CN204433064U - The adjustable unmanned plane of degree of balance - Google Patents
The adjustable unmanned plane of degree of balance Download PDFInfo
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- CN204433064U CN204433064U CN201420872032.6U CN201420872032U CN204433064U CN 204433064 U CN204433064 U CN 204433064U CN 201420872032 U CN201420872032 U CN 201420872032U CN 204433064 U CN204433064 U CN 204433064U
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Abstract
The utility model discloses the adjustable unmanned plane of a kind of degree of balance, comprise fuselage, mast and oar clamp pin axle, unmanned plane also comprises: driving engine, is fixed on the inside of fuselage; Driving engine comprises: at least one cylinder, and a side is provided with exhausr port; Cylinder body, is connected with described air cylinder detachable type; Air intake valve, is connected with described cylinder body is detachable; Kinetic balance parts, comprising: balance block, are provided with a mounting groove; Balance element, is fixed on the end of described balance block; Attaching parts, one end is fixedly connected with described balance block, and the other end and described oar clamp pin axle are rotationally connected, and described oar clamp pin axle is rotated relative to described attaching parts.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, particularly the adjustable unmanned plane of a kind of degree of balance.
Background technology
Robot airplane is called for short " unmanned plane ", is the not manned aircraft utilizing radio robot to handle with the process controller provided for oneself.Without driving compartment on machine, but the equipment such as autopilot, process controller, information collecting device are installed.On ground, naval vessels or machine tool command and control station personnel by equipment such as radars, it is followed the tracks of, locates, remote control, remote measurement and digital communication.Can take off as conventional airplane under radio telecommand or launch with booster rocket, also can be taken to by machine tool and throw in flight in the air.
Unmanned plane at least comprises fuselage, driving engine, mast and oar clamp pin axle.Wherein, mast and oar clamp pin axle are arranged on the tail end position of unmanned aerial vehicle body, and driving engine is arranged on the inside of unmanned aerial vehicle body, think that the rotor wing rotation of unmanned plane provides power.
But, the driving engine of unmanned plane is applied in prior art, the freeing pipe of its air intake valve and cylinder is arranged on and is positioned on the same side of driving engine, and the surface temperature of freeing pipe is generally at 600 degrees centigrade, by heat transfer effect, engine charge valve ambient air temperature is raised, and then the gas temperature causing driving engine to suck is also relatively high.Reduce because gas temperature raises rear density, and once the sucked gas volume of engine combustion is fixed value, the available oxygen atomic quantity causing unit volume to enter engine interior burning reduces, and then causes gaseous combustion insufficient, finally impacts the flight operation of unmanned plane.
Utility model content
The utility model provides a kind of degree of balance adjustable unmanned plane, and this unmanned plane solves or partly solve the technological deficiency impacted unmanned plane during flying operation that traditional driving engine causes because gaseous combustion is insufficient.
For solving the problems of the technologies described above, the utility model provides the adjustable unmanned plane of a kind of degree of balance, and comprise fuselage, mast and oar clamp pin axle, described unmanned plane also comprises:
Driving engine, is fixed on the inside of described fuselage;
Described driving engine comprises:
At least one cylinder, a side is provided with exhausr port;
Cylinder body, is connected with described air cylinder detachable type, and between described cylinder with described cylinder body, air-flow communicates;
Air intake valve, be connected with described cylinder body is detachable, and be positioned at a side of described cylinder body, air-flow is flowed into from described air intake valve, and entered in described cylinder by described cylinder body and burn, tail gas after burning is discharged from described exhausr port, and the angle that described air-flow is formed from the direction that described air intake valve flows into and described tail gas from the direction that described exhausr port is discharged is 0 °-90 °;
Airfilter, is fixed on the bottom of described fuselage, and is connected with described air intake valve is detachable;
Rotor attaching parts, is flexibly connected described mast with described oar clamp pin axle, and described oar clamp pin axle can be swung relative to described mast;
Kinetic balance parts, are set in described mast, and are flexibly connected with described oar clamp pin axle, and described oar clamp pin axle can be rotated relative to described kinetic balance parts.
Optionally,
One end face of described cylinder is provided with admission port;
One end face of described cylinder body is provided with communication port, and the described cylinder body end face that is provided with described communication port and described cylinder are provided with, and the end face of described admission port is detachable to be connected, described admission port and described communication port suitable, after making described air-flow enter described cylinder body, flowed in described cylinder by described communication port, described admission port successively.
