CN204548480U - Fixed-wing propeller aeroplane and actuating device thereof - Google Patents
Fixed-wing propeller aeroplane and actuating device thereof Download PDFInfo
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- CN204548480U CN204548480U CN201520052822.4U CN201520052822U CN204548480U CN 204548480 U CN204548480 U CN 204548480U CN 201520052822 U CN201520052822 U CN 201520052822U CN 204548480 U CN204548480 U CN 204548480U
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Abstract
The utility model discloses a kind of fixed-wing propeller aeroplane and actuating device thereof, actuating device comprises foot piece; And screw propeller, the axis of this screw propeller and the axis of foot piece are on the same line; And driver train, this driver train is arranged on foot piece, and the axis of Power output end and the axis of foot piece of driver train are located along the same line, and the Power output end of driver train is fixedly connected with screw propeller.The line of thrust that this actuating device produces can overlap with the center of gravity line of unmanned plane.
Description
Technical field
The utility model relates to technical field of aerospace, is specifically related to a kind of fixed-wing propeller aeroplane and actuating device thereof, and actuating device is wherein loaded into fixed-wing propeller aeroplane waist.
Background technology
Fixed-wing unmanned plane is the one in fixed-wing propeller aeroplane, and fixed-wing unmanned plane is a kind of by aerocraft unpiloted on power driven, machine.It usually by body, engine installation, flight control and managerial tools, launch reclaiming scrap etc. and form, can remote control or automatically fly, can single use, also can reclaim, repeatedly use.It is one of current high and new technology equipment, and being widely used in battlefield investigation, electronic countermeasure, after the war many warlike operations such as lesion assessment, air-to-ground attack, is the requisite equipment of IT-based warfare.At civil area, it be widely used in increase rain artificially, air remote sensing, aerial mapping, forest fire protection, the field such as coastline patrol.
For fixed-wing unmanned plane, generally, the voyage of fixed-wing unmanned plane can be subject to the restriction supplying the drive system energy, but except the energy, the voyage of structure to unmanned plane of drive system self also has a crucial factor.For current conventional fixed-wing class unmanned plane, power pack section can be divided into following several from layout division:
The first, draw before power: if publication number is CN202879791U, name is called the new patent of practicality of " the fixed-wing unmanned plane of airborne Two bors d's oeuveres camera ", the drive system of this fixed-wing unmanned plane is fixed on the front portion of fuselage, the advantage of this unmanned plane is: relatively good manipulation, directive property is accurate, and air-flow positive acting is on wing.Shortcoming is: drive system has conflict with FPV (the main vision of the first person), namely the most rational installation site of pick up camera is the head at fuselage, but the installation site of pick up camera is taken by drive system, the installation site of pick up camera is in the later part of the head of fuselage, cause the interference being subject to drive system during camera acquisition image, reduce the acquisition quality of image.In addition, the unmanned plane drawn before power when impaired always head first collide on fault thing, not only damaged area is large, and is easily damaged by whole airplane, is difficult to maintenance, there is the defect that cost is high.Usually, in order to make camera position obtain reasonable Arrangement, solution is: the line of pull of head dislocation and draw angle adjustment to wing, after adjustment line of pull, then draws angle to resist the problem that line of pull does not run through center of gravity of airplane line by adjusting wing.But, this line of pull and wing draw the adjustment at angle, the method not only adjustment difficulty is large, precision is low, the driftage phenomenon that the line of pull (center of gravity line of line of pull and aircraft is not on the same line) produced because of watt level when very easily causing drive system to work is inaccurate, and also can cause when gathering geography information and revolve the problems such as drift angle is excessive, affect the joining quality of photo.
The second, power pusher: as notification number is: CN301640436S, name is called the design patent of " fixed-wing unmanned plane (VF-1) ", the aircraft of this structure is the rear portion (position of empennage) power system being arranged on whole aircraft, advantage is: under the condition not affecting detecting devices installation, line of thrust runs through center of gravity line.Shortcoming: the center of gravity of aircraft rearward, causes needing superfluous weight to go to balance center of gravity, increases take-off weight, shorten air mileage.And the power system of back-pushed then can affect the parachute-opening of umbrella cabin, easy and umbrella rope is intertwined.
The third, power waist pushes away, and is arranged on the waist of aircraft by power.If notification number is CN203612198, name is called the utility model patent of the multi-functional fixed-wing unmanned plane of the formula of pulling in front and others push behind, the arrangement of the power system of this unmanned plane is: by high for one of them power system top of putting at fuselage, the problem that before this mode overcomes power, motive force systematic influence pick up camera is installed, the power system that it also avoid power pusher needs unnecessary weight balancing center of gravity and affects the problem of umbrella cabin parachute-opening, but, the power system of waist pushing-type still also exists following defect: put after back when power system is high, treat others with sincerity line and the center of gravity line of power system misplace (as shown in figure 17), need to increase the wing elevation angle or change line of thrust to balance the center of gravity of unmanned plane, ensured that anti-unmanned plane is straight, steadily.Significantly, increase the wing elevation angle unmanned plane can be made to be subject in flight course resistance increase, add the energy consumption of unmanned plane, voyage shortened, change line of thrust there will be with above-mentioned the first change the identical problem of line of pull.
