CN204415711U - A kind of exhausting formula empennage of closed microlight-type two-seater helicopter - Google Patents
A kind of exhausting formula empennage of closed microlight-type two-seater helicopter Download PDFInfo
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- CN204415711U CN204415711U CN201420805046.6U CN201420805046U CN204415711U CN 204415711 U CN204415711 U CN 204415711U CN 201420805046 U CN201420805046 U CN 201420805046U CN 204415711 U CN204415711 U CN 204415711U
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Abstract
The utility model belongs to microlight-type two-seater Helicopter Technology field, disclose a kind of exhausting formula empennage of closed microlight-type two-seater helicopter, solve that the cost of manufacture that existing empennage of helicopter exists is high, the problem that there is larger potential safety hazard and wind concentration difference.The utility model comprises the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.The utility model can either improve the centrality of wind-force, reduces the potential safety hazard of helicopter simultaneously.
Description
Technical field
The utility model belongs to microlight-type two-seater Helicopter Technology field, is specifically related to a kind of exhausting formula empennage of closed microlight-type two-seater helicopter.
Background technology
Not rotating with rotor opposite sense to control helicopter fuselage, needing to install an empennage additional at tail and producing a reversing sense air propels power and carry out stable fuselage, and regulating the angle of empennage speed and empennage blade to turn to control helicopter fuselage.
Such as application number be 201220536530.4 utility model patent disclose a kind of pilotless helicopter of spraying insecticide, comprise body, tail-rotor, empennage, rotor, spray tank, fuel tank, driving engine, alighting gear, cross bar, nozzle and Teat pipette, empennage and rotor are installed on rear end and the upper end of body respectively, fuel tank and driving engine are installed in body, alighting gear and cross bar are installed on the lower end of body, spray tank is installed between the alighting gear below body, nozzle is installed on cross bar, Teat pipette respectively with liquid medicine-chest, nozzle connects, also comprise and be installed on autopilot on body rear end and spray variable controller, spray variable controller to be connected with Teat pipette.The quantity of nozzle is 4, and symmetry is installed on the cross bar of body two side respectively.Cross bar is folding is installed on body lower end.Also comprise the gps antenna be connected with autopilot, gps antenna is installed on empennage.
Application number be 201320057750.3 utility model patent disclose a kind of Single-blade remote-control helicopter with preposition side direction screw propeller, comprise lifting device, head shell, frame and tail gear; Lifting device, head shell and tail gear are all fixedly connected in frame; Lifting device comprises main screw, balance gyro, break-in dish, steering wheel and drive motor; Electronic gyroscope is built-in with in lifting device; Balance gyro is connected to main screw upper end by bar linkage structure; Break-in dish is connected to the lower end of main screw by bar linkage structure; Break-in dish consists of the balanced connecting rod of both sides and steering wheel and is hinged, and steering wheel controls the action of break-in dish by balanced connecting rod, adjustment; Drive motor end is provided with driven wheel, and driven wheel engages with gear a, and the main shaft of gear a and main screw, to balance gyro axis be coaxial line, and it drives main screw to rotate; Tail gear comprises empennage drive motor, tail undercarriage and afterbody pipe link, and tail gear is fixedly connected in frame by afterbody pipe link; Empennage drive motor end winding support is connected with gear b, tail undercarriage is fixedly connected with gear c, and gear b engages with gear c; Frame comprises power supply, automatically controlled mainboard and be arranged at the flight support of frame lower end, it is characterized in that: the front end of frame is fixedly connected with preposition side direction screw; Preposition side direction screw comprises side propeller bracket, side screw propeller drive motor and side direction screw propeller; Side propeller bracket is fixedly connected with frame, and side screw propeller drive motor is fixedly connected on the propeller bracket of side, and side direction screw propeller is fixedly connected on the power take-off shaft of side screw propeller drive motor, by side screw propeller drive motor drive side to propeller rotational; The both sides of head shell are provided with exhaust outlet.
