CN211777732U - Two-stroke oil-leakage-proof air cooling cylinder for aviation - Google Patents
Two-stroke oil-leakage-proof air cooling cylinder for aviation Download PDFInfo
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- CN211777732U CN211777732U CN201922444537.8U CN201922444537U CN211777732U CN 211777732 U CN211777732 U CN 211777732U CN 201922444537 U CN201922444537 U CN 201922444537U CN 211777732 U CN211777732 U CN 211777732U
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Abstract
The utility model discloses a two-stroke leak protection oil aviation water cold air cylinder, including water-cooling cylinder body and water-cooling cylinder head, the cold air cylinder head is installed at water-cooling cylinder body top, water-cooling cylinder head top both sides are equipped with the lug respectively, be equipped with water inlet and delivery port on the lug respectively, water-cooling cylinder head outer end is the cambered surface, evenly be equipped with four sunkenly in the cambered surface, be equipped with the mounting hole in the sunkenly, be equipped with the high strength bolt of connecting water-cooling cylinder body in the mounting hole, the inside annular water course of going up that is equipped with of water-cooling cylinder head, the inside lower annular water course that is equipped with the bottom intercommunication of water-cooling cylinder body, it is linked together with. The utility model discloses rational in infrastructure, the modern design, easily processing, and water-cooling cylinder water inlet and delivery port all set up and have effectively increased cooling area on water-cooling cylinder jar head, and the cooling effect is good.
Description
Technical Field
The utility model relates to a cylinder water-cooling technical field specifically indicates a two-stroke leak protection oil aviation water cold air cylinder.
Background
In recent years, the market of unmanned aerial vehicles is rapidly developed, and especially, the unmanned aerial vehicle has the advantages of wide application, low cost, high efficiency and no casualty risk; the device has the advantages of strong survivability, good maneuverability, convenient use and the like, has extremely important function in military application, and has wider prospect in the civil field.
Unmanned aerial vehicles can be divided into military and civilian: in the military aspect: completing battlefield reconnaissance and monitoring, positioning and correcting, damage assessment, electronic warfare and the like; in the civil aspect: agriculture, plant protection, aerial photography, aerial prospecting, disaster monitoring, traffic patrol, public security monitoring and the like.
Unmanned aerial vehicle is when the start, if the cylinder high temperature and sealed not well exist the oil leak phenomenon, very easily cause engine power to descend, it is weak with higher speed, the oil consumption increases, the engine can not normally burn, and whole overheated still very easily leads to the fit clearance between the internal parts to diminish, hinders the normal operating of engine, very easily causes the engine to die, produces potential safety hazard and very big economic loss.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to overcome prior art shortcoming, provide a two-stroke leak protection oil aviation water air cooler jar, rational in infrastructure.
In order to solve the technical problem, the utility model provides a technical scheme does: a two-stroke oil leakage-proof aviation water cooling cylinder comprises a water cooling cylinder body and a water cooling cylinder head, wherein the water cooling cylinder head is installed at the top of the water cooling cylinder body, protruding blocks are arranged on two sides of the top of the water cooling cylinder head respectively, a water inlet and a water outlet are formed in the protruding blocks respectively, the outer end of the water cooling cylinder head is a cambered surface, four recesses are evenly formed in the cambered surface, mounting holes are formed in the recesses, high-strength bolts connected with the water cooling cylinder body are arranged in the mounting holes, an upper annular water channel is arranged inside the water cooling cylinder head, a lower annular water channel communicated with the bottom is arranged inside the water cooling cylinder body, the upper annular water channel is communicated with the lower annular water channel, the water inlet and the water outlet are communicated with an upper annular water channel, four groups of corresponding spacers are evenly arranged at the bottom of the upper annular water channel and the top of the lower annular water channel, and the high-, and a weight reduction area is arranged at the bottom of the water-cooling cylinder body.
Furthermore, the middle part in the water-cooling cylinder body is provided with an annular boss, and the bottom all is equipped with annular boss matched with annular concave station in the water-cooling cylinder head.
Furthermore, the water inlet and the water outlet are arranged in a water-cooling cylinder head central symmetry manner, and a water inlet pipe and a water outlet pipe are arranged on the water inlet and the water outlet.
Furthermore, the inner wall and the outer wall of the water-cooling cylinder body are provided with exhaust pipe orifices.
Furthermore, a spare spark plug hole position is arranged on the cylinder head of the water-cooled cylinder and is used for double ignition of the two-stroke oil-leakage-proof aviation water-cooled cylinder.
