, the above problems are solved. At the same time, the docking structure also features lightweight, easy disassembly and assembly, and convenient maintenance.

[0033] See Figure 1 , 2 This embodiment provides a docking structure for a drone engine and an air intake, including a docking frame 1, a sealing gasket 4, a pressure plate 5, an air intake flange 2-1, and an engine flange 3-1.

[0034] The rear end of the air intake duct 2 is equipped with an air intake flange 2-1, which is installed on the front side of the docking frame 1, with the front side of the docking frame 1 facing the UAV's flight path. The air intake end of the engine 3 is equipped with an engine flange 3-1, which is installed on the rear side of the docking frame 1. The air intake flange 2-1 and the engine flange 3-1 are coaxially docked through the docking frame 1.

[0035] like Figure 3 , 4As shown in Figures 7 and 8, in this embodiment, the main body of the docking frame 1 is a square thin-walled plate structure. The middle part of the docking frame 1 is provided with an air passage hole 1-3 that passes through the outlet of the air intake duct 2 and the air intake inlet of the engine 3. The diameter of the air passage hole 1-3 is equal to or slightly larger than the diameter of the air intake flange 2-1, so as to avoid affecting the air intake volume.

[0036] On the side of the docking frame 1 facing the air intake duct 2, an annular boss 1-4 is provided around the air passage 1-3 and coaxially with the air passage 1-3. Multiple mounting holes 1-5 are evenly distributed around the annular boss 1-4. Figure 3 , Figure 4 (Not shown in the image) The circumference of the multiple mounting holes 1-5 is concentric with the air passage hole 1-3. The mounting holes 1-5 are used to pass through the first bolt 6 to connect the air intake flange 2-1 and the engine flange 3-1 on both sides of the docking frame 1.

[0037] The docking frame 1 has flanges 1-6 at the top and bottom edges of the side facing the air intake, with the same height as the annular boss 1-4, which strengthen the support of the docking frame. Multiple reinforcing ribs 1-7 are arranged longitudinally and transversely around the annular boss 1-4, each extending from the outer edge of the annular boss 1-4 to the outer edge of the docking frame 1. The flanges 1-6, reinforcing ribs 1-7, and annular boss 1-4 together strengthen the support of the docking frame 1. Compared to a plate-shaped docking frame of uniform thickness, this invention's structure achieves weight reduction while maintaining support strength. Furthermore, multiple weight-reducing through holes 1-8 are provided in the non-functional areas of the docking frame 1 to further reduce weight. Multiple cable-passing holes 1-9 are provided on the docking frame 1 to allow cables to pass through, and the size and position of the cable-passing holes 1-9 are designed according to the internal wiring requirements of the UAV.

[0038] See Figure 3-7 On the side of the mating frame 1 facing the engine flange 3, a petal-shaped annular groove 1-1 is provided at the mating surface of the two. The groove 1-1 is coaxial with the vent 1-3. Six radially extending concave lugs are evenly distributed on the outer diameter of the groove 1-1, forming the petals of the groove 1-1. The groove 1-1 is a planar groove of uniform depth, with the petal lugs extending to the main ring of the groove 1-1, and the concave depth of the petal lugs is the same as the concave depth of the main ring. A petal-shaped annular sealing gasket 4 matching the groove shape is embedded in the groove 1-1, and the sealing gasket 4 has six lugs 4-1 corresponding to it. An annular limiting boss 1-2 is formed between the groove 1-1 and the vent 1-3 of the mating frame 1, which limits the sealing gasket 4 and prevents the sealing gasket 4 from being squeezed into the vent 1-3 after compression and deformation, which would affect the effective space of the vent 1-3 and thus affect the intake volume. The outer surface of the annular limiting boss 1-2 is flush with the compressed surface of the sealing gasket 4 to ensure that the mating surface is flat.

[0039] Referring to 5 and 8, a pressure plate 5 is installed at the outer edge of each lug 4-1 of the sealing gasket 4. The pressure plate 5 is a flat metal plate, and its shape is consistent with that of the lug 4-1 of the sealing gasket. The lug 4-1 of the sealing gasket is sandwiched between the mating frame 1 and the pressure plate 5, and the pressure plate 5 is screwed to the mating frame 1 for fixation. Specifically, the mating frame 1 has two through holes at each installation location of the pressure plate 5, and correspondingly, each lug 4-1 of the sealing gasket 4 has two through holes. The pressure plate 5 also has two matching through holes. A second bolt 10 passes through the pressure plate 5, the lug 4-1 of the sealing gasket, and the mating frame 1 in sequence. A second washer 12 is fitted onto the end of the second bolt 10, and the second nut 11 is threadedly locked to the second bolt 10 for fixation. The sealing gasket 4 is stably fixed in the inner groove 1-1 of the mating frame 1 through the screw connection between the pressure plate 5 and the mating frame 1, preventing it from falling off during use. The sealing gasket 4 adopts a mechanical connection with high reliability, and the connection method is detachable, making it easy to replace the sealing gasket 4 after failure.

