CN204726667U - A kind of rotor driver and install the cyclogyro of this rotor driver - Google Patents
A kind of rotor driver and install the cyclogyro of this rotor driver Download PDFInfo
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- CN204726667U CN204726667U CN201520349853.6U CN201520349853U CN204726667U CN 204726667 U CN204726667 U CN 204726667U CN 201520349853 U CN201520349853 U CN 201520349853U CN 204726667 U CN204726667 U CN 204726667U
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Abstract
The utility model discloses a kind of rotor driver, it comprises the rotor wings frame be connected in aircraft frame, described rotor wings frame is rotatably connected to the rotor sleeve that can be connected with engine installation power, rotor upper cartridge is equipped with symmetrically arranged two rotor connecting arms, on two rotor connecting arms, correspondence is connected with the rotor fin that can rotate around its axial direction, described rotor wings frame is connected with the blade angle setting device ordering about rotor arm and rotate.The utility model also provides a kind of cyclogyro installing this rotor driver, and it is connected with the rotor driver of said structure.The utility model structure is simple, have adjust flexibly blade angle, can standing start and the high advantage of flight alerting ability.
Description
Technical field
The utility model relates to a kind of rotor driver and installs the cyclogyro of this rotor driver.
Background technology
The helicopter that cyclogyro is particularly common, military affairs, industry, farming and animal husbandry, etc. field obtain application, from the cyclogyro (one of cyclogyro, usually directly cyclogyro is claimed) high security in all kinds of aircraft, cheap manufacture, buy, use and maintenance cost, between single driving make requirement, be subject to extensive concern in recent years, but because its characteristic can not original place landing, still need runway place, application is restricted, the forebody of cyclogyro installs the screw propeller driven by engine, the top of fuselage is provided with rotor head, symmetrically arranged rotor fin rotor head is equipped with, rotor fin is driven to rotate by engine, by controlling the rotating speed of rotor fin, realize the change of lift, namely flight attitude and the displacement of cyclogyro is controlled, because rotor fin is fixedly mounted on above-mentioned rotor head, this cyclogyro needs slippage certain distance just can take off, thus area occupied is large.
Utility model content
First technical matters to be solved in the utility model be to provide a kind of structure simple, can standing start and being applicable to fly the rotor driver that the strong cyclogyro of alerting ability uses.
For solving the problems of the technologies described above, provide the rotor driver with following structure, it comprises the rotor wings frame be connected in aircraft frame, described rotor wings frame is rotatably connected to the rotor sleeve that can be connected with engine installation power, its constructional feature is: described rotor upper cartridge is equipped with symmetrically arranged two rotor connecting arms, on two rotor connecting arms, correspondence is connected with the rotor fin that can rotate around its axial direction, described rotor wings frame is connected with the blade angle setting device ordering about rotor arm and rotate.
Blade angle setting device comprises the driving connecting lever be connected on rotor wings frame, rotor wings frame is connected with the blade angle actuating unit ordering about and drive swing arm to swing, described rotor sleeve is connected with can slide up and down and with the rotor shaft sliding sleeve of rotor sleeve normal-running fit, one support arm and the blade angle actuating unit of driving connecting lever are hinged, another support arm and rotor shaft sliding sleeve hinged, rotor shaft sliding sleeve is hinged with interlock connecting rod by spherical hinge, described rotor fin is connected with driving pivoted housing, drive blade angle adjustment cross bar pivoted housing being connected with and stretching out, blade angle adjustment cross bar is hinged by spherical hinge with interlock connecting rod.
Rotor wings frame is connected with rotor head main shaft, described rotor sleeve is rotatably connected on rotor head main shaft, described rotor shaft sliding sleeve is slidably connected on rotor head main shaft, the top of described rotor shaft sliding sleeve is rotatably connected to the driven wheel be connected with engine installation power, and the support arm stretched under described rotor sleeve passes through is connected with driven wheel power.
The top of rotor sleeve arranges spacing cover for seat, described driven wheel is equipped with on two and stretches support arm, and the transmission arm being arranged in spacing cover for seat is equipped with at the top of stretching support arm on two, described interlock connecting rod by spherical hinge and transmission arm hinged.
Described rotor wings frame is equipped with fixing hinge, and described driving connecting lever is provided with strip hole, drives connecting lever to be installed in strip hole by fixed pin shaft and is connected on rotor wings frame.