The power arrangement of above-mentioned three kinds of fixed-wing unmanned planes is compared, can find out, each own respective advantage, but all there is certain defect, comparatively speaking, due to the power system of waist pushing-type overcome power before draw the defect with power pusher, the layout of power system Dominant Facies to other two kinds of power systems of waist pushing-type is obvious.But the power system Problems existing of waist pushing-type is the line of thrust of power system and the center of gravity line of fuselage to misplace, if by this Resolving probiems, be resolved making multiple problems of unmanned plane, but, regrettably, according to applicant to known to the development history of unmanned plane, and applicant is to the inquiry of related data, does not also find that the fixed-wing unmanned plane of power waist pushing-type accomplishes to have made the line of thrust of power system and center of gravity line to coincide at present.Therefore, this is also those skilled in the art's issue to be resolved but problems do not achieved a solution all the time.
Summary of the invention
The purpose of this utility model is, provides a kind of actuating device of fixed-wing propeller aeroplane, and the line of thrust that this actuating device produces can overlap with the center of gravity line of fixed-wing propeller aeroplane.
The actuating device of fixed-wing propeller aeroplane, comprises foot piece; Also comprise:
Screw propeller, the axis of this screw propeller and the axis of foot piece are on the same line; And
Driver train, this driver train is arranged on foot piece, and the axis of Power output end and the axis of foot piece of driver train are located along the same line, and the Power output end of driver train is fixedly connected with screw propeller.
Preferably, driver train comprises supporting seat, and this supporting seat is arranged on foot piece; And
Actuator, actuator is fixed on supporting seat; And
Transmission device, the power intake of transmission device is connected with the clutch end of actuator, and the clutch end of transmission device is connected with screw propeller.
Preferably, described transmission device comprises driving wheel, and this driving wheel is fixed on the clutch end of actuator; And
Flower wheel, flower wheel and driving wheel engage each other, and one end of flower wheel is provided with hollow shaft, and flower wheel is bearing on foot piece by bearing.
Preferably, described transmission device comprises driving wheel, and this driving wheel is fixed on the clutch end of actuator; And
Flower wheel, this flower wheel is connected by driving band with driving wheel, and one end of flower wheel is provided with hollow shaft, and driven pulley is bearing on foot piece by bearing.
Preferably, the transmitting ratio of described driving wheel and flower wheel is 1: 2.
Preferably, described foot piece comprises the first foot piece and the second foot piece, and one end of supporting seat is fixed on the first foot piece, and the other end of supporting seat is provided with cavity, and described actuator is fixed in the cavity of supporting seat;
Described transmission device comprises hollow shaft, and one end of hollow shaft is connected with actuator, and the other end empty set of hollow shaft is on the second foot piece and to be exposed to the cavity of supporting seat outside; And
Clutch shaft bearing, the inner ring of this clutch shaft bearing is connected with the second foot piece, and the outer ring of clutch shaft bearing is fixed in the endoporus of hollow shaft; And
Second bearing, the inner ring of this second bearing is fixed on the outer circumference surface of hollow shaft, and the outer ring of the second bearing is fixed in the cavity of supporting seat.
Preferably, the internal face of described hollow shaft is provided with the gear teeth, and the clutch end of described actuator is provided with gear, and the gear teeth on this gear and inner wall of hollow shaft face engage each other.
Preferably, described driver train comprises external rotor electric machine, and one end of described foot piece is through external rotor electric machine, and the Power output portion of external rotor electric machine is connected with described screw propeller.
Another object of the present utility model is to provide the fixed-wing propeller aeroplane that a kind of line of thrust and center of gravity line overlap, and unmanned plane of the present utility model has the long feature of duration of voyage.
Fixed-wing propeller aeroplane, comprises fuselage, wing, empennage, and described wing is arranged on fuselage, also comprises actuating device, and one end of the foot piece in actuating device is fixedly connected with fuselage, and the other end of foot piece is connected with empennage.
Preferably, the body skin of described fuselage, wing, empennage adopt low-temperature carbon dioxide expanded material to make.
The utility model has the advantage of, due to the axial line of screw propeller and foot piece axial line on the same line, the axial line of foot piece and the center of gravity line of fixed-wing propeller aeroplane are on the same line, thus, the center of gravity line of the line of thrust produced during propeller works and fixed-wing propeller aeroplane keeps on the same line, the problem that the line for the treatment of others with sincerity that perfect structure of the present utility model solves power waist feeding office overlaps with center of gravity line, therefore, the utility model no longer needs by increasing the wing elevation angle or changing the center of gravity that line of thrust balances unmanned plane, not only thrust that screw propeller produces is utilized and maximize, can ensure that fixed-wing propeller aeroplane is straight when flying, steadily, but also be conducive to the voyage extending flight.And because be by the through transmission of the hard link of deceleration group, and the energy consumption causing obtaining equal thrust and need also reduces greatly.
Below in conjunction with the drawings and specific embodiments, structure of the present utility model and principle are described in detail.