Optionally,
Described exhausr port set on one side of described cylinder, with admission port set on an end face of described cylinder, be two opposition mouths of described cylinder, make described air-flow by described admission port, through the whole inner space of described cylinder, and discharge from described exhausr port again after Thorough combustion.
Optionally, described airfilter comprises:
Ventilation slot, is fixed on the bottom of described fuselage, with draw air;
Filter screen, is fixed in described ventilation slot, to purify described air;
Fairing, one end is connected with described air intake valve is detachable, and the other end is fixedly connected with described ventilation slot, makes described air flow into described air intake valve by described filter screen, described fairing successively.
Optionally, described airfilter also comprises:
Seal ring, is arranged between described fairing and described air intake valve, to seal connecting portion therebetween.
Optionally, described rotor attaching parts comprises:
Bolt;
Nut;
First flange bearing;
Second flange bearing;
Wherein, described in described screw bolt passes, the first flange bearing, described oar clamp pin axle, described mast, described second flange bearing are connected with described nut thread.
Optionally,
The end of described mast is provided with damping trough;
Described rotor attaching parts also comprises:
Damping washer, is set on described damping trough, and a side of described damping washer and described mast fit, and another side and described oar clamp pin axle fit;
Wherein, the internal diameter of described oar clamp pin axle is greater than the external diameter of described mast, to make to form a gap between described oar clamp pin axle and described mast, and the thickness of the width in described gap and described damping washer is suitable, when described oar clamp pin axle being rotated in described perpendicular by described gap, described oar clamp pin axle, on the direction perpendicular to described perpendicular, can swing relative to described mast.
Optionally, described kinetic balance parts comprise:
Balance block, is provided with a mounting groove, and described mast is rotationally connected through described mounting groove and described balance block, and described mast is rotated relative to described balance block;
Balance element, is fixed on the end of described balance block, to balance the center of gravity of described oar clamp pin axle;
Pipe link, one end is fixedly connected with described balance block, and the other end and described oar clamp pin axle are rotationally connected, and described oar clamp pin axle is rotated relative to described pipe link.
Optionally,
One end of described pipe link is provided with U-type groove, and is threaded by the top of described U-type groove with described balance block, and the other end of described pipe link is provided with pin-and-hole, and by described pin-and-hole and described oar clamp pin axle pinned connection.
Optionally,
The angle that described air-flow is formed from the direction that described air intake valve flows into and described tail gas from the direction that described exhausr port is discharged is 90 °.
The adjustable unmanned plane of a kind of degree of balance provided by the utility model, be arranged on the driving engine of this unmanned plane inside, the direction of being discharged by the direction that flowed into by air-flow and tail gas is arranged on the not ipsilateral of driving engine, make the air intake valve ambient air temperature of driving engine can not raise along with the rising of exhaust ports temperature like this, actv. avoids in prior art and is positioned on the same side of driving engine because the freeing pipe of air intake valve and cylinder is arranged on, and the engine interior gaseous combustion caused is insufficient, the final technological deficiency that unmanned plane during flying operation is impacted.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
The structural representation one of the adjustable unmanned plane of degree of balance that Figure 1A provides for the utility model embodiment;
The structural representation two of the adjustable unmanned plane of degree of balance that Figure 1B provides for the utility model embodiment;
The structural representation one of the driving engine that Fig. 2 A provides for the utility model embodiment;
The structural representation two of the driving engine that Fig. 2 B provides for the utility model embodiment;
The structural representation three of the driving engine that Fig. 2 C provides for the utility model embodiment;
The structural representation of the airfilter that Fig. 3 A provides for the utility model embodiment;
Fig. 3 B is the structural representation of airfilter of the prior art;
The structural representation of the rotor attaching parts that Fig. 4 provides for the utility model embodiment;
The structural representation of the kinetic balance parts that Fig. 5 provides for the utility model embodiment.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the utility model embodiment, be clearly and completely described the technical scheme in the utility model embodiment, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, the every other embodiment that those of ordinary skill in the art obtain, all belongs to the scope of the utility model protection; Wherein involved in this enforcement "and/or" keyword, represent and or two kinds of situations, in other words, A and/or B mentioned by the utility model embodiment, illustrate A and B, A or B two kinds of situations, describe three kinds of states existing for A and B, as A and/or B, represent: only include A and do not comprise B; Only include B and do not comprise A; Comprise A and B.