Blade angle actuating unit is the drive motor be connected on rotor wings frame, and the power take-off shaft of drive motor is equipped with crank, is connected with connecting rod between the support arm of described driving connecting lever and crank.
Rotor wings frame comprises the fixed mount be connected in aircraft frame, described fixed mount is connected with can to swing and can the tressel of swing, and described rotor sleeve is rotatably connected on tressel.
The hinge that fixed mount is arranged by horizontal cross is hinged with linkage rack, the hinge hinge that described tressel is longitudinally arranged by level is contained on linkage rack, described fixed mount is hinged with two power push-rods of longitudinal interval by spherical hinge, described tressel is equipped with the balance shaft longitudinally arranged, the upper end of described two power push-rods is hinged with balance shaft respectively.
Described engine installation comprises the power-driven machine be connected in aircraft frame, aircraft frame is rotatably connected to the axle drive shaft of prewhirling be connected with power driven mechanomotive force by power-transfer clutch, on the spiro rod section of prewhirling on axle drive shaft, power is connected with the driven wheel of prewhirling that can engage with driven wheel, described axle drive shaft of prewhirling is rotationally connected the top stop of restricted driven wheel rise height of prewhirling, top stop is equipped with and stretches out downwards and the jam-packed spring be positioned on described spiro rod section.
After adopting said structure, engine installation is utilized in advance rotary blade to be rotated to fair speed, after rotary blade departs from power, order about rotor arm by blade angle setting device to turn an angle, thus make the rotary blade of rotation have maximum lift, when lift exceedes the cyclogyro installing this rotor driver, the cyclogyro installing this rotor driver vertically can go up to the air in the short time, the flight of cyclogyro can be realized under the effect that cyclogyro self power promotes, realize the flexible flight of cyclogyro.
Another technical matters that the utility model solves is to provide a kind of cyclogyro, and it comprises aircraft frame, aircraft frame is connected with the screw propeller driven by engine installation, this aircraft frame is connected with the rotor driver of said structure.
In sum, the utility model structure is simple, have adjust flexibly blade angle, can standing start and the high advantage of flight alerting ability.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the utility model is further described:
Fig. 1 is the perspective view of cyclogyro in the utility model;
Fig. 2 is the structural representation of cyclogyro in the utility model;
Fig. 3 be in Fig. 2 A to structural representation;
Fig. 4 is the perspective view of Fig. 3;
Fig. 5 be in Fig. 3 B to structural representation;
Fig. 6 is the structural representation analysed and observe along C-C line in Fig. 3;
Fig. 7 is the structural representation analysed and observe along D-D line in Fig. 6;
Fig. 8 is that axle drive shaft of prewhirling is connected to structural representation in aircraft frame;
Fig. 9 is the structural representation analysed and observe along E-E line in Fig. 8.
Detailed description of the invention
As shown in Figures 1 to 7, the utility model provides a kind of rotor driver be arranged on cyclogyro, it comprises the rotor wings frame 2 be connected in aircraft frame 1, rotor wings frame 2 is rotatably connected to the rotor sleeve 3 that can be connected with engine installation power, symmetrically arranged two rotor connecting arms 4 are equipped with on rotor sleeve 3 top, on two rotor connecting arms 4, correspondence is connected with the rotor fin 5 that can rotate around its axial direction, rotor wings frame 2 is connected with the blade angle setting device ordering about rotor fin 5 and rotate, blade angle setting device comprises the driving connecting lever 6 be connected on rotor wings frame 2, fixing hinge 30 rotor wings frame 2 is equipped with, connecting lever 6 is driven to be provided with strip hole 34, driving connecting lever 6 to be installed in strip hole by fixed pin shaft is connected on rotor wings frame 2, rotor wings frame 2 is connected with the blade angle actuating unit ordering about and drive swing arm to swing, rotor sleeve 3 is connected with can slide up and down and with the rotor shaft sliding sleeve 7 of rotor sleeve 3 normal-running fit, one support arm and the blade angle actuating unit of driving connecting lever 6 are hinged, another support arm and rotor shaft sliding sleeve 7 hinged, in the present embodiment, blade angle actuating unit is the drive motor 31 be connected on rotor wings frame 2, crank 32 power take-off shaft of drive motor 31 is equipped with, connecting rod 33 is connected with between the support arm of described driving connecting lever 6 and crank, rotor shaft sliding sleeve 7 is hinged with interlock connecting rod 8 by spherical hinge, rotor fin 5 is connected with and drives