CN108661793A - A kind of horizontally-opposed aero-engine of four cylinder of small two-stroke - Google Patents
A kind of horizontally-opposed aero-engine of four cylinder of small two-stroke Download PDFInfo
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- CN108661793A CN108661793A CN201810778193.1A CN201810778193A CN108661793A CN 108661793 A CN108661793 A CN 108661793A CN 201810778193 A CN201810778193 A CN 201810778193A CN 108661793 A CN108661793 A CN 108661793A
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B75/00—Other engines
- F02B75/16—Engines characterised by number of cylinders, e.g. single-cylinder engines
- F02B75/18—Multi-cylinder engines
- F02B75/24—Multi-cylinder engines with cylinders arranged oppositely relative to main shaft and of "flat" type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B75/00—Other engines
- F02B75/34—Ultra-small engines, e.g. for driving models
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F3/00—Pistons
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F7/00—Casings, e.g. crankcases or frames
- F02F7/0002—Cylinder arrangements
- F02F7/0009—Crankcases of opposed piston engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B75/00—Other engines
- F02B75/16—Engines characterised by number of cylinders, e.g. single-cylinder engines
- F02B75/18—Multi-cylinder engines
- F02B2075/1804—Number of cylinders
- F02B2075/1816—Number of cylinders four
Abstract
The present invention relates to a kind of horizontally-opposed aero-engine of four cylinder of small two-stroke, compact-sized simple, high mechanical strength, ambient adaptability is wide, light-weight, efficient, and reliability is high, and good manufacturability is adaptable.This invention simplifies the manufacture of air door control system and debugging difficulty, the effective solution lubrication state of two stroke engine crank mechanism also improves the cooling problem when operation of crank rod movement pair.Bent axle of the present invention, connecting rod, piston, cylinder, crankcase structure adapt to aviation Intensive Flying demand, can reach continuous cruise in 10 hours under 3500 meters of above 5000 revs/min of operating modes of height above sea level and run.
Description
Technical field
The present invention relates to aero-engine technology fields, more particularly to a kind of horizontally-opposed boat of four cylinder of small two-stroke
Empty engine.
Background technology
Two-stroke piston engine can get machinery more higher than traditional straight engine due to its unique design feature
The advantages that efficiency and efficiency of combustion and high energy density and power to weight ratio, it is widely used in small and medium size unmanned aerial vehicles power.Traditional
Two-stroke multi-cylinder small aero is using twin-tub and four cylinders as typical structure, although technology maturation, larger, combustion that there are volumes
The problems such as oily economy is poor, multiple air inlet and oil supply mechanism synchronous controls are complicated.
The Chinese patent of notification number CN104343566B discloses " a kind of electric spray type aviation gasoline engine ", for one kind two
Stroke four cylinder engine, including crankcase, two-by-two horizontally-opposed four cylinder bodies be mounted in crankcase both sides, each cylinder body into
Gas port upward and connects an EFI mechanism, and EFI mechanism includes air inlet pipe, solar term door pivot, driving connecting lever, fuel injector, oil inlet
Pipe, the affixed air throttle of solar term door pivot and driving connecting lever, fuel injector are mounted in the side of air inlet pipe, and the lower part of fuel injector is equipped with spray
Mouth, middle part connect oil inlet pipe equipped with electromagnetic switch valve, top, and the top of air inlet pipe connects air cleaner.
The Chinese utility model patent of notification number CN203403950U discloses a kind of " four cylinder aeroplane engine of small two-stroke
Machine ", four cylinder bodies are horizontally-opposed in the both sides of crankcase, and four carburetors are on four cylinder body air inlets, power control machine
Structure is made of bottom plate, axis pin, rocking arm, torsional spring, pull rod, control stick, adjusting screw, and on the solar term door pivot of four carburetors
Four connecting lever connections, control air throttle action.
The Chinese utility model patent of notification number CN206158856U discloses " a kind of four cylinder unmanned vehicle engines ", starts
Machine is made of gas combustion apparatus, transmission device, driving device and exhaust apparatus, it is therefore intended that starts function when a cylinder failure
It works on.
Above three engine patent is horizontally-opposed four cylinder two-strokes gasoline aero-engine, and difference is that the former adopts
With electronic fuel injection fuel system, the latter two use supplying oil of carburetor mode, this passive fuel feeding of carburetor and EFI active
The difference of fuel system, only so that engine is different on fuel economy, and its engine mechanical structure is then complete
It is identical.But the provided engine of preceding two patents is since its carburetor mechanism or EFI mechanism structure position are identical, i.e.,
It is placed in cylinder air inlet mouth, there are problems that apparent crankcase lubrication, especially bent axle cannot well be moistened with crank mechanism
Sliding, there are lubrications and cooling deficiency, and bearing of the crank pin to be caused to overheat risk, and then influences engine power output and even fail, and
Four air inlet oil supply mechanism control airdoor controls are complicated, and synchronous adjustment is time-consuming and laborious.Section 3 patent is then that single cylinder is changed to four
Unmanned plane all standing caused by cylinder failure when cylinder is flight in order to prevent works in practical flight inevitable caused by middle cylinder failure
The result is that the cylinder body fail result of engine cut-off and flight stopping forced landing, multicylinder engine and single-cylinder engine is the same,
Increase cylinder body quantity, probability of malfunction can only be increased.The air inlets attachment mode such as aero-engine carburetor mechanism or EFI mechanism changes
Change or how much variations of cylinder body quantity are not the effective ways for improving engine performance and reliability.