Application number be 201410288090.9 patent of invention disclose the adjustable helicopter of a kind of empennage attitude, comprise fuselage, be arranged at the main rotor of described fuselage roof, and be arranged at the empennage of described fuselage afterbody, the end of described empennage has tail rotor, described main rotor is driven by sustainer, main engine, empennage comprises the first empennage portion be fixedly connected with described fuselage and the second empennage portion be rotationally connected with the end in described first empennage portion, described second empennage portion is driven by posture adjustment drive motor and rotates to make described main rotor and described tail rotor be positioned in same level around the end in described first empennage portion, described sustainer, main engine is connected with electrical generator, and described electrical generator connects described posture adjustment drive motor by process transfer device, described process transfer device is also connected with storage battery, and described storage battery is connected with described posture adjustment drive motor.Described first empennage portion internal fixtion has the first adapter shaft, and the end of described first adapter shaft has the first connecting bore, is provided with rolling bearing in described first connecting bore; Described second empennage portion internal fixtion has the second adapter shaft, one end that described second adapter shaft is connected with described first adapter shaft has the second connecting bore, described posture adjustment drive motor connects drop-gear box, and the output shaft of described drop-gear box is successively through described second connecting bore and described rolling bearing.The length ratio in described first empennage portion and described second empennage portion is 3: 1.The free end in described second empennage portion is provided with described tail rotor, and the rotating shaft of described tail rotor is connected with tail rotor drive motor, and described tail rotor drive motor is connected with described process transfer device.The control desk of described helicopter is provided with posture adjustment button, described in button of raising wages be connected with described posture adjustment drive motor.Described second empennage portion has two end positions, and described two end positions are respectively the position concordant with described first empennage portion and swing upwards into the position perpendicular with described first empennage portion.
As the helicopter of the prior art told about above, empennage is all adopt two paddle blade structure, but the empennage of two paddle blade structure also exists following problem:
One, two blade is identical with the power that rotor blade produces in order to ensure the antagonistic force produced, and the longer and wider width of blade of the length of blade, adds the cost of manufacture of blade;
Two, sweep leaf also exists larger potential safety hazard for crew during upper and lower machine;
Three, sweep leaf is unfavorable for low-latitude flying, and particularly helicopter is when performing the low-latitude flying such as agricultural fertilizer, pesticide spraying, and sweep leaf easily contacts with branch, causes the unbalance generation safety misadventure of aircraft.
Four, the wind concentration of blade is poor.
Utility model content
The utility model is in order to the problem that the cost of manufacture solving the existence of existing empennage of helicopter is high, there is larger potential safety hazard and wind concentration difference, and a kind of exhausting formula empennage of closed microlight-type two-seater helicopter is provided, by changing tail structure, length and the width of blade can be reduced, reduce manufacturing cost; The shortening of blade length, can reduce the upper and lower machine of crew and the potential safety hazard of helicopter when low-latitude flying; Improve the centrality of blade wind-force simultaneously, improve the handling of helicopter.
For solving the problems of the technologies described above, the technical scheme that the utility model adopts is:
A kind of exhausting formula empennage of closed microlight-type two-seater helicopter, it is characterized in that, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, and described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.
Described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.
Described back hub is connected to one end of caudal wing shaft, the other end of described caudal wing shaft is provided with tail gear case through bearing carrier ring, afterbody big gear wheel is provided with in described tail gear case, described afterbody big gear wheel is connected with helicopter engine through transmission shaft, the periphery of described caudal wing shaft is fixedly connected with afterbody miniature gears, and described afterbody miniature gears engages with afterbody big gear wheel.