Accompanying drawing explanation
Fig. 1 is the perspective view of the first embodiment of actuating device of the present utility model;
Fig. 2 is the exploded drawings of Fig. 1;
Fig. 3 is the perspective view of the second embodiment of actuating device of the present utility model;
Fig. 4 is the exploded drawings of Fig. 3;
Fig. 5 is the section-drawing of the 3rd embodiment of actuating device of the present utility model;
Fig. 6 is the section-drawing of the 4th embodiment of actuating device of the present utility model;
Fig. 7 is the perspective view of the 5th embodiment of actuating device of the present utility model;
Fig. 8 is the perspective view of the 6th embodiment of actuating device of the present utility model;
Fig. 9 is the perspective view of unmanned plane of the present utility model;
Figure 10 is the birds-eye view of unmanned plane of the present utility model;
Figure 11 is the schematic diagram of the camera head (wherein containing cradle head structure) of unmanned plane;
Figure 12 is the exploded drawings of Figure 11;
Figure 13 figure is the section-drawing of Figure 11;
Figure 14 is the schematic diagram after taking the second fairing and protecgulum in Figure 11 away;
Figure 15 is the schematic diagram of the first fairing;
Figure 16 is the schematic diagram of roll rocking arm;
Figure 17 is the structural representation of unmanned plane of the prior art.
Detailed description of the invention
First embodiment
As depicted in figs. 1 and 2, the actuating device of the first fixed-wing propeller aeroplane of the present utility model, comprises foot piece 10, screw propeller and driver train.Foot piece 10 adopts carbon fibre material to make, and one end of foot piece 10 is used for being fixedly connected with the fuselage of unmanned plane, and therefore, the axial line of foot piece 10 and the center of gravity line of whole frame unmanned plane are on the same line.Driver train is arranged on foot piece 10, the axis of the Power output end of driver train and the axis of foot piece 10 are located along the same line, therefore, after being fixedly connected with screw propeller the Power output end of driver train, the axis of screw propeller and the axis of foot piece 10 are on the same line.
Driver train comprises supporting seat 11, actuator 12 and transmission device, supporting seat 11 is arranged on foot piece 10, in present embodiment, supporting seat 11 is a housing with cavity 11a, supporting seat 11 is provided with the first axis hole and the second axis hole, in the first axis hole, be arranged on bearing, one end of foot piece 10 is passed from the endoporus of bearing.Actuator 12 is fixed on supporting seat 11, in present embodiment, actuator 12 is preferably inner rotor motor, actuator 12 can also be combustion engine, the clutch end of actuator 12 enters into the cavity 11a on this supporting seat 11 through the second axis hole on supporting seat 11, the power intake of transmission device is connected with the clutch end of actuator 12.
Transmission device comprises driving wheel 13 and flower wheel 14, and driving wheel 13 and flower wheel 14 are external-gearing spur-gear cylindrical gear, and the transmitting ratio of driving wheel and flower wheel is 1: 2.Driving wheel 13 and flower wheel 14 are all arranged in the cavity 11a of supporting seat 11, by cover plate 15, the oral area of cavity 11a are carried out capping, thus are protected driving wheel 13 and flower wheel 14, avoid being subject to the impurity such as dust and invade, affect transmission performance.Wherein, driving wheel 13 is fixed on the clutch end of actuator 12, and flower wheel 14 and driving wheel 13 engage each other, and one end of flower wheel 14 is provided with hollow shaft 16, hollow shaft 16 preferably adopts and the integrated structure of flower wheel, and flower wheel 14 is bearing on foot piece by bearing.The clutch end of transmission device is connected with screw propeller, hollow shaft 16 is as the clutch end of transmission device, the outer circumference surface of hollow shaft 16 is provided with annular boss 16a, the outer circumference surface of hollow shaft 16 is also provided with tapped bore 16b and a pair radial protrusion 16c, tapped bore 16b is between two radial protrusion 16c.
Screw propeller is made up of blade folder 17 and blade 18, blade folder 17 is in sleeve-shaped, blade folder 17 is enclosed within after on hollow shaft 16, be connected with the tapped bore 16b on hollow shaft 16 by screw, this blade folder 17 is integrated with hollow shaft 16, one end of blade folder 17 is by annular boss 16a axial limiting, and the other end of blade folder 17 is by being anchored on steady ring 19 axial limiting on foot piece 10.The inner periphery wall of blade folder 17 is provided with groove, and the radial protrusion 16c on this groove and hollow shaft 16 cooperatively interacts, and makes blade press from both sides 17 and obtains circumference location, presss from both sides 17, relative to hollow shaft 16, circumferential rotation occurs to avoid blade.The excircle wall of blade folder 17 is provided with Connection Block, and one end of blade 18 is connected with this Connection Block, and blade 18 can be connected by hinged form with Connection Block, and such blade 18 can fold before take-off or before landing.
