CN207972798U - The component that verts for manned more rotor flying vehicles - Google Patents
The component that verts for manned more rotor flying vehicles Download PDFInfo
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- CN207972798U CN207972798U CN201820350876.2U CN201820350876U CN207972798U CN 207972798 U CN207972798 U CN 207972798U CN 201820350876 U CN201820350876 U CN 201820350876U CN 207972798 U CN207972798 U CN 207972798U
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- manned
- component
- verts
- flying vehicles
- rotor flying
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Abstract
The utility model discloses a kind of components that verts for manned more rotor flying vehicles, including large drive wheel, small transmission wheel and force piece, the force piece is installed in the rack of manned more rotor flying vehicles, the small transmission wheel is installed on the output shaft of the force piece, the large drive wheel is fixedly installed in the end of the horn that verts of manned more rotor flying vehicles, is driven by transmission belt between the small transmission wheel and large drive wheel.The component that verts for manned more rotor flying vehicles of the utility model has many advantages, such as that simple in structure, the kind of drive is simple and reliable, is convenient for accurately controlling tilt angle.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to a kind of verting for manned more rotor flying vehicles
Component.
Background technology
Currently, small aircraft is used for carrying various measuring instruments (such as camera) mostly, aerological sounding or high-altitude are carried out
On object is thrown, it can apply in various fields such as agricultural, detection, meteorological, hazard forecasting and rescues.But can be manned it is small
Type aircraft is actually rare, there is larger research space.
Existing aircraft is divided into two kinds of Fixed Wing AirVehicle and rotor craft.Fixed Wing AirVehicle mainly passes through acquisition
Larger initial velocity forms lift in aerofoil and realizes flight, but can not hover, and stability is poor when low speed, be easy because stall and
Air crash, and need larger ground run distance.In addition Fixed Wing AirVehicle is generally turned to using two methods, a kind of pure
It is turned to by vertical tail, one is wing aileron cooperation tailplanes to turn to.Wherein purely the case where ratio is turned to by vertical tail
It is more rare because vertical tail in addition to have control aircraft turn function other than, there are one most important function be just to maintain it is winged
The stabilization of machine, it is impossible to significantly be turned using vertical tail.And wing aileron cooperation tailplane turns to, and is to pass through pair
The lifting of the wing, fuselage is tilted, and is turned round by the effect of centrifugal force, and this mode needs aircraft itself to have inclined effect,
It applies on personal aircraft, the security risk of driver can be increased, be not suitable for personal aircraft and use.
Another is rotor craft, and wherein rotor is primarily used to form lift, and flying speed needs by adjusting appearance
State forms lateral resultant force and could realize, larger and headway is relatively low so as to cause energy expenditure.In addition rotor craft is big
More is all to realize that attitude of flight vehicle changes by change of flight device engine output, or change blade screw pitch；And it is
So that aircraft smooth flight when adjusting each flight attitude needs the rotating speed for accurately calculating engine and change
The screw pitch of blade, process is cumbersome, is not suitable for flight environment of vehicle complicated and changeable, and still will appear inclination in flight course,
The same security risk for increasing driver.There is less producer to design dependency structure at present to be adjusted with the direction to rotor,
But structure is more complex, and more difficult to control and control accuracy is not high.
Utility model content
The technical problems to be solved in the utility model is that：For technical problem of the existing technology, this practicality is new
Type provides a kind of simple in structure, accurate component that verts for being reliably used for manned more rotor flying vehicles of control.
In order to solve the above technical problems, the utility model proposes technical solution be：
A kind of component that verts for manned more rotor flying vehicles, including large drive wheel, small transmission wheel and force piece, institute
It states force piece to be installed in the rack of manned more rotor flying vehicles, the small transmission wheel is installed on the output shaft of the force piece
On, the large drive wheel is fixedly installed in the end of the horn that verts of manned more rotor flying vehicles, the small transmission wheel with it is big
It is driven by transmission belt between driving wheel.
As a further improvement of the above technical scheme：
The force piece includes stepper motor and retarder, and the stepper motor is fastened in the rack, the stepping
The output shaft of motor is connected with the input shaft of the retarder, and the small transmission wheel is mounted on the output shaft of the retarder.
The retarder is slidably mounted on one and is fixed in the mounting base of rack, and the retarder slides simultaneously in mounting base
It is fastened by fastener to be tensioned transmission belt.
Two strip holes are provided in the mounting base, arranged direction and the transmission belt of the strip hole are generally aligned in the same plane
It is interior；The fastener includes the bolt being arranged on the pedestal of retarder, and the bolt is carried out after passing through strip hole by nut
Fastening.
