A general aircraft engine support tool

Abstract

This utility model discloses a universal aircraft engine support fixture, including a base and a first support mechanism, a second support mechanism, and a third support mechanism disposed on the base for connection with the engine. The first, second, and third support mechanisms are distributed at three points, and mounting holes are provided on the first, second, and third support mechanisms. The first support mechanism includes multiple first support rods, the second support mechanism includes multiple second support rods, and the third support mechanism includes multiple third support rods. This universal aircraft engine support fixture can fix and support the engine, allowing the entire engine to be suspended for display, facilitating training and teaching of engine maintenance operations. Its advantages include: firstly, facilitating training for multiple participants and shortening the training cycle; secondly, providing a larger operating space compared to actual aircraft operation, 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 fixture. 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 universal aircraft engine support fixture, particularly for training and instruction on how to facilitate engine maintenance operations. 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 fixture, intended 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 fixture, including a base and a first support mechanism, a second support mechanism, and a third support mechanism disposed on the base and used for connection with the engine. The first support mechanism, the second support mechanism, and the third support mechanism are distributed at three points. Mounting holes are provided on the first support mechanism, the second support mechanism, and the third support mechanism. The first support mechanism includes a plurality of first support rods, the second support mechanism includes a plurality of second support rods, and the third support mechanism includes a plurality of third support rods.

[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, the second support mechanism, and the third 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 mechanism further includes a first mounting plate, which is disposed on the upper frame, and the first support rod is vertically disposed on the first mounting plate.

[0012] The second support mechanism further includes a second mounting plate, which is disposed on the second support rod, and the second support rod is vertically disposed on the upper frame.

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

[0014] This utility model discloses a universal aircraft engine support fixture 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: 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 fixture. 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 fixture 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 schematic diagram of the structure of the general-purpose aircraft engine support tooling of this utility model;

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

[0018] The following are marked in the diagram: 1. First support rod; 2. Second support rod; 3. Third support rod; 4. First mounting plate; 5. Second mounting plate; 6. Diagonal brace; 7. Vertical brace; 8. Upper frame; 9. First horizontal brace; 10. Second horizontal brace; 11. Caster; 12. Caster mounting plate. 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," "second," and "third" do not represent an absolute distinction in structure and / or function, nor do they represent the order of execution; they 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 fixture, including a base and a first support mechanism, a second support mechanism, and a third support mechanism disposed on the base and used for connection with the engine. The first support mechanism, the second support mechanism, and the third support mechanism are distributed at three points. Mounting holes are provided on the first support mechanism, the second support mechanism, and the third support mechanism. The first support mechanism includes a plurality of first support rods 1, the second support mechanism includes a plurality of second support rods 2, and the third support mechanism includes a plurality of third support rods 3. A plurality of casters 11 are provided on the base.

[0022] Specifically, this utility model's universal aircraft engine support fixture, through its first, second, and third 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 11 are installed on the base, allowing for easy movement of the fixture and flexible placement 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 fixture 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 fixture 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, the second support mechanism, and the third 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 2 As 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 11 are installed on each of the first horizontal support rod 9 and the second horizontal support rod 10, for a total of four casters 11.

[0028] like Figure 1 and Figure 2 As shown, the first support mechanism also includes a first mounting plate 4, which is fixedly mounted on the upper frame 8. The first mounting plate 4 is horizontally mounted, and the first support rod 1 is vertically mounted on the first mounting plate 4. The lower end of the first support rod 1 is fixedly connected to the first mounting plate 4. Two first support rods 1 are provided, and 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 2As shown, the second support mechanism also includes a second mounting plate 5, which is disposed on the second support rod 2, and the second support rod 2 is vertically disposed on the upper frame 8. The lower end of the second support rod 2 is fixedly connected to the upper frame 8, and the second mounting plate 5 is fixedly connected to the upper end of the second support rod 2. Two second support rods 2 are provided. The upper end of the second mounting plate 5 is provided with mounting holes for connecting to the engine, and the mounting holes are for bolts to pass through.

[0030] like Figure 1 and Figure 2 As shown, two third support rods 3 are provided. The lower end of the third support rod 3 is fixedly connected to the upper frame 8, and the upper end of the third support rod 3 is provided with a mounting hole for connecting to the engine. The mounting hole is used to allow bolts to pass through.

[0031] like Figure 1 and Figure 2 As shown, the height of the second support rod 2 is greater than the heights of the first support rod 1 and the third support rod 3, matching the connection point on the engine. The two first support rods 1 are on the same straight line parallel to the first direction, the two second support rods 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, and the two third support rods 3 are also on the same straight line parallel to the first direction.

[0032] 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 first support rod 1, second support rod 2 and third support rod 3 are made of 40x40x3mm square steel tubes, resulting in high structural strength.

[0033] 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-purpose aircraft engine support fixture, characterized in that: It includes a base and a first support mechanism, a second support mechanism, and a third support mechanism disposed on the base and used for connection with an engine. The first support mechanism, the second support mechanism, and the third support mechanism are distributed at three points. Mounting holes are provided on the first support mechanism, the second support mechanism, and the third support mechanism. The first support mechanism includes a plurality of first support rods, the second support mechanism includes a plurality of second support rods, and the third support mechanism includes a plurality of third support rods.

2. The general-purpose aircraft engine support fixture 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, the second support mechanism, and the third support mechanism are provided on the upper frame.

3. The general-purpose aircraft engine support fixture 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 fixture 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 fixture 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 fixture according to any one of claims 2 to 5, characterized in that: The first support mechanism further includes a first mounting plate, which is disposed on the upper frame, and the first support rod is vertically disposed on the first mounting plate.

7. The general-purpose aircraft engine support fixture according to any one of claims 2 to 5, characterized in that: The second support mechanism further includes a second mounting plate, which is disposed on the second support rod, and the second support rod is vertically disposed on the upper frame.

8. The general-purpose aircraft engine support fixture 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 and the third support rod.

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