Refer to Figure 1A-1B, the adjustable unmanned plane of a kind of degree of balance that the utility model embodiment provides, on the one hand, this unmanned plane comprises basic component part: fuselage, mast and oar clamp pin axle, wherein, mast and oar clamp pin axle are arranged on the afterbody position of unmanned aerial vehicle body; On the other hand, this unmanned plane also at least include that four the utility model embodiments provide the structure element of novel original creation: driving engine, airfilter, rotor attaching parts and kinetic balance parts, wherein, driving engine is fixed on the inside of fuselage, airfilter is fixed on the bottom of fuselage and is connected with driving engine is detachable, rotor attaching parts is for connecting mast and the oar clamp pin axle of unmanned plane, and kinetic balance parts are fixed in mast to balance the center of gravity of unmanned plane tail rotor.
By above-mentioned driving engine, airfilter, rotor attaching parts and kinetic balance parts, the unmanned plane that the utility model embodiment is provided at least has possessed following characteristics: engine combustion efficiency greatly improves, impurity in air to be combusted obtains that actv. is removed, the vibrations of unmanned plane afterbody obtain that actv. controls, the center of gravity of unmanned plane tail rotor obtains accurate regulation and control.
Below, described in detail one by one respectively by driving engine, airfilter, rotor attaching parts and kinetic balance parts in the unmanned plane that provides the utility model embodiment, to support technical problem to be solved in the utility model:
For engine section
Refer to Fig. 2 A-2C, driving engine 100 at least comprises: cylinder 101, cylinder body 103 and air intake valve 104.
Wherein, a side of cylinder 101 is provided with at least one exhausr port 102 (can as shown in Figure 2 C), for discharging the tail gas in cylinder 101 after burning.Cylinder body 103 is connected with air cylinder detachable type, and between cylinder 101 with cylinder body 103, air-flow communicates.Air intake valve 104 is connected with cylinder body 103 is detachable, and is positioned at a side of cylinder body 103.
The above connection mode, on the one hand, detachable between cylinder 101, cylinder body 103 and air intake valve 104, three is substituted, easy to maintenance; On the other hand, between cylinder 101 with cylinder body 103, air-flow communicates, make air-flow from air intake valve 104 flow into after, by cylinder body 103 enter in cylinder 101 burn, and burning after tail gas discharge from described exhausr port 102.
It should be noted that, in driving engine 100, air-flow is 0 °-90 ° from the tail gas behind the direction that air intake valve 104 flows into and burning from the angle that the direction that exhausr port 102 is discharged is formed.In other words, air-flow inflow direction and tail gas discharge direction are not positioned at the same side of driving engine 100.
Because, being arranged on just because of the air intake valve of driving engine and the freeing pipe of cylinder in prior art is positioned on the same side of driving engine, and the surface temperature of freeing pipe is generally at 600 degrees centigrade, by heat transfer effect, engine charge valve ambient air temperature is raised, and then the gas temperature causing driving engine to suck is also relatively high.Reduce because gas temperature raises rear density, and once the sucked gas volume of engine combustion is fixed value, the available oxygen atomic quantity causing unit volume to enter engine interior burning reduces, and then causes gaseous combustion insufficient, finally affects the work efficiency of driving engine.
But the driving engine 100 that the utility model provides, the direction that the direction flowed into by air-flow just and tail gas are discharged is arranged on the same side not being positioned at driving engine 100.Preferred, air-flow can be set to 90 ° from the direction that air intake valve 104 flows into and tail gas from the angle that the direction that exhausr port 102 is discharged is formed, make the air intake valve 104 ambient air temperature of driving engine 100 can not raise along with the rising of exhausr port 102 place temperature like this, actv. avoids in prior art the impact that engine operating efficiency causes.
Specifically, an end face of cylinder 101 is provided with at least one admission port 105.One end face of cylinder body 103 is provided with at least one communication port 106.And the quantity of admission port 105 is identical with the quantity of communication port 106, a corresponding communication port 106 of admission port 105, for the formation of an air flow passage.In actual job process, according to the propulsive effort needed for unmanned plane rotor, the logarithm of admission port 105, communication port 106 can be rationally set, with the demand of satisfied difference " air flow passage " quantity.
