CN205602100U - Gyroplane is lift vertically to short -tail crust - Google Patents
Gyroplane is lift vertically to short -tail crust Download PDFInfo
- Publication number
- CN205602100U CN205602100U CN201620344120.8U CN201620344120U CN205602100U CN 205602100 U CN205602100 U CN 205602100U CN 201620344120 U CN201620344120 U CN 201620344120U CN 205602100 U CN205602100 U CN 205602100U
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- China
- Prior art keywords
- tail
- vertical pivot
- gyroplane
- tail undercarriage
- rotatable portion
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Abstract
The utility model provides a gyroplane is lift vertically to short -tail crust, but includes passenger cabin, individual layer main rotor displacement propeller hub, second vertical axis, automatic slope dish, main -gear box, engine, tail rotor, smooth wheel, the frame of running of undercarriage, and the main speed reduction box is passed through in the pivot of engine, is connected with second vertical axis and afterbody propeller component. Through total distance of automatic slope dish regulation main rotor, the size of control lift, required power when providing flight again, the direction of adjusting the next control flight of size of each main rotor pitch through automatic slope dish. Utilize on this tail rotor can concentrate on a model with autogiro and the advantage of lifting vertically gyroplane appearance and function, messenger's aircraft has autogiro's advantage: short and the security of tail, has the advantage of lifting vertically gyroplane: can the VTOL, the translation is hovered, to the flight of any direction, don't slide the race, flexible.
Description
Technical field
The invention belongs to the gyroplane of airborne vehicle, particularly a kind of short tail goes straight up to gyroplane.
Background technology
Existing gyroplane can be divided into goes straight up to gyroplane and autogiro.Go straight up to gyroplane by the master on top
Rotor wing rotation produces lift, by tail undercarriage to a cross air blasting, resists owing to main rotor moves ahead the body rotation caused, passes through
Control to resist the size of power to control the direction of aircraft turn, main rotor and tail undercarriage all by driving engine.From rotating
Wing machine, is that relative wind when flying blows top main rotor rotation to produce the rotary wing aircraft of lift, top before a kind of utilization
Main rotor is not connected with electromotor.The propeller that the power flown before autogyro is dried backward from afterbody, tail undercarriage
Connect with electromotor.In terms of profile, go straight up to gyroplane to meet load-carrying, main rotor surfaces of revolution diameter, tail undercarriage oar
Dish diameter, the length of tail, engine output, the connected mode of main rotor propeller hub, the quantity of main rotor, reach harmony
Balance, has just had inharmonic long tail.The longest tail of autogyro.Although autogyro in terms of profile with straight
The machine of liter is closely similar, but is essentially different at principle and configuration aspects, autogyro and helicopter, and wherein maximum
Difference be that two kinds of aircrafts seem identical main rotor.The main rotor of helicopter is the sole power source of helicopter, passes through
Wing drop dish regulation main rotor always away from, control the size of lift, required power when providing flight again, by automatically inclining
Swash plate regulates the size of each main rotor pitch and controls the direction of flight.Go straight up to gyroplane and include monolayer main rotor, variable
Away from propeller hub, main rotor vertical pivot, wing drop dish, main-gear box, electromotor, tail undercarriage assembly.Review autogyro, it
On the crown, greatly rotor is that discord engine driving system is connected when flight, and the rotation of rotor flies before fully relying on aircraft
Time relative wind blow the effect with self inertia, just look like a greatly windmill, and this " windmill " be only aircraft
Lift required during offer flight.Due to autorotation, the moment of torsion that the rotor of gyroplane passes to fuselage is the least, such gyroplane
Also be no need for helicopter such to the tail-rotor of a cross air blasting to carry out balance.The propeller dried the most backward provides and flies
The power that machine moves ahead.Most of autogyros can not carry out VTOL as helicopter, and must be as fixed wing airplane
Equally just can take off through sliding race.But, the rotor of gyroplane can carry out of short duration by clutch with electromotor when taking off
Connection, although this is not enough to produce enough lift and takes off vertically, but the active rotation of rotor can efficiently reduce
Ground run distance when taking off.In flight course, autogyro may only flight forward, and rotor always retreats
Oblique;Helicopter then can be flown even hovering to any direction with VTOL, the angle of inclination of rotor also with
The change of heading and change, this is also awing two kinds of aircraft intuitive ways of differentiation.When flying before autogyro
Power come from the propeller of aft, it is connected with the electromotor of gyroplane, rotates blow air backward, thus