Described tail gear case is connected with at least two tail-rotor displacement phase place pins, caudal wing shaft between described tail gear case and back hub is arranged with tail-rotor displacement swivel becket bearing, the excircle of described tail-rotor displacement swivel becket bearing is arranged with tail-rotor displacement swivel becket, described tail-rotor displacement swivel becket offers and the same number of plug helix of tail-rotor displacement phase place pin, described tail-rotor displacement phase place pin and plug helix mutually adaptive, described tail-rotor displacement swivel becket is connected with tail-rotor displacement arm, and described tail-rotor displacement arm is connected with the pedal tail vane steel wire pull bar of helicopter; Described tail-rotor displacement swivel becket bearing is also connected with the tail-rotor displacement sliding sleeve being set in caudal wing shaft periphery, and one end of described tail-rotor displacement sliding sleeve is connected with tail-rotor displacement swivel becket bearing, and the other end of tail-rotor displacement sliding sleeve is set in the centre hole of back hub; The periphery of described tail-rotor folder is connected with tail-rotor chuck, and described tail-rotor chuck is connected with tail-rotor displacement sliding sleeve.
The both sides of described tail gear case are provided with the side cover being set in caudal wing shaft periphery, are provided with oil sealing between described side cover and bearing.
Described tail gear case is equipped with powder sensor and tail gear case exhaust part.
The gear clearance that the periphery of described caudal wing shaft is also arranged with for supporting afterbody miniature gears regulates lining.Make the fixing of gap between afterbody big gear wheel and afterbody miniature gears.
Compared with prior art, the utility model has following beneficial effect:
Closed microlight-type two-seater empennage of helicopter of the present utility model, comprise the back hub be set on caudal wing shaft, back hub offers at least 4 mounting holes along the radial direction of back hub, in mounting hole, thrust bearing is installed, institute's thrust bearing is arranged with tail-rotor folder, tail-rotor is folded with tail-rotor, and the periphery of tail-rotor is provided with exhausting formula protective cover.The utility model, by changing the structure of back hub, is folded with at least 4 tail-rotors in the radial direction at back hub, by increasing the number of tail-rotor, can reduce length and the width of each tail-rotor, because this reducing manufacturing cost; Simultaneously the utility model reduces the potential safety hazard when length of tail-rotor and width can reduce crew's upper and lower helicopter, decreases the potential safety hazard of helicopter when low-latitude flying.
The utility model, by arranging the centrality that exhausting formula protective cover can either improve tail-rotor wind-force in the periphery of tail-rotor, can improve again the upper and lower machine of crew and the safety performance of helicopter when low latitude is in fashion by exhausting formula protective cover simultaneously further.
The utility model improves the centrality of blade wind-force simultaneously, improves the handling of helicopter.
Accompanying drawing explanation
Fig. 1 is block diagram structural representation of the present utility model;
Fig. 2 is the partial enlargement figure structure schematic representation at Fig. 1 A place;
Fig. 3 is cutaway view structural representation of the present utility model, namely along the cutaway view structural representation of caudal wing shaft axis direction;
Mark in figure: 1, transmission shaft, 2, tail gear case, 3, back hub, 4, tail-rotor, 5, caudal wing shaft, 6, tail-rotor displacement sliding sleeve, 7, tail-rotor chuck, 8, tail-rotor presss from both sides, 9, thrust bearing, 10, thrust washer, 11, tail-rotor displacement swivel becket bearing, 12, tail-rotor displacement arm, 13, tail-rotor displacement swivel becket, 14, tail-rotor displacement phase place pin, 15, side cover, 16, bearing, 17, tail gear case exhaust part, 18, afterbody big gear wheel, 19, gear clearance regulates lining, 20, afterbody miniature gears, 21, oil sealing, 22, powder sensor, 23, plug helix, 24, exhausting formula protective cover.
Detailed description of the invention
Below in conjunction with embodiment, the utility model will be further described, and described embodiment is only the utility model part embodiment, is not whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art, not making other embodiments used obtained under creative work prerequisite, belongs to protection domain of the present utility model.