Meanwhile, the end face that cylinder body 103 is provided with communication port 106 and cylinder 101 are provided with that the end face of admission port is detachable to be connected, and after making air-flow enter cylinder body 103, flowed in cylinder 101 successively burn by communication port 106, admission port 105.
As preferably, detachable in driving engine 100 between cylinder 101 with cylinder body 103 is connected, and detachable between cylinder body 103 with air intake valve 104 is connected, and can be all that bolt connects, or other modes that removably connect, to dismantle therebetween, substitute conveniently.
It should be noted that, refer to Fig. 2 C, exhausr port 102 set on a side of cylinder 101, with admission port 105 set on an end face of cylinder 101, is two opposition mouths of cylinder 101.In other words, admission port 105 and exhausr port 102 are positioned at the both sides in cylinder 101 internal-combustion space, after making air-flow be entered by admission port 105, through the then space, whole inside of cylinder 101, and discharge from exhausr port 102 again after Thorough combustion, to improve burning of gas efficiency.
As preferably, the quantity of cylinder 101 can be two, and two cylinders 101 are symmetricly set on two opposition end faces of cylinder body 103, and two opposite end faces correspondences from cylinder body 103 after making air-flow enter cylinder body 103 flow into each cylinders 101.Certainly, also can according to the propulsive effort needed for unmanned plane rotor in unmanned plane practical flight, the quantity of choose reasonable cylinder 101 is arranged.
For airfilter part
Refer to Fig. 3 A, airfilter 200 at least can comprise: ventilation slot 203, filter screen 201 and fairing 202.
Wherein, ventilation slot 203 is arranged on unmanned plane, and is positioned at the bottom of unmanned plane, burns so that the air drawing the external world enters in driving engine 100.Filter screen 201 is fixed on the inside of ventilation slot 203, so that when outside air is entered by ventilation slot 203, purify this air, the air plankton containing elements such as S, N in removing air, improves the combustion efficiency of air in driving engine 100.One end of fairing 202 is fixedly connected with air intake valve 104, the other end is fixedly connected with ventilation slot 203, after making outside air enter ventilation slot 203, air intake valve 104 is flowed into successively through filter screen 201, fairing 202, and final being entered in driving engine 100 by air intake valve 104 is burnt, and be that mechanical energy drives the rotor of unmanned plane to rotate by the thermal energy after burning.
Specifically, refer to Fig. 3 B, although airfilter is connected with air intake valve in the driving engine of unmanned plane in prior art, but, in prior art, airfilter is coniform, when air-flow enters unmanned plane from the side (circular conical surface) of airfilter, at least there is following defect:
Defect one, conical side surface 211 limited area of airfilter, makes the airflow volume that flows into from the conical side surface 211 of airfilter limited;
Defect two, the conical side surface 211 of airfilter and the air guide port 212 of air intake valve are close to vertical, and after causing air-flow vertically to flow into airfilter inside from conical side surface 211, flow direction also needs upset 90 ° could be inner by air guide port 212 inflow engine;
Defect three, the conical side surface 211 of airfilter is as air inlet face, air-flow is made to enter airfilter from 360 ° of directions, and then when air-flow lays respectively at conical side surface 211 two opposites (the upper side and lower side of conical side surface 211), two opposition air-flows form mutual resistance, affect air-flow and flow into;
Defect four, the communication port flowed into as air-flow by air guide port 212, due to the limitation of air intake valve air guide port 212 self space, makes the unit time interior gas volume flowed into by air guide port 212 less, affects the operating efficiency of driving engine.
But, the airfilter 200 that the utility model embodiment provides:
First, by arranging ventilation slot 203 in the bottom of unmanned plane, increasing the gas volume flowed into by ventilation slot 203 in the unit time, improve the operating efficiency of driving engine 100;
Secondly, by setting up filter screen 201, eliminate the air plankton containing elements such as S, N in air, and filter screen 201 is for facing type directly, compared with traditional conical side surface 211, overcome after air-flow vertically flows into airfilter inside from conical side surface 211, flow direction also needs upset 90 ° could be inner by air guide port 212 inflow engine;
Finally, by setting up filter screen 201, all inflow air all flow into air intake valve 104 from same direction, overcome the conical side surface 211 of traditional airfilter as air inlet face, air-flow is made to enter airfilter from 360 ° of directions, and then when air-flow lays respectively at conical side surface 211 two opposites (the upper side and lower side of conical side surface 211), two opposition air-flows form mutual resistance, affect air-flow and flow into.