Realize the flight forward of aircraft.And, autogyro has empennage, and needs to control the direction of flight by it.Attach most importance to most
Want, rotate owing to the main rotor of autogyro relies only on self inertia when flight, so in meeting with engine air
Suddenly, when parking runs out of steam completely, gyroplane flying height declines the ascending air caused can accelerate the rotation of rotor, thus
Compensate aircraft loss lift, gyroplane then can in the case of there is no power grease it in, higher safety is also
The design original intention of gyroplane.In sum, gyroplane advantage is gone straight up to: can hover with vertical lift, fly to any direction；
But it has a long tail, particularly light helicopter actually used in, a long tail in tow, just increase volume
With unsafe factor, can't the safety of autogyro be performed to best.Although autogiro tail is the longest,
Having original safety, but it does not has the maneuverability of helicopter, a segment distance is also slided in landing.
Summary of the invention
It is an object of the invention to provide a kind of aft and divide the tail undercarriage construction package of installation, this structure group
Part can meet in aircraft vertical lifting, and during hovering, tail undercarriage, to body one cross air blasting, is resisted the rotation of body, passed through
Adjustable screw oar is always away from controlling blowing size, to control aircraft turn direction.Cruise flight forward time, tail undercarriage gradually to
Rear blowing, it is provided that the power of autogyro.Utilize this tail undercarriage can be by autogiro and go straight up to gyroplane
The advantage of profile and function concentrates on a kind of type, makes the advantage that aircraft has autogiro: tail is short and safety.
There is the advantage going straight up to gyroplane: can translate with VTOL, hovering, fly to any direction, sliding race, motor-driven spirit
Live.Cruising speed is higher than current helicopter.The danger of vortex flow can also be rapidly separated.The technology solution of the present invention
Certainly scheme is as follows: a kind of short tail goes straight up to gyroplane, including passenger cabin, monolayer main rotor, variable-distance propeller hub, the second vertical pivot, from
Dynamic pitch, main-gear box, electromotor, tail undercarriage assembly, undercarriage sliding running wheel, frame, the rotating shaft of electromotor is by main
Reduction box and the second vertical pivot and tail undercarriage assembly connect.Tail undercarriage construction package include above rotatable portion and
Fixed pedestal below.Described rotatable portion above, has the first trunnion axis to can be used to install autogyro tail undercarriage leaf
Sheet；Trunnion axis hollow, this trunnion axis hollow space installs a drag link, and pull bar one end is stretched out from horizontal cross shaft center, stretched out
The end is installed one vertical with axis at conplane cross, and cross four end margin has connecting rod, respectively and tail undercarriage
, the arm of force of four propeller blade roots connects, and axle draw-in bar one end and seizing wire connect, and connecting portion places a pressure
Spring withstands pull bar location, and this design can ensure that steel wire rope pulls pull bar to adjust propeller always away from size, lineoutofservice signal pull solution
Removing, compression spring resets, and pushing drawing rod replys origin-location.The rotary power of tail undercarriage is by the cone on the first trunnion axis
The bevel gear combination transmission of shape gear and the first vertical pivot upper part.Rotatable base plane pressure bearing periphery fixed chain wheels,
Rotate to pull chain to control upper part, the blowing direction of tail undercarriage can be controlled.Described fixed pedestal below, is arranged on
Body position after second vertical pivot, by the second trunnion axis input power, with the conical tooth on the second trunnion axis inside fixed pedestal
Wheel and the first vertical pivot lower part bevel reduction gear set incompatible transmission power.Rotatable portion and following fixed pedestal share first above
Vertical pivot.This vertical pivot not only can transmit power but also as the location of rotatable portion above, and can pass through rotatable portion housing parts
Being enclosed within below on vertical pivot, applanation bearing increases the stability of rotatable portion.Further, described tail undercarriage
Utilize the motor being separately configured to provide power, a motor and tail undercarriage are fixed on same rotation housing, this shell
3rd vertical pivot is arranged at body bottom, is inserted in the circular hole of body, can rotate in circular hole, rotates installing connecting rods on housing on top, draws
Dynamic connecting rod can control the blowing direction of tail undercarriage.Feature of present invention is that tail undercarriage can change blowing direction, with
Existing gyroplane technology of going straight up to is compared, and can shorten long tail, increases safety, increases cruising speed.Fly with autorotating rotor
Machine is compared, and can translate with VTOL, hovering, flies to any direction, sliding race.
