CN109911178A - A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method - Google Patents
A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method Download PDFInfo
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Abstract
The present invention proposes a kind of tail-rotor for rotary-wing aircraft and promotes sharing system and control method, including variable-pitch propeller and its power source, switching mechanism.The present invention is realized by the way that the tail-rotor of rotary-wing aircraft and preceding winged propulsion system are shared a set of driving device, and corresponding switching mechanism is designed in sharing system, the power direction of driving device can be changed, to realize that the tail-rotor of rotary-wing aircraft and the function of preceding winged propulsion system may be implemented in a set of driving device；And it devises the tail-rotor of rotary-wing aircraft and promotes the control method of sharing system, guarantee the stationarity of conversion process.
Description
Technical field
The present invention relates to rotary-wing aircraft dynamical system technical field, specially a kind of tail for rotary-wing aircraft
Paddle and propulsion sharing system and control method.
Background technique
Rotary-wing aircraft is a kind of high-performance cruise performance of VTOL performance and fixed wing aircraft for having both helicopter
Novel layouts aircraft.Patent No. ZL201110213680.1, entitled " a kind of rotor blade that offline mode is variable is winged
Machine " Chinese patent be exactly a kind of typical type.The aircraft has the aerodynamic arrangement of Three-wing-surface.Wherein, host wing is in helicopter
Under offline mode, it can be used as rotor wing rotation as aircraft and the pulling force of needs be provided, meanwhile, when aircraft has certain flying speed
Afterwards, and it can be locked as fixed-wing, realizes the high efficiency flight of fixed-wing.Therefore, in the takeoff and landing stage, aircraft is using straight
Machine mode flight is risen, using fixed-wing mode flight, to deposit between helicopter mode and fixed-wing mode in cruise and task phase
In conversion mission phase.
For applicant during further progress rotary-wing aircraft, discovery has following problems to need to solve:
Rotary-wing aircraft needs to offset in helicopter mode the reaction torque of rotor blade using helicopter tail rotor, but
It is not needed again in fixed-wing mode using helicopter tail rotor, helicopter tail rotor system is exactly deadweight under fixed-wing mode.
And rotary-wing aircraft is needed using preceding drawing or pusher propeller under fixed-wing mode come the power that flies before generating, but going straight up to
It is not needed when machine mode using preceding drawing or pusher propeller, preceding drawing or pusher propeller (i.e. propulsion system) propulsion system are being gone straight up to
It is exactly deadweight under machine mode.If the power under both of which all derives from an engine and propelling screws and hair
Motivation output shaft is connected directly, then propelling screws can also consume additional power in helicopter mode.
Summary of the invention
There is system redundancy, this hair in propulsion system and helicopter tail rotor system existing rotary-wing aircraft
It is bright to propose a kind of tail-rotor for rotary-wing aircraft and promote sharing system and control method, by by rotary-wing aircraft
Tail-rotor and preceding winged propulsion system share a set of driving device and realize, and corresponding switching mechanism is designed in sharing system, can
Change driving device power direction, thus realize a set of driving device may be implemented rotary-wing aircraft tail-rotor and before fly to push away
Into the function of system；And it devises the tail-rotor of rotary-wing aircraft and promotes the control method of sharing system, guarantee converted
The stationarity of journey.
The technical solution of the present invention is as follows:
A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system, it is characterised in that: including variable-pitch propeller
Paddle and its power source, switching mechanism；
The switching mechanism can change the axis direction of variable-pitch propeller: in helicopter mode, switching mechanism can
Keep propeller axis vertical with the longitudinally asymmetric face of fuselage, plays the role of balance rotating wing reaction torque；Under fixed-wing mode, turn
Structure of changing planes can make propeller axis parallel with fuselage longitudinal axis, play the role of the power that flies before providing；Helicopter mode to
Fixed-wing mode converts mission phase, switching mechanism can be made according to forward flight speed propeller axis and the longitudinally asymmetric face of fuselage at
Corresponding angle flies resistance before so that the forward direction component of propeller pulling force is overcome and reaches the acceleration of requirement, propeller pulling force
Cross component force can balance rotating wing reaction torque effect；Mission phase is converted to helicopter mode in fixed-wing mode, is turned
Structure of changing planes can be such that propeller axis changes from fuselage longitudinal axis parallel direction to longitudinally asymmetric with fuselage in setting time
Face vertical direction.
