Turnover helicopter engine air inlet protection device
By designing a reversible helicopter engine air intake protection device and adopting a quick unloading pin connection structure, the problem of time-consuming and labor-intensive dismantling of traditional devices is solved, and the rapid flip and maintenance of the engine air intake passage is achieved, and the efficiency of flight inspection is improved.
Patent Information
- Application Number
- CN202422148776.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-03
- Publication Date
- 2025-08-05
- Estimated Expiration
- 2034-09-03
AI Technical Summary
The disassembly of the air intake protection device of traditional helicopter engines is time-consuming and labor-intensive, and it is difficult to meet the rapid maintenance and maintenance needs of the engine.
A flipped helicopter engine air intake protection device is designed, and a quick-release pin connection structure is adopted, including front outer ears, front inner ears, mounting brackets and rear inner ears. Quick-release pins are used to achieve rapid flip, combined with rubber pads to prevent skin damage to the fuselage.
It realizes rapid flip of the engine air intake duct, meets daily maintenance and maintenance needs, and improves flight inspection efficiency.
Smart Images
Figure CN223190519U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of helicopter engines, in particular to a flippable helicopter engine air intake protection device. Background Art
[0002] In order to improve the take-off and landing and flight safety of aircraft in sandy and dusty environments, an air intake protection device is installed on the front side of the engine air intake system to reduce the wear of sand and dust on the engine, provide clean air for the engine, and extend the service life of the engine. At the same time, in order to facilitate daily inspection and maintenance of the engine, it has a good protective effect on one side of the engine. Therefore, it is necessary to install a flippable helicopter engine air intake protection device to solve the above problems.
[0003] The engine needs regular inspection and maintenance, but the traditional bolt fixing and disassembly is time-consuming and labor-intensive. Flipping solves the problem of disassembly time and convenience. Utility Model Content
[0004] The purpose of this utility model is to provide a reversible helicopter engine air intake protection device.
[0005] In order to achieve the above-mentioned purpose, a flippable helicopter engine air intake protection device is provided, comprising a sand control device body, a mounting assembly is provided at the upper end of the sand control device body, a mounting interface assembly is provided on one side of the mounting assembly, a quick-release pin is provided between the mounting assembly and the mounting interface assembly, the mounting assembly comprises a front outer ear piece, a front inner ear piece, a mounting bracket, and a rear inner ear piece, the front outer ear piece is arranged on the front outer side of the sand control device body, the front inner ear piece is arranged on the front inner side of the sand control device body, the mounting bracket is arranged on the rear outer side of the sand control device body, the rear inner ear piece is arranged on the rear inner side of the sand control device body, and the mounting interface assembly comprises a front outer bracket, a front inner bracket, a mounting ear piece, and a rear inner bracket.
[0006] According to the reversible helicopter engine air intake protection device, a rubber pad is fixedly connected to one side of the sand control device body.
[0007] According to the reversible helicopter engine air intake protection device, an offset handle is fixedly connected to the other side of the sand control device body.
[0008] Beneficial effects:
[0009] The helicopter engine air intake protection device can be quickly flipped over to meet the daily maintenance and inspection of the engine air intake duct.
[0010] Additional aspects and advantages of the present invention will be given in part in the following description and will become apparent from the following description or learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS
[0011] The present invention will be further described below with reference to the accompanying drawings and embodiments;
[0012] Figure 1 This is a schematic structural diagram of a reversible helicopter engine air intake protection device proposed in the utility model;
[0013] Figure 2 This is a partial structural diagram of a reversible helicopter engine air intake protection device proposed in this utility model. Figure 1 ;
[0014] Figure 3 This is a partial structural diagram of a reversible helicopter engine air intake protection device proposed in this utility model. Figure 2 ;
[0015] Figure 4 This is a schematic structural diagram of a flippable helicopter engine air intake protection device proposed in the present invention after flipping;
[0016] Figure 5 This is a partial schematic diagram of the structure of a flippable helicopter engine air intake protection device proposed by the present invention, showing the flipped air intake protection device.
[0017] Legend:
[0018] 1. Sand control device body; 2. Mounting assembly; 21. Front outer ear; 22. Front inner ear; 23. Mounting bracket; 24. Rear inner ear; 3. Mounting interface assembly; 31. Front outer bracket; 32. Front inner bracket; 33. Mounting ear; 34. Rear inner bracket; 4. Rubber pad; 5. Offset handle; 6. Quick-release pin. DETAILED DESCRIPTION
[0019] This section will describe in detail the specific embodiments of the present invention. The preferred embodiments of the present invention are shown in the accompanying drawings. The purpose of the accompanying drawings is to supplement the description of the text part of the specification with graphics, so that people can intuitively and vividly understand each technical feature and overall technical solution of the present invention, but it cannot be understood as a limitation on the scope of protection of the present invention.