Further, a sealing ring is arranged on the outer ring of the water-cooling cylinder body, and a sealing gasket is arranged between the annular boss and the annular concave table.
Furthermore, the water-cooling cylinder body and the water-cooling cylinder head are both formed by aluminum casting.
Compared with the prior art, the utility model the advantage lie in: the utility model has reasonable structure, novel design and easy processing, the water inlet and the water outlet of the water-cooling cylinder are both arranged on the head of the water-cooling cylinder, the cooling area is effectively increased, the cooling effect is good, the arc-shaped design of the water inlet ensures that the matching of the water inlet and the water outlet is more reliable, the water passing efficiency is greatly improved, the water-cooling cylinder body and the water-cooling cylinder cover are more convenient to position while the bolts are arranged on the water-cooling cylinder body and the water-cooling cylinder cover, the sealing ring is arranged on the water-cooling cylinder body to effectively prevent the water-cooling cylinder from leaking, thus the better heat dissipation effect of the water-cooling cylinder can be realized, in addition, the combustion chamber of the water-cooling cylinder is changed into the sinking type design without changing the stroke of the water-cooling cylinder, the oil leakage phenomenon of the water-cooling cylinder is effectively prevented, the reduction of, the whole design is safe and reliable.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural view of the recycled water cooling cylinder body of the present invention.
Fig. 3 is a schematic structural view of the cylinder head of the reclaimed water cold air cylinder of the present invention.
Fig. 4 is a sectional structure view of the cylinder body of the reclaimed water cold air cylinder of the utility model.
As shown in the figure: 1. the water-cooling air cylinder comprises a water-cooling air cylinder body, 2, a water-cooling air cylinder head, 3, a convex block, 4, a water inlet, 5, a water outlet, 6, an arc surface, 7, a recess, 8, an installation hole, 9, an upper annular water channel, 10, a lower annular water channel, 11, a spacer block, 12, a weight reduction area, 13, an annular boss, 14, an annular concave table, 15, an exhaust pipe opening, 16, a spare spark plug hole position, 17, a sealing ring, 18 and a sealing gasket.
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "lateral", "up", "down", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified. Furthermore, the term "comprises" and any variations thereof is intended to cover non-exclusive inclusions.
The present invention will be described in further detail with reference to the accompanying drawings.
The utility model discloses when the concrete implementation, a two-stroke leak protection oil aviation water cold air cylinder, including water-cooling cylinder body 1 and water-cooling cylinder head 2, cold air cylinder head 2 is installed at water-cooling cylinder body 1 top, water-cooling cylinder head 2 top both sides are equipped with lug 3 respectively, be equipped with water inlet 4 and delivery port 5 on the lug 3 respectively, the outer end of water-cooling cylinder head 2 is cambered surface 6, evenly be equipped with four sunken 7 on cambered surface 6, be equipped with mounting hole 8 in the sunken 7, be equipped with the high strength bolt of connecting water-cooling cylinder body 1 in the mounting hole 8, water-cooling cylinder head 2 is inside to be equipped with upper annular water course 9, water-cooling cylinder body 1 is inside to be equipped with lower annular water course 10 that the bottom communicates, upper annular water course 9 and lower annular water course 10 communicate, water inlet 4 and delivery port 5 all communicate upper annular water course 9, four groups of corresponding spacing blocks 11 are uniformly arranged at the bottom of the upper annular water channel 9 and the top of the lower annular water channel 10, the high-strength bolts penetrate through the mounting holes 8 and are fixedly connected with the spacing blocks 11, and a weight reduction area 12 is arranged at the bottom of the water-cooling cylinder body 1.
Middle part is provided with annular boss 13 in the water-cooling cylinder body 1, the bottom all is equipped with annular boss 13 matched with annular concave station 14 in the water-cooling cylinder head 2, water inlet 4 and delivery port 5 are water-cooling cylinder head 2 central symmetry and set up, be provided with inlet tube and outlet pipe on water inlet 4 and the delivery port 5, be provided with exhaust pipe mouth 15 on the wall in the water-cooling cylinder body 1, be provided with reserve spark plug hole site 16 on the water-cooling cylinder head 2 for two stroke leak protection oil aviation water cold air cylinder dual-ignition, be provided with sealing washer 17 on the water-cooling cylinder body 1 outer lane, be equipped with seal gasket 18 between annular boss 13 and the annular concave station 14, water-cooling cylinder body 1 and water-cooling cylinder head 2 are the aluminium casting and form.