Four the cylinder piston formula aero-engine performance of small two-stroke is promoted, reliability is improved, needs in engine body core
Scheming part carries out structural improvement.It improves engine crankshaft, connecting rod and crankcase structure, improve piston element structure, mitigate
Weight improves kinematic pair lubricating condition.Meanwhile reducing engine volume, simplify air inlet and oil supply mechanism, improves power to weight ratio and combustion
Oily efficiency etc. obtains high power per liter, needs to solve by improving the design structure of engine body core engine parts.
Invention content
Present invention solves the technical problem that being：In view of the limitation in the prior art, the present invention provides a kind of small-sized
The horizontally-opposed piston aviation engine of four cylinder of two-stroke, its object is to by engine body core engine component structural
The small and medium size unmanned aerial vehicles that are improved to of design provide a kind of new engine, have compact-sized, light-weight, efficient, control letter
Clean, reliability is high, good manufacturability, adaptable small-sized piston formula aero-engine.
The technical scheme is that：A kind of horizontally-opposed aero-engine of four cylinder of small two-stroke, including magneto 7,
Exhaust pipe 9, check valve 4, bent axle, crankcase 14, is split up formula connecting rod, piston and four cylinder blocks 18 at shaft coupling 11；Its feature exists
In the crankcase 14 is located at using being integrally formed at engine center axis；The bent axle be it is forward and backward it is two segments combined before,
In, rear three-support structure bent axle, including leading portion crank throw unit 1-1, two baffle ring 1-2, to female connector 1-3, support ring 1-4, two
Bearing 1-5, back segment crank throw unit 1-6, by the way that the docking of front and rear sections crank throw unit is fixedly connected to female connector 1-3 inner ring, bent axle
Front and back ends are respectively equipped with axis of cone diameter, and two axis of cone end faces are equipped with internal thread hole；The formula connecting rod that is split up is the quenched conjunction of high intensity
Golden Steel material, structure include connecting rod cap 2-1, big end 2-3, connecting rod shank 2-4 and small end of connecting rod 2-5, connecting rod shank 2-
The section that rises of 4, connecting rod cap 2-1 and big end 2-3 are connected by bolt 2-7, and big end hole wall is continuous busbar；Even
Bar major part 2-3 is set along connecting rod shank 2-4 axisymmetricals there are two boss, and through-hole is respectively symmetrically provided on boss as being split up hole 2-
2, and be split up hole 2-2 axis and be mutually parallel with big end 2-3 axis, it is split up in the 2-2 of hole to be provided with two and be parallel to and is split up hole
Axis and the fault trough 2-6 that rises for being symmetrical with the axis；The piston-top surface, skirt section are curved-surface structure, in piston cavity, if being provided with
Dry reinforcing rib, to improve intensity and be conducive to heat dissipation.
The present invention further technical solution be：The piston-top surface is convexity three-dimension curved surface, and internal piston pin hole is convex
Platform is equipped with several reinforcing ribs integrally and is in dispersed and dispersion direction is towards top land, in top inner wall also towards top-direction
It is provided with a cross reinforcing, piston skirt is non-circular curved surface and sprays high temperature resistant self-lubricating mixture.
The present invention further technical solution be：The bent axle include leading portion crank throw unit 1-1, back segment crank throw unit 1-6,
To female connector 1-3 and bearing assembly；Described two crank throw cellular constructions are similar and are mutually butted, by female connector 1-3 inner ring by two
A crank throw unit docking is fixed, and by the way that the main shaft supporting in being used as to the bearing assembly on female connector 1-3 outer shrouds is arranged；Described two
A crank throw unit includes three cranks and two connecting rod journal diameters；Crank is rectangle and both ends are in arc-shaped, and crank is arranged in parallel,
It is connected by the connecting rod journal diameter being mutually parallel, connecting rod journal diameter axis is mutually perpendicular to crank；Two crank throw units far from docking at
Outermost crank lateral wall on, along main-shaft axis outward respectively successively be equipped with front and back ends main shaft diameter and front and back ends axis of cone diameter；
Axis of cone diameter end face is equipped with internal thread hole, is used for the fastening of joint outer part.
The present invention further technical solution be：The bearing assembly includes support ring 1-4, bearing 1-5, to female connector 1-3
With baffle ring 1-2；The inside and outside circle of bearing 1-5 in parallel is fixedly connected with to female connector 1-3 and support ring 1-4 for interference, and passes through baffle ring
1-2 is limited.
