CN209905075U - Vertical front-end mechanism of engine of unmanned helicopter - Google Patents
Vertical front-end mechanism of engine of unmanned helicopter Download PDFInfo
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- CN209905075U CN209905075U CN201920634773.3U CN201920634773U CN209905075U CN 209905075 U CN209905075 U CN 209905075U CN 201920634773 U CN201920634773 U CN 201920634773U CN 209905075 U CN209905075 U CN 209905075U
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Abstract
The utility model relates to a vertical leading mechanism of engine of unmanned helicopter, affiliated unmanned helicopter technical field, including the frame skeleton, be equipped with the frame on the frame skeleton and be responsible for the post, be equipped with the engine body on the frame skeleton, be equipped with the engine mounting bracket between the post is responsible for to engine body and frame, the engine mounting bracket is fixed with engine body looks spiral shell column type displacement adjustment, the frame is responsible for the capital end and is equipped with rotor erection bracing frame, engine body upper end and rotor erection bracing frame upper end all are equipped with the belt pulley transmission subassembly, be equipped with the flange axle between two belt pulley transmission subassemblies, rotor erection bracing frame upper end is equipped with the rotor drive link with belt pulley transmission subassembly looks jump ring gear engagement. The power output device has the advantages of compact structure, firm connection, high structural strength, high power output efficiency and long service cycle. The gravity center of the unmanned helicopter is balanced by the front engine, and the stability of the unmanned helicopter in high-altitude work is improved.
Description
Technical Field
The utility model relates to an unmanned helicopter technical field, concretely relates to vertical leading mechanism of engine of unmanned helicopter.
Background
When the unmanned helicopter is actively put into development in some developed countries in the world, the aviation industry in China is also in the head-burying state and develops the unmanned helicopter. In 29 th 9 th 1993, the first coaxial dual-rotor unmanned helicopter in China, namely the gull number, successfully flies first, which marks that China breaks through a series of corresponding technical difficulties. It is reported that "gull" weighs 300 kilograms and the engine power is 58.8 kilowatts. The aircraft is provided with a flight control navigation system and a remote measuring system, and can fly autonomously or remotely. The helicopter can also be used for military affairs and plays a special role in battlefield reconnaissance, detection and the like.
Under the situation of military and civil deep fusion and innovation-driven development, the civil unmanned aerial vehicle is widely applied to agriculture and meteorological observation. An unmanned aircraft, referred to as a "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Therefore, for the unmanned helicopter, since the unmanned helicopter does not need to carry people and the engine does not need to balance with the gravity center of the human body, improvement on the unmanned helicopter is needed when the engine is installed.
Disclosure of Invention
The utility model discloses mainly solve and have among the prior art that high altitude construction poor stability, joint strength are weak, output power inefficiency and life are short not enough, provide the vertical leading mechanism of engine of unmanned helicopter, its compact structure, firm in connection, structural strength height, output power efficiency height and life cycle are long. The gravity center of the unmanned helicopter is balanced by the front engine, and the stability of the unmanned helicopter in high-altitude work is improved.
The above technical problem of the present invention can be solved by the following technical solutions:
the vertical front-end engine mechanism of the unmanned helicopter comprises a base framework, wherein a main frame pipe column fixedly connected with the base framework through an embedded bolt is arranged on the base framework, the frame framework of the machine base is provided with an engine body movably connected with the main pipe column of the machine frame through bolts, an engine mounting rack connected with the main pipe column of the frame through semicircular embedded bolts is arranged between the engine body and the main pipe column of the frame, the engine mounting frame is fixed with the engine body through screw displacement adjustment, the top end of the main pipe column of the frame is provided with a rotor wing mounting support frame, the upper end of the engine body and the upper end of the rotor wing mounting support frame are both provided with belt pulley transmission components, a guide flange shaft which is in rotary shaft type nested transmission connection with the belt pulley transmission components is arranged between the two belt pulley transmission components, rotor erection bracing frame upper end be equipped with belt pulley transmission assembly looks jump ring gear engagement's rotor drive link.
Preferably, the belt pulley transmission assembly comprises a driven gear, a driving gear is arranged on the side edge of the driven gear, and an internal tooth transmission belt ring which is in annular tooth-shaped meshed sleeve joint is arranged on the outer walls of the driving gear and the driven gear.
The belt pulley transmission assembly on rotor erection bracing frame upper end adopts the driving gear to cup joint with the output flange axle on upper portion, and driven gear cup joints with rotor drive link. The belt pulley transmission assembly at the upper end of the engine body is sleeved with the engine body through a driving gear, and the driven gear is sleeved with an output flange shaft at the lower part. The output flange shaft is driven by the output power of the engine body to drive the rotor wing to drive the connecting frame to rotate.