Further preferred embodiment, a kind of tail-rotor for rotary-wing aircraft and propulsion sharing system, feature
Be: the switching mechanism includes transmission input shaft, power reversing transmission mechanism, power output shaft and conversion and control mechanism；Institute
It states transmission input shaft to connect with power source, and will be in power input power reversing transmission mechanism；The power reversing transmission mechanism
Realize the power transfer between transmission input shaft and power output shaft, and the axis folder between transmission input shaft and power output shaft
Angle variable-angle；The power output shaft will be in power output to variable-pitch propeller；The conversion and control mechanism can change biography
Axis angle between driven input shaft and power output shaft makes power output shaft axis meet the requirement of different mission phases.
Further preferred embodiment, a kind of tail-rotor for rotary-wing aircraft and propulsion sharing system, feature
Be: the power reversing transmission mechanism includes input bevel gear, drive bevel gear, output bevel gear wheel and shaft；Input cone tooth
Wheel is engaged with drive bevel gear, and output bevel gear wheel is engaged with drive bevel gear；Drive bevel gear coaxial sleeve is turning in shaft
Axial limiting on axis；
The conversion and control mechanism includes conversion rocker arm and steering engine；The conversion rocker arm also covers in shaft, and can be
Axis rotates around the shaft under servo driving；
The transmission input shaft is fixedly and coaxially connected after passing through mounting rack side with input bevel gear, and the mounting rack is opposite
Fuselage positions are fixed；The power output shaft is fixedly and coaxially connected after passing through conversion rocker arm side with output bevel gear wheel, works as conversion
When rocker arm axis rotation around the shaft, it is able to drive power output shaft synchronizing moving.
A kind of tail-rotor for rotary-wing aircraft and the control method for promoting sharing system, it is characterised in that: fly
Row control system automatically controls propeller axis direction and airscrewpiston according to the offline mode of rotary-wing aircraft.
Further preferred embodiment, a kind of tail-rotor for rotary-wing aircraft and the controlling party for promoting sharing system
Method, it is characterised in that:
In the helicopter mode flight stage, flight control system controls switching mechanism and keeps propeller axis and fuselage longitudinal
The plane of symmetry is vertical；
In the fixed-wing mode flight stage, flight control system controls switching mechanism and keeps propeller axis and fuselage longitudinal
Axis is parallel；
Mission phase is converted to fixed-wing mode in helicopter mode, flight control system is controlled according to forward flight speed and converted
Mechanism drives propeller axis to deflect to the longitudinally asymmetric face of fuselage into corresponding angle position, under the angle position, propeller
The forward direction component of pulling force winged resistance and the acceleration for making rotary-wing aircraft reach requirement, side of propeller pulling force before capable of overcoming
It being capable of the effect of balance rotating wing reaction torque to component；Flight control system is gone as course by adjusting airscrewpiston simultaneously
Stablize；
Mission phase is converted to helicopter mode in fixed-wing mode, flight control system controls switching mechanism for propeller
Axis from fuselage longitudinal axis parallel direction change to the longitudinally asymmetric face vertical direction of fuselage；Flight control system is led to simultaneously
Airscrewpiston is overregulated come the stabilization that goes as course.
Beneficial effect
The invention proposes a set of tail-rotor for rotary-wing aircraft and sharing system and its control method are promoted, is realized
The tail-rotor of rotary-wing aircraft and preceding winged propulsion system share the purpose of a set of power and driving device, can mitigate significantly winged
Machine is self-possessed and reduces the required horsepower that takes off.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1 is the schematic diagram (spiral shell of aircraft of the invention when VTOL state lower tail paddle shaft line is transformed into aircraft side
It is vertical with fuselage axis to revolve paddle shaft line).
Fig. 2 is the schematic diagram (propeller of aircraft of the invention when cruising condition lower tail paddle shaft line is transformed into airplane tail group
Axis is parallel with fuselage axis).
Fig. 3 is the tail-rotor axis direction variation schematic diagram of aircraft of the invention in full flight course.
In figure: A, the helicopter mode flight stage；B, mission phase is converted；C, the fixed-wing mode flight stage.
Fig. 4 and Fig. 5 is a kind of switching mechanism schematic diagram of the invention.
In figure: 1, inputting bevel gear；2, drive bevel gear；3, output bevel gear wheel；4, rocker arm is converted；5, mounting rack；6, spiral shell
Revolve paddle；7, shaft；8, electric steering engine.
Fig. 6 is another switching mechanism schematic diagram of the invention.
In figure: 9, transmission input shaft；10, the first drive bevel gear；11, belt wheel for inputting；12, switching mechanism fixed case
Body；13, belt；14, belt output wheel；15, the second drive bevel gear；16, power output shaft；17, switching mechanism rotating box；
18, steering engine connecting rod.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to is used to explain the present invention, and is not considered as limiting the invention.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside", " up time
The orientation or positional relationship of the instructions such as needle ", " counterclockwise " is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of
The description present invention and simplified description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with spy
Fixed orientation construction and operation, therefore be not considered as limiting the invention.