The working process of the actuating device of present embodiment is: the moment of torsion that actuator 12 exports drives driving wheel 13 to rotate, and driving wheel 13 drives flower wheel 14 to rotate, and hollow shaft 16 rotates in company with flower wheel 14, and hollow shaft carrying screws rotates.Due to the axial line of screw propeller and foot piece 10 axial line on the same line, the axial line of foot piece and the center of gravity line of fixed-wing propeller aeroplane are on the same line, thus, the center of gravity line of the line of thrust produced during propeller works and fixed-wing propeller aeroplane keeps on the same line, the problem that the line for the treatment of others with sincerity that this perfect structure solves power waist feeding office overlaps with center of gravity line, therefore, present embodiment no longer needs by increasing the wing elevation angle or changing the center of gravity that line of thrust balances unmanned plane, not only can ensure that fixed-wing propeller aeroplane is straight when flying, steadily, but also be conducive to the voyage extending flight.In addition, because driving wheel 13 and the transmitting ratio of flower wheel 14 are 1: 2, this transmission by slowing down makes outputting power obtain increase, improves the antagonism with air resistance in flight course, reduces the energy consumption in flight course significantly.
Second embodiment
As shown in Figure 3 and Figure 4, the actuating device of the second fixed-wing propeller aeroplane of the present utility model, comprises foot piece 20, screw propeller and driver train.Foot piece 20 adopts carbon fibre material to make, and one end of foot piece 20 is used for being fixedly connected with the fuselage of unmanned plane, and therefore, the axial line of foot piece 20 and the center of gravity line of whole frame unmanned plane are on the same line.Driver train is arranged on foot piece 20, the axis of the Power output end of driver train and the axis of foot piece 20 are located along the same line, therefore, after being fixedly connected with screw propeller the Power output end of driver train, the axis of screw propeller and the axis of foot piece 20 are on the same line.
Driver train comprises supporting seat 21, actuator 22 and transmission device, supporting seat 21 is arranged on foot piece 20, in present embodiment, supporting seat 21 is in tabular, the two ends of supporting seat 21 are curved, and the radius of one end circular arc is greater than the radius of other end circular arc, and supporting seat 21 is provided with the first axis hole and the second axis hole, in the first axis hole, be arranged on bearing, one end of foot piece 20 is passed from the endoporus of bearing.Actuator 22 is fixed on supporting seat 21, and in present embodiment, actuator 22 is preferably inner rotor motor, and actuator 22 can also be combustion engine, and the clutch end of actuator 22 is connected with transmission device through after the second axis hole on supporting seat 21.
Transmission device comprises driving wheel 23, flower wheel 24 and driving band 25, and driving wheel 23 is fixed on the clutch end of actuator 22, and flower wheel 24 is connected by driving band 25 with driving wheel 23, and driven belt 24 is bearing on foot piece 20 by bearing.Driving wheel 23 and flower wheel 24 preferably adopt the cylindrical wheel of external toothing, and driving wheel 23 is 1: 2 with the transmitting ratio of flower wheel 24.After driving wheel 23 and flower wheel 24 are preferably gear, the inside face of driving band 25 is provided with tooth, tooth on driving band 25 engages each other with the gear teeth on driving wheel 23 and flower wheel 24 respectively, this V belt translation structure is after adding tooth, can prevent from skidding in transmission process, improve the reliability of transmission.One end of flower wheel is provided with hollow shaft (not shown), and described screw propeller is fixedly connected on this hollow shaft.
Screw propeller comprises blade folder 26 and blade 27, the structure of hollow shaft, and the connection mode of blade folder 26 and hollow shaft, and blade 27 presss from both sides the connection mode of 26 with blade, all identical with enforcement formula one, does not repeat them here.
The working process of the actuating device of present embodiment is: the moment of torsion that actuator 22 exports drives driving wheel 23 to rotate, and driving wheel 23 drives flower wheel 24 to rotate by driving band 25, and hollow shaft rotates in company with flower wheel 24, and hollow shaft carrying screws rotates.Due to the axial line of screw propeller and foot piece 10 axial line on the same line, the axial line of foot piece and the center of gravity line of fixed-wing propeller aeroplane are on the same line, thus, the center of gravity line of the line of thrust produced during propeller works and fixed-wing propeller aeroplane keeps on the same line, the problem that the line for the treatment of others with sincerity that this perfect structure solves power waist feeding office overlaps with center of gravity line, therefore, present embodiment equally no longer needs by increasing the wing elevation angle or changing the center of gravity that line of thrust balances unmanned plane, not only can ensure that fixed-wing propeller aeroplane is straight when flying, steadily, but also be conducive to the voyage extending flight.In addition, because driving wheel 23 and the transmitting ratio of flower wheel 24 are 1: 2, this transmission by slowing down makes outputting power obtain increase, improves the antagonism dynamics with air resistance in flight course, reduces the energy consumption in flight course significantly.
3rd embodiment
As shown in Figure 5, the actuating device of the third fixed-wing propeller aeroplane of the present utility model, comprises foot piece, screw propeller and driver train.Described foot piece adopts carbon fibre material to make, in present embodiment, foot piece is made up of the first foot piece 30a and the second foot piece 30b, the axial line of the first foot piece 30a and the second foot piece 30b on the same line, one end of first foot piece 30a is for connecting the fuselage of unmanned plane, and the other end of the first foot piece 30a is connected with driver train.The axial line of the first foot piece 30a and the second foot piece 30b and the center of gravity line of whole frame unmanned plane are on the same line.The axis of the Power output end of driver train and the axis of the first foot piece 30a and the second foot piece 30b are located along the same line, therefore, after being fixedly connected with screw propeller the Power output end of driver train, the axis of the axis of screw propeller and the first foot piece 30a and the second foot piece 30b on the same line.
