CN208576722U - A kind of component that verts for more rotor flying vehicles - Google Patents
A kind of component that verts for more rotor flying vehicles Download PDFInfo
- Publication number
- CN208576722U CN208576722U CN201821018315.9U CN201821018315U CN208576722U CN 208576722 U CN208576722 U CN 208576722U CN 201821018315 U CN201821018315 U CN 201821018315U CN 208576722 U CN208576722 U CN 208576722U
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- verts
- component
- flying vehicles
- connecting shaft
- rotor flying
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Abstract
The utility model discloses a kind of components that verts for more rotor flying vehicles, including actuator, retarder and connection component；The connection component is installed on the flight vehicle frame, and wherein one end is connected with the horn fastening of verting of flight vehicle；The retarder is installed in the rack, and both ends are connected directly with actuator and connection component respectively；The actuator is installed in the rack, for driving connection component rotation after retarder slows down to drive horn rotation of verting.The component that verts for more rotor flying vehicles of the utility model has many advantages, such as that structure is simple, control is accurate and rotation is flexible, reliable.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to a kind of group of verting for more rotor flying vehicles
Part.
Background technique
As the improvement of people's living standards, for recreation and amusement, producing the small aircraft of purposes increasingly by people
Attention.Currently, small aircraft is used to carry 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.
Existing aircraft is divided into Fixed Wing AirVehicle and two kinds of 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 biggish ground run distance.
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 is just able to achieve, larger so as to cause energy consumption and route speed is lower.In addition rotor craft is big
It is mostly all to realize that attitude of flight vehicle changes by change of flight device engine output, or change blade screw pitch；And it is
Make aircraft smooth flight, when adjusting each flight attitude, needs to accurately calculate revolving speed and the change of engine
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 precision 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 is practical new
Type provides the component that verts that a kind of simple structure, high reliablity and control are accurately used for more rotor flying vehicles.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
A kind of component that verts for more rotor flying vehicles, including actuator, retarder and connection component；
The connection component is installed on the flight vehicle frame, and wherein one end and the horn that verts of flight vehicle are tight
Solid phase connects；
The retarder is installed in the rack, and both ends are connected directly with actuator and connection component respectively；
The actuator is installed in the rack, for driving connection component rotation to drive after retarder slows down
The horn that verts rotation.
As a further improvement of the above technical scheme:
The connection component includes
One group or more of bearing assembly is fixedly installed in the rack；
Connecting shaft is rotatablely installed in the bearing assembly, and both ends are connected with the retarder and the horn that verts respectively.
The bearing assembly includes
Bearing block is fixedly installed in the rack；
Bearing is sheathed in the connecting shaft and is installed in the bearing block.
The connecting shaft is multi-diameter shaft, and the positioning shaft shoulder on multi-diameter shaft is for positioning bearing.
The one or both sides of the bearing block are provided with annular slot, are provided with circlip in the annular slot, for pair
Bearing carries out axial limiting.
The quantity of the bearing assembly is two groups, is respectively arranged in the both ends of the connecting shaft.
The threaded one end of the connecting shaft is connected with locking nut, the side of the locking nut and the corresponding bearing block
Side offset；The other end of the connecting shaft, which is provided with, fastens the interconnecting piece being connected, the interconnecting piece and company with the horn that verts
Step surface is formed between spindle, is offseted with the side of another bearing block.
The interconnecting piece is cylindrical and is integrally formed with connecting shaft, is provided with loss of weight on the circumferencial direction of the interconnecting piece
Hole.
One end of the connecting shaft is connected by shaft coupling with the retarder.
The actuator is steering engine or servo motor or stepper motor.
Compared with the prior art, the advantages of the utility model are:
The component that verts for more rotor flying vehicles of the utility model, by by the knot of actuator and reducer group
Structure directly drives horn rotation of verting, and not only has the advantages of simple structure and easy realization, and since torque transmission link is few, reliability
Height, and the control of tilt angle is also more accurate.Connecting component structure is simple, rotates flexibility and reliability；Tilt angle is carried out
Real time monitoring, realizes being precisely controlled for tilt angle.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model flight vehicle.
Fig. 2 is the structural schematic diagram of component of verting in the utility model.
Fig. 3 is the structural schematic diagram of connection component in the utility model.
Fig. 4 is the decomposition texture schematic diagram of connection component in the utility model.
Figure label indicates: 1, rack；2, fixed horn；3, vert horn；4, Power Component；5, rotor；6, it verts group
Part；61, actuator；62, retarder；63, connection component；631, connecting shaft；6311, shaft coupling；6312, interconnecting piece；632, axis
Bearing assembly；6321, bearing block；6322, bearing；6323, circlip；6324, locking nut；64, angle detection piece.
