Engine fixing support of ultra-light aircraft

Abstract

An engine fixing support of an ultra-light aircraft comprises a front engine connecting end and a rear cabin connecting end, and further comprises a nose landing gear steering vertical pipe located between the engine connecting end and the cabin connecting end. The engine connecting end, the nose landing gear steering vertical pipe and the cabin connecting end are connected through rod pieces to form a space truss structure. According to the engine fixing support, the engine connecting end, the cabin connecting end and the nose landing gear steering stand pipe are connected into a whole to form a space truss structure, the problems that the nose landing gear steering stand pipe is difficult to arrange and fix are solved, and the overall strength of the engine fixing support is improved. Compared with an existing engine fixing support, the engine fixing support is higher in integration level, more compact in structure and lighter in weight, and meets the design requirements of ultra-light airplanes.

Description

Technical Field

[0001] The utility model relates to the technical field of ultra-light aircraft, and in particular to an engine fixing bracket for an ultra-light aircraft. Background Technique

[0002] The characteristics of ultra-light aircraft are small size, light weight, short take-off distance, and low requirements for take-off sites.

[0003] The patent with the application number 202121393468.3 discloses an engine mounting bracket for a light fixed-wing aircraft. This engine mounting bracket adopts a space truss structure, reduces its own weight, and realizes the detachable connection between the engine and the fuselage. However, this engine mounting bracket is not applicable to ultra-light aircraft because the engine fixing bracket of ultra-light aircraft needs to have a more compact structure, lighter weight, and integrate as many functional components as possible, such as the steering riser of the nose landing gear. Therefore, it is necessary to develop an engine fixing bracket suitable for ultra-light aircraft. Content of the Utility Model

[0004] In order to overcome the deficiencies in the background technique, the utility model discloses an engine fixing bracket for an ultra-light aircraft, and its purpose is: to make the engine fixing bracket have a more compact structure, lighter weight, and integrate more functional components while ensuring the overall strength.

[0005] Specifically, the utility model adopts the following technical scheme:

[0006] An engine fixing bracket for an ultra-light aircraft includes a front engine connection end and a rear cabin connection end, and also includes a nose landing gear steering riser located between the engine connection end and the cabin connection end; the engine connection end, the nose landing gear steering riser, and the cabin connection end are connected by rods to form a space truss structure.

[0007] After adopting the above technical scheme, the beneficial effects are as follows: The nose landing gear is installed in the nose landing gear steering riser. When the aircraft lands, the nose landing gear and the steering riser need to bear a large impact force. Therefore, the nose landing gear steering riser should be arranged at a relatively strong part of the fuselage and fixed in a reliable manner.

[0008] This engine fixing bracket integrates the engine connection end, the cabin connection end and the nose landing gear steering riser into one body and forms a space truss structure, which not only solves the problems of difficult layout and fixation of the nose landing gear steering riser, but also improves the overall strength of the engine fixing bracket. Compared with the existing engine fixing brackets, this engine fixing bracket has a higher integration degree, a more compact structure and a lighter weight, meeting the requirements of ultra-light aircraft design.

[0009] Further improve the technical solution. The engine connection end has multiple engine connection nodes, and is connected to the engine through connecting parts.

[0010] After adopting the above technical solution, the beneficial effects are as follows: The engine connection nodes have a connection structure matching the engine, which facilitates the disassembly and installation of the engine.

[0011] Further improve the technical solution. The cabin connection end has multiple cabin connection nodes, and is connected to the cabin through connecting parts.

[0012] After adopting the above technical solution, the beneficial effects are as follows: By setting the cabin connection nodes, the detachable connection between the engine fixing bracket and the cabin can be realized. Since the engines have different models and connection structures, when replacing engines of different models, the original engine fixing bracket can be removed as a whole, and an engine fixing bracket matching the model and connection structure of the existing engine can be replaced.

[0013] Further improve the technical solution. A sleeve-shaped upper connection node is provided at the upper part of the front landing gear steering riser, and a sleeve-shaped lower connection node is provided at the lower part of the front landing gear steering riser.

[0014] After adopting the above technical solution, the beneficial effects are as follows: The front landing gear steering riser with upper and lower connection nodes has better strength and can withstand greater impact force.

[0015] Further improve the technical solution. The cabin connection end has four cabin connection nodes arranged in a rectangle, namely the upper left node A1, the upper right node A2, the lower left node A3, and the lower right node A4; the engine connection end has four engine connection nodes arranged in a rectangle, namely the upper left node B1, the upper right node B2, the lower left node B3, and the lower right node B4; among them, A1 and B1, A1 and B3, A2 and B2, A2 and B2, A3 and B3, A4 and B4, B1 and B2, B2 and B4, B3 and B4, B1 and B4 are connected by rods; in addition, the upper connection nodes of the front landing gear steering riser are respectively connected to A3, A4, B3, and B4 by rods, and the lower connection nodes are respectively connected to A3, A4, B3, and B4 by rods.

[0016] After adopting the above technical solution, the beneficial effects are as follows: This technical solution is applicable to the structure where the cabin has four connection nodes and the engine also has four connection nodes.

[0017] Further improving the technical solution, the engine nacelle connection end has five nacelle connection nodes arranged in a pentagon, namely the upper left node a1, the upper right node a2, the lower left node a3, the lower right node a4, and the upper middle node a5; the engine connection end has four engine connection nodes arranged in a rectangle, namely the upper left node b1, the upper right node b2, the lower left node b3, and the lower right node b4; among them, a1 is connected to b1, a1 is connected to b3, a2 is connected to b2, a2 is connected to b2, a3 is connected to b3, a4 is connected to b4, b1 is connected to b2, b2 is connected to b4, b3 is connected to b4, a5 is connected to b1, and a5 is connected to b2 by rods; in addition, the upper connection nodes of the front landing gear steering riser are respectively connected to a3, a4, b3, and b4 by rods, and the lower connection nodes are respectively connected to a3 and a4 by rods.

[0018] After adopting the above technical solution, the beneficial effects are as follows: This technical solution is applicable to a structure where the nacelle has five connection nodes and the engine has four connection nodes.

[0019] Further improving the technical solution, the rod is a solid rod or a hollow rod, and the cross-sectional shape is circular or polygonal.

[0020] After adopting the above technical solution, the beneficial effects are as follows: Both solid rods and hollow rods can meet the strength requirements. In comparison, the hollow rod is lighter in weight.

[0021] Further improving the technical solution, the engine connection node is composed of a sleeve and a shock-absorbing sleeve installed inside the sleeve.

[0022] After adopting the above technical solution, the beneficial effects are as follows: When the engine is working, vibrations will be generated. The role of the shock-absorbing sleeve is to reduce and isolate vibrations, and reduce the impact of vibrations on the nacelle.

[0023] Further improving the technical solution, the engine fixing bracket further includes an engine nacelle partition, and the engine nacelle partition is fixed between the engine nacelle connection end and the nacelle.

[0024] After adopting the above technical solution, the beneficial effects are as follows: When the engine is working, noise will be generated. The role of the engine nacelle partition is to separate the engine nacelle from the nacelle and reduce the noise inside the nacelle. Description of the Drawings

[0025] Figure 1 The figure shows the structural schematic diagram of this engine fixing bracket in Embodiment 1.

[0026] Figure 2 The figure shows the structural schematic diagram of this engine fixing bracket from another perspective.

[0027] Figure 3The figure shows a schematic diagram of the installation structure of the engine compartment bulkhead.

[0028] Figure 4 The figure shows a schematic diagram of the structure of the engine fixing bracket in Embodiment 2.

[0029] In the drawings:

[0030] 1. Engine connection end; 1.1 Engine connection node;

[0031] 2. Cabin connection end; 2.1 Cabin connection node;

[0032] 3. Front landing gear steering riser; 3.1 Upper connection node; 3.2 Lower connection node;

[0033] 4. Rod member;

[0034] 5. Engine compartment bulkhead. Detailed implementation manners

[0035] The following describes the preferred implementation manners of the present invention with reference to the drawings. Those skilled in the art should understand that these implementation manners are only used to explain the technical principle of the present invention and are not intended to limit the protection scope of the present invention. It should be noted that in the description of the present invention, the terms indicating directions or positional relationships such as "front", "rear", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings. This is only for convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0036] Embodiment 1:

[0037] Referring to Figure 1 and Figure 2 , Figure 1 shows a schematic diagram of the structure of a fixed bracket for an ultra-light aircraft engine, and Figure 2 shows a schematic diagram of the structure of the engine fixing bracket from another perspective. From Figure 1 and Figure 2 it can be seen that the engine fixing bracket mainly consists of an engine connection end 1, a front landing gear steering riser 3, a cabin connection end 2, and multiple rod members 4. The following specifically describes its structure and functions.