[0040] See Figure 7 The sealing gasket 4 has multiple through holes evenly distributed around its main body ring, each matching one-to-one with the mounting holes 1-5 of the docking frame 1, for the passage of the first bolt 6 connecting the intake flange 2-1 and the engine flange 3-1. When the intake flange 2-1 and the engine flange 3-1 are installed together on both sides of the docking frame 1, the first bolt 6 passes sequentially through the engine flange 3-1, the sealing gasket 4, the docking frame 1, and the intake flange 2-1 from the side where the engine 3 is located. The end of the first bolt 6 is fitted with a first washer 8 and is locked in place by a first nut 7.

[0041] In this embodiment, the sealing gasket 4 is a flat rubber sealing gasket of uniform thickness, with a compression amount of 15%-40% as compensation for the installation design of the engine flange 3-1. (See reference...) Figure 9 Engine 3 employs two main mounting sections 14 and one auxiliary mounting section 15, which respectively connect to the joints and tie rods on the fuselage bulkhead 13. During engine 3 installation, after the main mounting sections 14 and auxiliary mounting sections 15 are successfully connected, the planar position of the engine 3's front inlet, i.e., the engine flange 3-1, is determined. There may be a gap or slight interference between it and the docking frame 1. Rubber sealing gaskets 4 are installed in the docking area between the docking frame 1 and the engine flange 3-1 as design compensation during engine 3 installation, preventing forced assembly and taking into account the expansion of the engine along the flight path during operation, thus reducing the impact on the flight path docking structure.

[0042] During installation, first install the sealing gasket 4 and pressure plate 5 on the docking frame 1. Then, adjust the intake flange 2-1 on the front side of the docking frame 1 and the rear engine flange 3-1 on the rear side of the docking frame 1 into position, aligning the flange connection holes with the mounting holes 1-5 on the docking frame 1. Use the first bolt 6 and its matching washer and nut assembly to achieve docking and fixation. During disassembly, remove the first bolt 6 assembly, remove the pressure plate 5, and remove the sealing gasket 4.

[0043] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. A docking structure for an unmanned aerial vehicle (UAV) engine and an air intake, comprising a docking frame, an air intake flange mounted on the front side of the docking frame, and an engine flange mounted on the rear side of the docking frame; Its features are, The mating frame has a petal-shaped annular groove on the side facing the engine flange, located at the mating surface of the two. Multiple radially arranged concave lugs are evenly distributed along the outer diameter of the groove to form the petals of the groove. The groove is used to embed and install a petal-shaped annular sealing gasket that matches the groove shape. An annular limiting boss is formed between the groove and the air passage of the mating frame to limit the sealing gasket. A pressure plate is installed at the outer edge of each lug of the sealing gasket, with the lugs of the gasket sandwiched between the bottom surface of the groove of the mating frame and the pressure plate. The pressure plate is screwed to the mating frame. Multiple through holes matching the mounting holes of the mating frame are evenly distributed around the sealing gasket for the passage of the first bolt connecting the intake flange and the engine flange.

2. The docking structure between the UAV engine and the air intake as described in claim 1, characterized in that, The main body of the docking frame is plate-shaped. On the side of the docking frame facing the air intake, there is an annular boss around the air passage hole and coaxial with the air passage hole. The mounting holes of the docking frame are evenly distributed on the annular boss and are used to pass through the first bolt to connect the air intake flange and the engine flange on both sides of the docking frame.

3. The docking structure between the UAV engine and the air intake as described in claim 2, characterized in that, The docking frame has flanges of the same height as the annular boss at two opposite edges facing the air intake. The annular boss has multiple reinforcing ribs arranged longitudinally and transversely around its perimeter, with each reinforcing rib extending from the outer ring of the annular boss to the outer edge of the docking frame. The flanges, reinforcing ribs, and annular boss together strengthen the docking frame.

4. The docking structure between the UAV engine and the air intake as described in claim 1, characterized in that, The inner groove of the docking frame is set to the same depth, and there are six ears at its ear plate.

5. The docking structure between the UAV engine and the air intake as described in claim 1, characterized in that, The shape of the pressure plate is consistent with the shape of the lug of the sealing gasket, and the pressure plate, the lug of the sealing gasket and the mating frame are fixedly connected by the second bolt in sequence.

6. The docking structure between the UAV engine and the air intake as described in claim 1, characterized in that, The sealing gasket is a rubber sealing gasket with a compression of 15%-40% as compensation for the engine flange installation design.

7. The docking structure between the UAV engine and the air intake as described in claim 1, characterized in that, The docking frame is provided with multiple weight-reducing through holes for weight reduction.

8. The docking structure between the UAV engine and the air intake as described in claim 1, characterized in that, The docking frame is provided with multiple wire-passing holes for cables to pass through.

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