It should be noted that, in the airfilter 200 that the utility model embodiment provides, for avoiding impurity air to enter by the gap of the connecting portions such as fairing 202, air intake valve 104, preferably, in airfilter 200, also comprising seal ring 204.Sealing circle 204 is arranged between fairing 202 and air intake valve 104, to seal connecting portion therebetween.
For rotor attaching parts part
Refer to Fig. 4, this rotor attaching parts 300 at least can comprise: mast 301, oar clamp pin axle 302 and damping washer 304.
Wherein, the end of mast 301 is provided with damping trough 303, this damping trough 303 channel-shaped structure ringwise, with the mating shapes of damping washer 304, this damping washer 304 is set on damping trough 303, and this damping washer 304 possesses spring function, to play antihunt action to rotor attaching parts 300.Meanwhile, oar clamp pin axle 302 is set in mast 301 rotationally, and oar clamp pin axle 302 can be rotated in perpendicular relative to mast 301.This perpendicular can be the plane in the Y direction shown in Fig. 4.Damping washer 304 is set in after on damping trough 303, and one side (medial surface) fits with the outer wall of mast 301, and another side (lateral surface) fits with the inwall of oar clamp pin axle.
Specifically, the inside of oar clamp pin axle 302 is fixed with the portable bar 309 that is hollow cylinder barrel structure, the internal diameter of this portable bar 309 is greater than the external diameter of mast 301, to make by forming a gap between the inwall of internal activity bar 308 and the outer wall of mast 301.And the width in gap suitable with the thickness of damping washer 304 (identical), be set on damping trough 303 to make damping washer 304, one side (medial surface) just fits with the outer wall of mast 301, another side (lateral surface) just fits with the inwall of oar clamp pin axle, like this when oar clamp pin axle 302 rotates in perpendicular, owing to there is a gap between oar clamp pin axle 302 and mast 301, mast 301 is swung on horizontal surface direction relative to oar clamp pin axle 302 by this gap.Wherein, described horizontal surface direction is the plane in the X-direction shown in Fig. 4.
It should be noted that, therebetween be completely fixed just because of the bearing pin (being equivalent to the oar clamp pin axle 302 in the utility model embodiment in rotor attaching parts 300) of the main shaft (being equivalent to the mast 301 in the utility model embodiment in rotor attaching parts 300) of tail rotor and oar folder in prior art, make the plane of revolution of tail-rotor in rotary course (being equivalent to the perpendicular in the utility model embodiment) be stationary plane.
But, when plane of revolution of the prior art is stationary plane, the vibrations that air flow field causes rotor are very large, very easily cause the fastening situation of each attaching parts of unmanned plane afterbody, and rotor drives the vibrations of unmanned plane afterbody, drive the vibrations of unmanned aerial vehicle body in succession, be unfavorable for the control of unmanned aerial vehicle body, easily cause aircraft accident.
But the rotor attaching parts 300 that the utility model embodiment provides, by forming a gap between portable bar 308 and mast 301, and arranges a damping trough 303 in the end of mast 301, with sheathed damping washer 304.When oar clamp pin axle 302 can be made like this to rotate in perpendicular relative to mast 301, also swing on horizontal surface direction relative to mast 301 by formed gap, the vibrations that air flow field causes rotor farthest can be reduced with this, and then avoid rotor because driving the vibrations of unmanned plane afterbody, and drive the vibrations of unmanned aerial vehicle body in succession, finally cause the generation of safety misadventure.
In addition, the damping washer 304 that rotor attaching parts 300 is set up, possesses spring function.In other words, when oar clamp pin axle 302 pass through formed gap swing on horizontal surface direction relative to mast 301 time, the medial surface of damping washer 304 fits with the outer wall of mast 301, the inwall of oar clamp pin axle 302 with lateral surface is corresponding respectively, to pass through damping washer 304 when by compression, there is elastic deformation, realize playing to go to delay to the swing between oar clamp pin axle 302 and mast 301 acting on, avoid oar clamp pin axle 302 and mast 301 directly collide and are damaged.