pivoted housing 9, drive the blade angle adjustment cross bar 10 pivoted housing 9 being connected with and stretching out, blade angle adjustment cross bar 10 is hinged by spherical hinge with interlock connecting rod 8, drive motor 31 drives crank 32 to rotate, thus pull or promote to drive connecting lever 6, connecting lever 6 is driven to order about rotor shaft sliding sleeve 7 slippage up or down, thus drive interlock connecting rod 8 to swing, owing to driving pivoted housing 9 and rotor fin affixed and rotor fin can rotate around its axis, thus when interlock connecting rod 8 swings the rotation driving blade angle adjustment cross bar 10 to produce certain angle, simultaneously for preventing catching phenomenon, the coordinating of above-mentioned set pin and strip hole the blade angle of rotor fin is rotated more flexible.Rotor wings frame 2 is connected with rotor head main shaft 11, rotor sleeve 3 is rotatably connected on rotor head main shaft by upper and lower two bearings, described rotor shaft sliding sleeve 7 is slidably connected on rotor head main shaft 11, the top of described rotor shaft sliding sleeve 7 is rotatably connected to the driven wheel 12 be connected with engine installation power, concrete power connects as follows: engine installation comprises the power-driven machine 25 be connected in aircraft frame 1, aircraft frame 1 is rotatably connected to the axle drive shaft 26 of prewhirling be connected with power-driven machine 25 power by power-transfer clutch, the power take-off shaft of power-driven machine 25 is connected with by above-mentioned power-transfer clutch and drives flexible axle 19, flexible axle 19 is driven to be connected with above-mentioned axle drive shaft 26 power of prewhirling, power-transfer clutch does not illustrate in the drawings, it can be communicated with or cut off power, prewhirl on axle drive shaft 26 and there is spiro rod section 261, on this spiro rod section 261, power is connected with the driven wheel 27 of prewhirling that can engage with driven wheel 12, that is this spiro rod section 261 is provided with screw thread, driven wheel 27 of prewhirling is screwed onto on this spiro rod section 261, prewhirl and axle drive shaft 26 is rotationally connected the top stop 28 of restricted driven wheel rise height of prewhirling, top stop 28 is equipped with and stretches out downwards and the jam-packed spring 29 be positioned on described spiro rod section, jam-packed spring 29 plays transferring power that can be more stable when driven wheel 27 of prewhirling rises to certain altitude, when driven wheel 27 of prewhirling rises, this jam-packed spring 29 is being prewhirled between driven wheel 27 and spiro rod section 261, the driven wheel 27 that makes to prewhirl can not freely move up and down, the support arm stretched under above-mentioned rotor sleeve 3 passes through is connected with driven wheel 12 power, namely the support arm stretched down is installed on driven wheel 12, when driven wheel rotates, rotor sleeve 3 can be made to drive rotor fin 5 to turn round, the top of rotor sleeve 3 arranges spacing cover for seat 13, driven wheel 12 is equipped with on two and stretches support arm 14, the transmission arm 15 being arranged in spacing cover for seat 13 is equipped with at the top of stretching support arm 14 on two, interlock connecting rod 8 by spherical hinge and transmission arm 15 hinged, the above-mentioned drive motor of two covers can be set like this and drive connecting lever 6 can realize the blade angle synchronous change certain angle simultaneously of the rotor fin of both sides, be conducive to reducing production difficulty and improving flight stability harmony.
The action of above-mentioned rotor driver is as follows: start power-driven machine 25, driving flexible axle 19 and axle drive shaft 26 of prewhirling is given by transmission of power by power-transfer clutch, driven wheel 27 of prewhirling under the rotary action of effect of inertia and preliminary election axle drive shaft rises along above-mentioned spiro rod section 261 and rotates, driven wheel 27 and driven wheel 12 engaged transmission until prewhirl, thus drive rotor sleeve 3 and rotor fin to rotate; When after rotor fin rotating speed to specified value, make disengaging of clutch, stop Power output, driven wheel 27 of prewhirling does passive rotation under rotor inertia drives, because gravity and this driven wheel 27 of prewhirling of effect of inertia can decline along above-mentioned spiro rod section 261, disconnect with the engaging of driven wheel 12, complete cyclogyro to prewhirl action, prewhirl in process above-mentioned, rotor fin rotating speed increases, lift increases, and wheel and the ground friction of installing the aircraft of this rotor driver reduce; Anti-twisted distance cannot overcome, and rotor vane angle will be made to reduce for this reason, reduces lift, when rotor fin reaches high rotating speed, cuts off power of prewhirling, increases rotor vane angle, and rotor lift is greater than fuselage weight lift-off, under the effect of propeller force, enters state of flight rapidly.
As shown in Figures 1 to 4, above-mentioned rotor wings frame 2 comprises the fixed mount 21 be connected in aircraft frame 1, described fixed mount 21 is connected with can to swing and can the tressel 22 of swing, and described rotor sleeve is rotatably connected on tressel 22.The hinge that fixed mount 21 is arranged by horizontal cross is hinged with linkage rack 23, the hinge hinge that described tressel 22 is longitudinally arranged by level is contained on linkage rack 23, described fixed mount 21 is hinged with two power push-rods 16 of longitudinal interval by spherical hinge, the balance shaft 17 longitudinally arranged described tressel 22 is equipped with, the upper end of described two power push-rods 16 is hinged with balance shaft 17 respectively, by the impetus of above-mentioned power push-rod 16, the tressel on fixed mount can be made to produce the swing of left and right directions or fore-and-aft direction, that is, tressel is made to produce the inclination of fore-and-aft direction or left and right directions, thus the direction of tilt of adjustment rotor fin and angle, thus the rising realized in flight course, decline, transverse direction and turn to flight.
As depicted in figs. 1 and 2, the utility model provides a kind of cyclogyro, it comprises aircraft frame 1, this aircraft frame 1 is frame type A, make the stability of integral-rack higher, aircraft frame 1 is connected with the screw propeller 18 driven by engine installation, this aircraft frame 1 has installed the rotor driver of said structure, above-mentioned engine installation is above-mentioned power-driven machine 25, it is prewhirled power for above-mentioned rotor driver provides and provides power for screw propeller, this cyclogyro can install remote control equipment (RCE), the remote control distributor of artificial ground can be adopted, and global position system and automatic flight control system can be equipped with, omnibearing monitoring can be realized automatically fly, cyclogyro is equipped with spraying mechanism and stocking mechanism, spray medicine or fertilising can be carried out for farmland.
The above is specific constructive form of the present utility model; the utility model is not restricted to the described embodiments; the art personnel, replace all in protection domain of the present utility model based on the equivalent variations of concrete structure on the utility model and parts.
Claims (10)
1. a rotor driver, comprise the rotor wings frame (2) be connected in aircraft frame (1), described rotor wings frame (2) is rotatably connected to the rotor sleeve (3) that can be connected with engine installation power, it is characterized in that: symmetrically arranged two rotor connecting arms (4) are equipped with on described rotor sleeve (3) top, the upper correspondence of two rotor connecting arms (4) is connected with the rotor fin (5) that can rotate around its axial direction, described rotor wings frame (2) is connected with the blade angle setting device ordering about rotor fin (5) and rotate.
2. rotor driver according to claim 1, it is characterized in that: described blade angle setting device comprises the driving connecting lever (6) be connected on rotor wings frame (2), rotor wings frame (2) is connected with the blade angle actuating unit ordering about and drive connecting lever (6) to swing, described rotor sleeve (3) is connected with can slide up and down and with the rotor shaft sliding sleeve (7) of rotor sleeve (3) normal-running fit, a support arm of connecting lever (6) is driven to be connected with blade angle actuating unit power, another support arm and rotor shaft sliding sleeve (7) hinged, rotor shaft sliding sleeve (7) is hinged with interlock connecting rod (8) by spherical hinge, described rotor fin (5) is connected with and drives pivoted housing (9), drive blade angle adjustment cross bar (10) pivoted housing (9) being connected with and stretching out, blade angle adjustment cross bar (10) is hinged by spherical hinge with interlock connecting rod (8).
