Internal noise reduction device for double-rotor unmanned helicopter
By designing internal noise reduction devices for buffer components and fixed components in dual-rotor unmanned helicopters, the problems of flight noise pollution and bearing service life are solved, and noise reduction and flight safety are improved.
Patent Information
- Application Number
- CN202420060735.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-01-10
- Publication Date
- 2025-03-04
- Estimated Expiration
- 2034-01-10
AI Technical Summary
During flight, twin-rotor unmanned helicopters have noise pollution caused by high-speed rotation of internal components, as well as the problems of flight safety and service life caused by dust.
An internal noise reduction device including a buffer assembly and a fixed assembly is designed. The buffer assembly forms an elastic structure through shock absorbing springs and slide rods, which is used to buffer the shaking of the fuselage housing and reduce noise; the fixing assembly protects the bearings through a protective mechanism to prevent dust from entering.
It effectively reduces the noise generated by twin-rotor unmanned helicopters during flight, and improves the service life and flight safety of bearings.
Smart Images
Figure CN222555164U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned helicopters, in particular to an internal noise reduction device for a double-rotor unmanned helicopter. Background Art
[0002] With the rapid development of drones and their wide application in various fields, drones are getting closer and closer to people's lives, especially after the emergence of drones used in the express delivery field, which need to fly near users' homes.
[0003] However, when the existing twin-rotor unmanned helicopter is performing flight observation work near the user's residence, the high-speed rotation of the rotor and the wings inside the twin-rotor unmanned helicopter causes internal collisions to generate huge noise, causing certain noise pollution. In addition, when the twin-rotor unmanned helicopter is flying at high altitudes, the wings take off through the high-speed rotation of the bearings and the rotor, but the bearings cannot be protected, resulting in the installed bearings being affected by dust and impurities, reducing the safety and service life of the flight. Therefore, in view of the above problems, an internal noise reduction device for a twin-rotor unmanned helicopter is proposed. Utility Model Content
[0004] In order to make up for the shortcomings of the prior art and solve the problem that when a twin-rotor unmanned helicopter is flying near a user's residence for observation work, the high-speed rotation of the internal rotor and the wings of the twin-rotor unmanned helicopter causes huge noise to be generated by mutual collision, causing certain noise pollution, and when the twin-rotor unmanned helicopter is flying at high altitude, the wings take off through the high-speed rotation of the bearings and the rotor, but the bearings cannot be protected, resulting in the installed bearings being affected by dust and impurities, thereby reducing the safety and service life of the flight. The utility model proposes an internal noise reduction device for a twin-rotor unmanned helicopter.
[0005] The technical solution adopted by the utility model to solve the technical problem is: the internal noise reduction device for a dual-rotor unmanned helicopter described in the utility model comprises a fuselage shell and a mounting mechanism arranged inside the fuselage shell, wherein the mounting mechanism comprises a buffer component and a fixing component;
[0006] The buffer assembly comprises a mounting seat, a wing, a first slide bar, a second slide bar, a connecting shaft, a connecting seat and a shock absorbing spring. The mounting seat is arranged above the fuselage shell, the interior of the mounting seat is rotatably connected to the wing, a connecting seat is arranged at the lower end of the wing, the surface of the connecting seat is rotatably connected to the connecting shaft, the interior of the connecting shaft is rotatably connected to the first slide bar, the lower end of the first slide bar is fixedly connected to the shock absorbing spring, and the surface of the shock absorbing spring is clamped and connected to the second slide bar;
[0007] The fixing assembly comprises a rotating machine, a fixing frame and a connecting rod. The connecting rod is fixedly connected inside the mounting seat. One end of the connecting rod is fixedly connected to the fixing frame. The rotating machine is fixedly connected inside the fixing frame.
[0008] Preferably, heat dissipation holes are evenly arranged on the surface of the fuselage shell, a support frame is fixedly connected to the lower end of the fuselage shell, a bearing is rotatably connected inside the wing, and a protective mechanism is arranged on the outer side of the bearing and the surface of the mounting seat.
[0009] Preferably, the connecting seat is rotationally connected to the first sliding rod via the connecting shaft, the first sliding rod is fixedly connected to the shock absorbing spring, and the first sliding rod forms an elastic structure with the second sliding rod via the shock absorbing spring.
[0010] Preferably, the mounting seat is snap-connected to the inner wall of the fuselage shell via a connecting seat, and the mounting seat and the connecting seat are fixedly connected.
[0011] Preferably, the rotating machine is fixedly connected to the inner wall of the fuselage shell through a fixing frame and a connecting rod.