Driver train comprises supporting seat 31, actuator 32 and transmission device.Supporting seat 31 is arranged on foot piece, and preferably, one end of supporting seat 31 is connected with the first foot piece 30a, the other end of supporting seat 31 is provided with cavity 31a, at the accent of cavity 31a, a cover plate (cover plate is not shown in the drawings) is set, enters in cavity to prevent the impurity such as dust.Actuator 32 is arranged in cavity 31a and is fixedly connected with supporting seat, and actuator 32 preferably adopts internal rotor electronics, and actuator 32 also can adopt combustion engine.The power intake of transmission device is connected with the clutch end of actuator 32, and described transmission device comprises hollow shaft 33, clutch shaft bearing 34, second bearing 35.One end of hollow shaft 33 is connected with actuator 32, the internal face of described hollow shaft 33 is provided with the gear teeth, namely one end of hollow shaft 33 is an internal gear with internal tooth, the clutch end of described actuator 32 is provided with gear 32a, this gear is fastened on the clutch end of actuator 32, the gear teeth on gear 32a and hollow shaft 33 internal face engage each other, and the transmitting ratio of the internal gear on gear 32a and hollow shaft 33 is preferably 1: 2.The other end empty set of hollow shaft 33 is on the second foot piece 31b and be exposed to the outside of supporting seat 31 cavity 31a, the inner ring of clutch shaft bearing 34 and the second foot piece 31b interference fit, the outer ring of clutch shaft bearing 34 is fixed on by the mode of interference fit in the endoporus of hollow shaft 33, the both sides of clutch shaft bearing 34 are provided with back-up ring 34a, form bearing by back-up ring 34a to clutch shaft bearing spacing, back-up ring 34a is fixed on the second foot piece 31b.The inner ring of the second bearing 35 is fixed on by the mode of interference fit on the outer circumference surface of hollow shaft 33, the outer ring of the second bearing 35 is fixed on by the mode of interference fit in the cavity of supporting seat 31, the both sides of the second bearing 35 are provided with back-up ring 35a, form bearing by back-up ring 35a to the second bearing spacing, back-up ring 35a is fixed on the internal face of supporting seat 31.Like this, by clutch shaft bearing 34 and the second bearing 35, second foot piece 31b and hollow shaft 33 have been bearing on supporting seat 31.
The clutch end of transmission device is connected with screw propeller, the clutch end of part as transmission device being exposed to the outside of supporting seat 31 cavity 31a of hollow shaft 33, screw propeller is fixed on above the part being exposed to the outside of the cavity 31a of supporting seat 31 of hollow shaft 33.Screw propeller is made up of blade folder 36 and blade 37, the connection structure of hollow shaft 33 and screw propeller, and blade 37 presss from both sides the connection mode of 36 with blade, all identical with enforcement formula one, does not repeat them here.
The working process of the actuating device of present embodiment is: the moment of torsion driven gear 32a that actuator 32 exports rotates, and gear 32a drives hollow shaft 33 to rotate, and hollow shaft 33 carrying screws rotates.Due to the axial line of screw propeller and foot piece axial line on the same line, the axial line of foot piece and the center of gravity line of fixed-wing propeller aeroplane are on the same line, thus, the center of gravity line of the line of thrust produced during propeller works and fixed-wing propeller aeroplane keeps on the same line, the problem that the line for the treatment of others with sincerity that this structure also solves the power waist feeding office of fixed-wing propeller aeroplane overlaps with center of gravity line, therefore, present embodiment also no longer needs by increasing the wing elevation angle or changing the center of gravity that line of thrust balances unmanned plane, can ensure that fixed-wing propeller aeroplane is straight when flying, steadily, but also be conducive to the voyage extending flight.In addition, the transmitting ratio due to the inner gear on gear 32a and hollow shaft 33 is 1: 2, and this transmission by slowing down makes outputting power obtain increase, improves the antagonism dynamics with air resistance in flight course, reduces the energy consumption in flight course significantly.
4th embodiment
As shown in Figure 6, the actuating device of the 4th kind of fixed-wing propeller aeroplane of the present utility model, present embodiment is with the difference of the 3rd embodiment: actuator 32 is directly connected with hollow shaft by coupler 32a.All the other structures of present embodiment are identical with the 3rd embodiment.
The working process of the actuating device of present embodiment is: the moment of torsion that actuator 32 exports drives coupler 32a to rotate, and coupler 32a drives hollow shaft 33 to rotate, and hollow shaft 33 carrying screws rotates.Due to the axial line of screw propeller and foot piece axial line on the same line, the axial line of foot piece and the center of gravity line of fixed-wing propeller aeroplane are on the same line, thus the center of gravity line of the line of thrust produced during propeller works and fixed-wing propeller aeroplane keeps on the same line.