The mounting base is disposed horizontally or vertically in the rack.
Angled detection piece is arranged in the side of the large drive wheel, is monitored for the tilt angle to large drive wheel.
The angle detection piece is connect with the large drive wheel by a connection component and is rotated synchronously with large drive wheel.
The connection component includes axis pin and taper sheath, and the axis pin is installed on inside the large drive wheel and across described
The axle center of large drive wheel, one end of the taper sheath are provided with mounting hole to be connect with the shaft swelling of angle detection piece, described
The other side of taper sheath is then provided with card slot, and the axis pin is arranged in the card slot.
The angle detection piece is fastened in the rack.
Angled detection piece is arranged in the side of the reducer output shaft, is carried out for the output angle to stepper motor real
When monitor.
The angle detection piece is fastened on by flange on the retarder.
The angle detection piece is rotary encoder.
The large drive wheel and small transmission wheel are belt wheel, and the transmission belt is driving belt.
The large drive wheel and small transmission wheel are gear, and the transmission belt is chain.
Compared with prior art, the utility model has the advantage of：
The component that verts for manned more rotor flying vehicles of the utility model coordinates driving wheel transmission by force piece
Mode, realize adjusting to the horn tilt angle that verts, it is not only simple in structure, be easily achieved, and the kind of drive is simple
Reliably, convenient for accurately controlling tilt angle.
Description of the drawings
Fig. 1 is the dimensional structure diagram of manned more rotor flying vehicles in the utility model.
Fig. 2 is the structural schematic diagram of the component that verts in the utility model.
Fig. 3 is the mounting structure schematic diagram of angle detection piece in the utility model embodiment one.
Fig. 4 is the mounting structure schematic diagram of angle detection piece in the utility model embodiment two.
Fig. 5 is the structural schematic diagram of angle detection piece in the utility model embodiment two.
Figure label indicates：1, rack；11, bearing block；2, fixed horn；3, vert horn；4, Power Component；5, it revolves
The wing；6, vert component；61, mounting base；611, strip hole；612, fastener；62, force piece；621, stepper motor；622, slow down
Device；63, small transmission wheel；64, large drive wheel；65, transmission belt；66, angle detection piece；67, flange；68, connection component；681, it sells
Axis；682, taper sheath；69, mounting bracket；7, undercarriage.
Specific implementation mode
The utility model is further described below in conjunction with Figure of description and specific embodiment.
Embodiment one：
As shown in Figure 1 to Figure 3, manned more rotor flying vehicles in the present embodiment can be rotorcycle or flight
Automobile, concrete structure include keel open frame 1, and the bottom of rack 1 is provided with undercarriage 7, seat is provided in rack 1 (in figure
It is not shown), the front or dead astern of rack 1 are provided with outwardly extending fixed horn 2, and the both sides of rack 1 are symmetrical and rotate
It is provided with the outwardly extending horn 3 that verts, bearing block 11 is provided in rack 1, the one end for the horn 3 that verts then is rotated by bearing
It is arranged in bearing block 11, the end of fixed horn 2 and the horn 3 that respectively verts is installed with 4 (such as gasoline internal combustion of Power Component
Machine), rotor 5 is installed, gasoline engine is for driving rotor 5 to be rotated to produce lift on gasoline engine；Specifically, this reality
The component that verts for applying example is then installed on rack 1 between the horn 3 that respectively verts, for driving the rotation of horn 3 of verting to vert to adjust
The direction (rotor face) of rotor 5 is tilted along the front or behind of rack 1 on horn 3, coordinates corresponding control strategy, is realized to flying
The adjustment of the flight attitudes such as landing, acceleration and deceleration, steering, translation and the hovering of driving, in the process, rack 1 is in always
Maintenance level state ensures the traffic safety and riding comfort of driver or passenger；Specifically, as shown in Figures 2 and 3, the component 6 that verts wraps
Large drive wheel 64, small transmission wheel 63 and force piece 62 are included, force piece 62 is installed in rack 1, and small transmission wheel 63 is installed on power
On the output shaft of part 62, large drive wheel 64 is fixedly installed in the end for the horn 3 that verts, between small transmission wheel 63 and large drive wheel 64
It is driven by transmission belt 65.Wherein stepper motor 621 is controlled by control unit, and stepper motor 621 rotates centainly
Angle slows down through retarder 622 and obtains high-torque, drives small transmission wheel 63 to rotate, then by transmission belt 65 in a manner of V belt translation
Large drive wheel 64 is driven to rotate, horn 3 rotates predetermined angular to make to vert, and realizes the change of 5 direction of rotor.The utility model
The component that verts for manned more rotor flying vehicles, driving wheel transmission by way of, realize verting to the horn 3 that verts
The adjusting of angle is not only simple in structure, is easily achieved, and the kind of drive is simple and reliable, accurate convenient for being carried out to tilt angle
Control.