Furthermore, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Therefore, define " first ", the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
A kind of tail-rotor for rotary-wing aircraft proposed by the present invention and promote sharing system, including variable-pitch propeller and
Its power source, switching mechanism.
As shown in FIG. 1 to 3, the switching mechanism can change the axis direction of variable-pitch propeller: in helicopter mode
Under, switching mechanism can make propeller axis vertical with the longitudinally asymmetric face of fuselage, play the role of balance rotating wing reaction torque；?
Under fixed-wing mode, switching mechanism can make propeller axis parallel with fuselage longitudinal axis, play the role of the power that flies before providing；
Mission phase is converted to fixed-wing mode in helicopter mode, switching mechanism can make propeller axis and machine according to forward flight speed
The longitudinally asymmetric face of body flies resistance before so that the forward direction component of propeller pulling force is overcome and reaches the acceleration of requirement at corresponding angle
The cross component force of degree, propeller pulling force being capable of the effect of balance rotating wing reaction torque；Turn in fixed-wing mode to helicopter mode
Change mission phase, switching mechanism can make propeller axis setting time from fuselage longitudinal axis parallel direction change to
The longitudinally asymmetric face vertical direction of fuselage.
The switching mechanism includes transmission input shaft 9, power reversing transmission mechanism, power output shaft 16 and conversion and control machine
Structure；The transmission input shaft 9 is connect with power source, and will be in power input power reversing transmission mechanism；The power commutation passes
Motivation structure realizes the power transfer between transmission input shaft 9 and power output shaft 16, and transmission input shaft 9 and power output shaft 16
Between axis angle variable-angle；The power output shaft 16 will be in power output to variable-pitch propeller 6；The conversion and control
Mechanism can change the axis angle between transmission input shaft 9 and power output shaft 16, meet power output shaft axis different
The requirement of mission phase.
As shown in Figure 4 and Figure 5, one kind of switching mechanism is achieved in that, the power reversing transmission mechanism includes input
Bevel gear 1, drive bevel gear 2, output bevel gear wheel 3 and shaft 7；Input bevel gear 1 engages with drive bevel gear 2, output bevel gear
Wheel 3 is engaged with drive bevel gear 2, and input bevel gear 1 drives drive bevel gear 2 to rotate, and then output bevel gear wheel 3 is driven to rotate,
Output bevel gear wheel 3 drives coaxial mounted propeller 6 to rotate.2 coaxial sleeve of drive bevel gear is in shaft 7, and the axis in shaft 7
To limit.The conversion and control mechanism includes conversion Rocker arm 4 and steering engine 8；The conversion Rocker arm 4 also covers in shaft 7, and can
7 axis rotate around the shaft under the driving of steering engine 8.The transmission input shaft 9 is coaxial with input bevel gear 1 behind mounting rack side
It is fixedly connected, the opposite fuselage positions of the mounting rack 5 are fixed, and afterbody is mounted on；The power output shaft 16 passes through conversion
It is fixedly and coaxially connected behind Rocker arm 4 side with output bevel gear wheel 3, when converting Rocker arm 47 axis rotation around the shaft, is able to drive dynamic
16 synchronizing moving of power output shaft.Certainly, the rotate driving mode of Rocker arm 4 is converted, it can also be using its other party different from steering engine
Formula.
As shown in fig. 6, the another kind of switching mechanism is achieved in that, the power reversing transmission mechanism includes input cone tooth
Take turns the 1, first drive bevel gear 10, input belt pulley 11, belt 13, output belt pulley 14, the second drive bevel gear 15 and output
Bevel gear 3.
Input bevel gear 1, the first drive bevel gear 10, input belt pulley 11, belt 13, output belt pulley 14 are mounted on and turn
It changes planes in structure static housing 12, switching mechanism static housing 12 is fixedly mounted on afterbody；Second drive bevel gear 15 and defeated
Bevel gear 3 is mounted in switching mechanism rotating box 17 out, and switching mechanism rotating box 17 can be around output belt pulley 14 and the
Drive shaft axis rotation between two drive bevel gears 15.
Transmission input shaft 9 is fixedly and coaxially connected after passing through 12 wall surface of switching mechanism static housing with input bevel gear 1, is inputted
Bevel gear 1 engages with the first drive bevel gear 10, and the first drive bevel gear 10 is coaxially connected with input belt pulley 11 by transmission shaft
It connects；It inputs belt pulley 11 and output belt pulley 14 is driven by belt；It exports between belt pulley 14 and the second drive bevel gear 15
It is coaxially connected by the transmission shaft for passing through 17 wall surface of switching mechanism rotating box, the second drive bevel gear 15 and output bevel gear wheel 3
Engagement, output bevel gear wheel 3 drive coaxial mounted propeller 6 to rotate.
The conversion and control mechanism realizes that steering engine 8 is logical using the steering engine 8 being fixedly mounted on switching mechanism static housing 12
It crosses steering engine connecting rod 18 and rotates and position with manual converting mechanism rotating box 17.Certainly, the rotation of switching mechanism rotating box 17 is driven
Flowing mode, can also be using the other modes different from steering engine.
For the above-mentioned tail-rotor for rotary-wing aircraft and promote sharing system, control method are as follows: flight control system
System automatically controls propeller axis direction and and airscrewpiston according to the offline mode of rotary-wing aircraft.Specifically
It is:
In the helicopter mode flight stage, flight control system controls switching mechanism and keeps propeller axis and fuselage longitudinal
The plane of symmetry is vertical；
In the fixed-wing mode flight stage, flight control system controls switching mechanism and keeps propeller axis and fuselage longitudinal
Axis is parallel；
Mission phase is converted to fixed-wing mode in helicopter mode, flight control system is controlled according to forward flight speed and converted
Mechanism drives propeller axis to deflect to the longitudinally asymmetric face of fuselage into corresponding angle position, under the angle position, propeller
The forward direction component of pulling force winged resistance and the acceleration for making rotary-wing aircraft reach requirement, side of propeller pulling force before capable of overcoming
It being capable of the effect of balance rotating wing reaction torque to component；Flight control system is gone as course by adjusting airscrewpiston simultaneously
Stablize；
Mission phase is converted to helicopter mode in fixed-wing mode, flight control system controls switching mechanism in setting
Between at the uniform velocity by propeller axis from fuselage longitudinal axis parallel direction change to the longitudinally asymmetric face vertical direction of fuselage；Flight
Control system is simultaneously by adjusting airscrewpiston come the stabilization that goes as course.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (5)
1. a kind of tail-rotor for rotary-wing aircraft and promoting sharing system, it is characterised in that: including variable-pitch propeller and its
Power source, switching mechanism；
The switching mechanism can change the axis direction of variable-pitch propeller: in helicopter mode, switching mechanism can make spiral shell
It is vertical with the longitudinally asymmetric face of fuselage to revolve paddle shaft line, plays the role of balance rotating wing reaction torque；Under fixed-wing mode, interpreter
Structure can make propeller axis parallel with fuselage longitudinal axis, play the role of the power that flies before providing；In helicopter mode to fixation
Wing mode converts mission phase, and switching mechanism can make propeller axis with the longitudinally asymmetric face of fuselage at corresponding according to forward flight speed
Angle flies resistance before so that the forward direction component of propeller pulling force is overcome and reaches the acceleration of requirement, the side of propeller pulling force
It being capable of the effect of balance rotating wing reaction torque to component；Mission phase, interpreter are converted to helicopter mode in fixed-wing mode
Structure can be such that propeller axis changes from fuselage longitudinal axis parallel direction to vertical with the longitudinally asymmetric face of fuselage in setting time
Histogram to.
2. a kind of tail-rotor for rotary-wing aircraft and propulsion sharing system according to claim 1, it is characterised in that: institute
Stating switching mechanism includes transmission input shaft, power reversing transmission mechanism, power output shaft and conversion and control mechanism；The transmission is defeated
Enter axis to connect with power source, and will be in power input power reversing transmission mechanism；The power reversing transmission mechanism realizes transmission
Power transfer between input shaft and power output shaft, and the axis angle angle between transmission input shaft and power output shaft can
Become；The power output shaft will be in power output to variable-pitch propeller；The conversion and control mechanism can change transmission input shaft
Axis angle between power output shaft makes power output shaft axis meet the requirement of different mission phases.
3. a kind of tail-rotor for rotary-wing aircraft and propulsion sharing system according to claim 2, it is characterised in that: institute
Stating power reversing transmission mechanism includes input bevel gear, drive bevel gear, output bevel gear wheel and shaft；Input bevel gear and transmission
Bevel gear engagement, output bevel gear wheel are engaged with drive bevel gear；Drive bevel gear coaxial sleeve is axial in shaft, and in shaft
Limit；
The conversion and control mechanism includes conversion rocker arm and steering engine；The conversion rocker arm also covers in shaft, and can be in steering engine
Axis rotates around the shaft under driving；
The transmission input shaft is fixedly and coaxially connected after passing through mounting rack side with input bevel gear, and the mounting rack is with respect to fuselage
Position is fixed；The power output shaft is fixedly and coaxially connected after passing through conversion rocker arm side with output bevel gear wheel, when conversion rocker arm
When axis rotates around the shaft, it is able to drive power output shaft synchronizing moving.