The present invention further technical solution be：The left and right sides of the unsplit crankcase 14 misplaces horizontally-opposed two-by-two
Four cylinder blocks 18 are equipped with the split type bent axle through crankcase inside unsplit crankcase 14, pacify on four crank throws of bent axle
The formula connecting rod that is split up of dress is connected with the piston inside cylinder block 18, and 14 top of crankcase is equipped with unidirectionally along axis by flange
Valve 4, check valve 4 connect two sets of admission gears of installation above, and admission gear upper end is air cleaner 1, and will by throttle linkage 2
Two sets of admission gear's air doors hingedly synchronize control, and 14 front end of crankcase is connected with forward flange 6 and magneto 7, crankcase 14
Rear end is connected with rear cabinet 10 and shaft coupling 11, and four 18 downsides of cylinder block respectively connect an exhaust pipe 9 by air vent seat 8.
Invention effect
The technical effects of the invention are that：By adopting the above-described technical solution, the small-sized piston formula aviation hair of the present invention
Motivation is compact-sized simple, and high mechanical strength, ambient adaptability is wide, light-weight, efficient, and reliability is high, good manufacturability, adapts to
Property is strong.This invention simplifies the manufacture of air door control system and debugging difficulty, effective solution two stroke engine bent axle machine
The lubrication state of structure also improves the cooling problem when operation of crank rod movement pair.Bent axle of the present invention, connecting rod, piston, vapour
Cylinder, crankcase structure adapt to aviation Intensive Flying demand, can reach under 3500 meters of height above sea level or more 5000 revs/min of operating modes
The continuous operation of cruise in 10 hours.
Description of the drawings
Fig. 1 is the structural schematic diagram of inventive engine；
Fig. 2 is the vertical view of the structural schematic diagram of inventive engine；
Fig. 3 is the right view of the structural schematic diagram of inventive engine；
Fig. 4 is the structural schematic diagram of inventive engine vuilt-up crankshaft；
Fig. 5 is that inventive engine rises the structural schematic diagram of disconnected formula connecting rod；
Fig. 6 is the structural schematic diagram of inventive engine unsplit crankcase；
Fig. 7 is the structural schematic diagram of inventive engine cylinder block；
Fig. 8 is the structural schematic diagram of inventive engine piston.
Attached drawing mark, 1-air cleaner, 2-throttle linkages, 3-fuel feed pumps, 4-check valves, 5-magneto rotors,
6-forward flanges, 7-magnetos, 8-bolts, 9-exhaust pipes, 10-rear cabinets, 11-shaft couplings, 12-throttle rockers, 13-
Carburetor, 14-crankcases, 15-spark plugs, 16-firing cables, 17-ignition coils, 18-cylinder blocks；1-1-leading portion is bent
Unit, 1-2-baffle ring, 1-3-are turned to female connector, 1-4-support ring, 1-5-bearing, 1-6-back segment crank throw unit；2-1-company
Bowl cover, 2-2-are split up hole, 2-3-big end, 2-4-connecting rod shank, 2-5-small end of connecting rod, 2-6-are split up line, 2-7-
Connecting-rod bolts；3-1-crankcase, 3-2-stud.
Specific implementation mode
Referring to Fig. 1-Fig. 8, the present invention provides a kind of horizontally-opposed piston aviation engine of four cylinder of small two-stroke, the hair
Motivation uses the opposed frame mode of typical level, that is, is located at the crankcase in central symmetry axes and its bent axle of inside, along song
Four cylinder bodies that axis misplaces opposed two-by-two, two carburetor mechanisms or EFI mechanism being located in crankcase central symmetry axes；
Bent axle is two-period form dock separate structure and uses three support patterns, installs a cracking type on four cranks of bent axle respectively and connects
Bar, big end bearing of the crank pin use retainer opposite opened needle bearing structure, small end of connecting rod to connect by monoblock type needle bearing
Connect a piston, piston structure is top surface convexity three-dimension curved surface, at the top of the vertical emitting shape reinforcing rib in inner cavity three and one willfully
Strengthening tendons structure；And using the dual-active plug ring for carving face structure；Crankcase is using whole penetration type structure；Cylinder block is multiple using Metal Substrate
Close ceramic plating working face；Crankshaft front end is propeller mounting flange, can be mounted directly high performance airscrew, can also connect and subtract
Fast device is to install slow spin paddle；Crankshaft rear end is that generator installs the outer axis of cone.Bent axle box back is for engine and aircraft
The rear cabinet of connection.