As preferably, damping washer 304 can be the ring-shaped rubber packing ring possessing spring function.
As preferably, be rotationally connected by a movable part between mast 301 and oar clamp pin axle 302.Also namely, be rotationally connected by a movable part between portable bar 308 and oar clamp pin axle 302.This movable part at least can comprise: bolt 306, nut 305, the first flange bearing 307, second flange bearing 308.
Wherein, bolt 306 is threaded with nut 305 through the first flange bearing 307, oar clamp pin axle 302, mast 301, second flange bearing 308 successively.And by this mode be threaded between mast 301 with oar clamp pin axle 302, also can make between mast 301 and oar clamp pin axle 302 detachable, there is replacement, feature easy to maintenance.
For kinetic balance element portion,
Refer to Fig. 5, these kinetic balance parts at least can comprise: balance block 401, balance element 402, and pipe link 403.
Wherein, balance block 401 is provided with a mounting groove, mast 301 is passed offered mounting groove and is rotationally connected with balance block 401, oar clamp pin axle 302 respectively, and mast 301 can be rotated relatively with balance block 401, oar clamp pin axle 302.Meanwhile, balance element 402 is fixed on the end of balance block, with the center of gravity of balance paddle clamp pin axle 302.One end of pipe link 403 is fixedly connected with balance block, and the other end is fixedly connected with oar clamp pin axle 302.
It should be noted that, in prior art, because two tail rotors 404 of unmanned plane can only, regulating along prize wing direction of principal axis does kinetic balance, make the center of gravity of rotor assemblies (tail rotor 404+ rotor bearing pin 302) near rotor bearing pin 302, to make complete machine steady.But for making rotor assemblies center of gravity near rotor bearing pin 302, and when blindly increasing the local weight of tail rotor 404/ rotor bearing pin 302, also can affect the rotating speed of tail rotor 404, affect unmanned plane during flying operation.
But, the kinetic balance parts that the utility model embodiment provides, by other positions at non-tail rotor 404/ rotor bearing pin 302, set up balance block 401, balance element 402, and the mounting groove that mast 301 is offered through balance block 401 middle part is rotationally connected with it.Make the utility model embodiment, then add the weight at unmanned plane two tail rotor 404 positions by balance block 401, balance element 402, under have adjusted the prerequisite of the center of flying gravity of tail rotor 404, the rotating speed of tail rotor 404 is not had any impact.Otherwise, reducing unmanned plane tail vibration level by kinetic balance parts, overcoming because blindly increasing the local weight of tail rotor 404/ rotor bearing pin 302 in prior art, and to the technological deficiency that tail rotor 404 rotating speed impacts.
What needs were said especially is, the kinetic balance parts that the utility model embodiment provides, also can according to the flight demand of unmanned plane, the quantity of reasonable increasing/subtract balance block 401 two ends balance element 402, to realize carrying out fine adjustment to the center of gravity of rotor assemblies, the rotor assemblies center of gravity accommodation accuracy of further raising, has the advantages that safety performance is high.
As preferably, one end of pipe link 403 is provided with a U-type groove, and is connected with position, the top bolt of balance block by U-type groove, and the other end of pipe link 403 is provided with pin-and-hole, and by the top boss pinned connection of pin-and-hole and oar clamp pin axle 302.Finally realize oar clamp pin axle 302, mast 301 can relative to pipe link 403 High Rotation Speed.Wherein, the quantity of pipe link 403 can be two, and the upper/lower terminal being distributed in balance block 401 of two pipe link 403 symmetries, and the centre part of balance block 403 is by offering mounting groove and balance block 401 is rotationally connected.