[0012] Preferably, the protective mechanism includes a first bracket, a second bracket and a threaded bolt, the protective mechanism is provided on the surface of the mounting seat, the first bracket is fitted and connected to the right side of the mounting seat, the second bracket is fitted and connected to the surface of the first bracket, and the first bracket is rotatably connected to the inside of the first bracket.
[0013] Preferably, the first bracket and the second bracket form a fixing structure through a threaded bolt, and the first bracket and the second bracket are internally snap-connected with bearings.
[0014] Preferably, four sets of support frames are arranged at the lower end of the fuselage shell. The utility model is beneficial in that:
[0015] 1. The utility model sets a shock-absorbing spring, and the installed connecting seat is rotatably connected with the first slide bar through the connecting shaft, so that when the rotating machine inside the mounting seat causes shaking during operation, it collides with the surface of the fuselage shell to cause huge noise. Then, the first slide bar and the shock-absorbing spring are fixedly connected, and the first slide bar and the second slide bar have a certain elastic structure through the shock-absorbing spring. The coefficient of the installed shock-absorbing spring is small, which is convenient for a certain buffering and decompression effect when the fuselage shell is shaken, thereby reducing the noise caused by the shaking between the internal parts of the dual-rotor unmanned helicopter when it is shaken during use;
[0016] 2. The utility model provides a protective mechanism, and the installed first bracket can be fixed to a certain extent by a threaded bolt and the second bracket, and is convenient for certain disassembly work. The first bracket and the second bracket are internally engaged and connected with bearings, which are used to provide a certain protective shielding effect when the wings of the twin-rotor unmanned helicopter rotate through the bearings, thereby preventing dust from entering when the twin-rotor unmanned helicopter is rotating at high speed, thereby reducing the service life of the bearings. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.
[0018] FIG1 is a schematic diagram of the overall structure of the utility model;
[0019] FIG2 is a schematic diagram of the internal structure of the body shell of the utility model;
[0020] FIG3 is a schematic diagram of the internal structure of the connection base of the utility model;
[0021] FIG. 4 is a schematic diagram of the first sliding rod connection structure of the present invention.
[0022] In the figure: 1. fuselage shell; 2. support frame; 3. heat dissipation hole; 4. mounting seat; 5. protection mechanism; 501. first bracket; 502. second bracket; 503. threaded bolt; 6. wing; 7. first slide bar; 8. second slide bar; 9. connecting shaft; 10. connecting seat; 11. bearing; 12. rotating machine; 13. fixing frame; 14. connecting support rod; 15. shock-absorbing spring. DETAILED DESCRIPTION
[0023] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0024] Embodiment 1
[0025] Please refer to Figures 1-4, an internal noise reduction device for a dual-rotor unmanned helicopter includes a fuselage shell 1 and a mounting mechanism disposed inside the fuselage shell 1, wherein the mounting mechanism includes a buffer component and a fixing component;
[0026] The buffer assembly includes a mounting seat 4, a wing 6, a first slide bar 7, a second slide bar 8, a connecting shaft 9, a connecting seat 10 and a shock-absorbing spring 15. The mounting seat 4 is arranged above the fuselage shell 1. The interior of the mounting seat 4 is rotatably connected to the wing 6. The lower end of the wing 6 is provided with a connecting seat 10. The surface of the connecting seat 10 is rotatably connected to the connecting shaft 9. The interior of the connecting shaft 9 is rotatably connected to the first slide bar 7. The lower end of the first slide bar 7 is fixedly connected to the shock-absorbing spring 15. The surface of the shock-absorbing spring 15 is engaged and connected to the second slide bar 8.
[0027] The fixing assembly includes a rotating machine 12, a fixing frame 13 and a connecting rod 14. The connecting rod 14 is fixedly connected inside the mounting seat 4. One end of the connecting rod 14 is fixedly connected to the fixing frame 13. The rotating machine 12 is fixedly connected inside the fixing frame 13.
[0028] Furthermore, the connecting seat 10 is rotationally connected to the first slide bar 7 through the connecting shaft 9, the first slide bar 7 and the shock-absorbing spring 15 are fixedly connected, the first slide bar 7 and the second slide bar 8 form an elastic structure through the shock-absorbing spring 15, and the installed connecting seat 10 is rotationally connected to the first slide bar 7 through the connecting shaft 9, which is used for when the rotating machine 12 inside the mounting seat 4 causes shaking during operation and collides with the surface of the fuselage shell 1 to cause huge noise, then the first slide bar 7 and the shock-absorbing spring 15 are fixedly connected, and the first slide bar 7 and the second slide bar 8 form a certain elastic structure through the shock-absorbing spring 15, and the coefficient of the installed shock-absorbing spring 15 is small, which is convenient for a certain buffering and decompression effect when the fuselage shell 1 is shaken.