Closed microlight-type two-seater empennage of helicopter of the present utility model, comprise the back hub 3 be set on caudal wing shaft 5, back hub 3 offers at least 4 mounting holes along the radial direction of back hub 3, thrust bearing 9 is installed in mounting hole, institute's thrust bearing 9 is arranged with tail-rotor folder 8, tail-rotor folder 8 is folded with tail-rotor 4, and the periphery of tail-rotor 4 is provided with exhausting formula protective cover 24.The utility model, by changing the structure of back hub 3, is folded with at least 4 tail-rotors 4 in the radial direction at back hub 3, by increasing the number of tail-rotor 4, can reduce length and the width of each tail-rotor 4, because this reducing manufacturing cost; Simultaneously the utility model reduces the potential safety hazard when length of tail-rotor and width can reduce crew's upper and lower helicopter, decreases the potential safety hazard of helicopter when low-latitude flying.Particularly in agricultural utilization process, helicopter needs low-latitude flying, and the reduction of tail-rotor length can reduce the chance of tail-rotor and branch or line contacts, thus potential safety hazard when decreasing helicopter low-latitude flying.
Back hub of the present utility model can be arranged 4,6 or 8 tail-rotors 4, as a kind of preferred mode of the utility model, back hub is provided with 8 tail-rotors, again can reduce length and the width of tail-rotor 4, when improving further the upper and lower helicopter of crew and the safety performance of low-latitude flying.
The utility model, by arranging the centrality that exhausting formula protective cover 24 can either improve tail-rotor wind-force in the periphery of tail-rotor 4, at the same conditions, can reduce the power of helicopter engine, cost-saving; The upper and lower machine of crew and the safety performance of helicopter when low latitude is in fashion can be improved again further by exhausting formula protective cover simultaneously.Because decrease the direct chance contacted with foreign object of tail-rotor 4 by exhausting formula protective cover 24.
The utility model improves the centrality of blade wind-force simultaneously, improves the handling of helicopter.
As a kind of preferred mode of the utility model, mounting hole is stepped hole, is provided with thrust washer 10 between described thrust bearing 9 and the ladder of mounting hole.Back hub is provided with centre hole and mounting hole, and centre hole is used for sheathed caudal wing shaft, and mounting hole is for installing tail-rotor folder 8, and mounting hole and centre hole are mutually through.Mounting hole of the present utility model is stepped, is convenient to the installation of tail-rotor folder 8, improves practicality of the present utility model.
As the preferred mode of one of the present utility model, back hub 3 is connected to one end of caudal wing shaft 5, the other end of described caudal wing shaft 5 is arranged with tail gear case 2 through bearing 15, afterbody big gear wheel 18 is provided with in described tail gear case 2, described afterbody big gear wheel 18 is connected with helicopter engine through transmission shaft 1, the periphery of described caudal wing shaft 5 is fixedly connected with afterbody miniature gears 20, and described afterbody miniature gears 20 engages with afterbody big gear wheel 18.The power of helicopter engine passes to the afterbody big gear wheel 18 in tail gear case 2 through transmission shaft 1, afterbody big gear wheel 18 engages with afterbody miniature gears 20, afterbody miniature gears 20 drives caudal wing shaft 5 to rotate, and caudal wing shaft 5 is with the back hub 3 be automatically connected on caudal wing shaft 5 to rotate, and then drives tail-rotor 4 to rotate.It is simple that the utility model has structure, the feature of dependable performance.
The gear clearance that the periphery of the utility model caudal wing shaft 5 is also arranged with for supporting afterbody miniature gears 20 regulates lining 19, make the fixing of gap between afterbody big gear wheel 18 and afterbody miniature gears 20, improve the precision that afterbody big gear wheel 18 engages with afterbody miniature gears 20, improve practicality of the present utility model.
Empennage of the present utility model is also equipped with the control apparatus of the pitch (i.e. the angle of inclination of tail-rotor) for regulating tail-rotor 4, can regulate the pitch of tail-rotor 4 according to different situations, meets the different flight condition of helicopter, improves the airworthiness of helicopter.