[0020] Reference Figure 1-5, the utility model embodiment is a reversible helicopter engine air intake protection device, which includes a sand control device body 1, which is a box-shaped design as a whole and is arranged on the engine air intake. The upper end of the sand control device body 1 is provided with a mounting assembly 2, which is arranged on the sand control device body 1, and a hinge is provided at one end of the mounting assembly 2. The sand control device body 1 can be quickly opened and closed by the hinge and the quick-release pin 6. A mounting interface assembly 3 is provided on one side of the mounting assembly 2. The mounting interface assembly 3 is arranged on the helicopter skin. One end of the mounting interface assembly 3 is connected to the mounting assembly 2 through a hinge, and the other end of the mounting interface assembly 3 is connected to the mounting assembly 2 through a quick-release pin 6. A quick-release pin 6 is provided between the mounting assembly 2 and the mounting interface assembly 3. The mounting assembly 2 includes a front outer ear piece 21 and a front inner ear piece 22. , mounting bracket 23, rear inner ear piece 24, the front outer ear piece 21 is arranged on the front outer side of the sand control device body 1, the front inner ear piece 22 is arranged on the front inner side of the sand control device body 1, the mounting bracket 23 is arranged on the rear outer side of the sand control device body 1, and the rear inner ear piece 24 is arranged on the rear inner side of the sand control device body 1. The mounting interface assembly 3 includes a front outer bracket 31, a front inner bracket 32, a mounting ear piece 33, and a rear inner bracket 34. The front outer bracket 31 is arranged on the front outer side of the fuselage skin; the front inner bracket 32 is arranged on the front inner side of the fuselage skin; the mounting ear piece 33 is arranged on the rear outer side of the fuselage skin; the rear inner bracket 34 is arranged on the rear inner side of the fuselage skin. When the sand control device body 1 is flipped over, the front outer ear piece 21 and the front outer bracket 31 are connected by the quick-release pin 6 to achieve positioning.
[0021] A rubber pad 4 is fixedly connected to one side of the sand control device body 1.
[0022] An offset handle 5 is fixedly connected to the other side of the sand control device body 1 .
[0023] Working principle: After the device is installed, the installation assembly 2 includes a front outer ear piece 21, which is arranged on the front outer side of the sand control device body 1; a front inner ear piece 22 is arranged on the front inner side of the sand control device body 1; a mounting bracket 23 is arranged on the rear outer side of the sand control device body 1; a rear inner ear piece 24 is arranged on the rear inner side of the sand control device body 1; an offset handle 5 is arranged on the rear side of the sand control device body 1; a rubber pad 4 is arranged on the front side of the sand control device body 1; the installation interface assembly 3 includes a front outer bracket 31 arranged on the front outer side of the fuselage skin; a front inner bracket 32 is arranged on the front inner side of the fuselage skin; a mounting ear piece 33 is arranged on the rear outer side of the fuselage skin; a rear inner bracket 34 It is arranged on the rear inner side of the fuselage skin; the front outer ear 21 is hinged to the front outer bracket 31, the front inner ear 22 is hinged to the front inner bracket 32, the mounting bracket 23 is connected to the mounting ear 33 by a quick-release pin 6, and the rear inner ear 24 is connected to the rear inner bracket 34 by a quick-release pin 6. When the sand control device body 1 is flipped over, the front outer ear 21 and the front outer bracket 31 are connected by the quick-release pin 6 to achieve positioning; the rubber pad 4 comes into contact with the fuselage skin to prevent the sand control device body 1 from damaging the fuselage skin. When the aircraft engine needs to be inspected and maintained, the device can be quickly opened and closed, thereby improving the efficiency of flight inspection.
[0024] The embodiments of the present invention are described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Various changes can be made within the scope of knowledge possessed by ordinary technicians in the technical field without departing from the purpose of the present invention.
Claims
1. A reversible helicopter engine air intake protection device, comprising a sand control device body (1), characterized in that: The upper end of the sand control device body (1) is provided with a mounting assembly (2), a mounting interface assembly (3) is provided on one side of the mounting assembly (2), a quick release pin (6) is provided between the mounting assembly (2) and the mounting interface assembly (3), the mounting assembly (2) comprises a front outer ear piece (21), a front inner ear piece (22), a mounting bracket (23), and a rear inner ear piece (24), the front outer ear piece (21) is provided on the front outer side of the sand control device body (1), the front inner ear piece (22) is provided on the front inner side of the sand control device body (1), the mounting bracket (23) is provided on the rear outer side of the sand control device body (1), and the rear inner ear piece (24) is provided on the rear inner side of the sand control device body (1), the mounting interface assembly (3) comprises a front outer bracket (31), a front inner bracket (32), a mounting ear piece (33), and a rear inner bracket (34).
2. The reversible helicopter engine air intake protection device according to claim 1, characterized in that: A rubber pad (4) is fixedly connected to one side of the sand control device body (1).
3. The reversible helicopter engine air intake protection device according to claim 1, characterized in that: An offset handle (5) is fixedly connected to the other side of the sand control device body (1).