[0029] Furthermore, the mounting seat 4 is snap-connected to the inner wall of the fuselage shell 1 through the connecting seat 10, and the mounting seat 4 and the connecting seat 10 are fixedly connected. The installed mounting seat 4 is snap-connected to the fuselage shell 1 through the connecting seat 10, and then the mounting seat 4 and the connecting seat 10 are fixedly connected, thereby reducing the shaking of the internal rotating machine 12 caused by the high-speed rotation of the wing 6, causing collision between them and generating noise.
[0030] Furthermore, the rotating machine 12 is fixedly connected to the inner wall of the fuselage shell 1 through the fixing frame 13 and the connecting support rod 14. The installed rotating machine 12 can be fixedly connected to the inner wall of the fuselage shell 1 through the fixing frame 13 and the connecting support rod 14, and a certain space is generated between the installed rotating machine 12 and the fuselage shell 1 to dissipate the heat generated by the installed rotating machine 12 when it is running at high speed.
[0031] Embodiment 2
[0032] Please refer to Figures 1 and 4, for comparison with Example 1, as another implementation of the present utility model, the surface of the fuselage shell 1 is evenly provided with heat dissipation holes 3, the lower end of the fuselage shell 1 is fixedly connected to a support frame 2, the inside of the wing 6 is rotatably connected to a bearing 11, and the outer side of the bearing 11 and the surface of the mounting seat 4 are provided with a protective mechanism 5.
[0033] Furthermore, the protective mechanism 5 includes a first bracket 501, a second bracket 502 and a threaded bolt 503. The protective mechanism 5 is provided on the surface of the mounting seat 4. The first bracket 501 is fitted and connected to the right side of the mounting seat 4. The second bracket 502 is fitted and connected to the surface of the first bracket 501. The first bracket 501 is rotatably connected to the inside with a threaded bolt 503.
[0034] Furthermore, the first bracket 501 forms a fixed structure with the second bracket 502 through the threaded bolt 503, and the first bracket 501 and the second bracket 502 are internally snap-connected with the bearing 11. The installed first bracket 501 can be fixed to a certain extent and convenient for certain disassembly work through the threaded bolt 503 and the second bracket 502, and the first bracket 501 and the second bracket 502 are internally snap-connected with the bearing 11, which is used to provide a certain protective shielding effect when the wing 6 of the twin-rotor unmanned helicopter rotates through the bearing 11, so as to avoid the entry of dust when the twin-rotor unmanned helicopter rotates at high speed, thereby reducing the service life of the bearing 11.
[0035] Furthermore, four groups of support frames 2 are set at the lower end of the fuselage shell 1, and the surface of the installed fuselage shell 1 is evenly provided with heat dissipation holes 3 for dissipating the heat inside the fuselage shell 1, and four groups of support frames 2 are set at the lower end of the fuselage shell 1 to prevent wear caused by mutual collision between the fuselage shell 1 and the ground when the twin-rotor unmanned helicopter is taking off and landing.
[0036] Working principle, first, a certain buffering effect is performed on the twin-rotor unmanned helicopter when it rotates, the installed mounting seat 4 is snap-connected with the fuselage shell 1 through the connecting seat 10, and then the mounting seat 4 and the connecting seat 10 are fixedly connected to reduce the shaking of the internal rotating machine 12 caused by the high-speed rotation of the wing 6, causing mutual collision and noise, and the installed connecting seat 10 is rotatably connected with the first slide bar 7 through the connecting shaft 9, which is used for when the internal rotating machine 12 of the mounting seat 4 causes shaking during operation, and collides with the surface of the fuselage shell 1 to cause huge noise, then the first slide bar 7 and the shock-absorbing spring 15 are fixedly connected, and the first slide bar 7 has a certain elastic structure with the second slide bar 8 through the shock-absorbing spring 15, and the coefficient of the installed shock-absorbing spring 15 is small, which is convenient for a certain buffering and decompression effect when the fuselage shell 1 is shaken.
