CN217260678U - Model aeroplane and model ship driving system optimizes shock attenuation antitorque structure - Google Patents
Model aeroplane and model ship driving system optimizes shock attenuation antitorque structure Download PDFInfo
- Publication number
- CN217260678U CN217260678U CN202221103044.3U CN202221103044U CN217260678U CN 217260678 U CN217260678 U CN 217260678U CN 202221103044 U CN202221103044 U CN 202221103044U CN 217260678 U CN217260678 U CN 217260678U
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- unit
- partition frame
- cantilever
- engine
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- 230000035939 shock Effects 0.000 title claims description 5
- 238000005192 partition Methods 0.000 claims abstract description 40
- 238000013016 damping Methods 0.000 claims abstract description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 17
- 229910052799 carbon Inorganic materials 0.000 claims description 17
- 238000000926 separation method Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 5
- 239000002023 wood Substances 0.000 claims description 5
- 241000219071 Malvaceae Species 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 8
- 125000006850 spacer group Chemical group 0.000 abstract description 4
- 230000005284 excitation Effects 0.000 abstract description 2
- OKKJLVBELUTLKV-UHFFFAOYSA-N Methanol Chemical compound OC OKKJLVBELUTLKV-UHFFFAOYSA-N 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Vibration Prevention Devices (AREA)
Abstract
An optimized damping and torsion-resistant structure of an aeromodelling power system comprises an engine base unit, a cantilever unit and a spacer frame unit; the engine base unit comprises an engine base and an engine head box, the engine base is arranged at the top of the engine head box, and the engine base is used for installing an engine; the two groups of cantilever units are arranged in a V shape, one end of each cantilever unit is connected with the engine head box, and the other end of each cantilever unit is connected with the partition frame unit; the partition frame unit is provided with a front partition frame, a rear partition frame and four laminate partition frames connecting the front partition frame and the rear partition frame. The utility model can reduce the vibration amplitude, reduce the vibration amplitude and frequency under different excitations, and reduce the stress generated by the structure; the torque transmitted from the power part is reduced by the bulkhead unit and then transmitted to the aircraft body, so that the integral stability in the flight process is ensured.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle structure field especially relates to a model aeroplane and model ship driving system optimizes shock attenuation antitorque structure.
Background
For two-stroke methanol engines, vibration is an important indicator of engine operating quality. Excessive vibration can accelerate fatigue damage of components, cause damage to a carburetor, a steering engine and the like, and can also shake off fixing parts such as fastening bolts and the like, so that an engine is damaged. Therefore, for the fixed wing load unmanned aerial vehicle, effective vibration reduction measures are taken under the condition of improving the output efficiency of the engine, the more stable the working condition of the engine is, and the more convenient the flight process is to control.
Disclosure of Invention
An object of the utility model is to solve the above-mentioned problem among the prior art, provide a simple structure, less model aeroplane and model ship driving system of materials optimizes shock attenuation antitorque structure for the engine is more steady at the during operation.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
an optimized damping and torsion-resistant structure of an aeromodelling power system comprises an engine base unit, a cantilever unit and a spacer frame unit; the engine base unit comprises an engine base and an engine head box, the engine base is mounted at the top of the engine head box, and the engine base is used for mounting an engine; the two groups of cantilever units are arranged in a V shape, one end of each cantilever unit is connected with the engine head box, and the other end of each cantilever unit is connected with the partition frame unit; the partition frame unit is provided with a front partition frame, a rear partition frame and four laminate partition frames connecting the front partition frame and the rear partition frame.
Each group of cantilever units comprises two groups of cantilever strips which are arranged in parallel from top to bottom, and a cantilever connecting plate is arranged between the cantilever strips.
And a plurality of carbon laths are arranged in the partition frame unit, are connected with the front partition frame and the rear partition frame and penetrate through the front partition frame to be connected with the cantilever unit.
The carbon plate strip is equipped with 4, is located the upper and lower position of bulkhead unit inner both sides respectively.
The front partition frame and the rear partition frame are made of carbon plates; the four laminated plate separation frames are made of wood.
The wood material is a basswood material.
Compared with the prior art, the utility model discloses technical scheme obtains beneficial effect is:
on one hand, when the overall length of the nose is increased, the cantilever unit can be shortened, the vibration amplitude is reduced, and four layer plate separation frames in the increased separation frame unit are formed by basswood layer plates, so that the effect of reducing weight is achieved; on the other hand, because the square spacer unit has a better anti-torsion effect, in the flight process, the torque transmitted from the power part passes through the square spacer unit, is reduced and then is transmitted to the airframe, the anti-torsion effect of the airframe is enhanced, and the integral stability in the flight process is ensured. In the actual flight process, because the stability is improved, the phenomenon that the aircraft is out of control due to the fact that the carburetor falls off and the bolt is broken by vibration is greatly reduced, and the flight process is smoother.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Reference numerals: the engine comprises an engine 1, an engine head box 2, an engine base 3, a laminate partition frame 4, a rear partition frame 5, a front partition frame 6, a cantilever strip 7, a carbon strip 8 and a cantilever connecting plate 9.
Detailed Description
In order to make the technical problem, technical solution and beneficial effects of the present invention to be solved clearer and more obvious, the following description is made in detail by combining the accompanying drawings and embodiments.