The present invention further technical solution be：The bent axle be it is a kind of it is forward and backward it is two segments combined before, during and after three bearings
Structure bent axle, including leading portion crank throw unit, back segment crank throw unit, to female connector and bearing assembly；Described two crank throw cellular constructions
It is similar and be mutually butted, by the way that two crank throw units docking are fixed to female connector inner ring, and by being arranged on to female connector outer shroud
Bearing assembly be used as in main shaft supporting, middle main shaft supporting bearing is using two ball bearings in parallel；Two crank throw units are equal
Including three cranks and two connecting rod journal diameters；Crank is rectangle and both ends are in arc-shaped, and crank is arranged in parallel, by being mutually parallel
Connecting rod journal diameter be connected, connecting rod journal diameter axis is mutually perpendicular to crank；Two crank throw units are far from the outermost crank at docking
On lateral wall, front end main shaft diameter, the front-end-cone diameter of axle and rear end main shaft diameter, the rear end axis of cone are equipped with successively respectively outward along main-shaft axis
Diameter；The front-end-cone diameter of axle connect and transmits torque for external engine with rear end axis of cone diameter, and two axis of cone end faces are equipped with interior spiral shell
Pit is used for the fastening of joint outer part.This structure so that crankshaft structure is compact simple, and bearing is abundant, whole rigid of bent axle
Degree and intensity are ensured, are conducive to promote product reliability；Meanwhile the length of bent axle has effectively been shortened, and make bent axle
Weight controlled, be convenient for tissue engine structure, improve the power to weight ratio of engine, and the crankshaft structure is succinctly advantageous
In reaching higher machining accuracy.
The present invention further technical solution be：The connecting rod is a kind of quenched steel alloy cracking type connecting rod of high intensity,
Including gonnecting rod body and connecting rod cap and be bolted, specially connecting rod cap, big end, connecting rod shank, small end of connecting rod,
Cracking hole, bolt composition.The right end of the gonnecting rod body is small end of connecting rod, and middle part is connecting rod shank, and left end is big end, even
Small head bore and big end hole are additionally provided on the body of rod；The gonnecting rod body is with connecting rod cap by connecting bolt in the face absolutely of rising of big end
Place's connection, special big end hole wall are continuous busbar, and symmetrically cracking hole, cracking hole are offered at the disconnected place of rising of big end
On symmetrically arranged two boss in big end both sides, the boss and cracking hole are symmetrical with link centerline；It is described
The cross section of connecting rod shank is I-shape cross section.The material of the gonnecting rod body and connecting rod cap is using high-strength alloy quenched and tempered steel and right
Part uses carburizing or Nitrizing Treatment.This technical solution, the fault trough that rises are not arranged on big end hole wall, but big in connecting rod
Cracking hole is set on head boss, the fault trough that rises is set in cracking hole, does not also apply one kind new knot of mechanical force when rising disconnected from big end hole
Structure solves the broken face structure problem absolutely that rises of quenched alloyed steel linkage rod so that connecting rod cracking technical process simplifies, and is convenient for process
Control, reduces the section forced area that rises, and makes disconnected power reduction of rising so that defect size reduction of having no progeny of rising, big end when rising disconnected
Hole does not stress, and reduces big end deformation, improves the quality on joint surface, make connecting rod bearing capacity, anti-shear ability and dress
With Quality advance；The structure makes outer surface defect after connecting rod cracking reduce, and it is disconnected to realize rising for the quenched alloyed steel linkage rod of high intensity,
Convenient for tissue engine structure, the use scope of small-sized aviation piston engine has been widened；The link mechanism is compact, intensity is high,
Good, the light-weight and good manufacturability of rigidity, improves product reliability.
The present invention further technical solution be：The crankcase is integrated with crankshaft-link rod using whole penetration type structure
It is support holes in the forward and backward mounting hole of mechanism, bent axle, cylinder mounting hole, air inlet, lubrication channel, cooling system, fuel system, preceding
The engine crankshaft box of multiple systems such as rear end attachment connector.The bent axle punch-out equipment is bilateral symmetry, arranged on left and right sides
Spacing of four cylinder mounting holes on engine front-rear direction is the adjacent crank link path position difference of bent axle；Gas handling system position
It is two rectangular configuration air flues and corresponding with bent axle front and rear sections crank throw position above the crankcase in symmetrical center line, with profit
It is lubricated along crankcase lubrication and design of Cooling System structure in mixed oil and gas, cools down crank connecting link bearing and small end of connecting rod
Bearing, cylinder and piston ring kinematic pair, to improve engine reliability of operation and stability；If being also set up above crankcase
The mounting arrangements of involvement connection interface stud or threaded hole for oil, electric system attachment；Front and back ends are arranged in crankcase front and rear end
The connecting stud of output attachments is surrounded on the surrounding of front and back ends face；Watch window is set below crankcase.Preferably, this song
Axle box is cast using magnesium alloy materials, has good thermal stability and weight/power ratio, lateral wall perpendicular angularly disposed equipped with several
Reinforcing rib, be conducive to further loss of weight and improve babinet intensity.The crankcase is compact-sized, stablizes, and dimensional accuracy is by ring
Border temperature influence is small, is suitable for wider range of flying height range and weather, improves adaptability；Processing and assembly process process
It is good so that engine can obtain higher mechanical precision, and it is long-term under the operating mode higher than 5000 revs/min to be conducive to engine
Operating.