The adjustable unmanned plane of degree of balance provided by the utility model, its beneficial effect is as described below:
1. the direction that, the utility model is discharged by the direction that flowed into by air-flow and tail gas is arranged on the same side not being positioned at driving engine 100, the angle formed from the direction that air intake valve 104 flows into and tail gas from the direction that exhausr port 102 is discharged by air-flow is set to 90 °, make the air intake valve 104 ambient air temperature of driving engine 100 can not raise along with the rising of exhausr port 102 place temperature like this, actv. avoids in prior art the impact that engine operating efficiency causes;
2., in the utility model, admission port 105 and exhausr port 102 are positioned at the both sides in cylinder 101 internal-combustion space, after air-flow is entered by admission port 105, through the then space, whole inside of cylinder 101, and discharge from exhausr port 102 again after Thorough combustion, improve burning of gas efficiency;
3., detachable between cylinder 101, cylinder body 103 and air intake valve 104 in the utility model, three is substituted, easy to maintenance;
4., the utility model by arranging ventilation slot 203 in the bottom of unmanned plane, increase in the unit time gas volume flowed into by ventilation slot 203, improve the operating efficiency of driving engine 100;
5., the utility model is by setting up filter screen 201, eliminate the air plankton containing elements such as S, N in air, and filter screen 201 is for facing type directly, compared with traditional conical side surface 211, overcome after air-flow vertically flows into airfilter inside from conical side surface 211, flow direction also needs upset 90 ° could be inner by air guide port 212 inflow engine;
6., the utility model is by setting up filter screen 201, all inflow air all flow into air intake valve 104 from same direction, overcome the conical side surface 211 of traditional airfilter as air inlet face, air-flow is made to enter airfilter from 360 ° of directions, and then when air-flow lays respectively at conical side surface 211 two opposites (the upper side and lower side of conical side surface 211), two opposition air-flows form mutual resistance, affect air-flow and flow into;
7., the utility model by forming a gap between portable bar 308 and mast 301, and a damping trough 303 is set in the end of mast 301, with sheathed damping washer 304, when oar clamp pin axle 302 can be made like this to rotate in perpendicular relative to mast 301, also swing on horizontal surface direction relative to mast 301 by formed gap, the vibrations that air flow field causes rotor farthest can be reduced with this, and then avoid rotor because driving the vibrations of unmanned plane afterbody, and drive the vibrations of unmanned aerial vehicle body in succession, finally cause the generation of safety misadventure,
8., the utility model is by fitting corresponding respectively to the medial surface of damping washer 304 and lateral surface with the outer wall of mast 301, the inwall of oar clamp pin axle 302, to pass through damping washer 304 when by compression, there is elastic deformation, realize playing to go to delay to the swing between oar clamp pin axle 302 and mast 301 acting on, avoid oar clamp pin axle 302 and mast 301 directly collide and are damaged;
9., the utility model by other positions of non-tail rotor 404/ rotor bearing pin 302, set up balance block 401, balance element 402, and the mounting groove that mast 301 is offered through balance block 401 middle part is rotationally connected with it.Make the utility model embodiment, then add the weight at unmanned plane two tail rotor 404 positions by balance block 401, balance element 402, under have adjusted the prerequisite of the center of flying gravity of tail rotor 404, the rotating speed of tail rotor 404 is not had any impact.Otherwise, reducing unmanned plane tail vibration level by kinetic balance parts, overcoming because blindly increasing the local weight of tail rotor 404/ rotor bearing pin 302 in prior art, and to the technological deficiency that tail rotor 404 rotating speed impacts;
10., the utility model by rationally increasing/subtracting the quantity of balance block 401 two ends balance element 402, to realize carrying out fine adjustment to the center of gravity of rotor assemblies, the rotor assemblies center of gravity accommodation accuracy improved further, has the advantages that safety performance is high.
Although described preferred embodiment of the present utility model, those skilled in the art once obtain the basic creative concept of cicada, then can make other change and amendment to these embodiments.So claims are intended to be interpreted as comprising preferred embodiment and falling into all changes and the amendment of the utility model scope.
Obviously, those skilled in the art can carry out various change and modification to the utility model and not depart from spirit and scope of the present utility model.Like this, if these amendments of the present utility model and modification belong within the scope of the utility model claim and equivalent technologies thereof, then the utility model is also intended to comprise these change and modification.