Preferably, the driven gear include the internal tooth dish, the internal tooth dish periphery be equipped with the external tooth dish of the movable profile of tooth meshing of internal tooth transmission belt ring mutually, external tooth dish and internal tooth dish between be equipped with a plurality of fixed link rods that are the equidistant distribution of annular.
Preferably, an oil tank body mounting frame fixedly connected with a rack main pipe phase bolt is arranged between the rotor wing mounting support frame and the engine body, the oil tank body mounting frame is in bearing type limiting sleeve connection with the guide flange shaft, and an oil tank body communicated with the engine body phase oil pipe is arranged on the oil tank body mounting frame. The oil tank body provides fuel for the engine body.
Preferably, the oil tank body and the oil tank body mounting frame are connected and fixed in a nesting manner through anchor ear type bolts.
Preferably, the engine body and the oil tank body mounting frame are provided with a tail gas discharge tank communicated with the engine body through a pipeline, a tail gas discharge tank support fixedly connected with the oil tank body mounting frame through a bolt is arranged between the tail gas discharge tank and the oil tank body mounting frame, and the tail gas discharge tank support is fixedly connected with the tail gas discharge tank through a flange plate type bolt. The tail gas discharged by the engine body is firstly cooled in the tail gas discharge tank and then discharged, and the effective precipitation and collection of large solid particles are realized through the tail gas discharge tank. The filtering effect on the exhaust emission is improved, and the concentration of the exhaust gas is reduced.
Preferably, an output flange shaft which is in clamping spring type limiting nesting with the belt pulley transmission assembly is arranged between the guide flange shaft and the upper and lower belt pulley transmission assemblies, and a transition flange shaft is arranged between the output flange shaft and the guide flange shaft.
The rotary shaft between the engine body and the rotor wing driving connecting frame is connected through a sectional structure of an output flange shaft, a guide flange shaft and a transition flange shaft. The fatigue resistance is improved while the same strength is kept, and the deformation of the rotating shaft due to the overlong shearing stress is prevented. And is convenient to disassemble, repair and maintain. The coaxiality of the rotating shaft structure is improved, and the stability of kinetic energy transfer is improved.
Preferably, the upper end of the engine body is provided with a belt pulley guard plate seat which is connected with an output flange shaft bearing type flange in a nested manner, and a belt pulley transmission assembly arranged in the belt pulley guard plate seat is fixedly connected with a flat key clamp spring type shaft sleeve of the engine body. The belt pulley guard plate seat not only protects the operation of the belt pulley transmission assembly, but also improves the rotation stability of the output flange shaft and plays a role in reducing eccentric rotation.
Preferably, the engine body is provided with a plurality of driving motors which are connected and fixed with the engine body in a flange manner, and the side edge of the engine body is provided with an air filtering flange which is arranged in a coaxial structure with the driving motors. A piston cylinder in the engine body is started by a driving motor to perform fuel oil type piston motion so as to provide power for the rotor wing driving connecting frame. The air filter flange provides fresh air for the sufficient burning of fuel and filters the air, improves the life of engine body.
The utility model discloses can reach following effect:
the utility model provides a vertical leading mechanism of engine of unmanned helicopter compares with prior art, has compact structure, firm in connection, structural strength height, output power efficiency height and life cycle length. The gravity center of the unmanned helicopter is balanced by the front engine, and the stability of the unmanned helicopter in high-altitude work is improved.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural view of the pulley transmission assembly of the present invention.
In the figure: rotor erection bracing frame 1, rotor drive link 2, the frame is responsible for post 3, belt pulley transmission subassembly 4, the oil tank jar body 5, output flange axle 6, transition flange axle 7, guide flange axle 8, the oil tank jar body mounting bracket 9, exhaust emission jar support 10, belt pulley backplate seat 11, exhaust emission jar 12, driving motor 13, engine body 14, air filter flange 15, frame skeleton 16, engine mounting bracket 17, driven gear 18, internal tooth drive belt ring 19, driving gear 20, external tooth dish 21, fixed connection rod 22, internal tooth dish 23.
Detailed Description
The technical solution of the present invention is further specifically described below by way of examples and with reference to the accompanying drawings.
Example (b): as shown in fig. 1 and 2, a vertical front-end engine mechanism of an unmanned helicopter includes a base frame 16, a main frame pipe 3 fixed to the base frame 16 by means of an embedded bolt is disposed on the base frame 16, an engine body 14 fixed to the main frame pipe 3 by means of a movable bolt is disposed on the base frame 16, 2 driving motors 13 are disposed on the engine body 14 and are distributed vertically and equidistantly and fixed to the engine body 14 by means of a flange, and an air filtering flange 15 disposed on a side of the engine body 14 and coaxially with the driving motors 13 is disposed on the engine body 14. Be equipped with between engine body 14 and frame are responsible for 3 of post with the frame and be responsible for the engine mounting bracket 17 of 3 looks semicircle inlay formula bolted connection of post, engine mounting bracket 17 is adjusted fixedly with 14 looks double-screw bolt formulas displacement of engine body, the frame is responsible for 3 tops of post and is equipped with rotor erection bracing frame 1, be equipped with between rotor erection bracing frame 1 and engine body 14 and be responsible for 3 looks bolted connection fixed oil tank body mounting bracket 9 of post with the frame, oil tank body mounting bracket 9 cup joints with 8 looks bearing types of flange axle are spacing, be equipped with the oil tank body 5 with 14 looks oil pipe intercommunications of engine body on the oil tank body mounting bracket 9. The oil tank body 5 and the oil tank body mounting frame 9 are connected and fixed in a hooping type bolt nesting mode. Be equipped with the exhaust emission jar 12 with engine body 14 looks pipeline intercommunication between engine body 14 and the oil tank jar body mounting bracket 9, be equipped with between exhaust emission jar 12 and the oil tank jar body mounting bracket 9 looks bolted connection fixed exhaust emission jar support 10 with the oil tank jar body mounting bracket 9, exhaust emission jar support 10 is fixed with exhaust emission jar 12 looks flange plate formula bolted connection. 14 upper ends of engine body and rotor installation support frame 1 upper end all are equipped with belt pulley transmission assembly 4, and belt pulley transmission assembly 4 includes driven gear 18, and driven gear 18 includes internal tooth dish 23, and internal tooth dish 23 periphery is equipped with the external tooth dish 21 with the 19 movable profile of tooth meshing of internal tooth transmission belt ring mutually, is equipped with 5 fixed connecting rods 22 that are the equidistant distribution of annular between external tooth dish 21 and internal tooth dish 23. The side of the driven gear 18 is provided with a driving gear 20, and the outer walls of the driving gear 20 and the driven gear 18 are provided with an inner tooth transmission belt ring 19 which is in annular tooth-shaped meshed sleeve joint. A guide flange shaft 8 which is in rotary shaft type nested transmission connection with the belt pulley transmission component 4 is arranged between the two belt pulley transmission components 4, an output flange shaft 6 which is in clamp spring type spacing nested connection with the belt pulley transmission component 4 is arranged between the guide flange shaft 8 and the upper and lower belt pulley transmission components 4, and a transition flange shaft 7 is arranged between the output flange shaft 6 and the guide flange shaft 8. The upper end of the engine body 14 is provided with a belt pulley guard plate seat 11 which is connected with the output flange shaft 6 in a bearing type flange nesting way, and a belt pulley transmission assembly 4 arranged in the belt pulley guard plate seat 11 is fixedly connected with the engine body 14 in a flat key clamp spring type shaft sleeve way. The upper end of the rotor wing installation support frame 1 is provided with a rotor wing driving connecting frame 2 which is engaged with a belt pulley transmission assembly 4-phase clamp spring type gear.
To sum up, the vertical front-end mechanism of the engine of the unmanned helicopter has the advantages of compact structure, firm connection, high structural strength, high output power efficiency and long service cycle. The gravity center of the unmanned helicopter is balanced by the front engine, and the stability of the unmanned helicopter in high-altitude work is improved.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without deviating from the basic characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
In conclusion, the above description is only the specific embodiment of the present invention, but the structural features of the present invention are not limited thereto, and any person skilled in the art can make changes or modifications within the scope of the present invention.
Claims (9)
1. The utility model provides a vertical leading mechanism of engine of unmanned helicopter which characterized in that: comprises a machine base framework (16), a machine frame main pipe column (3) fixedly connected with the machine base framework (16) in an embedded and inserted mode through bolts is arranged on the machine base framework (16), an engine body (14) fixedly connected with the machine frame main pipe column (3) through movable bolts is arranged on the machine base framework (16), an engine mounting frame (17) connected with the machine frame main pipe column (3) through semicircular embedded bolts is arranged between the engine body (14) and the machine frame main pipe column (3), the engine mounting frame (17) is fixedly adjusted with the engine body (14) through stud type displacement, a rotor installation support frame (1) is arranged at the top end of the machine frame main pipe column (3), belt pulley transmission components (4) are arranged at the upper end of the engine body (14) and the upper end of the rotor installation support frame (1), a guide flange shaft (8) connected with the belt pulley transmission components (4) through rotary shaft type embedded transmission is arranged between the two belt pulley transmission components (4), rotor erection bracing frame (1) upper end be equipped with belt pulley transmission assembly (4) looks jump ring gear engagement's rotor drive link (2).