Accompanying drawing explanation
Fig. 1 is the overall structure front view of the present invention；Fig. 2 is the overall structure top view of the present invention；Fig. 3 is the present invention's
Overall structure right view；Fig. 4 is enforcement (2) the design overall structure figure of the present invention；Fig. 5 is technical scheme (1) tail undercarriage
Steering structure complete graph；Fig. 6 is technical scheme (1) tail undercarriage steering structure rotatable upper part structure chart；Fig. 7 is technology
The internal structure of scheme (1) tail undercarriage hollow axle and outside adjustable screw oar are always away from structure chart.
In figure, tail undercarriage (1), the first trunnion axis (2), angle basin tooth combination (3), basin tooth (4), chain pitch wheel (5), the
One vertical pivot (6), tail undercarriage base housing (7), tail undercarriage Spin Control chain (8), applanation bearing (9), general
Axis holds (10), belt pulley (14), the second trunnion axis (15), main rotor propeller hub (16), main rotor (17), the second vertical pivot (18),
Wing drop dish (19), passenger cabin (21), main speed reduction box (23), electromotor (24), belt pulley (25), seat (26), sliding running wheel
(27), frame (28), variable-speed motor (29), cross (30), the propeller root arm of force (31), seizing wire (32), pressure
Spring (33), push-pull bar (34), push-pull bar abutment sleeve (35), connecting rod (36), tail undercarriage rotating base (37), the 3rd erects
Axle (38).
Detailed description of the invention
Implement 1
With reference to Fig. 1, shown in 2,3,5,6,7, a kind of short tail goes straight up to gyroplane, including passenger cabin (21), monolayer main rotor
(17), variable-distance propeller hub (16), the second vertical pivot (18), wing drop dish (19), main-gear box (23), electromotor (24), afterbody
Propeller assembly (1), sliding running wheel (27), frame (28), electromotor (24) passes through main speed reduction box (23), with the second vertical pivot (18) and
Tail undercarriage (1) assembly connects..Tail undercarriage construction package is divided into upper and lower two parts, above rotatable portion Fig. 6 and
Fixed pedestal below.Rotatable portion above, has the first trunnion axis (2) to can be used to install autogyro tail undercarriage (1)
Blade；Trunnion axis hollow, this trunnion axis hollow space installs a horizontal push-pull bar (34), and pull bar one end is stretched from horizontal cross shaft center
Going out, the end installation one stretched out is vertical with axis in conplane cross (30), and cross four end margin has connecting rod (36),
This connecting rod (36) respectively with tail undercarriage, the arm of force (31) of four propeller blade roots connects, axle draw-in bar one end and
Seizing wire connects (32), and connecting portion is placed a compression spring (33) and withstood push-pull bar (34) location, and this design can ensure
Steel wire rope pulls pull bar to adjust propeller always away from size, and lineoutofservice signal pull releases, and compression spring resets, and pushing drawing rod is replied original
Position.The rotary power of tail undercarriage is by the angular wheel (3) on the first trunnion axis and the umbrella of the first vertical pivot (6) upper part
Shape gear (4) combination transmission.The peripheral fixed chain wheels of rotatable base plane pressure bearing (9), to pull (8) chain to control top
Divide and rotate, the blowing direction of tail undercarriage (1) can be controlled.Bottom is divided into fixed pedestal part, after being arranged on the second vertical pivot
Body position, face, by the second trunnion axis (15) input power, is the angular wheel on the second trunnion axis (15) inside fixed pedestal
Bevel reduction gear set incompatible transmission power with the first vertical pivot (6) lower part.Rotatable portion and following fixed pedestal share above
First vertical pivot (6).This vertical pivot not only can transmit power but also as the location of rotatable portion above, and can pass through rotatable portion
The applanation bearing (9) being enclosed within below housing parts on vertical pivot (6) increases the stability of rotatable portion.