In the present embodiment, large drive wheel 64 and small transmission wheel 63 are belt wheel or gear, and wherein transmission belt 65 corresponds to pass
Dynamic belt or chain, simple in structure and reliable transmission；Certainly, in other embodiments, gear wheel and small tooth can also be used
It takes turns intermeshing mode and realizes transmission.
As shown in figs. 2 to 4, in the present embodiment, force piece 62 includes stepper motor 621 (or servo motor) and retarder
622, wherein retarder 622 is fastened in rack 1, and the output shaft of stepper motor 621 is connected with the input shaft of retarder 622, small
Driving wheel 63 is mounted on the output shaft of retarder 622.Wherein stepper motor 621 is controlled by control unit, stepping electricity
Machine 621 turns an angle, through retarder 622 slow down obtain high-torque, drive small transmission wheel 63 rotate, then by transmission belt 65 with
The mode of V belt translation drives large drive wheel 64 to rotate, and to make to vert, horn 3 rotates predetermined angular, realizes changing for 5 direction of rotor
Become.
As shown in figure 4, in the present embodiment, the floor installation of retarder 622 in one be fixed on rack 1 be horizontally mounted seat 61
On, strip hole 611 is provided in mounting base 61, arranged direction and the transmission belt 65 of strip hole 611 are generally aligned in the same plane interior, deceleration
Fastener 612 (such as bolt and nut) is provided on the pedestal of device 622, bolt is slidedly arranged in strip hole 611, by stepper motor 621
Stepper motor 621 is fastened on peace after tensile force of the interior sliding of strip hole 611 to adjust driving belt, then by bolt and nut
It fills on seat 61.Certainly, in other embodiments, can also be realized to transmission by the way of the whole oscilaltion of retarder 622
Retarder 622 is such as slidably installed in vertically arranged mounting base 61 by the adjusting of belt tension, tight again by bolt and nut etc.
Gu mode fastens it.
As shown in figure 3, angled 66 (such as rotary encoder of detection piece is arranged in the other end of the output shaft of retarder 622
Deng), for the horn 3 that verts real-time angular and tilt angle rate of change is monitored and to feed back to corresponding control single
Member ensures the accurate reliability of tilt angle control.Specifically, rotary encoder is fixed on by flange 67 on retarder 622,
It can ensure the good anti-seismic performance of rotary encoder, improve the reliability of angle detection.
Embodiment two：
The present embodiment is differed only in embodiment one：The installation site of angle detection piece 66 is different, such as Fig. 4 and Fig. 5
Shown, angle detection piece 66 (such as rotary encoder) is installed on one end of large drive wheel 64, and rotary encoder passes through a connection group
Part 68 connect with large drive wheel 64 and is rotated synchronously with large drive wheel 64.Wherein connection component 68 includes axis pin 681 and taper sheath
682, axis pin 681 is installed on 64 inside (such as being penetrated from the outside of large drive wheel 64) of large drive wheel and the axis across large drive wheel 64
The heart, one end of taper sheath 682 are provided with mounting hole to be connect with the shaft swelling of angle detection piece 66, taper sheath 682 it is another
Side is then provided with card slot, and axis pin 681 is arranged in card slot.When large drive wheel 64 rotates, axis pin 681 rotates synchronously, band mantle
682 rotation of shape set, to realize the synchronous rotation of rotary encoder.In addition, mounting bracket 69 is fastened in rack 1, then will
Rotary encoder is fastened in mounting bracket 69, to improve its anti-seismic performance, ensures the reliability of its work.It is other not described interior
Appearance is identical as embodiment one, and details are not described herein.
Above are merely preferred embodiments of the utility model, the scope of protection of the utility model is not limited merely to above-mentioned
Embodiment, technical solution belonging to the idea of the present invention belong to the scope of protection of the utility model.It should be pointed out that pair
For those skilled in the art, several improvements and modifications without departing from the principle of the utility model,
It should be regarded as the scope of protection of the utility model.
Claims (14)
1. a kind of component that verts for manned more rotor flying vehicles, which is characterized in that including large drive wheel (64), small transmission
Wheel (63) and force piece (62), the force piece (62) are installed in the rack (1) of manned more rotor flying vehicles, the brief biography
Driving wheel (63) is installed on the output shaft of the force piece (62), and the large drive wheel (64) is fixedly installed in manned more rotors and flies
Driving the horn that verts (3) end, between the small transmission wheel (63) and large drive wheel (64) by transmission belt (65) into
Row transmission.