3. rotor driver according to claim 2, it is characterized in that: described rotor wings frame (2) is connected with rotor head main shaft (11), described rotor sleeve (3) is rotatably connected on rotor head main shaft, described rotor shaft sliding sleeve (7) is slidably connected on rotor head main shaft (11), the top of described rotor shaft sliding sleeve (7) is rotatably connected to the driven wheel (12) be connected with engine installation power, and the support arm that described rotor sleeve (3) is stretched under passing through is connected with driven wheel (12) power.
4. rotor driver according to claim 3, it is characterized in that: the top of described rotor sleeve (3) arranges spacing cover for seat (13), described driven wheel (12) is equipped with on two and stretches support arm (14), the transmission arm (15) being arranged in spacing cover for seat (13) is equipped with at the top of stretching support arm (14) on two, described interlock connecting rod (8) by spherical hinge and transmission arm (15) hinged.
5. rotor driver according to claim 2, it is characterized in that: described rotor wings frame (2) is equipped with fixing hinge (30), described driving connecting lever (6) is provided with strip hole (34), drives connecting lever (6) to be installed in strip hole by fixed pin shaft and is connected on rotor wings frame (2).
6. rotor driver according to claim 2, it is characterized in that: described blade angle actuating unit is for being connected to the drive motor (31) on rotor wings frame (2), the power take-off shaft of drive motor (31) is equipped with crank (32), between the support arm of described driving connecting lever (6) and crank, is connected with connecting rod (33).
7. the rotor driver according to any one of claim 1-4, it is characterized in that: described rotor wings frame (2) comprises the fixed mount (21) be connected in aircraft frame (1), described fixed mount (21) is connected with and can swings and can the tressel (22) of swing, described rotor sleeve is rotatably connected on tressel (22).
8. rotor driver according to claim 7, it is characterized in that: the hinge by longitudinally arranging on described fixed mount (21) is hinged with linkage rack (23), described tressel (22) is contained on linkage rack (23) by the hinge hinge of horizontally set, described fixed mount (21) is hinged with laterally spaced two power push-rods (16) by spherical hinge, described tressel (22) is equipped with the balance shaft (17) of horizontally set, the upper end of described two power push-rods (16) is hinged with balance shaft (17) respectively.
9. the rotor driver according to claim 3 or 4, it is characterized in that: described engine installation comprises the power-driven machine (25) be connected in aircraft frame (1), aircraft frame (1) is rotatably connected to the axle drive shaft of prewhirling (26) be connected with power-driven machine (25) power by power-transfer clutch, on the spiro rod section of prewhirling on axle drive shaft (26), power is connected with the driven wheel of prewhirling (27) that can engage with driven wheel (12), described axle drive shaft of prewhirling (26) is rotationally connected the top stop (28) of restricted driven wheel rise height of prewhirling, top stop (28) is equipped with and stretches out downwards and the jam-packed spring (29) be positioned on described spiro rod section.
10. a cyclogyro, comprise aircraft frame (1), aircraft frame (1) is connected with the screw propeller (18) driven by engine installation, it is characterized in that: (1) is connected with the rotor driver described in any one of claim 1-9 to described aircraft frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520349853.6U CN204726667U (en) | 2015-05-27 | 2015-05-27 | A kind of rotor driver and install the cyclogyro of this rotor driver |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520349853.6U CN204726667U (en) | 2015-05-27 | 2015-05-27 | A kind of rotor driver and install the cyclogyro of this rotor driver |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204726667U true CN204726667U (en) | 2015-10-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520349853.6U Withdrawn - After Issue CN204726667U (en) | 2015-05-27 | 2015-05-27 | A kind of rotor driver and install the cyclogyro of this rotor driver |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204726667U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104802987A (en) * | 2015-05-27 | 2015-07-29 | 刘志军 | Rotor device and rotor machine with same |
| CN107344617A (en) * | 2017-08-22 | 2017-11-14 | 盐城市翔盛碳纤维科技有限公司 | The method for improving of rotor head, gyroplane and gyroplane |
-
2015
- 2015-05-27 CN CN201520349853.6U patent/CN204726667U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104802987A (en) * | 2015-05-27 | 2015-07-29 | 刘志军 | Rotor device and rotor machine with same |
| CN107344617A (en) * | 2017-08-22 | 2017-11-14 | 盐城市翔盛碳纤维科技有限公司 | The method for improving of rotor head, gyroplane and gyroplane |
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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 |
Granted publication date: 20151028 Effective date of abandoning: 20170329 |
|
| AV01 | Patent right actively abandoned |