Embodiment 2
With reference to shown in Fig. 4, overall structure is the same with implementing 1, except for the difference that gives with single variable-speed motor (29)
Tail undercarriage (1) provides power, and a motor (29) and tail undercarriage (1) are fixed on same rotating base (37),
3rd vertical pivot (38) is arranged at this base bottom, is inserted in the circular hole of body, can rotate in circular hole, rotates housing side peace on top
Load bar, pulls connecting rod can control the blowing direction of tail undercarriage.
Feature of present invention is that tail undercarriage can change blowing direction, with existing go straight up to gyroplane technology compared with, can
To shorten long tail, increase safety, increase cruising speed.Compared with autogiro, can translate with VTOL, outstanding
Stop, fly to any direction, sliding race.
The foregoing is only embodiments of the invention, not thereby limit the scope of the claims of the present invention, every utilize this
Equivalent structure or equivalence flow process that bright description and accompanying drawing content are made convert, or are directly or indirectly used in other relevant skills
Art field, is the most in like manner included in the scope of patent protection of the present invention.
Claims (2)
1. short tail goes straight up to a gyroplane, including passenger cabin (21), monolayer main rotor (17), variable-distance propeller hub (16), second
Vertical pivot (18), wing drop dish (19), main-gear box (23), electromotor (24), tail undercarriage (1), sliding running wheel (27), frame
(28), the rotating shaft of electromotor (24) is connected with the second vertical pivot (18) and tail undercarriage (1) assembly by main speed reduction box (23), its
Be characterised by: tail undercarriage assembly can change blowing direction, tail undercarriage assembly include above rotatable portion and under
Face fixed pedestal, described rotatable portion above, there is the first trunnion axis (2) to can be used to install the propeller of autorotating rotor drive end unit
(1) blade；Trunnion axis hollow, this trunnion axis hollow space installs a horizontal push-pull bar (34), and push-pull bar one end is from horizontal cross shaft
The heart stretches out, and the end installation one stretched out is vertical with axis in conplane cross (30), and cross four end margin has connecting rod
(36), this connecting rod (36) respectively with tail undercarriage, the arm of force (31) of four propeller blade roots connects, axle draw-in bar one
End and seizing wire connect (32), and connecting portion is placed a compression spring (33) and withstood push-pull bar (34) location, and this design can
Ensureing that steel wire rope pulls pull bar to adjust propeller always away from size, lineoutofservice signal pull releases, and compression spring resets, and promotes push-pull bar to return
Multiple origin-location, the rotary power of tail undercarriage is by the angular wheel (3) on the first trunnion axis and the first vertical pivot (6) top
Bevel gear (4) the combination transmission divided, the peripheral fixed chain wheels of rotatable base plane pressure bearing (9), to pull (8) chain control
Upper part processed rotates, and can control the blowing direction of tail undercarriage (1), described fixed pedestal below, be arranged on the second vertical pivot
Body position below, by the second trunnion axis (15) input power, with the conical tooth on the second trunnion axis (15) inside fixed pedestal
Wheel and the bevel reduction gear set incompatible transmission power of the first vertical pivot (6) lower part, above rotatable portion and following fixed pedestal altogether
With the first vertical pivot (6), this vertical pivot (6) not only can transmit power but also can be as the location of rotatable portion above, and by can
The applanation bearing (9) being enclosed within below rotating part housing on the first vertical pivot (6) increases the stability of rotatable portion.