As a kind of preferred mode of the utility model, control apparatus is: tail gear case 2 is connected with at least two tail-rotor displacement phase place pins 14, preferably, the both sides of tail gear case 2 are provided with the side cover 15 being set in caudal wing shaft 5 periphery, be provided with oil sealing between side cover 15 and bearing 16, tail-rotor displacement phase place pin 14 is fixedly connected on side cover.Caudal wing shaft 5 between tail gear case 2 and back hub 3 is arranged with tail-rotor displacement swivel becket bearing 11, the excircle of described tail-rotor displacement swivel becket bearing 11 is arranged with tail-rotor displacement swivel becket 13, described tail-rotor displacement swivel becket 13 offers and the same number of plug helix 23 of tail-rotor displacement phase place pin, that is to say plug helix and tail-rotor displacement phase place pin one_to_one corresponding, described tail-rotor displacement phase place pin 14 and plug helix 23 are mutually adaptive, preferably, spiral fluted number is 6, and is opened in uniformly on tail-rotor displacement swivel becket 13.Described tail-rotor displacement swivel becket 13 is connected with tail-rotor displacement arm 12, and described tail-rotor displacement arm 12 is connected with the pedal tail vane steel wire pull bar of helicopter; Described tail-rotor displacement swivel becket bearing 11 is also connected with the tail-rotor displacement sliding sleeve 6 being set in caudal wing shaft 5 periphery, one end of described tail-rotor displacement sliding sleeve 6 is connected with tail-rotor displacement swivel becket bearing 11, and the other end of tail-rotor displacement sliding sleeve 6 is set in the centre hole of back hub 3; The periphery of described tail-rotor folder 8 is connected with tail-rotor chuck 7, and described tail-rotor chuck 7 is connected with tail-rotor displacement sliding sleeve 6.The utility model for regulating the principle of work of the pitch adjustment means of tail-rotor 4 is: the pedal tail vane steel wire pull bar of helicopter drives tail-rotor displacement arm 12 to rotate, tail-rotor displacement arm 12 drives tail-rotor displacement swivel becket 13 to rotate, under the effect of plug helix 23 and tail-rotor displacement phase place pin 14, tail-rotor displacement swivel becket 13 is rotated along the axial direction of caudal wing shaft 5, the axial motion of tail-rotor displacement swivel becket 13 drives tail-rotor displacement sliding sleeve 6 to rotate along the axial direction of caudal wing shaft 5, the axial motion of tail-rotor displacement sliding sleeve 6 drives tail-rotor chuck 7 to rotate, and then drive the tail-rotor that is fixedly connected with tail-rotor chuck 7 to press from both sides 8 to rotate, realize the adjustment of tail-rotor 4 pitch (angle of inclination).It is simple that the utility model has structure, the feature of dependable performance.
As a kind of preferred mode of the utility model, tail gear case 2 is equipped with powder sensor 22 and tail gear case exhaust part 17, the operating mode of tail gear case is detected by arranging powder sensor 22, improve the ability automatically detected, be convenient to grasp in time and understand working condition, improve practicality of the present utility model.Wherein powder sensor and tail gear case exhaust part belong to prior art products, and those skilled in the art can understand and understand, and does not repeat them here.
Embodiment one
The exhausting formula empennage of the closed microlight-type two-seater helicopter of the present embodiment, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.
Embodiment two
The exhausting formula empennage of the closed microlight-type two-seater helicopter of the present embodiment, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.Described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.
Embodiment three
The exhausting formula empennage of the closed microlight-type two-seater helicopter of the present embodiment, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.Described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.Described back hub is connected to one end of caudal wing shaft, the other end of described caudal wing shaft is provided with tail gear case through bearing carrier ring, afterbody big gear wheel is provided with in described tail gear case, described afterbody big gear wheel is connected with helicopter engine through transmission shaft, the periphery of described caudal wing shaft is fixedly connected with afterbody miniature gears, and described afterbody miniature gears engages with afterbody big gear wheel.
Embodiment four
The exhausting formula empennage of the closed microlight-type two-seater helicopter of the present embodiment, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.Described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.Described back hub is connected to one end of caudal wing shaft, the other end of described caudal wing shaft is provided with tail gear case through bearing carrier ring, afterbody big gear wheel is provided with in described tail gear case, described afterbody big gear wheel is connected with helicopter engine through transmission shaft, the periphery of described caudal wing shaft is fixedly connected with afterbody miniature gears, and described afterbody miniature gears engages with afterbody big gear wheel.Described tail gear case is connected with at least two tail-rotor displacement phase place pins, caudal wing shaft between described tail gear case and back hub is arranged with tail-rotor displacement swivel becket bearing, the excircle of described tail-rotor displacement swivel becket bearing is arranged with tail-rotor displacement swivel becket, described tail-rotor displacement swivel becket offers and the same number of plug helix of tail-rotor displacement phase place pin, described tail-rotor displacement phase place pin and plug helix mutually adaptive, described tail-rotor displacement swivel becket is connected with tail-rotor displacement arm, and described tail-rotor displacement arm is connected with the pedal tail vane steel wire pull bar of helicopter; Described tail-rotor displacement swivel becket bearing is also connected with the tail-rotor displacement sliding sleeve being set in caudal wing shaft periphery, and one end of described tail-rotor displacement sliding sleeve is connected with tail-rotor displacement swivel becket bearing, and the other end of tail-rotor displacement sliding sleeve is set in the centre hole of back hub; The periphery of described tail-rotor folder is connected with tail-rotor chuck, and described tail-rotor chuck is connected with tail-rotor displacement sliding sleeve.
Embodiment five
The exhausting formula empennage of the closed microlight-type two-seater helicopter of the present embodiment, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.Described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.Described back hub is connected to one end of caudal wing shaft, the other end of described caudal wing shaft is provided with tail gear case through bearing carrier ring, afterbody big gear wheel is provided with in described tail gear case, described afterbody big gear wheel is connected with helicopter engine through transmission shaft, the periphery of described caudal wing shaft is fixedly connected with afterbody miniature gears, and described afterbody miniature gears engages with afterbody big gear wheel.Described tail gear case is connected with at least two tail-rotor displacement phase place pins, caudal wing shaft between described tail gear case and back hub is arranged with tail-rotor displacement swivel becket bearing, the excircle of described tail-rotor displacement swivel becket bearing is arranged with tail-rotor displacement swivel becket, described tail-rotor displacement swivel becket offers and the same number of plug helix of tail-rotor displacement phase place pin, described tail-rotor displacement phase place pin and plug helix mutually adaptive, described tail-rotor displacement swivel becket is connected with tail-rotor displacement arm, and described tail-rotor displacement arm is connected with the pedal tail vane steel wire pull bar of helicopter; Described tail-rotor displacement swivel becket bearing is also connected with the tail-rotor displacement sliding sleeve being set in caudal wing shaft periphery, and one end of described tail-rotor displacement sliding sleeve is connected with tail-rotor displacement swivel becket bearing, and the other end of tail-rotor displacement sliding sleeve is set in the centre hole of back hub; The periphery of described tail-rotor folder is connected with tail-rotor chuck, and described tail-rotor chuck is connected with tail-rotor displacement sliding sleeve.The both sides of described tail gear case are provided with the side cover being set in caudal wing shaft periphery, are provided with oil sealing between described side cover and bearing.
Embodiment six
The exhausting formula empennage of the closed microlight-type two-seater helicopter of the present embodiment, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.Described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.Described back hub is connected to one end of caudal wing shaft, the other end of described caudal wing shaft is provided with tail gear case through bearing carrier ring, afterbody big gear wheel is provided with in described tail gear case, described afterbody big gear wheel is connected with helicopter engine through transmission shaft, the periphery of described caudal wing shaft is fixedly connected with afterbody miniature gears, and described afterbody miniature gears engages with afterbody big gear wheel.Described tail gear case is connected with at least two tail-rotor displacement phase place pins, caudal wing shaft between described tail gear case and back hub is arranged with tail-rotor displacement swivel becket bearing, the excircle of described tail-rotor displacement swivel becket bearing is arranged with tail-rotor displacement swivel becket, described tail-rotor displacement swivel becket offers and the same number of plug helix of tail-rotor displacement phase place pin, described tail-rotor displacement phase place pin and plug helix mutually adaptive, described tail-rotor displacement swivel becket is connected with tail-rotor displacement arm, and described tail-rotor displacement arm is connected with the pedal tail vane steel wire pull bar of helicopter; Described tail-rotor displacement swivel becket bearing is also connected with the tail-rotor displacement sliding sleeve being set in caudal wing shaft periphery, and one end of described tail-rotor displacement sliding sleeve is connected with tail-rotor displacement swivel becket bearing, and the other end of tail-rotor displacement sliding sleeve is set in the centre hole of back hub; The periphery of described tail-rotor folder is connected with tail-rotor chuck, and described tail-rotor chuck is connected with tail-rotor displacement sliding sleeve.The both sides of described tail gear case are provided with the side cover being set in caudal wing shaft periphery, are provided with oil sealing between described side cover and bearing.Described tail gear case is equipped with powder sensor and tail gear case exhaust part.
Embodiment seven
The exhausting formula empennage of the closed microlight-type two-seater helicopter of the present embodiment, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.Described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.Described back hub is connected to one end of caudal wing shaft, the other end of described caudal wing shaft is provided with tail gear case through bearing carrier ring, afterbody big gear wheel is provided with in described tail gear case, described afterbody big gear wheel is connected with helicopter engine through transmission shaft, the periphery of described caudal wing shaft is fixedly connected with afterbody miniature gears, and described afterbody miniature gears engages with afterbody big gear wheel.Described tail gear case is connected with at least two tail-rotor displacement phase place pins, caudal wing shaft between described tail gear case and back hub is arranged with tail-rotor displacement swivel becket bearing, the excircle of described tail-rotor displacement swivel becket bearing is arranged with tail-rotor displacement swivel becket, described tail-rotor displacement swivel becket offers and the same number of plug helix of tail-rotor displacement phase place pin, described tail-rotor displacement phase place pin and plug helix mutually adaptive, described tail-rotor displacement swivel becket is connected with tail-rotor displacement arm, and described tail-rotor displacement arm is connected with the pedal tail vane steel wire pull bar of helicopter; Described tail-rotor displacement swivel becket bearing is also connected with the tail-rotor displacement sliding sleeve being set in caudal wing shaft periphery, and one end of described tail-rotor displacement sliding sleeve is connected with tail-rotor displacement swivel becket bearing, and the other end of tail-rotor displacement sliding sleeve is set in the centre hole of back hub; The periphery of described tail-rotor folder is connected with tail-rotor chuck, and described tail-rotor chuck is connected with tail-rotor displacement sliding sleeve.The both sides of described tail gear case are provided with the side cover being set in caudal wing shaft periphery, are provided with oil sealing between described side cover and bearing.Described tail gear case is equipped with powder sensor and tail gear case exhaust part.The gear clearance that the periphery of described caudal wing shaft is also arranged with for supporting afterbody miniature gears regulates lining.
Claims (7)
1. the exhausting formula empennage of a closed microlight-type two-seater helicopter, it is characterized in that, comprise the back hub be set on caudal wing shaft, described back hub offers at least 4 mounting holes along the radial direction of back hub, in described mounting hole, thrust bearing is installed, described thrust bearing is arranged with tail-rotor folder, and described tail-rotor is folded with tail-rotor, and the periphery of described tail-rotor is provided with exhausting formula protective cover.
2. the exhausting formula empennage of closed microlight-type two-seater helicopter according to claim 1, it is characterized in that, described mounting hole is stepped hole, is provided with thrust washer between described thrust bearing and the ladder of mounting hole.