5th embodiment
As shown in Figure 7, the actuating device of the 5th kind of fixed-wing propeller aeroplane of the present utility model, comprises foot piece 40, screw propeller and driver train.Foot piece 40 adopts carbon fibre material to make, and one end of foot piece 40 is used for being fixedly connected with the fuselage of unmanned plane, and therefore, the axial line of foot piece 40 and the center of gravity line of whole frame unmanned plane are on the same line.Driver train is arranged on foot piece 40, the axis of the Power output end of driver train and the axis of foot piece 40 are located along the same line, therefore, after being fixedly connected with screw propeller the Power output end of driver train, the axis of screw propeller and the axis of foot piece 40 are on the same line.
Driver train comprises external rotor electric machine 41, and the bolster 42 of this external rotor electric machine 41 is hollow shaft, and one end of described foot piece 40 is passed from the endoporus of bolster 42, and the two ends of hollow shaft 42 are by being fixed on the lock ring 42a axial limiting on foot piece.The Power output portion of external rotor electric machine 41 is connected with described screw propeller, the outer rotor 43 of external rotor electric machine 41 is the Power output portion of this external rotor electric machine 41, the periphery of the outer rotor 43 of external rotor electric machine 41 is provided with Connection Block 44, Connection Block 44 preferably adopts and the integrated mode of outer rotor 43, Connection Block 44 also can be an independent part, adopts welding or screw and outer rotor 43 to be fastened as a whole.Described screw propeller is blade 45, and one end of blade 45 is connected with Connection Block 44, and connection mode preferably adopts the hinged blade that makes to fold.
The working process of the actuating device of present embodiment is: drive outer rotor 43 to rotate when external rotor electric machine 41 works, outer rotor 43 drives blade to rotate, because the endoporus of foot piece 40 from bolster 42 passes, therefore the axial line of the axial line of foot piece 40 and bolster 42 on the same line, the axial line of outer rotor and the axial line of foot piece are also on the same line, like this, the center of gravity line of the line of thrust produced during propeller works and fixed-wing propeller aeroplane keeps on the same line.Thus, the problem that the line for the treatment of others with sincerity that this structure also solves the power waist feeding office of fixed-wing propeller aeroplane overlaps with center of gravity line, therefore, present embodiment equally no longer needs by increasing the wing elevation angle or changing the center of gravity that line of thrust balances unmanned plane, can ensure that fixed-wing propeller aeroplane is straight, steady when flying, but also be conducive to the voyage extending flight.
6th embodiment
As shown in Figure 8, the actuating device of the 6th kind of fixed-wing propeller aeroplane of the present utility model, the structure of the screw propeller of present embodiment is different from the 5th embodiment with mounting means, be specially: screw propeller presss from both sides 46 by blade 45 and blade and forms, blade 45 is fixed on blade folder 46, and blade folder 46 is fixed on the axial end of outer rotor 43 of external rotor electric machine 41.All the other structures of present embodiment are identical with the 5th embodiment.
The working process of the actuating device of present embodiment is: drive outer rotor 43 to rotate when external rotor electric machine 41 works, outer rotor 43 drives blade to rotate, because the endoporus of foot piece 40 from bolster 42 passes, therefore the axial line of the axial line of foot piece 40 and bolster 42 on the same line, the axial line of outer rotor and the axial line of foot piece are also on the same line, like this, the center of gravity line of the line of thrust produced during propeller works and fixed-wing propeller aeroplane keeps on the same line.
Below, the battery of 4S 5000MAH (4S represents the normal voltage of 14.8V) is adopted to carry out experimental taking a flight test to traditional unmanned plane and aircraft of the present utility model, course continuation mileage after changing to check dynamic structure layout and flight time, the result of inspection and contrast is as follows:
As can be seen from relatively above-mentioned, when capacity of cell is equal, the utility model is after the structure changing actuating device and layout, flight time and course continuation mileage obtain lifting all significantly, compare traditional several structures, tool has an enormous advantage, particularly the first embodiment of the present utility model, the second embodiment and the 3rd embodiment, its flight time traditional dynamic structure relative to course continuation mileage, has turned over one especially and has turned over.
As shown in Figure 9 and Figure 10, fixed-wing propeller aeroplane of the present utility model, comprises fuselage 50, wing 60, empennage 70, and described wing 60 is arranged on fuselage 50.Also comprise any one actuating device (actuating device here in conjunction with the first embodiment is described) in the above-mentioned first to the 6th embodiment, one end of foot piece 10 in actuating device is fixedly connected with fuselage 50, and the other end of foot piece 10 is connected with empennage 70.The body skin of described fuselage 50, wing 60, empennage 70 all adopt low-temperature carbon dioxide expanded material to make.Low-temperature carbon dioxide expanded material has lightweight, good toughness, intensity is high, by force restorative, fire-resistant corrosion-resistant, environmental protection series of advantages, because this material is under the weight of taking off equally, carrier rigidity toughness can be made to increase substantially, and make unmanned plane not fragile, considerably increase the durability of unmanned plane.Because aircraft is when falling, the probability that its head first lands is larger, and therefore, the utility model, by selecting low-temperature carbon dioxide expanded material, enhances the durability of unmanned plane.