The utility model discloses a theory of operation: the cooling water enters the upper annular water channel 9 and the lower annular water channel 10 after passing through the water inlet 4, so that the water-cooled cylinder body 1 obtains a larger cooling area, the water after absorbing heat is discharged from the water outlet 5 on the water-cooled cylinder head 2, the high-strength bolt on the water-cooled cylinder head 2, the spacing blocks 11 and the mounting holes 8 are mounted, the positioning of the water-cooled cylinder head 2 is facilitated, and thus the technical effects of good heat dissipation effect and reliable structure can be realized, the fit clearance of internal moving parts is prevented from being reduced, and the normal use is prevented.
The present invention and the embodiments thereof have been described above, but the description is not limited thereto, and the embodiment shown in the drawings is only one of the embodiments of the present invention, and the actual structure is not limited thereto. In summary, those skilled in the art should understand that they should not be limited to the embodiments described above, and that they can design the similar structure and embodiments without departing from the spirit of the invention.
Claims (6)
1. The utility model provides a two-stroke leak protection oil water cooling cylinder for aviation, includes water-cooling cylinder body (1) and water-cooling cylinder head (2), its characterized in that: the air cooling cylinder head (2) is arranged at the top of a water cooling cylinder body (1), the two sides of the top of the water cooling cylinder head (2) are respectively provided with a convex block (3), the convex block (3) is respectively provided with a water inlet (4) and a water outlet (5), the outer end of the water cooling cylinder head (2) is an arc surface (6), four recesses (7) are evenly arranged on the arc surface (6), mounting holes (8) are arranged in the recesses (7), high-strength bolts connected with the water cooling cylinder body (1) are arranged in the mounting holes (8), an upper annular water channel (9) is arranged inside the water cooling cylinder head (2), a lower annular water channel (10) communicated with the bottom is arranged inside the water cooling cylinder body (1), the upper annular water channel (9) is communicated with the lower annular water channel (10), the water inlet (4) and the water outlet (5) are both communicated with the upper annular water channel (9), four groups of corresponding spacing blocks (11) are uniformly arranged at the bottom of the upper annular water channel (9) and the top of the lower annular water channel (10), and the high-strength bolts penetrate through the mounting holes (8) and are fixedly connected with the spacing blocks (11).
2. The two-stroke oil-leakage-proof air cooling cylinder for aviation of claim 1, wherein: the water-cooling air cylinder is characterized in that an annular boss (13) is arranged in the middle of the interior of the water-cooling air cylinder body (1), and annular bosses (13) and annular concave platforms (14) matched with each other are arranged at the bottom of the interior of the water-cooling air cylinder head (2).
3. The two-stroke oil-leakage-proof air cooling cylinder for aviation of claim 1, wherein: the water inlet (4) and the water outlet (5) are arranged in a water-cooling cylinder head (2) in a central symmetry manner, and the water inlet (4) and the water outlet (5) are provided with a water inlet pipe and a water outlet pipe.
4. The two-stroke oil-leakage-proof air cooling cylinder for aviation of claim 1, wherein: and a spare spark plug hole (16) is arranged on the water-cooled cylinder head (2) and is used for double ignition of the two-stroke oil-leakage-proof aviation water-cooled cylinder.
5. The two-stroke oil-leakage-proof air cooling cylinder for aviation of claim 2, wherein: a sealing ring (17) is arranged on the outer ring of the water-cooling cylinder body (1), and a sealing gasket (18) is arranged between the annular boss (13) and the annular concave table (14).
6. The two-stroke oil-leakage-proof air cooling cylinder for aviation of claim 1, wherein: the water-cooling air cylinder body (1) and the water-cooling air cylinder head (2) are both formed by aluminum casting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922444537.8U CN211777732U (en) | 2019-12-30 | 2019-12-30 | Two-stroke oil-leakage-proof air cooling cylinder for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922444537.8U CN211777732U (en) | 2019-12-30 | 2019-12-30 | Two-stroke oil-leakage-proof air cooling cylinder for aviation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211777732U true CN211777732U (en) | 2020-10-27 |
Family
ID=72978833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922444537.8U Active CN211777732U (en) | 2019-12-30 | 2019-12-30 | Two-stroke oil-leakage-proof air cooling cylinder for aviation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211777732U (en) |
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2019
- 2019-12-30 CN CN201922444537.8U patent/CN211777732U/en active Active
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