The present invention further technical solution be：The piston is a kind of intensity height, light-weight cast structure, piston top
Face structure is convexity three-dimension curved surface, and in the inner cavity of piston, it is in emitting shape angle that piston-pin boss is equipped with three towards top-direction
The reinforcing rib of degree stretches to top land along wall, meanwhile, one cross reinforcing of setting on the wall at the top of piston cavity, four
Reinforcing rib is connected and is connected with piston pin hole convex edge.Further, piston is cast using hypereutectic aluminium alloy, and top land is adopted
It is handled with hard anodized, piston skirt is using non-circular amendment linear structure and sprays the mixing of molybdenum disulfide high temperature resistant self-lubricating
Object forms porous structure and is stored conducive to lubricating oil.This piston structure so that engine is continuously transported at 5000 revs/min when flight
When row, top land partial pressure directly can directly be passed to piston-pin boss by the reinforcing rib on piston cavity top wall
It passs, improves piston force-bearing situation, meanwhile, reinforcing rib equally increases the heat dissipation area of piston, improves the heat dissipation way of piston
Diameter.
The horizontally-opposed aero-engine of four cylinder of the present embodiment small two-stroke is that a kind of novel unmanned plane is sent out with small-sized piston
Motivation is illustrated by taking carburetor type as an example in the present embodiment, as shown in Fig. 1-8, composition include two air cleaners 1,
The fuel feed pump 3, two of throttle linkage 2, two check valve 4, magneto rotor 5, forward flange 6,7, four air vent seats 8 of magneto,
14, four four exhaust pipes 9, rear cabinet 10,11, two, shaft coupling throttle rocker 12, two carburetor 13, crankcase spark plugs
15, four cylinder blocks 18 of ignition coil 17, four of firing cable 16, four.And leading portion crank throw unit 1-1, two baffle ring 1-
2, to female connector 1-3, support ring 1-4, two bearing 1-5, back segment crank throw unit 1-6；Connecting rod cap 2-1, to be split up hole 2-2, connecting rod big
Head 2-3, connecting rod shank 2-4, small end of connecting rod 2-5, line 2-6, two connecting-rod bolts 2-7 are split up；30 stud 3-2.
As shown in Fig. 1-8, four the cylinder piston formula aero-engine of two-stroke of the present invention uses the opposed structure side of typical level
Formula is located at the crankcase 14 arranged on the engine center axis of symmetry and its is set to its internal combined type song claimed on axis
Axis (Fig. 4) misplaces horizontally-opposed four cylinder blocks 18 two-by-two along two side of bent axle, is located in 14 central symmetry axes of crankcase
Two 13 mechanism accessory units of carburetor；Bent axle is two-period form dock Split assembled structure, is pacified respectively on four cranks of bent axle
A cracking type connecting rod (Fig. 5) is filled, big end bearing of the crank pin uses retainer opposite opened needle bearing structure, small end of connecting rod logical
It crosses monoblock type needle bearing and connects a piston (Fig. 8), piston-top surface structure is convexity three-dimension curved surface structure, and skirt section is non-circular
Curved-surface structure, and using the dual-active plug ring for carving face structure；Crankcase 14 is used using whole penetration type structure, cylinder block (Fig. 7)
Composite ceramics plating working face；Crankshaft front end is propeller mounting flange 6, can be mounted directly high performance airscrew, can also connect
Retarder is connect to install slow spin paddle；Crankshaft rear end is that generator installs the outer axis of cone and gapless is soft connects formula shaft coupling 11.It is bent
Axle box rear end is the rear cabinet 10 being connect with aircraft for engine.
As shown in figure 4, bent axle described in the embodiment of the present invention be it is a kind of it is forward and backward it is two segments combined before, during and after three bearing knots
Structure bent axle, including it is leading portion crank throw unit 1-1, two baffle ring 1-2, bent to female connector 1-3, support ring 1-4, two bearing 1-5, back segment
Turn unit 1-6.Described two crank throw unit leading portion crank throw unit 1-1, back segment crank throw unit 1-6 structures are similar and are mutually butted,
By the way that two crank throw unit leading portion crank throw unit 1-1 are docked fixation with back segment crank throw unit 1-6 to female connector 1-3 inner ring, and lead to
It crosses and the main shaft supporting in being used as to the bearing assembly bearing 1-5 on female connector 1-3 outer shrouds is set, middle main shaft supporting bearing 1-5 is used
Two ball bearings in parallel；Two crank throws unit leading portion crank throw unit 1-1 and back segment crank throw unit 1-6 includes three cranks
With two connecting rod journal diameters；Crank is rectangle and both ends are in arc-shaped, and crank is arranged in parallel, solid by the connecting rod journal diameter being mutually parallel
Even, connecting rod journal diameter axis is mutually perpendicular to crank；Two crank throw unit leading portion crank throw unit 1-1 are remote with back segment crank throw unit 1-6
From on the outermost crank lateral wall at docking, front end main shaft diameter, the front-end-cone diameter of axle are equipped with successively respectively outward along main-shaft axis
With rear end main shaft diameter, rear end axis of cone diameter；The front-end-cone diameter of axle and rear end axis of cone diameter connect and transmit torque for external engine, and two
A axis of cone end face is equipped with internal thread hole, is used for the fastening of joint outer part.This structure so that crankshaft structure is compact simple, branch
It holds fully, the rigidity and intensity of bent axle entirety are ensured, are conducive to promote product reliability；Meanwhile song is effectively shortened
The length of axis, and the weight of bent axle is made to be controlled, it is convenient for tissue engine structure, improves the power to weight ratio of engine.And
And the crankshaft structure is succinct, is conducive to reach higher machining accuracy and economy；When product is realized, to leading portion crank throw unit
1-1 is grouped assembly with back segment crank throw unit 1-6 by the place's of docking diameter of axle, can obtain the antitorque effect of higher bent axle and reliable
Property.