4. the control method described in a kind of claim 1 for the tail-rotor of rotary-wing aircraft and propulsion sharing system, feature
Be: flight control system automatically controls propeller axis direction and propeller paddle according to the offline mode of rotary-wing aircraft
Away from.
5. the control method of a kind of tail-rotor for rotary-wing aircraft and propulsion sharing system according to claim 4,
It is characterized in that:
In the helicopter mode flight stage, flight control system controls switching mechanism and keeps propeller axis and fuselage longitudinally asymmetric
Face is vertical；
In the fixed-wing mode flight stage, flight control system controls switching mechanism and keeps propeller axis and fuselage longitudinal axis
In parallel；
Mission phase is converted to fixed-wing mode in helicopter mode, flight control system controls switching mechanism according to forward flight speed
Propeller axis is driven to deflect to the longitudinally asymmetric face of fuselage into corresponding angle position, under the angle position, propeller pulling force
Forward direction component can overcome before winged resistance and reach the acceleration of requirement, the cross component force of propeller pulling force being capable of balance rotating
The effect of wing reaction torque；Flight control system is simultaneously by adjusting airscrewpiston come the stabilization that goes as course；
Mission phase is converted to helicopter mode in fixed-wing mode, flight control system controls switching mechanism for propeller axis
From with fuselage longitudinal axis parallel direction change to the longitudinally asymmetric face vertical direction of fuselage；Flight control system passes through tune simultaneously
Airscrewpiston is saved come the stabilization that goes as course.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910188820.0A CN109911178A (en) | 2019-03-13 | 2019-03-13 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910188820.0A CN109911178A (en) | 2019-03-13 | 2019-03-13 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
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|---|---|---|---|---|
| FR2831933A1 (en) * | 2001-11-06 | 2003-05-09 | Eurocopter France | SWITCHING TRANSMISSION WITH PIVOTING CONNECTION WITH SLIDING BEARINGS |
| CN102826220A (en) * | 2012-09-14 | 2012-12-19 | 西北工业大学 | Thrust device capable of balancing reactive torque |
| CN104743111A (en) * | 2013-12-17 | 2015-07-01 | 空客直升机 | Rotorcraft fitted with an anti-torque tail rotor that contributes selectively to providing the rotorcraft with lift and with propulsion |
| CN106043685A (en) * | 2016-01-27 | 2016-10-26 | 北京航空航天大学 | Double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft |
| CN205738061U (en) * | 2015-12-02 | 2016-11-30 | 西北工业大学 | A kind of ducted fan vector propulsion system of rotor/wing convertible plane |
| CN106986005A (en) * | 2017-03-29 | 2017-07-28 | 北京华信智航科技有限公司 | A kind of structure of verting of the dynamic tilt rotor aircraft of oil |
| CN108128449A (en) * | 2016-12-01 | 2018-06-08 | 及兰平 | Double mode rotary wing aircraft based on folding wing |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
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2019
- 2019-03-13 CN CN201910188820.0A patent/CN109911178A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2831933A1 (en) * | 2001-11-06 | 2003-05-09 | Eurocopter France | SWITCHING TRANSMISSION WITH PIVOTING CONNECTION WITH SLIDING BEARINGS |
| CN102826220A (en) * | 2012-09-14 | 2012-12-19 | 西北工业大学 | Thrust device capable of balancing reactive torque |
| CN104743111A (en) * | 2013-12-17 | 2015-07-01 | 空客直升机 | Rotorcraft fitted with an anti-torque tail rotor that contributes selectively to providing the rotorcraft with lift and with propulsion |
| CN205738061U (en) * | 2015-12-02 | 2016-11-30 | 西北工业大学 | A kind of ducted fan vector propulsion system of rotor/wing convertible plane |
| CN106043685A (en) * | 2016-01-27 | 2016-10-26 | 北京航空航天大学 | Double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft |
| CN108128449A (en) * | 2016-12-01 | 2018-06-08 | 及兰平 | Double mode rotary wing aircraft based on folding wing |
| CN106986005A (en) * | 2017-03-29 | 2017-07-28 | 北京华信智航科技有限公司 | A kind of structure of verting of the dynamic tilt rotor aircraft of oil |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
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