Specific embodiment
The utility model is further described below in conjunction with Figure of description and specific embodiment.
As shown in Figure 1, flight vehicle can be manned motor, hovercar or unmanned plane, tool in the present embodiment
Body structure includes rack 1, and the front or dead astern of rack 1 are provided with outwardly extending fixed horn 2, the two sides pair of rack 1
Claim and rotate to be provided with the outwardly extending horn 3 that verts, the end of fixed horn 2 and the horn 3 that respectively verts is fixedly installed with dynamic
Power component 4(such as gasoline engine), rotor 5 is installed, gasoline engine is for driving the rotation of rotor 5 to produce on gasoline engine
Raw lift.The component 6 that verts of the present embodiment is then installed on rack 1 between the horn 3 that respectively verts, and verts 3 turns of horn for driving
It is dynamic to be tilted with the direction (rotor face) for adjusting rotor 5 on the horn 3 that verts along the front or behind of rack 1, cooperate corresponding control
Strategy realizes the adjustment to flight attitudes such as the landing of flight vehicle, acceleration and deceleration, steering, translation and hoverings.Institute as shown in Figure 1 to Figure 4
Show, the component 6 that verts for more rotor flying vehicles of the present embodiment, specific structure includes actuator 61, retarder 62 and connects
Connected components 63；Wherein connection component 63 are installed in the rack 1 of flight vehicle, wherein the horn 3 that verts of one end and flight vehicle
Fastening is connected；Retarder 62 is installed in rack 1, and both ends pass through shaft coupling 6311 and actuator 61 and connection component 63 respectively
The other end be connected directly；Actuator 61 is installed in rack 1, for exporting rotate driving power, through 62 deceleration rear-guard of retarder
Dynamic connection component 63 rotates, to drive the rotation of horn 3 of verting, realizes that the direction of rotor 5 is adjusted；Wherein actuator 61 is servo
Motor, stepper motor or steering engine etc..The component 6 that verts for more rotor flying vehicles of the utility model, by by actuator
61 modes combined with retarder 62 directly drive the rotation of horn 3 of verting, and not only have the advantages of simple structure and easy realization, and due to
Torque transmission link is few, high reliablity, and the control of tilt angle is also more accurate.
As shown in Figure 3 and Figure 4, in the present embodiment, connection component 63 includes one group or more and is fixedly installed in rack 1
Bearing assembly 632, and rotational installation is in the company that in bearing assembly 632, both ends are connected with retarder 62 and the horn 3 that verts respectively
Spindle 631.Wherein the quantity of bearing assembly 632 preferably uses two groups, is separately mounted to the both ends of connecting shaft 631.Specifically, axis
Bearing assembly 632 includes the bearing block 6321 being fixedly installed in rack 1 and is sheathed in connecting shaft 631 and is installed on bearing block
Bearing 6322 in 6321, middle (center) bearing 6322 can be ball bearing or tapered roller bearing or deep-groove roller bearing etc..Such as
Shown in Fig. 4, in the present embodiment, connecting shaft 631 is multi-diameter shaft, and there is positioning shaft shoulder at both ends, and wherein positioning shaft shoulder is then used to prevent
Only bearing 6322 moves axially (left side in such as Fig. 4 is mobile) to side；Further, in the one or both sides of bearing block 6321
It is provided with annular slot, circlip 6323 is provided in annular slot, carries out axial limit for the one or both sides to bearing 6322
Position, to further limit the axial displacement of bearing 6322.
As shown in Figure 3 and Figure 4, in the present embodiment, one end that connecting shaft 631 is connect with retarder 62 is provided with external screw thread,
It is threadedly coupled with a locking nut 6324, wherein the side of locking nut 6324 and the side of corresponding shaft bearing seat 6321 offset, by
It in bearing block 6321 is fastened in rack 1, is offseted by locking nut 6324 and bearing block 6321, so as to avoid connecting
Axis 631 moves axially and skids off (as shown in figure 4, preventing connecting shaft 631 from deviating from from left side) from rack 1.In addition, in connecting shaft
631 other end, which is provided with, fastens the interconnecting piece 6312 being connected with the horn 3 that verts, and the outer diameter of interconnecting piece 6312 is greater than connecting shaft
631 outer diameter, to form step surface in its transition part, the side of bearing block 6321 then offsets with step surface, prevents connecting shaft
631 axial displacements；I.e. two bearings seat 6321 offsets with locking nut 6324 and step surface respectively, so as to prevent connecting shaft
Bidirectional displacement on 631 axial direction.Therefore, this connection component 63 is not only simple in structure and rotates flexibly, reliably.