[0038] The engine connection end 1 faces the engine compartment. The engine connection end 1 has a plurality of engine connection nodes 1.1. The structure of the engine connection nodes 1.1 matches the connection structure of the engine, and detachable connection with the engine can be achieved through connecting pieces. For shock absorption, the engine connection nodes 1.1 are composed of a sleeve body and a shock-absorbing sleeve installed inside the sleeve body.

[0039] The cabin connection end 2 faces the cabin (also called the cockpit). The cabin connection end 2 has a plurality of cabin connection nodes 2.1. The structure of the cabin connection nodes 2.1 matches the connection structure on the cabin, and detachable connection with the cabin can be achieved through connecting pieces.

[0040] The front landing gear steering riser 3 is located between the engine connection end 1 and the cabin connection end 2. The function of the front landing gear steering riser 3 is to connect the front landing gear and enable the front landing gear to rotate left and right within the front landing gear steering riser 3. Since the front landing gear needs to bear a large impact force when the aircraft lands, the front landing gear steering riser 3 should be arranged at a relatively high-strength part of the fuselage and fixed in a reliable manner.

[0041] In this embodiment, the aircraft cabin (not shown in the figure) has five connection nodes arranged in a pentagon, and the engine (not shown in the figure) has four connection nodes arranged in a rectangle. Correspondingly, the cabin connection end 2 has five cabin connection nodes 2.1 arranged in a pentagon, namely the upper left node a1, the upper right node a2, the lower left node a3, the lower right node a4, and the upper middle node a5. The engine connection end 1 has four engine connection nodes 1.1 arranged in a rectangle, namely the upper left node b1, the upper right node b2, the lower left node b3, and the lower right node b4. Among them, a1 and b1, a1 and b3, a2 and b2, a2 and b2, a3 and b3, a4 and b4, b1 and b2, b2 and b4, b3 and b4, a5 and b1, a5 and b2 are connected by rods 4.

[0042] It should be noted that the two rods 4 between a5 and b1, a5 and b2 can be connected to b1 and b2, or to the rod between b1 and b2, as shown in the appendix. Figure 2 Also, no rod is connected between b1 and b3 to make room.

[0043] In addition, a sleeve-shaped upper connection node 3.1 is provided at the upper part of the front landing gear steering riser 3, and a sleeve-shaped lower connection node 3.2 is provided at the lower part of the front landing gear steering riser 3. The upper connection node 3.1 of the front landing gear steering riser 3 is respectively connected to a3, a4, b3, and b4 through a rod member 4, and the lower connection node 3.2 is respectively connected to a3 and a4 through the rod member 4. In this embodiment, the rod member 4 is a hollow circular tube, which can reduce the weight of the rod member while ensuring the strength. It should be understood that the rod member can also be a solid rod member, and the cross-sectional shape can also be rectangular or other shapes.

[0044] In this way, a space truss structure is formed between the engine connection end 1, the front landing gear steering riser 3, and the cabin connection end 2 through the connection of the rod member 4, and most of the connection nodes have a stable truss structure of a triangle. Obviously, such a structure not only solves the problems of difficult layout and fixation of the front landing gear steering riser, but also improves the overall strength, making the engine fixing bracket have a higher integration degree, a more compact structure, and a lighter weight.

[0045] Refer to the appendix Figure 3 , the appendix Figure 3 shows a schematic installation structure diagram of the engine compartment partition. It can be seen from the appendix Figure 3 that an engine compartment partition 5 is fixed between the cabin connection end 2 and the cabin through a connecting member. When the engine is working, it will generate noise, and the function of the engine compartment partition 5 is to separate the engine compartment from the cabin and reduce the noise in the cabin.

[0046] Embodiment 2:

[0047] Refer to the appendix Figure 4 . Different from Embodiment 1, the aircraft cabin in this embodiment has four connection nodes arranged in a rectangle, and the engine also has four connection nodes arranged in a rectangle.

