Supporting structure for general aero-engine test

Abstract

The utility model provides a supporting structure for a general aero-engine test, and solves the technical problems that a conventional general aero-engine supporting device can only realize supporting, cannot adjust the direction of a supported aero-engine, and is relatively inconvenient to use. Comprising a supporting assembly, a supporting base, a driving assembly and a second supporting spring. The supporting assembly comprises an upper sleeve and a lower sleeve which are detachably connected, the lower sleeve is provided with a sliding block, and the upper sleeve and the lower sleeve define a cavity used for containing the aero-engine; the supporting base is provided with an arc-shaped sliding groove, and the sliding block of the supporting assembly is connected to the arc-shaped sliding groove in a sliding mode; the driving assembly is connected to the supporting assembly and drives the supporting assembly to reciprocate in the extending direction of the sliding groove; the supporting spring is connected to the supporting assembly and the ground so as to support the supporting assembly in the radial direction of the upper sleeve and the lower sleeve, the supporting assembly can move in a reciprocating mode along the arc-shaped sliding groove, the rotating effect of supporting the whole base is achieved, and the supporting direction of the aero-engine is adjusted in a small range.

Description

Technical Field

[0001] The utility model relates to the technical field of supporting devices, in particular to a supporting structure for general aviation engine testing. Background Art

[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry. Every important change in human aviation history is closely related to the technological progress of aircraft engines.

[0003] During the test of an aircraft engine, a supporting device is required to support the aircraft engine. In the prior art, the supporting device can only provide support but cannot adjust the position of the supported aircraft engine, which is inconvenient to use. Utility Model Content

[0004] The utility model aims to provide a general aviation engine test support structure to solve the technical problem that the current general aviation engine support device can only provide support but cannot adjust the position of the supported aviation engine, which is inconvenient to use.

[0005] The embodiments of the present invention are implemented by the following technical solutions:

[0006] A support structure for general aviation engine testing, comprising a support assembly, a support base, and a second support spring of a drive assembly;

[0007] The support assembly comprises an upper sleeve and a lower sleeve which are detachably connected, the lower sleeve is provided with a sliding block, and the upper sleeve and the lower sleeve together enclose a cavity for accommodating the aircraft engine;

[0008] The support base is provided with an arc-shaped slide groove, and the slider of the support assembly is slidably connected to the arc-shaped slide groove;

[0009] The driving assembly is connected to the supporting assembly and drives the supporting assembly to reciprocate along the extending direction of the slideway;

[0010] The support spring is connected to the support assembly and the ground to support the support assembly along the radial direction of the upper sleeve and the lower sleeve.

[0011] In some embodiments, the upper sleeve and the lower sleeve are both provided with a connecting plate, and the connecting plate is connected to the supporting spring.

[0012] In some embodiments, the driving assembly includes a rotating motor, a rotating shaft, and a rotating plate, wherein the rotating plate is arranged in a circumferential direction of the rotating shaft and connected to the supporting assembly, and the rotating motor is connected to the rotating shaft.

[0013] In some embodiments, a plurality of the support springs are provided and are spaced apart along the axial direction of the upper sleeve and the lower sleeve.

[0014] In some embodiments, the upper sleeve is further provided with a lifting lug.

[0015] In some embodiments, the lifting ears are provided in plurality and are spaced apart along the axial direction of the upper sleeve.

[0016] In some embodiments, inner walls of the upper sleeve and the lower sleeve are both provided with elastic cushion layers.

[0017] The technical solution of the embodiment of the utility model has at least the following advantages and beneficial effects:

[0018] (1) The utility model is provided with an arc-shaped slide groove, and the slider of the support assembly is slidably connected to the arc-shaped slide groove, that is, the support assembly can reciprocate along the arc-shaped slide groove to achieve the overall rotation effect of the support base, so as to adjust the support position of the aircraft engine in a small range.

[0019] (2) The utility model is provided with a support spring to radially support the support assembly, thereby providing auxiliary support for the aircraft engine.

[0020] (3) The utility model is provided with an upper sleeve and a lower sleeve that are detachably connected and are sleeved on the outside of the aircraft engine to increase the fixing effect on the aircraft engine.

[0021] (4) The utility model has reasonable design, simple structure and good practicality. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 A schematic diagram of the structure of the support structure for aircraft engine testing provided by an embodiment of the utility model;

[0024] Figure 2 A schematic diagram of the structure of the support structure for aircraft engine testing provided by an embodiment of the utility model without the support spring;

[0025] icon:

[0026] 100. Support base;

[0027] 210, upper sleeve; 220, lower sleeve; 230, connecting plate; 240, lifting lug;

[0028] 310, rotating motor; 320, rotating shaft; 330, rotating plate;

[0029] 400, support spring;

[0030] 500. Limiting parts. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Generally, the components of the embodiments of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

[0032] Example

[0033] An embodiment of the present application provides a support structure for general aviation engine testing, so as to adjust the orientation of the aviation engine when the aviation engine is located on the support structure.

