General aviation aircraft engine support system

Abstract

This utility model discloses a general-purpose aircraft engine support device, including a base and a first support mechanism and a second support mechanism disposed on the base for connection with the engine. The first and second support mechanisms are arranged opposite to each other, and mounting holes are provided on both mechanisms. The first support mechanism includes multiple first support rods, and the second support mechanism includes a positioning block and multiple second support rods. Positioning holes are provided on the positioning block. This general-purpose aircraft engine support device can fix and support the engine, allowing the entire engine to be suspended for display, facilitating training and instruction in engine maintenance. Its advantages include: firstly, it facilitates training for multiple participants, shortening the training cycle; secondly, compared to actual aircraft operation, it provides a larger operating space, preventing injuries and unsafe incidents to trainees.

Description

Technical Field

[0001] This utility model belongs to the field of general aviation auxiliary equipment technology. Specifically, this utility model relates to a general aircraft engine support device. Background Technology

[0002] In the practical training for basic maintenance licenses of general aviation aircraft, one part of the syllabus covers the maintenance of various types of engines, requiring trainees to master some maintenance tasks for aircraft engines. However, because real aircraft engines are installed high up, it is inconvenient for trainees to operate and understand the working principles of the engine's oil and electrical systems, making training difficult.

[0003] Chinese Patent Application No. 202421070402.4 discloses a support device for an aircraft landing gear, including a first support structure and a second support structure. The aircraft landing gear includes a landing gear body and a central wing. The first support structure is connected to the central wing, and the second support structure is connected to the landing gear body. The first support structure and the second support structure together support the aircraft landing gear.

[0004] The aim is to provide a general-purpose aircraft engine support device, particularly for training and instruction on how to facilitate engine maintenance work. Utility Model Content

[0005] This invention aims to solve at least one of the technical problems existing in the prior art. To this end, this invention provides a universal aircraft engine support device, the purpose of which is to facilitate training and instruction in engine maintenance operations.

[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows: a general-purpose aircraft engine support device, including a base and a first support mechanism and a second support mechanism disposed on the base and used for connection with the engine. The first support mechanism and the second support mechanism are arranged opposite to each other. Mounting holes are provided on the first support mechanism and the second support mechanism. The first support mechanism includes a plurality of first support rods, and the second support mechanism includes a positioning block and a plurality of second support rods. Positioning holes are provided on the positioning block.

[0007] The base includes an upper frame, a base frame, and vertical support rods connected to the upper frame and the base frame. Multiple vertical support rods are provided, and the first support mechanism and the second support mechanism are provided on the upper frame.

[0008] The base also includes diagonal braces connected to the vertical support rod and the base frame. Multiple diagonal braces are provided, and the diagonal braces are inclined.

[0009] The base frame includes a first horizontal support rod and a second horizontal support rod connected to each other, and the first horizontal support rod and the second horizontal support rod are connected to the diagonal support rod and the vertical support rod.

[0010] Casters are installed on the first and second horizontal support rods.

[0011] The first support rod is vertically mounted on the upper frame, and two first support rods are provided.

[0012] The second support rod is vertically mounted on the upper frame, and two second support rods are provided.

[0013] The height of the second support rod is greater than the height of the first support rod.

[0014] This utility model discloses a universal aircraft engine support device that can fix and support the engine, allowing the entire engine to be suspended for display, facilitating training and teaching of engine maintenance operations. The advantages are twofold: firstly, it facilitates training for multiple participants, shortening the training cycle; secondly, it provides a larger operating space compared to actual aircraft operation, preventing injuries and safety incidents to trainees. Furthermore, for ease of teaching, casters are installed on the base, allowing for easy movement of the tooling. It can be flexibly deployed in both indoor and outdoor settings to meet diverse teaching needs. Moreover, compared to using actual aircraft for training, this tooling is more cost-effective and better suited for educational training. Attached Figure Description

[0015] This manual includes the following figures, which illustrate the following:

[0016] Figure 1 This is a structural schematic diagram of the general-purpose aircraft engine support device of this utility model;