Go straight up to gyroplane the most as claimed in claim 1, it is characterised in that: give afterbody spiral shell with single variable-speed motor (29)
Rotation oar (1) provides power, a motor (29) and tail undercarriage (1) is fixed on same rotating base (37), this base
3rd vertical pivot (38) is arranged at bottom, is inserted in the circular hole of body, can rotate in circular hole, rotates housing side on top and installs even
Bar, pulls connecting rod can control the blowing direction of tail undercarriage；And it is enclosed within vertical pivot (38) by below rotatable portion housing parts
On applanation bearing (9) increase rotatable portion stability.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620344120.8U CN205602100U (en) | 2016-04-23 | 2016-04-23 | Gyroplane is lift vertically to short -tail crust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620344120.8U CN205602100U (en) | 2016-04-23 | 2016-04-23 | Gyroplane is lift vertically to short -tail crust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205602100U true CN205602100U (en) | 2016-09-28 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620344120.8U Expired - Fee Related CN205602100U (en) | 2016-04-23 | 2016-04-23 | Gyroplane is lift vertically to short -tail crust |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205602100U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892103A (en) * | 2017-01-23 | 2017-06-27 | 南京航空航天大学 | The helicopter rotor system and method for the electronic displacement of energy and automatic installing/dismounting blade |
| CN109229348A (en) * | 2017-07-10 | 2019-01-18 | 阿基米德航天航空精密工业科技(深圳)有限公司 | Sliding rotation helicopter |
| CN109466751A (en) * | 2018-12-29 | 2019-03-15 | 河南三和航空工业有限公司 | A kind of helicopter |
| CN110506001A (en) * | 2017-09-28 | 2019-11-26 | 维纳缇有限公司 | With the rotor craft of propulsion device on swingle |
| CN113353254A (en) * | 2021-07-14 | 2021-09-07 | 空中舞者(威海)航空动力技术有限公司 | Vertical take-off and landing gyroplane |
| CN113682475A (en) * | 2021-08-27 | 2021-11-23 | 沈阳无距科技有限公司 | Modularization unmanned aerial vehicle |
-
2016
- 2016-04-23 CN CN201620344120.8U patent/CN205602100U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892103A (en) * | 2017-01-23 | 2017-06-27 | 南京航空航天大学 | The helicopter rotor system and method for the electronic displacement of energy and automatic installing/dismounting blade |
| CN109229348A (en) * | 2017-07-10 | 2019-01-18 | 阿基米德航天航空精密工业科技(深圳)有限公司 | Sliding rotation helicopter |
| CN110506001A (en) * | 2017-09-28 | 2019-11-26 | 维纳缇有限公司 | With the rotor craft of propulsion device on swingle |
| CN109466751A (en) * | 2018-12-29 | 2019-03-15 | 河南三和航空工业有限公司 | A kind of helicopter |
| CN109466751B (en) * | 2018-12-29 | 2024-02-06 | 河南三和航空工业有限公司 | Helicopter gyroplane |
| CN113353254A (en) * | 2021-07-14 | 2021-09-07 | 空中舞者(威海)航空动力技术有限公司 | Vertical take-off and landing gyroplane |
| CN113353254B (en) * | 2021-07-14 | 2023-02-28 | 空中舞者(威海)航空动力技术有限公司 | Vertical take-off and landing gyroplane |
| CN113682475A (en) * | 2021-08-27 | 2021-11-23 | 沈阳无距科技有限公司 | Modularization unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160928 Termination date: 20200423 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |