CN109131872A - A kind of rotor of VTOL Fixed Wing AirVehicle verts mode and mechanism - Google Patents
A kind of rotor of VTOL Fixed Wing AirVehicle verts mode and mechanism Download PDFInfo
- Publication number
- CN109131872A CN109131872A CN201811274661.8A CN201811274661A CN109131872A CN 109131872 A CN109131872 A CN 109131872A CN 201811274661 A CN201811274661 A CN 201811274661A CN 109131872 A CN109131872 A CN 109131872A
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- CN
- China
- Prior art keywords
- rotor
- revolute pair
- pivoted arm
- verts
- fixed wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
Abstract
A kind of rotor of VTOL Fixed Wing AirVehicle verts mode and mechanism, belongs to aircraft field, mode of verting are as follows: rotor verts around revolute pair, switches between rotor wing rotation planar horizontal state and vertical state.One tangent line of the tip turning circumference of the fin of the axis and rotor of revolute pair is parallel, and the axis of revolute pair and the tangent line are close.Inclining rotary mechanism includes rotor, engine, pivoted arm, revolute pair, bracket.Rotor connects engine, and engine is mounted on one end of pivoted arm, and the other end of pivoted arm is connected by revolute pair with bracket.Revolute pair is near the airfoil tip of rotor.When the rotating circular disk of rotor is in a horizontal position, the mounting height of revolute pair and the rotating circular disk of rotor are the same as high or slightly below rotor rotating circular disk.Pivoted arm is set to rotate that rotor is driven to vert around revolute pair using hydraulic device or electric device or pneumatic device or wire saws device.Rotor of the present invention, which verts, to be easier to, and wind direction will not be random, and the transition of offline mode is relatively more steady, safe.
Description
Technical field
A kind of rotor of VTOL Fixed Wing AirVehicle verts mode and mechanism, belongs to vehicle technology field, especially relates to
And a kind of rotor verts mode and mechanism.
Background technique
The rotor side of verting of traditional VTOL fixed wing aircraft and traditional tiltrotor (such as: osprey V-22)
Formula is: mostly using the horizontal line for crossing the center of gravity of engine or the point of close engine center of gravity as shaft, making the rotating circular disk of rotor
Switch between horizontal position and vertical position, to realize that aircraft generates upward liter from helicopter flight mode i.e. rotor
Force mode generates the switching of the flight attitude of horizontal pull or thrust mode to fixed-wing offline mode, that is, rotor.The rotation of this sample loading mode
The wing verts relatively difficult, because rotor high-speed rotation has gyroscopic effect, and confusion can occur for the wind direction that verts in this way, be easy to cause
Local wind shear.Traditional mode of verting makes flight attitude become fixed-wing offline mode from helicopter flight mode or from solid
Determine wing offline mode become helicopter flight mode transitional period it is very dangerous, be easy to happen safety accident.
Summary of the invention
The purpose of the invention is to overcome the shortcomings of that traditional rotor verts the above-mentioned technology of mode, a kind of convenience is invented
The rotor of the VTOL Fixed Wing AirVehicle of the safety of manipulation verts mode and mechanism.
A kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle, including rotor, engine, pivoted arm, revolute pair, branch
Frame.Rotor connects engine, and rotor is rotated by engine driving generates pulling force.Engine is mounted on one end of pivoted arm, pivoted arm
The other end is connected by revolute pair with bracket, and the fuselage or wing of bracket and aircraft are connected.Revolute pair is in the fin of rotor
Near tip, a tangent line of the rotation round of the airfoil tip of the axis and rotor of revolute pair is close and the axis of revolute pair with
The tangent line is parallel, and fin will not be touched with revolute pair when rotor rotational, and fin will not be touched with pivoted arm.When the rotational circle of rotor
When disk is in a horizontal position, in vertical direction, the rotating circular disk of revolute pair and rotor is close but is no more than the rotating circular disk of rotor
Height and position, i.e., the rotating circular disk of the mounting height of revolute pair and rotor is the same as high or slightly below rotor rotating circular disk.Using
Hydraulic device or electric device or pneumatic device or wire saws device make pivoted arm rotate that rotor is driven to vert around revolute pair.Turn
The angle of arm rotation is 90 ° or substantially 90 °.