3. the exhausting formula empennage of closed microlight-type two-seater helicopter according to claim 1 and 2, it is characterized in that, described back hub is connected to one end of caudal wing shaft, the other end of described caudal wing shaft is provided with tail gear case through bearing carrier ring, afterbody big gear wheel is provided with in described tail gear case, described afterbody big gear wheel is connected with helicopter engine through transmission shaft, and the periphery of described caudal wing shaft is fixedly connected with afterbody miniature gears, and described afterbody miniature gears engages with afterbody big gear wheel.
4. the exhausting formula empennage of closed microlight-type two-seater helicopter according to claim 3, it is characterized in that, described tail gear case is connected with at least two tail-rotor displacement phase place pins, caudal wing shaft between described tail gear case and back hub is arranged with tail-rotor displacement swivel becket bearing, the excircle of described tail-rotor displacement swivel becket bearing is arranged with tail-rotor displacement swivel becket, described tail-rotor displacement swivel becket offers and the same number of plug helix of tail-rotor displacement phase place pin, described tail-rotor displacement phase place pin and plug helix mutually adaptive, described tail-rotor displacement swivel becket is connected with tail-rotor displacement arm, described tail-rotor displacement arm is connected with the pedal tail vane steel wire pull bar of helicopter, described tail-rotor displacement swivel becket bearing is also connected with the tail-rotor displacement sliding sleeve being set in caudal wing shaft periphery, and one end of described tail-rotor displacement sliding sleeve is connected with tail-rotor displacement swivel becket bearing, and the other end of tail-rotor displacement sliding sleeve is set in the centre hole of back hub, the periphery of described tail-rotor folder is connected with tail-rotor chuck, and described tail-rotor chuck is connected with tail-rotor displacement sliding sleeve.
5. the exhausting formula empennage of closed microlight-type two-seater helicopter according to claim 3, it is characterized in that, the both sides of described tail gear case are provided with the side cover being set in caudal wing shaft periphery, are provided with oil sealing between described side cover and bearing.
6. the exhausting formula empennage of closed microlight-type two-seater helicopter according to claim 4, is characterized in that, described tail gear case is equipped with powder sensor and tail gear case exhaust part.
7. the exhausting formula empennage of closed microlight-type two-seater helicopter according to claim 5, is characterized in that, the gear clearance that the periphery of described caudal wing shaft is also arranged with for supporting afterbody miniature gears regulates lining.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420805046.6U CN204415711U (en) | 2014-12-19 | 2014-12-19 | A kind of exhausting formula empennage of closed microlight-type two-seater helicopter |
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| CN201420805046.6U CN204415711U (en) | 2014-12-19 | 2014-12-19 | A kind of exhausting formula empennage of closed microlight-type two-seater helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229366A (en) * | 2018-08-02 | 2019-01-18 | 哈尔滨飞机工业集团有限责任公司 | A kind of ducted tail rotor helicopter digital tail reducer radome fairing |
-
2014
- 2014-12-19 CN CN201420805046.6U patent/CN204415711U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229366A (en) * | 2018-08-02 | 2019-01-18 | 哈尔滨飞机工业集团有限责任公司 | A kind of ducted tail rotor helicopter digital tail reducer radome fairing |
| CN109229366B (en) * | 2018-08-02 | 2021-07-16 | 哈尔滨飞机工业集团有限责任公司 | Digitized tail speed reducer fairing of ducted tail rotor helicopter |
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Effective date of registration: 20191016 Address after: 843000 in Zhejiang clothing (home textile) Industrial Park, Aksu textile industrial city (Development Zone), Aksu region, Xinjiang Uygur Autonomous Region Patentee after: Aksu Jingshi Unmanned Helicopter Technology Co., Ltd. Address before: 618300, No. 74, middle section, middle Taiwan Road, Guanghan, Sichuan, Deyang Patentee before: SICHUAN JINGSHI AEROSPACE TECHNOLOGY DEVELOPMENT CO., LTD. |
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