[0037] Finally, the twin-rotor unmanned helicopter is protected to a certain extent. The installed rotating machine 12 can be fixedly connected to the inner wall of the fuselage shell 1 through the fixing frame 13 and the connecting support rod 14, and a certain space is generated between the installed rotating machine 12 and the fuselage shell 1 for dissipating the heat generated by the installed rotating machine 12 when it is running at high speed. The surface of the installed fuselage shell 1 is evenly provided with heat dissipation holes 3 for dissipating the heat inside the fuselage shell 1, and four groups of support frames 2 are provided at the lower end of the fuselage shell 1 for the wear caused by the mutual collision between the fuselage shell 1 and the ground when the twin-rotor unmanned helicopter is taking off and landing. Then, the installed first bracket 501 can be fixed to a certain extent between the threaded bolt 503 and the second bracket 502, and it is convenient to carry out certain disassembly work. The first bracket 501 and the second bracket 502 are internally engaged and connected with the bearing 11, which is used for the wing 6 of the twin-rotor unmanned helicopter to pass through the bearing 11. A certain protective shielding effect is performed during rotation to prevent dust from entering when the dual-rotor unmanned helicopter is rotating at high speed, thereby reducing the service life of the bearing 11.
[0038] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.
[0039] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments, and the above embodiments and descriptions are only for explaining the principle of the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, and these changes and improvements fall within the scope of the utility model to be protected.
Claims
1. An internal noise reduction device for a twin-rotor unmanned helicopter, comprising a fuselage shell (1) and a mounting mechanism arranged inside the fuselage shell (1), characterized in that: The mounting mechanism includes a buffer component and a fixing component; The buffer assembly comprises a mounting seat (4), a wing (6), a first slide bar (7), a second slide bar (8), a connecting shaft (9), a connecting seat (10) and a shock absorbing spring (15); the mounting seat (4) is arranged above the fuselage shell (1); the interior of the mounting seat (4) is rotatably connected to the wing (6); the lower end of the wing (6) is provided with a connecting seat (10); the surface of the connecting seat (10) is rotatably connected to the connecting shaft (9); the interior of the connecting shaft (9) is rotatably connected to the first slide bar (7); the lower end of the first slide bar (7) is fixedly connected to the shock absorbing spring (15); the surface of the shock absorbing spring (15) is snap-connected to the second slide bar (8); The fixing assembly comprises a rotating machine (12), a fixing frame (13) and a connecting rod (14); the connecting rod (14) is fixedly connected inside the mounting seat (4); one end of the connecting rod (14) is fixedly connected to the fixing frame (13); and the rotating machine (12) is fixedly connected inside the fixing frame (13).
2. The internal noise reduction device for a twin-rotor unmanned helicopter according to claim 1, characterized in that: The surface of the fuselage shell (1) is evenly provided with heat dissipation holes (3); the lower end of the fuselage shell (1) is fixedly connected to a support frame (2); the interior of the wing (6) is rotatably connected to a bearing (11); and a protective mechanism (5) is provided on the outer side of the bearing (11) and the surface of the mounting seat (4).
3. The internal noise reduction device for a twin-rotor unmanned helicopter according to claim 1, characterized in that: The connecting seat (10) is rotationally connected to the first sliding rod (7) via the connecting shaft (9), the first sliding rod (7) is fixedly connected to the shock absorbing spring (15), and the first sliding rod (7) forms an elastic structure with the second sliding rod (8) via the shock absorbing spring (15).
4. The internal noise reduction device for a twin-rotor unmanned helicopter according to claim 1, characterized in that: The mounting seat (4) is snap-fittedly connected to the inner wall of the fuselage shell (1) via the connecting seat (10), and the mounting seat (4) and the connecting seat (10) are fixedly connected.
5. The internal noise reduction device for a twin-rotor unmanned helicopter according to claim 1, characterized in that: The rotating machine (12) is fixedly connected to the inner wall of the body shell (1) via a fixing frame (13) and a connecting support rod (14).
6. The internal noise reduction device for a twin-rotor unmanned helicopter according to claim 2, characterized in that: The protective mechanism (5) comprises a first bracket (501), a second bracket (502) and a threaded bolt (503); the protective mechanism (5) is arranged on the surface of the mounting seat (4); the first bracket (501) is fitted and connected to the right side of the mounting seat (4); the second bracket (502) is fitted and connected to the surface of the first bracket (501); and the threaded bolt (503) is rotatably connected inside the first bracket (501).
7. The internal noise reduction device for a twin-rotor unmanned helicopter according to claim 6, characterized in that: The first bracket (501) and the second bracket (502) form a fixed structure through a threaded bolt (503), and the first bracket (501) and the second bracket (502) are internally snap-connected with a bearing (11).
8. The internal noise reduction device for a twin-rotor unmanned helicopter according to claim 2, characterized in that: Four groups of support frames (2) are arranged at the lower end of the fuselage shell (1).