As shown in figure 5, connecting rod described in the embodiment of the present invention is a kind of quenched steel alloy cracking type connecting rod of high intensity, packet
It includes gonnecting rod body and connecting rod cap and is bolted, specially connecting rod cap 2-1, be split up hole 2-2, big end 2-3, connecting rod
Shaft 2-4, small end of connecting rod 2-5, line 2-6, two connecting-rod bolts 2-7 compositions are split up.The right end of the connecting rod is small end of connecting rod 2-
5, thereon and it is equipped with small head bore, middle part is connecting rod shank 2-4, and left end is big end 2-3, thereon and is equipped with big end hole；It is described
Gonnecting rod body is connect by connecting-rod bolts 2-7 in the disconnected section part that rises of big end 2-3 with connecting rod cap 2-1, special big end
2-3 hole walls are continuous busbar, are symmetrically offered at the disconnected place of rising of big end 2-3 and are split up hole 2-2, are split up hole 2-2 and be located at connecting rod
On symmetrically arranged two boss in the both sides major part 2-3, the boss and to be split up hole 2-2 symmetrical with link centerline；The company
The cross section of club body 2-4 is the excessive I-shape cross section of circular arc.The material of the gonnecting rod body and connecting rod cap 2-1 use high intensity
Quenching and tempering steel simultaneously uses carburizing, quenching treatment, the present embodiment that can also use nitriding process part.This skill of the present invention
Art scheme, the fault trough that rises are not arranged on big end hole wall, but setting is split up hole 2- on the boss of big end both sides
2, it is split up on the 2-2 hole walls of hole and two fault troughs that rise respectively is set, also apply a kind of new construction of mechanical force when rising disconnected not from big end hole,
Solves the broken face structure problem absolutely that rises of quenched alloyed steel linkage rod so that connecting rod cracking technical process simplifies, and is convenient for program-controlled
System, reduces the section forced area that rises, and the disconnected power that makes to rise reduces, defect size reduction of having no progeny of rising, when rising disconnected crank pin end pore not by
Power reduces big end bore deformation, improves the quality on joint surface, makes connecting rod bearing capacity, anti-shear ability and assembly matter
Amount improves；Outer surface defect is reduced after the structure makes connecting rod cracking, and it is disconnected to realize rising for the quenched alloyed steel linkage rod of high intensity；Together
When, also achieve that crank pin end pore busbar is continuous, and big end hole wall can be directly as crank connecting link needle bearing outer ring so that
Link mechanism is succinct, is convenient for tissue engine structure, has widened the use scope of small-sized aviation piston engine；The link mechanism
It is compact, intensity is high, rigidity is good, light-weight and good manufacturability, effectively improve product reliability.
As shown in fig. 6, in the embodiment of the present invention, the crankcase 14 uses monoblock type penetration type structure, is integrated with bent axle
Support holes, cylinder mounting hole, air inlet, lubrication channel, cooling system, Fuel System in the forward and backward mounting hole of link mechanism, bent axle
The engine crankshaft box of multiple systems such as system, front and back end attachment connector.The crankcase 14 is bilateral symmetry, left,
Spacing of 18 mounting hole of cylinder of right both sides four on engine front-rear direction is the adjacent crank link path position difference of bent axle；Into
Gas system is located in 14 top symmetrical center line of crankcase, be two rectangular configuration air flues and with bent axle front and rear sections crank throw position
It is corresponding, so that mixed oil and gas is lubricated along crankcase lubrication and design of Cooling System structure, cools down crank connecting link bearing
And small end bearing, cylinder 18 and piston ring kinematic pair are lubricated, are cooled down, to improve engine reliability of operation and
Stability；The top of crankcase 14 also set up several connecting interface stud 3-2 for oil, electric system attachment mounting arrangements；Bent axle
The connecting stud 3-2 of front and back ends output attachments is arranged in 18 front and rear end of case, is surrounded on the surrounding of front and back ends face；Crankcase
Watch window is arranged in 14 lower sections.Preferably, this crankcase 14 is cast using magnesium alloy materials, has good thermal stability and ratio
Weight, lateral wall are equipped with several perpendicular angularly disposed reinforcing ribs, are conducive to further loss of weight and improve babinet intensity.The bent axle
Body structure is compact, stablizes, and dimensional accuracy is influenced by ambient temperature small, is suitable for wider range of flying height range and weather,
Improve adaptability；Processing is good with assembly process process so that engine can obtain higher mechanical precision, be conducive to engine
It is operated for a long time under the operating mode higher than 5000 revs/min.