2. The vertical front-end engine mechanism of an unmanned helicopter of claim 1, characterized in that: the belt pulley transmission assembly (4) comprises a driven gear (18), a driving gear (20) is arranged on the side edge of the driven gear (18), and an internal tooth transmission belt ring (19) which is in annular tooth-shaped meshed sleeve joint is arranged on the outer walls of the driving gear (20) and the driven gear (18).
3. The vertical front-end engine mechanism of an unmanned helicopter of claim 2, characterized in that: driven gear (18) include internal tooth dish (23), internal tooth dish (23) periphery be equipped with internal tooth drive belt ring (19) movable profile of tooth meshing's external tooth dish (21) mutually, external tooth dish (21) and internal tooth dish (23) between be equipped with a plurality of fixed link rods (22) that are the equidistant distribution of annular.
4. The vertical front-end engine mechanism of an unmanned helicopter of claim 1, characterized in that: rotor erection bracing frame (1) and engine body (14) between be equipped with frame main pipe column (3) looks bolted connection fixed oil tank body mounting bracket (9), oil tank body mounting bracket (9) and guide flange axle (8) looks bearing type spacing cup joint, oil tank body mounting bracket (9) on be equipped with the oil tank body (5) with engine body (14) looks oil pipe intercommunication.
5. The vertical front-end engine mechanism of an unmanned helicopter of claim 4, characterized in that: the oil tank body (5) and the oil tank body mounting rack (9) are connected and fixed in a hooping type bolt nesting mode.
6. The vertical front-end engine mechanism of an unmanned helicopter of claim 4, characterized in that: engine body (14) and oil tank body mounting bracket (9) between be equipped with engine body (14) exhaust emissions jar (12) of looks pipeline intercommunication, exhaust emissions jar (12) and oil tank body mounting bracket (9) between be equipped with oil tank body mounting bracket (9) looks bolted connection fixed exhaust emissions jar support (10), exhaust emissions jar support (10) fixed with exhaust emissions jar (12) looks flange plate type bolted connection.
7. The vertical front-end engine mechanism of an unmanned helicopter of claim 1, characterized in that: an output flange shaft (6) which is in clamping spring type limiting nesting with the belt pulley transmission component (4) is arranged between the guide flange shaft (8) and the upper and lower belt pulley transmission components (4), and a transition flange shaft (7) is arranged between the output flange shaft (6) and the guide flange shaft (8).
8. The vertical front-end engine mechanism of an unmanned helicopter of claim 7, characterized in that: the belt pulley guard plate device is characterized in that a belt pulley guard plate seat (11) which is connected with an output flange shaft (6) in a bearing type flange nesting mode is arranged at the upper end of the engine body (14), and a belt pulley transmission assembly (4) arranged in the belt pulley guard plate seat (11) is fixedly connected with the engine body (14) in a flat key clamp spring type shaft sleeve mode.
9. The vertical front-end engine mechanism of an unmanned helicopter of claim 1, characterized in that: the engine body (14) on be equipped with a plurality of driving motor (13) of being connected fixedly with engine body (14) looks flange formula, engine body (14) side be equipped with driving motor (13) be coaxial structure setting air filter flange (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920634773.3U CN209905075U (en) | 2019-05-06 | 2019-05-06 | Vertical front-end mechanism of engine of unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920634773.3U CN209905075U (en) | 2019-05-06 | 2019-05-06 | Vertical front-end mechanism of engine of unmanned helicopter |
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| Publication Number | Publication Date |
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| CN209905075U true CN209905075U (en) | 2020-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920634773.3U Active CN209905075U (en) | 2019-05-06 | 2019-05-06 | Vertical front-end mechanism of engine of unmanned helicopter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112145285A (en) * | 2020-08-14 | 2020-12-29 | 武汉司南翼航航空工程技术有限责任公司 | Low-oil-consumption long-endurance aircraft engine |
| CN114110107A (en) * | 2021-11-19 | 2022-03-01 | 中国直升机设计研究所 | Transmission system of unmanned helicopter with front engine |
-
2019
- 2019-05-06 CN CN201920634773.3U patent/CN209905075U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112145285A (en) * | 2020-08-14 | 2020-12-29 | 武汉司南翼航航空工程技术有限责任公司 | Low-oil-consumption long-endurance aircraft engine |
| CN114110107A (en) * | 2021-11-19 | 2022-03-01 | 中国直升机设计研究所 | Transmission system of unmanned helicopter with front engine |
| CN114110107B (en) * | 2021-11-19 | 2023-11-07 | 中国直升机设计研究所 | Transmission system of unmanned helicopter with front-mounted engine |
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