2. the component that verts according to claim 1 for manned more rotor flying vehicles, which is characterized in that the power
Part (62) includes stepper motor (621) and retarder (622), and the stepper motor (621) is fastened in the rack (1), institute
The output shaft for stating stepper motor (621) is connected with the input shaft of the retarder (622), and the small transmission wheel (63) is mounted on institute
On the output shaft for stating retarder (622).
3. the component that verts according to claim 2 for manned more rotor flying vehicles, which is characterized in that the deceleration
Device (622) is slidably mounted on one and is fixed in the mounting base (61) of rack (1), and the retarder (622) is in mounting base (61)
It slides and is fastened by fastener (612) to be tensioned transmission belt (65).
4. the component that verts according to claim 3 for manned more rotor flying vehicles, which is characterized in that the installation
Two strip holes (611) are provided on seat (61), arranged direction and the transmission belt (65) of the strip hole (611) are located at same put down
In face；The fastener (612) includes the bolt being arranged on the pedestal of retarder (622), and the bolt passes through strip hole
(611) it is fastened by nut after.
5. the component that verts according to claim 4 for manned more rotor flying vehicles, which is characterized in that the installation
Seat (61) is disposed horizontally or vertically in the rack (1).
6. the component that verts as claimed in any of claims 2 to 5 for manned more rotor flying vehicles, feature
It is, angled detection piece (66) is arranged in the side of the large drive wheel (64), for the tilt angle to large drive wheel (64)
It is monitored.
7. the component that verts according to claim 6 for manned more rotor flying vehicles, which is characterized in that the angle
Detection piece (66) is connect with the large drive wheel (64) by a connection component (68) and is rotated synchronously with large drive wheel (64).
8. the component that verts according to claim 7 for manned more rotor flying vehicles, which is characterized in that the connection
Component (68) includes axis pin (681) and taper sheath (682), the axis pin (681) be installed on the large drive wheel (64) it is internal and
Axle center across the large drive wheel (64), one end of the taper sheath (682) be provided with mounting hole with angle detection piece
(66) shaft swelling connection, the other side of the taper sheath (682) are then provided with card slot, and the axis pin (681) is arranged in institute
It states in card slot.
9. the component that verts according to claim 8 for manned more rotor flying vehicles, which is characterized in that the angle
Detection piece (66) is fastened in the rack (1).
10. the component that verts as claimed in any of claims 2 to 5 for manned more rotor flying vehicles, special
Sign is that angled detection piece (66) is arranged in the side of retarder (622) output shaft, for stepper motor (621)
Output angle is monitored in real time.
11. the component that verts according to claim 10 for manned more rotor flying vehicles, which is characterized in that the angle
Degree detection piece (66) is fastened on by flange (67) on the retarder (622).
12. the component that verts according to claim 6 for manned more rotor flying vehicles, which is characterized in that the angle
It is rotary encoder to spend detection piece (66).
13. the component that verts as claimed in any of claims 1 to 5 for manned more rotor flying vehicles, special
Sign is that the large drive wheel (64) and small transmission wheel (63) are belt wheel, and the transmission belt (65) is driving belt.
14. the component that verts as claimed in any of claims 1 to 5 for manned more rotor flying vehicles, special
Sign is that the large drive wheel (64) and small transmission wheel (63) are gear, and the transmission belt (65) is chain.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820350876.2U CN207972798U (en) | 2018-03-14 | 2018-03-14 | The component that verts for manned more rotor flying vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820350876.2U CN207972798U (en) | 2018-03-14 | 2018-03-14 | The component that verts for manned more rotor flying vehicles |
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| Publication Number | Publication Date |
|---|---|
| CN207972798U true CN207972798U (en) | 2018-10-16 |
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ID=63765599
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820350876.2U Active CN207972798U (en) | 2018-03-14 | 2018-03-14 | The component that verts for manned more rotor flying vehicles |
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| Country | Link |
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| CN (1) | CN207972798U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108372930A (en) * | 2018-03-14 | 2018-08-07 | 长沙市云智航科技有限公司 | The component that verts for manned more rotor flying vehicles |
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2018
- 2018-03-14 CN CN201820350876.2U patent/CN207972798U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108372930A (en) * | 2018-03-14 | 2018-08-07 | 长沙市云智航科技有限公司 | The component that verts for manned more rotor flying vehicles |
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