As shown in figure 8, in the embodiment of the present invention, the plug piston is a kind of intensity height, light-weight cast structure, piston
Top surface structure is convexity three-dimension curved surface, and in the inner cavity of piston, it is in emitting shape that piston-pin boss is equipped with three towards top-direction
The reinforcing rib of angle stretches to top land along wall, meanwhile, one cross reinforcing of setting on the wall at the top of piston cavity, four
Reinforcing rib is connected and is connected with piston pin hole convex edge.Further, piston is cast using hypereutectic aluminium alloy, top land
It is handled using hard anodized, piston skirt uses non-circular amendment linear structure and sprays molybdenum disulfide high temperature resistant self-lubricating and mixes
Object is closed, and forms porous structure and is stored conducive to lubricating oil, prevents from embracing cylinder or scuffing of cylinder bore, meanwhile, when this piston structure makes flight
When engine is continuously run at 5000 revs/min, top land partial pressure can pass through the reinforcing rib on piston cavity top wall
It is directly directly transmitted to piston-pin boss, improves piston force-bearing situation, meanwhile, reinforcing rib equally increases the heat dissipation of piston
Area improves the sinking path of piston.
As shown in Fig. 1-3, in the present embodiment, illustrated by taking carburetor as an example, further embodiment of this invention is electricity
H type engine h is sprayed, two 4 top carburetor of check valve, 13 mechanism units are changed to EFI mechanism unit attachment, and air door
Control mode still uses throttle linkage 2 and throttle rocker 12 to carry out control completion.
In the present embodiment, as shown in Fig. 1-3,4 or more attachment of admission gear i.e. two check valve, using bent with engine
The perpendicular mounting means of shaft centre line, in practical application, arrange demand to reduce engine front face area or aircraft system, it can
By on the basis of 4 symmetrical center line of check valve, admission gear is carried out within the scope of 65 ° tilting；Equally, four exhaust pipes 9
Air inlet mouth of pipe can be carried out within the scope of 90 ° tilting so that horizontal on the basis of 8 symmetrical center line of air vent seat.
Claims (5)
1. a kind of horizontally-opposed aero-engine of four cylinder of small two-stroke, including magneto (7), exhaust pipe (9), shaft coupling
(11), check valve (4), bent axle, crankcase (14), be split up formula connecting rod, piston and four cylinder blocks (18)；It is characterized in that, institute
Crankcase (14) is stated using being integrally formed, is located at engine center axis；The bent axle be it is forward and backward it is two segments combined before, in,
Three-support structure bent axle afterwards, including leading portion crank throw unit (1-1), two baffle rings (1-2), to female connector (1-3), support ring (1-4),
Two bearings (1-5), back segment crank throw unit (1-6) are fixed by docking front and rear sections crank throw unit to female connector (1-3) inner ring
Connection, bent axle front and back ends are respectively equipped with axis of cone diameter, and two axis of cone end faces are equipped with internal thread hole；The formula connecting rod that is split up is height
The quenched alloy steel material of intensity, structure include that connecting rod cap (2-1), big end (2-3), connecting rod shank (2-4) and connecting rod are small
Head (2-5), connecting rod shank (2-4), connecting rod cap (2-1) and the section that rises of big end (2-3) are connected by bolt (2-7), and
And big end hole wall is continuous busbar；Big end (2-3) is set along connecting rod shank (2-4) axisymmetrical there are two boss, convex
It is respectively symmetrically provided with through-hole on platform as being split up hole (2-2), and is split up hole (2-2) axis and big end (2-3) axis is mutual
It is parallel, it is split up and is provided with two in hole (2-2) and is parallel to the fault trough that rises (2-6) for being split up axially bored line and being symmetrical with the axis；It is described
Piston-top surface, skirt section are curved-surface structure, in piston cavity, are provided with several reinforcing ribs, to improve intensity and conducive to heat dissipation.
2. a kind of horizontally-opposed aero-engine of four cylinder of small two-stroke as described in claim 1, which is characterized in that the work
Plug top surface is convexity three-dimension curved surface, and for internal piston pin hole boss towards top-direction, it is in dispersion to be equipped with several reinforcing ribs integrally
Shape and dispersion direction is towards top land, is additionally provided with a cross reinforcing, piston skirt is non-circular curved surface in top inner wall
And spray high temperature resistant self-lubricating mixture.