[0017] Figure 2 This is another structural schematic diagram of the general-purpose aircraft engine support device of this utility model;

[0018] The following are marked in the diagram: 1. First support rod; 2. Second support rod; 3. Positioning block; 4. Caster mounting plate; 5. Caster; 6. Diagonal brace; 7. Vertical brace; 8. Upper frame; 9. First horizontal brace; 10. Second horizontal brace. Detailed Implementation

[0019] The specific embodiments of this utility model will be further described in detail below with reference to the accompanying drawings, in order to help those skilled in the art to have a more complete, accurate and in-depth understanding of the concept and technical solution of this utility model, and to facilitate its implementation.

[0020] It should be noted that in the following embodiments, the terms "first" and "second" do not represent an absolute distinction in structure and / or function, nor do they represent the order of execution, but are merely for the convenience of description.

[0021] like Figure 1 and Figure 2 As shown, this utility model provides a universal aircraft engine support device, including a base and a first support mechanism and a second support mechanism disposed on the base and used for connecting to the engine. The first support mechanism and the second support mechanism are arranged opposite to each other. The first support mechanism and the second support mechanism are provided with mounting holes. The first support mechanism includes a plurality of first support rods 1, and the second support mechanism includes a positioning block 3 and a plurality of second support rods 2. The positioning block 3 is provided with positioning holes and is used to position the engine. A plurality of casters 5 are provided on the base.

[0022] Specifically, this utility model's universal aircraft engine support device, through its first and second support mechanisms, enables multi-point fixation and support of the engine, allowing for suspended display of the entire engine and facilitating training and instruction in engine maintenance. This offers several advantages: firstly, it facilitates multi-person training, shortening the training cycle; secondly, it provides a larger operating space compared to actual aircraft operation, preventing injuries and safety incidents for trainees. Furthermore, for ease of teaching, casters 5 are installed on the base, allowing for easy movement of the tool and flexible deployment in both indoor and outdoor settings to meet diverse teaching needs.

[0023] Compared to training on actual aircraft, the use of this universal aircraft engine support device not only facilitates student practice and operation but also allows for a more convenient understanding of the disassembly and assembly of aircraft engine components, making it easier for students to comprehend and conduct practical training. Furthermore, compared to training on actual aircraft, this tooling is less expensive and more suitable for educational use.

[0024] like Figure 1 and Figure 2 As shown, the base includes an upper frame 8, a base frame, and vertical support rods 7 connected to the upper frame 8 and the base frame. The upper frame 8 is a horizontally arranged rectangular frame structure, and the first support mechanism and the second support mechanism are arranged on the upper frame 8.

[0025] like Figure 1 and Figure 2 As shown, the vertical support rods 7 are vertically arranged, and multiple vertical support rods 7 are provided. The first support arm, the second support arm, the third support arm, and the fourth support arm are arranged on the upper frame 8. The base also includes multiple diagonal support rods 6 connected to the vertical support rods 7 and the base frame, and the diagonal support rods 6 are arranged at an angle. The base frame includes a first horizontal support rod 9 and a second horizontal support rod 10 connected to each other. The first horizontal support rod 9 and the second horizontal support rod 10 are connected to the diagonal support rods 6 and the vertical support rods 7.

[0026] like Figure 1 and Figure 2As shown, in this embodiment, four vertical support rods 7 are provided, and the four vertical support rods 7 are fixedly connected to the upper frame 8 at the four right-angle corners respectively. The first horizontal support rod 9 and the second horizontal support rod 10 are horizontally arranged and fixedly connected. The length of the first horizontal support rod 9 and the second horizontal support rod 10 is greater than the length of the upper frame 8. The first horizontal support rod 9 is fixedly connected to the lower end of two of the vertical support rods 7, and the second horizontal support rod 10 is fixedly connected to the lower end of the other two vertical support rods 7. Four diagonal support rods 6 are provided. The upper end of each diagonal support rod 6 is fixedly connected to one vertical support rod 7, the lower ends of two diagonal support rods 6 are fixedly connected to the first horizontal support rod 9, and the lower ends of the other two diagonal support rods 6 are fixedly connected to the second horizontal support rod 10. The lower ends of the diagonal support rods 6 are far away from the vertical support rods 7 to form a stable support structure. This design makes the entire base structure more stable and reliable.

