CN210479017U

CN210479017U - Novel fuel chain drive multiaxis aircraft

Info

Publication number: CN210479017U
Application number: CN201920761086.8U
Authority: CN
Inventors: 李明珠
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-05-24
Filing date: 2019-05-24
Publication date: 2020-05-08
Anticipated expiration: 2029-05-24

Abstract

The embodiment of the utility model discloses novel fuel chain drive multiaxis aircraft relates to aircraft technical field, and its technical scheme includes frame, evenly distributed screw in the frame, drive screw pivoted engine and sets up the reduction gears between screw and engine, and screw and engine are all fixed at the frame upper surface, reduction gears is including setting up at the little chain dish at engine top, setting up at the big chain dish and the cooperation setting at the screw top little chain dish with chain between the big chain dish. The method is used for solving the problems of slow response, power waste and reduced sensitivity and stability of the aircraft caused by the direct connection mode of the engine and the propeller in the prior art.

Description

Novel fuel chain drive multiaxis aircraft

Technical Field

The embodiment of the utility model provides a relate to aircraft technical field, concretely relates to novel fuel chain drive multiaxis aircraft.

Background

Most of the existing fuel multi-shaft aircraft transmission modes adopt an engine direct-drive mode (an engine crankshaft and a propeller are directly connected together by bolts), the engine is mostly a two-stroke horizontally-opposed engine, and a plurality of two-stroke horizontally-opposed engines directly drive the propeller to rotate so as to push the aircraft to take off, land, adjust the attitude and the like. Because the engine and the propeller are directly connected without a speed reducing mechanism and cannot use the speed reducing propeller with larger push-pull force, the power reaction of the engine and the propeller is slow, and the sensitivity and the stability of the aircraft are not high. And because of the limitation of the rotating speed of the propeller (when the rotating speed of the propeller tip is close to the sound velocity, the noise of the propeller is obviously increased, the push-pull force is greatly reduced, the propeller shakes, the power of the engine is insufficient and the like), the engine always works in a middle-low rotating speed area, the whole power of the engine cannot be exerted, and a large amount of waste of the power of the engine is caused.

Meanwhile, the two-stroke horizontally-opposed engine adopted by the aircraft has the same structure as the traditional two-stroke engine, and the mixed oil obtained by mixing the engine oil and the gasoline according to a certain proportion is used as the fuel and the lubricant at the same time, so that the lubricating effect is poor, and the pollution of waste gas discharged by the engine is more serious than that of a four-stroke engine.

The traditional two-stroke engine (including two-stroke horizontally-opposed engine) is an internal combustion engine with simple structure and extremely light weight, and the opening and closing of an air inlet and an air outlet distributed on a cylinder are controlled only by the sealing performance and the relative motion position between a piston and the cylinder without a cam, a rocker arm, a mandril and other valve mechanisms of a four-stroke engine, and scavenging (scavenging and discharging exhaust gas) is carried out by means of positive pressure mixed gas in a crankcase. The traditional two-stroke horizontally-opposed engine needs to burn mixed oil like the traditional two-stroke engine, the mixed oil is vaporized by a carburetor and then is sucked into a crankcase, and lubricating oil is attached to moving parts such as a crankshaft, a connecting rod, a piston pin and the like in the crankcase in a vaporized form so as to play a certain lubricating role. Because the crankcase and the cylinder of the engine are communicated, the mixed gas enters the cylinder to sweep the waste gas and is combusted in the cylinder due to the air pressure difference generated by the up-and-down movement of the piston, and the lubricating oil components in the mixed gas are extremely difficult to combust, so the lubricating oil components are left in the cylinder after the combustion and are attached to the wall of the cylinder to play a role in lubricating the wall of the cylinder and the piston, and part of the lubricating oil is discharged along with the waste gas, thereby causing the two-stroke engine to have large pollution, blue smoke emission and serious waste of the engine oil. Because the traditional two-stroke engine adopts a mixed gas lubrication mode, lubricating oil is not stored in a crankcase of the two-stroke engine, so that the lubricating effect is poor, the engine is easy to overheat, metal chips generated by friction between a piston and a cylinder wall cannot be washed and discharged out of the cylinder by flowing lubricating oil like the lubricating oil splash lubrication adopted by the four-stroke engine, and the service life of the common two-stroke engine is extremely short and is only less than one eighth to one tenth of that of the four-stroke engine.

SUMMERY OF THE UTILITY MODEL

Therefore, the embodiment of the utility model provides a novel fuel chain drive multiaxis aircraft to solve among the prior art because the aircraft that engine and screw adopt the lug connection mode to lead to react delay, the power is extravagant, the sensitivity of aircraft and the problem of stability reduction.

In order to achieve the above object, the embodiment of the present invention provides the following technical solutions:

according to the embodiment of the utility model, a novel fuel chain drive multiaxis aircraft is provided, its technical scheme main points include frame, evenly distributed screw in the frame, drive screw pivoted engine and set up the reduction gears between screw and engine, and screw and engine are all fixed at the frame upper surface, reduction gears is in including setting up little chain dish at the engine top, setting up big chain dish and the cooperation setting at the screw top little chain dish with chain between the big chain dish.

Furthermore, the frame includes a pair of horizontal pole and a pair of vertical pole that is parallel to each other, and two horizontal poles are located between two vertical poles, and mutually perpendicular between horizontal pole and the vertical pole, the screw sets up the both ends at each vertical pole, and the engine just sets up in one side of screw with the screw one-to-one.

Further, a pressure piston lubricating system is arranged inside the crankshaft connecting rod mechanism of the engine.

Further, the pressure piston lubricating system comprises two rings of grooves formed in the connecting position of the outer side of the piston skirt portion and the radial center of the piston pin, a first lubricating oil hole channel formed in the connecting position of the middle position of the piston pin and the center of the connecting rod, and a second lubricating oil hole channel formed in the connecting position of the crankshaft and the connecting rod, wherein the grooves are communicated with the piston pin hole.

Furthermore, an eccentric wear resistant mechanism is arranged on a crankshaft connecting rod mechanism in the engine.

Further, the eccentric wear resistant mechanism comprises a first strong magnet arranged on the outer side wall of the piston skirt portion and a second strong magnet arranged on the outer side wall of the cylinder and corresponding to the first strong magnet.

Furthermore, an accommodating groove for fixing the first strong magnet is formed in the outer side wall of the piston, and the shape of the first strong magnet is matched with that of the accommodating groove.

Further, an air filter element device is arranged on the side wall of the shell of the engine.

The embodiment of the utility model provides a have following advantage:

the embodiment of the utility model transmits power between the large chain plate and the small chain plate in a chain form through the arranged speed reducing mechanism, because the circumference of one circle of rotation of the small chain plate is several times smaller than that of one circle of rotation of the large chain plate, the purpose of speed reduction is achieved, by the pressure piston lubricating system, the engine has a perfect and sufficient lubricating mode to lubricate each moving part in the crankcase without additional aid of mixed gas lubrication, therefore, the service life of the engine is greatly prolonged, and because additional mixed gas lubrication is not needed, lubricating oil components do not need to be added into the fuel according to the proportion, the fuel can use pure gasoline, therefore, the emission pollution level of the engine is greatly reduced, the power is further improved, and the pressure and the abrasion of the lower part of the engine cylinder and the lower part of the piston are greatly reduced through the arranged eccentric wear resistant mechanism, so that the service life of the engine is further prolonged.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.

The structure, ratio, size and the like shown in the present specification are only used for matching with the content disclosed in the specification, so as to be known and read by people familiar with the technology, and are not used for limiting the limit conditions which can be implemented by the present invention, so that the present invention has no technical essential significance, and any structure modification, ratio relationship change or size adjustment should still fall within the scope which can be covered by the technical content disclosed by the present invention without affecting the efficacy and the achievable purpose of the present invention.

Fig. 1 is a schematic overall structure diagram of a novel fuel chain drive multi-axis aircraft provided by an embodiment of the present invention;

fig. 2 is a schematic diagram of a novel oil chain drive multi-axis aircraft embodying a speed reduction mechanism provided by an embodiment of the present invention;

fig. 3 is a schematic view of a novel fuel chain drive multi-axis aircraft embodying a crankshaft link mechanism according to an embodiment of the present invention;

fig. 4 is a cross-sectional view of the novel multi-axis aircraft with fuel chain transmission embodying a pressure piston lubrication system provided by the embodiment of the present invention.

In the figure: 1. a frame; 11. a cross bar; 12. a longitudinal bar; 2. a propeller; 3. an engine; 31. An air filter cartridge; 4. a speed reduction mechanism; 41. a small chain plate; 42. a large chain plate; 43. a chain; 5. a groove; 6. a first lubricant oil gallery; 7. a second lubricant duct; 8. an anti-eccentric wear mechanism; 81. a first strong magnet; 82. a second strong magnet; 9. a containing groove.

Detailed Description

The present invention is described in terms of specific embodiments, and other advantages and benefits of the present invention will become apparent to those skilled in the art from the following disclosure. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In the present specification, the terms "upper", "lower", "left", "right", "middle", and the like are used for the sake of clarity only, and are not intended to limit the scope of the present invention, and changes or adjustments of the relative relationship thereof are also considered to be the scope of the present invention without substantial changes in the technical content.

A novel fuel chain drive multi-shaft aircraft is shown in figure 1 and comprises a frame 1, propellers 2 evenly distributed on the frame 1, an engine 3 driving the propellers 2 to rotate and a speed reducing mechanism 4 arranged between the propellers 2 and the engine 3, wherein the propellers 2 and the engine 3 are fixed on the upper surface of the frame 1. An air filter 31 is provided on the side wall of the casing of the engine 3 to reduce the dust content in the air sucked by the engine 3 and reduce the wear of the cylinders and pistons of the engine 3.

The frame 1 includes a pair of horizontal pole 11 and a pair of vertical pole 12 that are parallel to each other, and two horizontal poles 11 are located between two vertical poles 12, mutually perpendicular between horizontal pole 11 and the vertical pole 12, and screw 2 is provided with four, and four screws 2 set up respectively at the both ends of each vertical pole 12, and engine 3 and screw 2 one-to-one just set up in one side of screw 2.

As shown in fig. 2, the reduction mechanism 4 includes a small chain wheel 41 provided on the power output shaft of the engine 3, a large chain wheel 42 provided on the top of the propeller 2, and a chain 43 wound between the small chain wheel 41 and the large chain wheel 42.

The power is transmitted between the large chain disc 42 and the small chain disc 41 in the form of the chain 43, and the circumference of one circle of rotation of the small chain disc 41 is several times smaller than that of one circle of rotation of the large chain disc 42, so that the purpose of speed reduction is achieved, the speed reduction propeller 2 with larger push-pull force can be used, the power reaction capacity of the engine 3 and the propeller 2 is improved, and the overall sensitivity and stability of the aircraft are improved.

As shown in fig. 3 and 4, a pressure piston lubrication system is provided inside the crankshaft connecting rod mechanism of the engine 3 (see fig. 2). The pressure piston lubricating system comprises two rings of grooves 5 arranged at the joint of the outer side of a piston skirt part and the radial center of a piston pin, a first lubricating oil pore passage 6 arranged at the joint of the middle position of the piston pin and the center of a connecting rod, and a second lubricating oil pore passage 7 arranged at the joint of a crankshaft and the connecting rod, wherein the grooves 5 are communicated with piston pin holes.

The pressure lubricating oil is sucked out from the lubricating oil groove through the lubricating oil pump, passes through the crankshaft pore passage, the second lubricating oil pore passage 7 and the first lubricating oil pore passage 6 until the pressure lubricating oil is filled in the piston pin and flows into the groove 5, so that the pressure lubricating oil can lubricate the inner wall of the cylinder at the joint with the piston, and the inner wall of the cylinder adhered with the pressure lubricating oil indirectly lubricates the whole outer wall of the piston through the relative motion with the piston.

As shown in fig. 3 and 4, an anti-eccentric mechanism 8 is further provided on the crankshaft connecting rod mechanism in the engine 3 (see fig. 2). The anti-eccentric wear mechanism 8 comprises a first strong magnet 81 arranged on the outer side wall of the piston skirt part and a second strong magnet 82 arranged on the outer side wall of the cylinder and corresponding to the first strong magnet 81 in position. An accommodating groove 9 for fixing the first strong magnet 81 is formed in the outer side wall of the piston, and the shape of the first strong magnet 81 is matched with that of the accommodating groove 9.

The first strong magnet 81 can attract the second strong magnet 82 on the outer wall of the cylinder and the cylinder sleeve of the cylinder to offset the gravity of the piston, so that the pressure and the abrasion of the lower part of the cylinder and the lower part of the piston of the engine 3 (see fig. 2) are greatly reduced, the abrasion degree of the piston of the engine 3 and the abrasion degree of the cylinder are consistent, and the service life of the engine 3 is further prolonged.

Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Therefore, such modifications and improvements are intended to be within the scope of the invention as claimed.

Claims

1. The utility model provides a novel fuel chain drive multiaxis aircraft which characterized in that: including frame (1), evenly distributed screw (2) in frame (1), drive screw (2) pivoted engine (3) and set up reduction gears (4) between screw (2) and engine (3), screw (2) and engine (3) are all fixed in frame (1) upper surface, reduction gears (4) are including setting up little chain dish (41) at engine (3) top, setting up big chain dish (42) and the cooperation setting at screw (2) top are in little chain dish (41) with chain (43) between big chain dish (42).

2. The novel oil chain drive multi-axis aircraft as claimed in claim 1, wherein: frame (1) includes a pair of horizontal pole (11) and a pair of vertical pole (12) that are parallel to each other, and two horizontal poles (11) are located between two vertical pole (12), mutually perpendicular between horizontal pole (11) and the vertical pole (12), screw (2) set up the both ends at each vertical pole (12), and engine (3) and screw (2) one-to-one just set up the one side at screw (2).

3. The novel oil chain drive multi-axis aircraft as claimed in claim 1, wherein: and a pressure piston lubricating system is arranged in a crankshaft connecting rod mechanism of the engine (3).

4. The novel oil chain drive multi-axis aircraft of claim 3, wherein: the pressure piston lubricating system comprises two rings of grooves (5) formed in the connecting position of the outer side of a piston skirt portion and the radial center of a piston pin, a first lubricating oil hole channel (6) formed in the connecting position of the middle position of the piston pin and the center of a connecting rod, and a second lubricating oil hole channel (7) formed in the connecting position of a crankshaft and the connecting rod, wherein the grooves (5) are communicated with piston pin holes.

5. The novel oil chain drive multi-axis aircraft as claimed in claim 1, wherein: an anti-eccentric wear mechanism (8) is also arranged on the crankshaft connecting rod mechanism in the engine (3).

6. The novel oil chain drive multi-axis aircraft as claimed in claim 5, wherein: the eccentric wear resistant mechanism (8) comprises a first strong magnet (81) arranged on the outer side wall of the piston skirt portion and a second strong magnet (82) arranged on the outer side wall of the cylinder and corresponding to the first strong magnet (81).

7. The novel oil chain drive multi-axis aircraft of claim 6, wherein: an accommodating groove (9) for fixing the first strong magnet (81) is formed in the outer side wall of the piston, and the shape of the first strong magnet (81) is matched with that of the accommodating groove (9).

8. The novel oil chain drive multi-axis aircraft as claimed in claim 1, wherein: an air filter element device (31) is arranged on the side wall of the shell of the engine (3).