When using hydraulic device, one end of hydraulic cylinder is fixed on pivoted arm, and the other end of hydraulic cylinder is fixed on bracket.It is logical
It crosses hydraulic cylinder push-and-pull pivoted arm rotation and rotor is driven to vert.
When using pneumatic device, one end of cylinder is fixed on pivoted arm, and the other end of cylinder is fixed on bracket.Pass through gas
Cylinder push-and-pull pivoted arm rotates and rotor is driven to vert.
When using electric device, drive pivoted arm rotation with steering engine, the shell of steering engine is fixed on bracket, the swing arm of steering engine with
Pivoted arm is connected.
When using wire saws device, " rope " in wire saws device refers to rope, using wirerope or cordage or other
The rope of material, is similar to brake of motorcycle steel rope system, and the thickness of wirerope is selected according to the size of rotor thrust
It selects, when using wire saws device, is applied to the pulling force on rope using the pulling force of rotor generation and using mechanical or manpower and makes work
The rotor of work verts.
Further, locking device is equipped between revolute pair and pivoted arm, locking device can be required according to flight by pivoted arm
It is locked in any angular position.Locking device is using mechanical or electromagnetic type device.
Preferably, the Plane of rotation of the axis and rotor of revolute pair is in same plane.
Further, engine uses motor, and motor is battery powered.
Further, the rotor is replaced with propeller.
A kind of rotor mode of verting of VTOL Fixed Wing AirVehicle is: rotor verts around revolute pair, and rotor wing rotation is flat
It verts from horizontality to vertical state in face；Or it verts from vertical state to horizontality.The axis of revolute pair and rotor
One tangent line of the tip turning circumference of fin is parallel, and the axis of revolute pair and the tangent line are close, but the axis of revolute pair with
The tip turning circumference of fin is non-intersecting.
Preferably, the tip turning circumference of the fin of the axis and rotor of revolute pair is in same plane.
A kind of rotor of VTOL Fixed Wing AirVehicle of the invention vert mode the advantages of at least: 1, rotor verts ratio
It is easier to；2, wind direction will not be random, does not easily cause wind shear；3, the transition of offline mode is relatively more steady, safe.
Detailed description of the invention
Fig. 1 is a kind of forward situation of the rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle of the present invention its revolute pair
Schematic diagram；Fig. 2 is a kind of situation of the rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle of the present invention its revolute pair rearward
Schematic diagram.
In figure, 1- rotor, 2- engine, 3- pivoted arm, 4- revolute pair, 5- bracket, the instruction of 6- rotor thrust forward direction,
The instruction of 7- rotor thrust upwardly direction；1a indicates that rotor is in a vertical state, and 2a indicates to start when rotor is in a vertical state
The position of machine, 3a indicate the position of pivoted arm when rotor is in a vertical state.
Specific embodiment
According to the installation site of revolute pair, the rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle of the present invention at least this
Two kinds of situations: 1, when in a horizontal state in the Plane of rotation of rotor, revolute pair is in the front of rotor, such as the situation of Fig. 1；2, exist
The Plane of rotation of rotor is when in a horizontal state, and revolute pair is at the rear of rotor, such as the situation of Fig. 2.
Illustrated now in conjunction with attached drawing to the present invention: a kind of rotor of VTOL Fixed Wing AirVehicle verts machine
Structure, including rotor 1, engine 2, pivoted arm 3, revolute pair 4, bracket 5.Rotor 1 connects engine 2, and rotor 1 is driven by engine 2
Rotation generates pulling force.Engine 2 is mounted on one end of pivoted arm 3, and the other end of pivoted arm 3 is connected with bracket 5 by revolute pair 4, is propped up
The fuselage or wing of frame 5 and aircraft are connected.Revolute pair 4 is near the airfoil tip of rotor 1, the axis of revolute pair 4 and rotation
One tangent line of the rotation round of the airfoil tip of the wing 1 is close and the axis of revolute pair 4 is parallel with the tangent line, when rotor 1 rotates
Fin will not be touched with revolute pair 4, and fin will not be touched with pivoted arm 3.When the rotating circular disk of rotor 1 is in a horizontal position,
In vertical direction, the rotating circular disk of revolute pair 4 and rotor 1 is close but is no more than the height and position of the rotating circular disk of rotor 1, that is, turns
The mounting height of dynamic pair 4 and the rotating circular disk of rotor 1 are the same as high or slightly below rotor 1 rotating circular disk.Using hydraulic device or electricity
Dynamic device or pneumatic device or wire saws device make pivoted arm 3 rotate that rotor 1 is driven to vert around revolute pair 4.What pivoted arm 3 rotated
Angle is 90 °.