[0027] like Figure 1 and Figure 2 As shown, two casters 5 are each installed on the first horizontal support rod 9 and the second horizontal support rod 10, for a total of four casters 5.

[0028] like Figure 1 and Figure 2 As shown, the first support rod 1 is vertically mounted on the upper frame 8. There are two first support rods 1. The lower end of the first support rod 1 is fixedly connected to the upper frame 8. The upper end of the first support rod 1 is provided with a mounting hole for connecting to the engine. The mounting hole is used to allow bolts to pass through.

[0029] like Figure 1 and Figure 2 As shown, two second support rods 2 are vertically mounted on the upper frame 8. The lower end of each second support rod 2 is fixedly connected to the upper frame 8. One positioning block 3 is provided, and it is fixedly connected to the upper end of each second support rod 2. The positioning hole extends downward from the top surface of the positioning block 3 into its interior. The positioning hole is semi-circular, and its axis is parallel to the second direction. The positioning block 3 also has mounting holes for connecting to the engine, allowing bolts to pass through.

[0030] like Figure 1 and Figure 2 As shown, the height of the second support rod 2 is greater than the height of the first support rod 1, matching the connection point on the engine. The two first support rods 1 are on the same straight line parallel to the first direction, and the two second support rods 2 are on another straight line parallel to the first direction. Each first support rod 1 and one second support rod 2 are on the same straight line parallel to the second direction. Both the first and second directions are horizontal and perpendicular to each other.

[0031] In this embodiment, the diagonal brace 6, vertical brace 7, first horizontal brace 9 and second horizontal brace 10 are made of 40x40x3mm square steel tubes, the upper frame 8 is made of 80x40x3mm square tubes and 40x40x3mm square tubes, and the second support rod 2 is made of 40x40x3mm square steel tubes, resulting in high structural strength.

[0032] The present invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited to the above-described manner. Any non-substantial improvements made using the inventive concept and technical solution of the present invention; or the direct application of the inventive concept and technical solution to other situations without modification, are all within the protection scope of the present invention.

Claims

1. A general aviation aircraft engine support device, characterized in that: The device includes a base and a first support mechanism and a second support mechanism disposed on the base for connection with an engine. The first support mechanism and the second support mechanism are arranged opposite to each other. Mounting holes are provided on the first support mechanism and the second support mechanism. The first support mechanism includes a plurality of first support rods, and the second support mechanism includes a positioning block and a plurality of second support rods. Positioning holes are provided on the positioning block.

2. The general-purpose aircraft engine support device according to claim 1, characterized in that: The base includes an upper frame, a base frame, and vertical support rods connected to the upper frame and the base frame. Multiple vertical support rods are provided, and the first support mechanism and the second support mechanism are provided on the upper frame.

3. The general-purpose aircraft engine support device according to claim 2, characterized in that: The base also includes diagonal braces connected to the vertical support rod and the base frame. Multiple diagonal braces are provided, and the diagonal braces are inclined.

4. The general-purpose aircraft engine support device according to claim 3, characterized in that: The base frame includes a first horizontal support rod and a second horizontal support rod connected to each other, and the first horizontal support rod and the second horizontal support rod are connected to the diagonal support rod and the vertical support rod.

5. The general-purpose aircraft engine support device according to claim 4, characterized in that: Casters are installed on the first and second horizontal support rods.

6. The general-purpose aircraft engine support device according to any one of claims 2 to 5, characterized in that: The first support rod is vertically mounted on the upper frame, and two first support rods are provided.

7. The general-purpose aircraft engine support device according to any one of claims 2 to 5, characterized in that: The second support rod is vertically mounted on the upper frame, and two second support rods are provided.

8. The general-purpose aircraft engine support device according to any one of claims 2 to 5, characterized in that: The height of the second support rod is greater than the height of the first support rod.

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