As shown in fig. 1, the optimized damping and torsion-resisting structure of the model airplane power system in the embodiment comprises an engine base unit, a cantilever unit and a bulkhead unit;
the engine base unit comprises an engine base 3 and an engine head box 2, the engine base 3 is mounted at the top of the engine head box 2, and the engine base 3 is used for mounting an engine 1;
the cantilever units are arranged in two groups in a V shape, each group of cantilever units comprises two groups of cantilever strips 7 which are arranged in parallel up and down, and a cantilever connecting plate 9 is arranged between the cantilever strips 7; one end of the cantilever unit is connected with the engine head box 2, and the other end of the cantilever unit is connected with the bulkhead unit; in this embodiment, the cantilever bar 7 is made of a carbon plate with a thickness of 2 mm;
the bulkhead unit is provided with a front bulkhead 6, a rear bulkhead 5 and four laminate bulkheads 4 for connecting the front bulkhead and the rear bulkhead, a plurality of carbon laths 8 are arranged in the bulkhead unit, the carbon laths 8 are connected with the front bulkhead 6 and the rear bulkhead 5, penetrate through the front bulkhead 6 to be connected with the cantilever unit, and penetrate through the rear bulkhead 5 to be connected with the machine body.
In this embodiment, the carbon laths 8 are provided with 4 carbon laths respectively located at the upper and lower positions of two sides in the bulkhead unit.
The front partition frame 6 and the rear partition frame 5 are made of carbon plates; the four layer plate separation frames 4 are made of basswood.
The principle of the utility model is as follows:
the engine 1 generates vibration in the process of airplane flight, the vibration is transmitted to the cantilever bars 7 through the engine head box 2 and the engine base 3, and then is transmitted to the four carbon laths 8 through the cantilever bars 7, and the vibration is reduced through the laminate bulkhead 4, the front bulkhead 6 and the rear bulkhead 5 on the four sides of the bulkhead unit; at the same time, the bulkhead unit enhances the torsion resistance of the machine head.
In the utility model, the engine base unit consists of a fixed engine base and an engine head box, thereby increasing the structural strength; the vibration at the connection part of the machine head of the machine body is reduced by the four layer plate separation frames with the wood structure, and the weight is reduced compared with that of a carbon plate separation frame; the torsional strength of the whole partition frame unit is greatly enhanced through the strength of the partition frames of the two front and rear carbon plates; through four carbon laths, can strengthen the intensity of bulkhead unit, reduce the vibration of cantilever.
The utility model can reduce the vibration amplitude, reduce the vibration amplitude and frequency under different excitations, and reduce the stress generated by the structure; the torque transmitted from the power part is reduced by the bulkhead unit and then transmitted to the aircraft body, so that the integral stability in the flight process is ensured.
Claims (6)
1. The utility model provides a model aeroplane and model ship driving system optimizes shock attenuation antitorque structure which characterized in that: comprises an engine base unit, a cantilever unit and a bulkhead unit; the engine base unit comprises an engine base and an engine head box, the engine base is arranged at the top of the engine head box, and the engine base is used for installing an engine; the two groups of cantilever units are arranged in a V shape, one end of each cantilever unit is connected with an engine head box, and the other end of each cantilever unit is connected with the partition frame unit; the partition frame unit is provided with a front partition frame, a rear partition frame and four laminate partition frames connecting the front partition frame and the rear partition frame.
2. The optimized damping and torsion-resisting structure for the model airplane power system as claimed in claim 1, wherein: each group of cantilever units comprises two groups of cantilever strips which are arranged in parallel from top to bottom, and a cantilever connecting plate is arranged between the cantilever strips.
3. The optimized damping and torsion-resisting structure of the model airplane power system, as claimed in claim 1, wherein: and a plurality of carbon laths are arranged in the partition frame unit, are connected with the front partition frame and the rear partition frame and penetrate through the front partition frame to be connected with the cantilever unit.
4. The optimized damping and torsion-resisting structure for the model airplane power system as claimed in claim 3, wherein: the carbon plate strip is equipped with 4, is located the upper and lower position of bulkhead unit inner both sides respectively.
5. The optimized damping and torsion-resisting structure of the model airplane power system, as claimed in claim 1, wherein: the front partition frame and the rear partition frame are made of carbon plates; the four laminate separation frames are made of wood.
6. The optimized damping and torsion-resisting structure for the model airplane power system as claimed in claim 5, wherein: the wood material is a basswood material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221103044.3U CN217260678U (en) | 2022-05-09 | 2022-05-09 | Model aeroplane and model ship driving system optimizes shock attenuation antitorque structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221103044.3U CN217260678U (en) | 2022-05-09 | 2022-05-09 | Model aeroplane and model ship driving system optimizes shock attenuation antitorque structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217260678U true CN217260678U (en) | 2022-08-23 |
Family
ID=82885106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221103044.3U Expired - Fee Related CN217260678U (en) | 2022-05-09 | 2022-05-09 | Model aeroplane and model ship driving system optimizes shock attenuation antitorque structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217260678U (en) |
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2022
- 2022-05-09 CN CN202221103044.3U patent/CN217260678U/en not_active Expired - Fee Related
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220823 |
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| CF01 | Termination of patent right due to non-payment of annual fee |