[0048] Correspondingly, the cabin connection end 2 has four cabin connection nodes 2.1 arranged in a rectangle, namely the upper left node A1, the upper right node A2, the lower left node A3, and the lower right node A4; the engine connection end 1 has four engine connection nodes 1.1 arranged in a rectangle, namely the upper left node B1, the upper right node B2, the lower left node B3, and the lower right node B4; among them, A1 and B1, A1 and B3, A2 and B2, A2 and B2, A3 and B3, A4 and B4, B1 and B2, B2 and B4, B3 and B4, B1 and B4 are connected through the rod member 4. Compared with Embodiment 1, although the cabin connection end 2 has one less cabin connection node 2.1, the strength between the four engine connection nodes 1.1 of the engine connection end 1 is strengthened.

[0049] In addition, the upper connection nodes 3.1 of the front landing gear steering riser 3 are respectively connected to A3, A4, B3, and B4 through the rods 4, and the lower connection nodes 3.2 are respectively connected to A3, A4, B3, and B4 through the rods 4. Compared with Embodiment 1, the strength of the engine connection end and the lower connection node 3.2 of the front landing gear steering riser is enhanced.

[0050] It should be understood that the number of the cabin connection nodes and the engine connection nodes is not limited to four or five, and shall be determined according to the specific conditions of the aircraft cabin and the engine. Similarly, the number and connection mode of the rods shall also be determined according to the overall strength and installation conditions of the aircraft.

[0051] The parts not described in detail are the prior art. Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The protection scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An engine mounting bracket for an ultra-light aircraft, comprising a front engine connection end and a rear cabin connection end, characterized in that: It also includes a front landing gear steering riser located between the engine connection end and the cabin connection end; the engine connection end, the front landing gear steering riser, and the cabin connection end are connected by rods to form a space truss structure.

2. The engine fixing bracket of an ultra-light aircraft according to claim 1, characterized in that: The engine connection end has multiple engine connection nodes and is connected to the engine through connectors.

3. The engine fixing bracket of an ultra-light aircraft according to claim 2, characterized in that: The cabin connection end has multiple cabin connection nodes and is connected to the cabin through connectors.

4. The engine mounting bracket of an ultra-light aircraft according to claim 3, characterized in that: A sleeve-shaped upper connection node is provided at the upper part of the front landing gear steering riser, and a sleeve-shaped lower connection node is provided at the lower part of the front landing gear steering riser.

5. The engine mounting bracket of an ultra-light aircraft according to claim 4, wherein: The cabin connection end has four cabin connection nodes arranged in a rectangle, namely the upper left node A1, the upper right node A2, the lower left node A3, and the lower right node A4; the engine connection end has four engine connection nodes arranged in a rectangle, namely the upper left node B1, the upper right node B2, the lower left node B3, and the lower right node B4; among them, A1 and B1, A1 and B3, A2 and B2, A2 and B2, A3 and B3, A4 and B4, B1 and B2, B2 and B4, B3 and B4, B1 and B4 are connected by rods; in addition, the upper connection nodes of the front landing gear steering riser are respectively connected to A3, A4, B3, and B4 by rods, and the lower connection nodes are respectively connected to A3, A4, B3, and B4 by rods.

6. The engine fixing bracket of an ultra-light aircraft according to claim 4, characterized in that: The cabin connection end has five cabin connection nodes arranged in a pentagon, namely the upper left node a1, the upper right node a2, the lower left node a3, the lower right node a4, and the upper middle node a5; the engine connection end has four engine connection nodes arranged in a rectangle, namely the upper left node b1, the upper right node b2, the lower left node b3, and the lower right node b4; among them, a1 and b1, a1 and b3, a2 and b2, a2 and b2, a3 and b3, a4 and b4, b1 and b2, b2 and b4, b3 and b4, a5 and b1, a5 and b2 are connected by rods; in addition, the upper connection nodes of the front landing gear steering riser are respectively connected to a3, a4, b3, and b4 by rods, and the lower connection nodes are respectively connected to a3 and a4 by rods.

7. The engine fixing bracket of an ultra-light aircraft as claimed in claim 1, characterized in that: The rod is a solid rod or a hollow rod, and the cross-sectional shape is circular or polygonal.

8. The engine fixing bracket of an ultra-light aircraft according to claim 2, characterized in that: The engine connection node is composed of a sleeve and a shock-absorbing sleeve installed in the sleeve.

9. The engine fixing bracket of an ultra-light aircraft according to claim 1, characterized in that: The engine fixing bracket also includes an engine compartment partition, and the engine compartment partition is fixed between the cabin connection end and the cabin.

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