In the present embodiment, interconnecting piece 6312 is cylindrical and is integrally formed with connecting shaft 631, the circumference side of interconnecting piece 6312
Lightening hole has been set up, has mitigated weight on the basis of guaranteeing structural strength.It is provided with multiple screw holes on interconnecting piece 6312, inclines
Make a connection arm 3 one end it is also cylindrical and be set in outside interconnecting piece 6312, will be verted horn 3 and interconnecting piece 6312 by bolt
Fastening.
As shown in Fig. 2, angled detection piece 64(such as rotary encoder etc. is arranged in the other end of the output shaft of retarder 62),
For to the horn 3 that verts real-time angular and tilt angle rate of change be monitored and feed back to corresponding control unit,
Guarantee the accurate reliability of tilt angle control.Specifically, rotary encoder is fixed on retarder 62 by flange, Neng Goubao
The good anti-seismic performance of rotary encoder is demonstrate,proved, the reliability of angle detection is improved.
Above are merely preferred embodiments of the utility model, the protection scope 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 protection scope 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 protection scope of the utility model.
Claims (10)
1. a kind of component that verts for more rotor flying vehicles, which is characterized in that including actuator (61), retarder (62) and
Connection component (63)；
The connection component (63) is installed on the flight vehicle frame (1), wherein the horn that verts of one end and flight vehicle
(3) fastening is connected；
The retarder (62), is installed on the rack (1), and both ends are direct with actuator (61) and connection component (63) respectively
It is connected；
The actuator (61), is installed on the rack (1), for driving connection component (63) after retarder (62) slow down
Rotation is to drive the horn that verts (3) to rotate.
2. the component that verts according to claim 1 for more rotor flying vehicles, which is characterized in that the connection component
(63) include
One group or more of bearing assembly (632), is fixedly installed on the rack (1)；
Connecting shaft (631), rotational installation in the bearing assembly (632), both ends respectively with the retarder (62) and vert
Horn (3) is connected.
3. the component that verts according to claim 2 for more rotor flying vehicles, which is characterized in that the bearing assembly
(632) include
Bearing block (6321) is fixedly installed on the rack (1)；
Bearing (6322) is sheathed on the connecting shaft (631) and is installed in the bearing block (6321).
4. the component that verts according to claim 3 for more rotor flying vehicles, which is characterized in that the connecting shaft
It (631) is multi-diameter shaft, the positioning shaft shoulder on multi-diameter shaft is for positioning bearing (6322).
5. the component that verts according to claim 4 for more rotor flying vehicles, which is characterized in that the bearing block
(6321) one or both sides are provided with annular slot, and circlip (6323) are provided in the annular slot, for bearing
(6322) axial limiting is carried out.
6. the component that verts according to claim 4 or 5 for more rotor flying vehicles, which is characterized in that the bearing
The quantity of component (632) is two groups, is respectively arranged in the both ends of the connecting shaft (631).
7. the component that verts according to claim 6 for more rotor flying vehicles, which is characterized in that the connecting shaft
(631) threaded one end is connected with locking nut (6324), the side of the locking nut (6324) and the corresponding bearing block
(6321) side offsets；The other end of the connecting shaft (631), which is provided with, fastens the interconnecting piece being connected with the horn that verts (3)
(6312), step surface is formed between the interconnecting piece (6312) and connecting shaft (631), the side phase with another bearing block (6321)
It supports.
8. the component that verts according to claim 7 for more rotor flying vehicles, which is characterized in that the interconnecting piece
(6312) cylindrical and be integrally formed with connecting shaft (631), loss of weight is provided on the circumferencial direction of the interconnecting piece (6312)
Hole.
9. the component that verts as claimed in any of claims 2 to 5 for more rotor flying vehicles, feature exist
In one end of the connecting shaft (631) is connected by shaft coupling (6311) with the retarder (62).
10. the component that verts as claimed in any of claims 1 to 5 for more rotor flying vehicles, feature exist
In the actuator (61) is steering engine or servo motor or stepper motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018315.9U CN208576722U (en) | 2018-06-29 | 2018-06-29 | A kind of component that verts for more rotor flying vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018315.9U CN208576722U (en) | 2018-06-29 | 2018-06-29 | A kind of component that verts for more rotor flying vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208576722U true CN208576722U (en) | 2019-03-05 |
Family
ID=65508117
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821018315.9U Active CN208576722U (en) | 2018-06-29 | 2018-06-29 | A kind of component that verts for more rotor flying vehicles |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208576722U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639321A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of component that verts for more rotor flying vehicles |
| CN112977804A (en) * | 2021-03-26 | 2021-06-18 | 陕西飞机工业有限责任公司 | Control surface lock |
-
2018
- 2018-06-29 CN CN201821018315.9U patent/CN208576722U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639321A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of component that verts for more rotor flying vehicles |
| CN112977804A (en) * | 2021-03-26 | 2021-06-18 | 陕西飞机工业有限责任公司 | Control surface lock |
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