3. a kind of horizontally-opposed aero-engine of four cylinder of small two-stroke as described in claim 1, which is characterized in that the song
Axis includes leading portion crank throw unit (1-1), back segment crank throw unit (1-6), to female connector (1-3) and bearing assembly；Described two crank throws
Cellular construction is similar and is mutually butted, and by fixing two crank throw unit docking to female connector (1-3) inner ring, and is existed by setting
Main shaft supporting in being used as to the bearing assembly on female connector (1-3) outer shroud；Two crank throw units include three cranks and two
A connecting rod journal diameter；Crank is rectangle and both ends are in arc-shaped, and crank is arranged in parallel, is connected by the connecting rod journal diameter being mutually parallel,
Connecting rod journal diameter axis is mutually perpendicular to crank；Two crank throw units are far from the outermost crank lateral wall at docking, along main shaft
Axis is equipped with front and back ends main shaft diameter and front and back ends axis of cone diameter successively respectively outward；Axis of cone diameter end face is equipped with internal thread hole, uses
In the fastening of joint outer part.
4. a kind of small-sized aviation piston engine novel combination type crank mechanism as claimed in claim 3, which is characterized in that institute
It includes support ring (1-4), bearing (1-5), to female connector (1-3) and baffle ring (1-2) to state bearing assembly；In bearing (1-5) in parallel,
Outer ring is fixedly connected with to female connector (1-3) and support ring (1-4) for interference, and is limited by baffle ring (1-2).
5. a kind of horizontally-opposed aero-engine of four cylinder of small two-stroke as described in claim 1, which is characterized in that described whole
The left and right sides of body formula crankcase (14) misplaces horizontally-opposed four cylinder blocks (18) two-by-two, peace inside unsplit crankcase (14)
Equipped with the split type bent axle through crankcase, that is installed on four crank throws of bent axle is split up the work internal with cylinder block (18) of formula connecting rod
Plug is connected, and crankcase (14) top is equipped with check valve (4) along axis by flange, and check valve (4) connects installation two above
Admission gear is covered, and admission gear upper end is air cleaner (1), and two sets of admission gear's air doors is hinged by throttle linkage (2)
Control is synchronized, crankcase (14) front end is connected with forward flange (6) and magneto (7), after crankcase (14) rear end is connected with
Cabinet (10) and shaft coupling (11), four cylinder blocks (18) downsides pass through air vent seat (8) respectively one exhaust pipe (9) of connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810778193.1A CN108661793A (en) | 2018-07-16 | 2018-07-16 | A kind of horizontally-opposed aero-engine of four cylinder of small two-stroke |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810778193.1A CN108661793A (en) | 2018-07-16 | 2018-07-16 | A kind of horizontally-opposed aero-engine of four cylinder of small two-stroke |
Publications (1)
| Publication Number | Publication Date |
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| CN108661793A true CN108661793A (en) | 2018-10-16 |
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ID=63788911
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| Application Number | Title | Priority Date | Filing Date |
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|---|---|---|---|---|
| CA2018504A1 (en) * | 1989-07-31 | 1991-01-31 | Robert Mrdjenovich | Hollow connecting rod |
| CA2473433A1 (en) * | 2003-07-30 | 2005-01-30 | Honda Motor Co., Ltd. | Engine |
| CN201461933U (en) * | 2009-06-10 | 2010-05-12 | 北京中清能发动机技术有限公司 | Piston, and internal combustion engine and a compressor using same |
| CN203403950U (en) * | 2013-08-07 | 2014-01-22 | 厦门林巴贺航空发动机股份有限公司 | Small two-stroke four-cylinder aero-engine |
| CN104421322A (en) * | 2013-09-10 | 2015-03-18 | 沈阳航天誉兴机械制造有限公司 | Expansion fracture connecting rod assembly of engine piston |
| CN107387537A (en) * | 2017-09-15 | 2017-11-24 | 西北工业大学 | A kind of small-sized aviation piston engine novel combination type crank mechanism |
| CN208595007U (en) * | 2018-07-16 | 2019-03-12 | 西安爱生技术集团公司 | A kind of horizontally-opposed aero-engine of four cylinder of small two-stroke |
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2018
- 2018-07-16 CN CN201810778193.1A patent/CN108661793A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2018504A1 (en) * | 1989-07-31 | 1991-01-31 | Robert Mrdjenovich | Hollow connecting rod |
| CA2473433A1 (en) * | 2003-07-30 | 2005-01-30 | Honda Motor Co., Ltd. | Engine |
| CN201461933U (en) * | 2009-06-10 | 2010-05-12 | 北京中清能发动机技术有限公司 | Piston, and internal combustion engine and a compressor using same |
| CN203403950U (en) * | 2013-08-07 | 2014-01-22 | 厦门林巴贺航空发动机股份有限公司 | Small two-stroke four-cylinder aero-engine |
| CN104421322A (en) * | 2013-09-10 | 2015-03-18 | 沈阳航天誉兴机械制造有限公司 | Expansion fracture connecting rod assembly of engine piston |
| CN107387537A (en) * | 2017-09-15 | 2017-11-24 | 西北工业大学 | A kind of small-sized aviation piston engine novel combination type crank mechanism |
| CN208595007U (en) * | 2018-07-16 | 2019-03-12 | 西安爱生技术集团公司 | A kind of horizontally-opposed aero-engine of four cylinder of small two-stroke |
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