Further, locking device is equipped between revolute pair 4 and pivoted arm 3, locking device can require turn according to flight
Arm 3 is locked in any angular position.Locking device is using mechanical or electromagnetic type device.
Preferably, the Plane of rotation of the axis Yu rotor 1 of revolute pair 4 is in same plane.
Further, engine 2 uses motor, and motor is battery powered.
Further, the rotor 1 is replaced with propeller.
When using hydraulic device, one end of hydraulic cylinder is fixed on pivoted arm 3, and the other end of hydraulic cylinder is fixed on bracket 5.
Pushing and pulling the rotation of pivoted arm 3 by hydraulic cylinder drives rotor 1 to vert.Hydraulic cylinder is not drawn into figure.
When using pneumatic device, one end of cylinder is fixed on pivoted arm 3, and the other end of cylinder is fixed on bracket 5.Pass through
Cylinder push-and-pull pivoted arm 3 rotates and rotor 1 is driven to vert.Cylinder is not drawn into figure.
When using electric device, pivoted arm 3 is driven to rotate with steering engine, the shell of steering engine is fixed on bracket 5, the swing arm of steering engine
It is connected with pivoted arm 3.Steering engine is not drawn into figure.
When using wire saws device, " rope " in wire saws device refers to rope, using wirerope or cordage or other
The rope of material, is similar to brake of motorcycle steel rope system, and the thickness of wirerope is selected according to the size of 1 pulling force of rotor
It selects, when using wire saws device, is applied to the pulling force on rope using the pulling force of the generation of rotor 1 and using mechanical or manpower and makes work
The rotor of work verts.
When using wire saws device, such as the situation of Fig. 1, rope ties up on pivoted arm 3 or (is not drawn into rope in figure on engine 2
Son), when rotor 1 does not work, rotor 1 is in horizontality；When rotor 1 works, to make the rotating circular disk of rotor 1 continue to locate
In horizontality, is tightened up a rope with mechanical force or manpower and the pulling force of rotor 1 is overcome to be in a horizontal position rotor 1；To transformation
Offline mode makes the rotating circular disk of rotor become vertical state, i.e. 1a state in Fig. 1, as long as slacking off, in the pulling force of rotor
Acting on lower rotor, engine and pivoted arm can rotate counterclockwise that rotor is made to become vertical state around revolute pair 4.At this moment if wanted
Make rotary wing changing return water level state it is necessary to apply pulling force on rope, make pivoted arm around revolute pair 4 rotate clockwise by rotor draw to
Horizontality.
When using wire saws device, such as the situation of Fig. 2, rope ties up on pivoted arm 3 or (is not drawn into rope in figure on engine 2
Son), when rotor 1 works, to keep the rotating circular disk of rotor in a vertical state, is tightened up a rope and overcome with mechanical force or manpower
The pulling force of rotor keeps rotor in a vertical position；To convert offline mode, the rotating circular disk of rotor is set to become horizontality, only
It slacks off, rotor, engine and pivoted arm can rotate clockwise to make rotor around revolute pair 4 under the pulling force effect of rotor
Become horizontality.At this moment if it is desired that rotor becomes vertical state again it is necessary to apply pulling force on rope, make pivoted arm around revolute pair
It rotates counterclockwise and draws rotor to vertical state.
A kind of rotor mode of verting of VTOL Fixed Wing AirVehicle is: rotor 1 verts around revolute pair 4, and rotor 1 rotates
Plane is verted from horizontality to vertical state, or is verted from vertical state to horizontality.The axis and rotor of revolute pair 4
One tangent line of the tip turning circumference of 1 fin is parallel, and the axis of revolute pair 4 and the tangent line are close, but the axis of revolute pair 4
The tip turning circumference of line and fin is non-intersecting.The tip turning circumference of the axis of revolute pair 4 and the fin of rotor 1 is in same
In plane.