[0034] See also Figure 1 as well as Figure 2 , a general aviation engine test support structure, including a support assembly, a support base 100, and a second support spring 400 of a drive assembly;

[0035] A support assembly includes an upper sleeve 210 and a lower sleeve 220 that are detachably connected, the lower sleeve 220 is provided with a slider, the upper sleeve 210 and the lower sleeve 220 are combined to form a cavity for accommodating an aircraft engine, in some embodiments, the upper sleeve 210 and the lower sleeve 220 are connected by bolts, in some embodiments, the upper sleeve 210 and the lower sleeve 220 both include connected ferrules and ferrule connecting rods, and the ferrules are arranged at intervals along the extension direction of the aircraft engine;

[0036] The support base 100 is provided with an arc-shaped slide groove, and the slider of the support assembly is slidably connected to the arc-shaped slide groove to reciprocate along the circumference of the arc-shaped slide groove;

[0037] A driving assembly is connected to the supporting assembly and drives the supporting assembly to reciprocate along the extending direction of the slide slot to adjust the orientation of the aircraft engine;

[0038] The support spring 400 is connected to the support assembly and the ground to support the support assembly in the radial direction of the upper sleeve 210 and the lower sleeve 220. In some embodiments, the support spring 400 is connected to both sides of the support assembly.

[0039] In some embodiments, both the upper sleeve 210 and the lower sleeve 220 are provided with a connecting plate 230, and the connecting plate 230 is connected to the support spring 400. In some embodiments, a connecting plate 230 is provided on the top of the upper sleeve 210, and in some embodiments, a connecting plate 230 is provided on the bottom of the lower sleeve 220.

[0040] In some embodiments, the driving assembly includes a rotating motor 310, a rotating shaft 320 and a rotating plate 330. The rotating plate 330 is arranged on the circumference of the rotating shaft 320 and is connected to the supporting assembly. The rotating motor 310 is connected to the rotating shaft 320. In some embodiments, the rotating plate 330 is connected to the bottom of the connecting plate 230 to connect the upper sleeve 210 and the lower sleeve 220. In some embodiments, the sliders are arranged on both sides of the rotating plate 330.

[0041] In some embodiments, a plurality of support springs 400 are provided and are spaced apart along the axial direction of the upper sleeve 210 and the lower sleeve 220 . In some embodiments, a plurality of support springs 400 are provided and are evenly arranged along both sides of the upper sleeve 210 and the lower sleeve 220 .

[0042] In some embodiments, the upper sleeve 210 is further provided with a lifting ear 240 . In some embodiments, a plurality of lifting ears 240 are provided. In some embodiments, the top of the upper sleeve 210 is connected to the connecting plate 230 , and a plurality of lifting ears 240 are connected to the top of the connecting plate 230 .

[0043] In some embodiments, a plurality of lifting ears 240 are provided, which are spaced apart along the axial direction of the upper sleeve 210 . In some embodiments, two lifting ears 240 are provided.

[0044] In some embodiments, the support base 100 is provided with a limiting member 500 to limit the radial position of the support assembly.

[0045] In some embodiments, the inner walls of the upper sleeve 210 and the lower sleeve 220 are both provided with elastic cushion layers to prevent scratches on the outer wall of the aircraft engine and to increase the friction effect.

[0046] The following is a detailed description of the use process of the general aviation engine test support structure of the present application:

[0047] When in use, place the aircraft engine on the lower sleeve 220, then connect and fix the upper sleeve 210 and the lower sleeve 220, and rotate the motor 310 to drive the rotating shaft 320 and the rotating plate 330 to rotate, thereby driving the supporting assembly to rotate, thereby driving the aircraft engine to slide on the supporting base 100 and adjust its orientation.

[0048] The general aviation engine test support structure of the present application has at least the following advantages:

[0049] (1) The utility model is provided with an arc-shaped slide groove, and the slider of the support assembly is slidably connected to the arc-shaped slide groove, that is, the support assembly can reciprocate along the arc-shaped slide groove to achieve the overall rotation effect of the support base, so as to adjust the support position of the aircraft engine in a small range.

[0050] (2) The utility model is provided with a support spring to radially support the support assembly, thereby providing auxiliary support for the aircraft engine.

[0051] (3) The utility model is provided with an upper sleeve and a lower sleeve that are detachably connected and are sleeved on the outside of the aircraft engine to increase the fixing effect on the aircraft engine.

[0052] (4) The utility model has reasonable design, simple structure and good practicality.

[0053] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may be subject to various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A general aviation engine test support structure, characterized in that: include: A support assembly, comprising an upper sleeve and a lower sleeve which are detachably connected, wherein the lower sleeve is provided with a sliding block, and the upper sleeve and the lower sleeve together enclose a cavity for accommodating the aircraft engine; The support base is provided with an arc-shaped slide groove, and the slider of the support assembly is slidably connected to the arc-shaped slide groove; A driving assembly, connected to the supporting assembly, driving the supporting assembly to reciprocate along the extending direction of the slideway; A support spring is connected to the support assembly and the ground to support the support assembly along the radial direction of the upper sleeve and the lower sleeve.

2. The general aviation engine test support structure according to claim 1, characterized in that: The upper sleeve and the lower sleeve are both provided with connecting plates, and the connecting plates are connected to the supporting springs.

3. The general aviation engine test support structure according to claim 1, characterized in that: The driving assembly includes a rotating motor, a rotating shaft and a rotating plate. The rotating plate is arranged in the circumference of the rotating shaft and connected to the supporting assembly. The rotating motor is connected to the rotating shaft.

4. The general aviation engine test support structure according to claim 1, characterized in that: The support springs are provided in plurality and are spaced apart along the axial direction of the upper sleeve and the lower sleeve.

5. The general aviation engine test support structure according to any one of claims 1 to 4, characterized in that: The upper sleeve is also provided with a lifting lug.

6. The general aviation engine test support structure according to claim 5, characterized in that: The lifting ears are provided in plurality and are spaced apart along the axial direction of the upper sleeve.

7. The general aviation engine test support structure according to any one of claims 1 to 4, characterized in that: The inner walls of the upper sleeve and the lower sleeve are both provided with elastic cushion layers.

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