Can find out in figure 9 and in figure 10, install camera cradle head A at the leading section of fuselage, as illustrated in figures 11-16, this camera cradle head A comprises inner housing, roll rocking arm 3, roll steering wheel 4, first fairing 5, pitch-control motor 6, second fairing 7.
Inner housing has accommodating chamber, and described inner housing is made up of protecgulum 1 and bonnet 2, after protecgulum 1 and bonnet 2 are fixed as one, forms described accommodating chamber between protecgulum and bonnet.The overall globulate of inner housing, but clip a part two relative sides, makes these two relative sides be cutting plane, but not cambered surface, these two cutting planes are respectively used to connect pitch-control motor and bearing set.
Roll rocking arm 3 and roll steering wheel 4 are arranged in the accommodating chamber on inner housing, and one end of roll rocking arm 3 is connected with one end of roll steering wheel 4, and the other end of roll steering wheel 4 is fixed on the internal face of inner housing.Described roll rocking arm 3 comprises contiguous block 3a, turns back respectively and form rocking arm 3b in the two ends of contiguous block 3a.The end of described rocking arm 3b is provided with the first breach 3c, the second breach 3d and the 3rd breach 3e, and the second breach 3d is between the first breach 3c and the 3rd breach 3e.First breach 3c, the second breach 3d and the 3rd breach 3e are respectively used to assemble with pick up camera.Be provided with baffle plate 3f at the oral area of the 3rd breach 3e, by the barrier effect of baffle plate 3f, pick up camera side direction in the swing process with roll rocking arm 3 can be avoided to skid off.
The outside wall surface of inner housing side is provided with bearing set, and inner housing is connected with the first fairing 5 is movable by this bearing set.Bearing set comprises bearing (not shown), bearing sleeve 2a, and described bearing is fixed on inner housing, and particularly, bearing is fixed on the bonnet 2 of inner housing.One end of bearing sleeve 2a to be enclosed within bearing and to be fastened as a whole with bearing 2a, the outer ring interference fit of bearing sleeve 2a and bearing.First fairing 5 is provided with axle 5a, and one end of this axle 5a and the other end of bearing sleeve 2a are fastened as a whole.Described first fairing 5 is provided with through hole, and the outer wall of the first fairing is provided with the case 5b covering described through hole, and the other end of described axle 5a is connected on the internal face of case 5b with through after described through hole.
One end of pitch-control motor 6 is connected in the outside wall surface of inner housing opposite side, and preferably, one end of pitch-control motor 6 is fixed on the side wall surface of bonnet 2.The other end of pitch-control motor 6 is connected with the second fairing 7.Described second fairing 7 is provided with through hole, the outer wall of the second fairing 7 is provided with the cover body 7a covering described through hole, the internal face of cover body arranges the box body 7b that has opening, a part for described pitch-control motor 6 is arranged in this box body 7b, and pitch-control motor 6 is fixed by screws in box body 7b.
After second fairing 7 is connected with the first fairing 5, what reserve a confession inner housing is exposed to outer breach at least partially.The end of the second fairing 7 and the first fairing 5 is equipped with arc notch, when the second fairing 7 and the first fairing 5 in conjunction with time, the breach that between second fairing 7 and the first fairing 5, formation one is circular, like this, just make a part for inner housing be exposed to outside, the head for pick up camera can visit external environment condition.After second fairing 7 and the first fairing 5 combine, a pitot 1a is installed in the junction at both tops.
As shown in Figure 11 to 13, the utility model is on the basis based on camera cradle head A, also be provided with a kind of camera head of unmanned plane, comprise pick up camera 8 and figure biography device 9, also comprise the camera cradle head A described in above-mentioned embodiment, described position for video camera is in the accommodating chamber of inner housing, inner housing is provided with resigning hole, pick up camera 8 is connected with the other end of roll rocking arm 3, the side wall surface of pick up camera 8 is provided with cylinder 8a, each side wall surface is provided with three cylinder 8a, and these three cylinders coordinate with the first breach 3c, the second breach 3d of rocking arm 3, the 3rd breach 3f respectively.The head of pick up camera 8 extend in the resigning hole on inner housing, and described figure passes device 9 and is connected with the first fairing 5 and the second fairing 7 respectively.Described figure passes device 9 and comprises permanent seat 9a and figure biography device 9b, and figure passes device 9b and is fixed on permanent seat 9a, and the two ends of permanent seat 9a are connected with the first fairing 5 and the second fairing 7 respectively.