A kind of rotor of VTOL Fixed Wing AirVehicle of the invention vert mode the advantages of at least: 1, rotor verts ratio
It is easier to；2, wind direction will not be random, does not easily cause wind shear；3, the transitional period of offline mode is relatively more steady, safe.
Claims (10)
- The mode 1. a kind of rotor of VTOL Fixed Wing AirVehicle verts, it is characterised in that: rotor verts around revolute pair, rotor Plane of rotation verts from horizontality to vertical state；Or it verts from vertical state to horizontality；The axis of revolute pair with One tangent line of the tip turning circumference of the fin of rotor is parallel, and the axis of revolute pair and the tangent line are close, but revolute pair The tip turning circumference of axis and fin is non-intersecting.
- The mode 2. a kind of rotor of VTOL Fixed Wing AirVehicle according to claim 1 verts, it is characterised in that: turn The Plane of rotation for moving secondary axis and rotor is in same plane.
- 3. a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle, it is characterised in that: including rotor, engine, pivoted arm, Revolute pair, bracket；Rotor connects engine, and engine is mounted on one end of pivoted arm, and the other end of pivoted arm passes through revolute pair and branch Frame is connected；Revolute pair is near the airfoil tip of rotor, the rotation round of the airfoil tip of the axis and rotor of revolute pair One tangent line is close and the axis of revolute pair is parallel with the tangent line, and fin will not be touched with revolute pair when rotor rotational, fin It will not be touched with pivoted arm；The angle of pivoted arm rotation is 90 ° or substantially 90 °.
- 4. a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle according to claim 3, it is characterised in that: when When the rotating circular disk of rotor is in a horizontal position, the rotating circular disk of revolute pair and rotor is close but is no more than the rotating circular disk of rotor Height and position.
- 5. a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle according to claim 3, it is characterised in that: turn The rotating circular disk of secondary mounting height and rotor is moved with high.
- 6. a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle according to claim 3, it is characterised in that: adopt Pivoted arm is set to rotate that rotor is driven to vert around revolute pair with hydraulic device or electric device or pneumatic device or wire saws device.
- 7. a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle according to claim 6, it is characterised in that: adopt When with hydraulic device, one end of hydraulic cylinder is fixed on pivoted arm, and the other end of hydraulic cylinder is fixed on bracket；Using pneumatic device When, one end of cylinder is fixed on pivoted arm, and the other end of cylinder is fixed on bracket；When using electric device, driven with steering engine Pivoted arm rotation, the shell of steering engine are fixed on bracket, and the swing arm of steering engine is connected with pivoted arm；When using wire saws device, rope system On pivoted arm, rope uses wirerope or cordage.
- 8. a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle according to claim 3 or 4 or 5 or 6 or 7, It is characterized by: being equipped with locking device between revolute pair and pivoted arm, locking device can require to lock pivoted arm in office according to flight Meaning angle position.
- 9. a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle according to claim 3 or 4 or 5 or 6 or 7, It is characterized by: engine uses motor.
- The mode 10. a kind of rotor of VTOL Fixed Wing AirVehicle according to claim 1 or 2 verts, or according to power Benefit require 3 or 4 or 5 or 6 or 7 described in a kind of rotor inclining rotary mechanism of VTOL Fixed Wing AirVehicle, it is characterised in that: institute Rotor is stated to be replaced with propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274661.8A CN109131872A (en) | 2018-10-30 | 2018-10-30 | A kind of rotor of VTOL Fixed Wing AirVehicle verts mode and mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274661.8A CN109131872A (en) | 2018-10-30 | 2018-10-30 | A kind of rotor of VTOL Fixed Wing AirVehicle verts mode and mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109131872A true CN109131872A (en) | 2019-01-04 |
Family
ID=64806517
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274661.8A Withdrawn CN109131872A (en) | 2018-10-30 | 2018-10-30 | A kind of rotor of VTOL Fixed Wing AirVehicle verts mode and mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109131872A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111532428A (en) * | 2020-04-28 | 2020-08-14 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
-
2018
- 2018-10-30 CN CN201811274661.8A patent/CN109131872A/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111532428A (en) * | 2020-04-28 | 2020-08-14 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190104 |
|
| WW01 | Invention patent application withdrawn after publication |