Claims (5)
1. the adjustable unmanned plane of degree of balance, comprise fuselage, mast and oar clamp pin axle, it is characterized in that, described unmanned plane also comprises:
Driving engine, is fixed on the inside of described fuselage, comprises:
At least one cylinder, described cylinder is provided with exhausr port;
Cylinder body, is connected with described air cylinder detachable type, and between described cylinder with described cylinder body, air-flow communicates;
Air intake valve, be connected with described cylinder body is detachable, air-flow is flowed into from described air intake valve, and entered in described cylinder by described cylinder body and burn, tail gas after burning is discharged from described exhausr port, and the angle that described air-flow is formed from the direction that described air intake valve flows into and described tail gas from the direction that described exhausr port is discharged is 0 °-90 °;
Kinetic balance parts, comprising:
Balance block, is provided with a mounting groove, and described mast is rotationally connected through described mounting groove and described balance block, and described mast is rotated relative to described balance block;
Balance element, is fixed on the end of described balance block, to balance the center of gravity of described oar clamp pin axle;
Attaching parts, one end is fixedly connected with described balance block, and the other end and described oar clamp pin axle are rotationally connected, and described oar clamp pin axle is rotated relative to described attaching parts;
Rotor attaching parts, comprising:
Mast, end is provided with damping trough;
Oar clamp pin axle, is set in described mast;
Damping washer, is set on described damping trough, and a side of described damping washer and described mast fit, and another side and described oar clamp pin axle fit;
Wherein, the internal diameter of described oar clamp pin axle is greater than the external diameter of described mast, to make to form a gap between described oar clamp pin axle and described mast, and the thickness of the width in described gap and described damping washer is suitable, when described oar clamp pin axle being rotated in perpendicular by described gap, described oar clamp pin axle, on the direction perpendicular to described perpendicular, can swing relative to described mast.
2. the adjustable unmanned plane of degree of balance as claimed in claim 1, is characterized in that,
Described cylinder is also provided with admission port;
Described cylinder body is provided with communication port, and the described cylinder body end face that is provided with described communication port and described cylinder are provided with, and the end face of described admission port is detachable to be connected, described admission port and described communication port suitable, after making described air-flow enter described cylinder body, flowed in described cylinder by described communication port, described admission port successively.
3. the adjustable unmanned plane of degree of balance as claimed in claim 2, is characterized in that,
Described exhausr port set on described cylinder, with admission port set on described cylinder, be two opposition mouths of described cylinder, make described air-flow by described admission port, through the whole inner space of described cylinder, and discharge from described exhausr port again after Thorough combustion.
4. the adjustable unmanned plane of degree of balance as claimed in claim 1, is characterized in that,
Be rotationally connected by a movable part between described mast and described oar clamp pin axle;
Described movable part comprises:
Bolt;
Nut;
First flange bearing;
Second flange bearing;
Wherein, described in described screw bolt passes, the first flange bearing, described oar clamp pin axle, described mast, described second flange bearing are connected with described nut thread.
5. the adjustable unmanned plane of degree of balance as claimed in claim 1, is characterized in that:
One end of described attaching parts is provided with U-type groove, and is threaded by the top of described U-type groove with described balance block, and the other end of described attaching parts is provided with pin-and-hole, and presss from both sides pinned connection by described pin-and-hole and described oar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420872032.6U CN204433064U (en) | 2014-12-31 | 2014-12-31 | The adjustable unmanned plane of degree of balance |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420872032.6U CN204433064U (en) | 2014-12-31 | 2014-12-31 | The adjustable unmanned plane of degree of balance |
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| Publication Number | Publication Date |
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| CN204433064U true CN204433064U (en) | 2015-07-01 |
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| CN201420872032.6U Expired - Fee Related CN204433064U (en) | 2014-12-31 | 2014-12-31 | The adjustable unmanned plane of degree of balance |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253312A (en) * | 2015-09-28 | 2016-01-20 | 湖北易瓦特科技股份有限公司 | Flexible exhaust passage with dynamic balance system |
-
2014
- 2014-12-31 CN CN201420872032.6U patent/CN204433064U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253312A (en) * | 2015-09-28 | 2016-01-20 | 湖北易瓦特科技股份有限公司 | Flexible exhaust passage with dynamic balance system |
| CN105253312B (en) * | 2015-09-28 | 2017-08-25 | 易瓦特科技股份公司 | Flexible exhaust passage with dynamic balance system |
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Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Patentee after: Easy Technology Co Ltd Address before: 430000 Hubei province Wuhan Shiqiao Road No. 6 high-tech building Patentee before: EWATT CO., LTD. |
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Granted publication date: 20150701 Termination date: 20181231 |