The working process of camera cradle head is: when the The Cloud Terrace carrying pick up camera is subject to the disturbance of air-flow, the horizontal and vertical angle of pick up camera all can change, roll servo driving roll rocking motion, pick up camera swings along with roll rocking motion, to adjust the horizontal deflection angle of pick up camera.Pitch-control motor drives inner housing to rotate, and pick up camera swings along with the action of inner housing, to adjust longitudinal deflection angle of pick up camera.When the horizontal and vertical angle of pick up camera can obtain adjustment, the position of pick up camera can not change all the time.Camera cradle head is under the function prerequisite meeting adjustment camera angle, inner housing, roll rocking arm, roll steering wheel, the first fairing, the second fairing, pitch-control motor rational layout and design have been carried out, above-mentioned part is assembled with in narrow space, possesses the feature of compact overall structure, and it is without any redundant structure weight, lighter by 50% than conventional peripheral formula The Cloud Terrace.。
Claims (10)
1. the actuating device of fixed-wing propeller aeroplane, comprises foot piece; It is characterized in that, also comprise:
Screw propeller, the axis of this screw propeller and the axis of foot piece are on the same line; And
Driver train, this driver train is arranged on foot piece, and the axis of Power output end and the axis of foot piece of driver train are located along the same line, and the Power output end of driver train is fixedly connected with screw propeller.
2. the actuating device of fixed-wing propeller aeroplane according to claim 1, is characterized in that: driver train comprises supporting seat, and this supporting seat is arranged on foot piece; And
Actuator, actuator is fixed on supporting seat; And
Transmission device, the power intake of transmission device is connected with the clutch end of actuator, and the clutch end of transmission device is connected with screw propeller.
3. the actuating device of fixed-wing propeller aeroplane according to claim 2, it is characterized in that: described transmission device comprises driving wheel, this driving wheel is fixed on the clutch end of actuator; And
Flower wheel, flower wheel and driving wheel engage each other, and one end of flower wheel is provided with hollow shaft, and flower wheel is bearing on foot piece by bearing.
4. the actuating device of fixed-wing propeller aeroplane according to claim 2, it is characterized in that: described transmission device comprises driving wheel, this driving wheel is fixed on the clutch end of actuator; And
Flower wheel, this flower wheel is connected by driving band with driving wheel, and one end of flower wheel is provided with hollow shaft, and driven pulley is bearing on foot piece by bearing.
5. the actuating device of the fixed-wing propeller aeroplane according to claim 3 or 4, is characterized in that: the transmitting ratio of described driving wheel and flower wheel is 1: 2.
6. the actuating device of fixed-wing propeller aeroplane according to claim 2, it is characterized in that: described foot piece comprises the first foot piece and the second foot piece, one end of supporting seat is fixed on the first foot piece, and the other end of supporting seat is provided with cavity, and described actuator is fixed in the cavity of supporting seat;
Described transmission device comprises hollow shaft, and one end of hollow shaft is connected with actuator, and the other end empty set of hollow shaft is on the second foot piece and to be exposed to the cavity of supporting seat outside; And
Clutch shaft bearing, the inner ring of this clutch shaft bearing is connected with the second foot piece, and the outer ring of clutch shaft bearing is fixed in the endoporus of hollow shaft; And
Second bearing, the inner ring of this second bearing is fixed on the outer circumference surface of hollow shaft, and the outer ring of the second bearing is fixed in the cavity of supporting seat.
7. the actuating device of fixed-wing propeller aeroplane according to claim 6, it is characterized in that: the internal face of described hollow shaft is provided with the gear teeth, the clutch end of described actuator is provided with gear, and the gear teeth on this gear and inner wall of hollow shaft face engage each other.
8. the actuating device of fixed-wing propeller aeroplane according to claim 1, is characterized in that: described driver train comprises external rotor electric machine, and one end of described foot piece is through external rotor electric machine, and the Power output position of external rotor electric machine is connected with described screw propeller.
9. a fixed-wing propeller aeroplane, comprise fuselage, wing, empennage, described wing is arranged on fuselage, it is characterized in that: also comprise the actuating device as described in claim 1 to 8 any one, one end of foot piece in actuating device is fixedly connected with fuselage, and the other end of foot piece is connected with empennage.
10. fixed-wing propeller aeroplane according to claim 9, is characterized in that: the body skin of described fuselage, wing, empennage adopt low-temperature carbon dioxide expanded material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520052822.4U CN204548480U (en) | 2015-01-21 | 2015-01-21 | Fixed-wing propeller aeroplane and actuating device thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520052822.4U CN204548480U (en) | 2015-01-21 | 2015-01-21 | Fixed-wing propeller aeroplane and actuating device thereof |
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| Publication Number | Publication Date |
|---|---|
| CN204548480U true CN204548480U (en) | 2015-08-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520052822.4U Withdrawn - After Issue CN204548480U (en) | 2015-01-21 | 2015-01-21 | Fixed-wing propeller aeroplane and actuating device thereof |
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| CN (1) | CN204548480U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882943A (en) * | 2015-01-21 | 2016-08-24 | 常州华奥航空科技有限公司 | Fixed wing propeller-driven aircraft and driving device thereof |
-
2015
- 2015-01-21 CN CN201520052822.4U patent/CN204548480U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882943A (en) * | 2015-01-21 | 2016-08-24 | 常州华奥航空科技有限公司 | Fixed wing propeller-driven aircraft and driving device thereof |
| CN105882943B (en) * | 2015-01-21 | 2018-06-26 | 常州华奥航空科技有限公司 | Fixed rotor and propeller aircraft and its driving device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150812 Effective date of abandoning: 20180626 |