CN113928540A - Helicopter inertia variable-pitch rotor wing - Google Patents
Helicopter inertia variable-pitch rotor wing Download PDFInfo
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- CN113928540A CN113928540A CN202111391773.3A CN202111391773A CN113928540A CN 113928540 A CN113928540 A CN 113928540A CN 202111391773 A CN202111391773 A CN 202111391773A CN 113928540 A CN113928540 A CN 113928540A
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- 230000002441 reversible effect Effects 0.000 claims description 16
- 230000008859 change Effects 0.000 claims description 4
- 230000000737 periodic effect Effects 0.000 abstract description 12
- 239000011295 pitch Substances 0.000 description 77
- 230000001133 acceleration Effects 0.000 description 11
- 230000009471 action Effects 0.000 description 11
- 238000000034 method Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000033001 locomotion Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 125000004122 cyclic group Chemical group 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/32—Blade pitch-changing mechanisms mechanical
- B64C11/34—Blade pitch-changing mechanisms mechanical automatic
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention provides a helicopter inertia variable-pitch rotor, which comprises: a motor disposed on the top of the helicopter; a central hub connected to a rotor of the motor; a variable pitch gear set connected to the central hub; the phase sensor is arranged at the bottom of the motor and used for detecting the phase of the blade; the rotating speed controller is connected with the motor and is used for controlling the rotating speed of the motor; according to the inertia variable-pitch rotor wing structure, the periodic variable-pitch control can be simply and conveniently realized, the difficulty of the periodic variable-pitch technology is greatly reduced, the difficulty of using and maintaining a helicopter is reduced, and the popularization and application of the helicopter are facilitated.
Description
Technical Field
The invention belongs to the technical field of helicopter rotors, and particularly relates to a helicopter inertia variable-pitch rotor.
Background
As is known, the flight control of helicopters relies on the cyclic pitch of the rotor, which is achieved mainly by means of an automatic tilter and a servo-control system. The automatic inclinator well realizes the function of periodic pitch change, but the weight of the automatic inclinator is large, so that the efficiency improvement of the helicopter is limited; meanwhile, the servo control system is complex in mechanism and high in use and maintenance cost.
In the course of exploring rotors without automatic tilters, an electric control rotor appears, that is, a servo actuating mechanism is directly arranged in a hub or a blade, and periodic variable-pitch operation is performed in real time according to the rotating phase of the blade.
The automatic tilter of the rotor wing aims to solve the problems that the automatic tilter of the rotor wing is complex in mechanism, heavy in weight and high in cost, the technical difficulty of the electric control rotor wing is high, the popularity is low and the like. The application provides a cyclic variable-pitch rotor without an automatic tilter and a servo control mechanism.
Disclosure of Invention
In view of the above technical problem, the present invention provides a helicopter inertia variable-pitch rotor, comprising:
a motor disposed on the top of the helicopter;
a central hub connected to a rotor of the motor;
a variable pitch gear set connected to the central hub;
the phase sensor is arranged at the bottom of the motor and used for detecting the phase of the blade;
and the rotating speed controller is connected with the motor and is used for controlling the rotating speed of the motor.
Preferably, the pitch gearset comprises:
a first gear fixedly connected to the central hub;
and the second gear is meshed with the first gear and is used for driving the blades to change the pitch.
Preferably, the pitch gearset further comprises:
and the third gear is meshed with the second gear and can rotate freely.
Preferably, the pitch gearset comprises:
a positive pitch gearset connected to one end of the central hub;
and the reverse variable pitch gear set is connected with the other end of the central hub.
Preferably, the method further comprises the following steps:
one end of the paddle clamp is connected with the second gear, and the other end of the paddle clamp is connected with the paddle;
a paddle blade connected with the paddle clip.
Preferably, the rotation speed controller is connected with the phase sensor; the rotating speed controller controls the rotating speed of the motor in real time according to the phase signals detected by the phase sensor.
Preferably, the central axis of the first gear is parallel to the rotation axis of the motor and is fixedly arranged on the central hub; the central axis of the second gear is perpendicular to the rotation axis of the motor.
Preferably, the third gear is disposed opposite to the first gear.
The invention has the beneficial technical effects that:
according to the inertia variable-pitch rotor wing structure, the periodic variable-pitch control can be simply and conveniently realized, the difficulty of the periodic variable-pitch technology is greatly reduced, the difficulty of use and maintenance is reduced, and the popularization and application of a helicopter are facilitated.
Drawings
FIG. 1 is a schematic structural view of a variable-pitch rotor of a helicopter according to an embodiment of the present invention;
FIG. 2 is a schematic view of an alternate helicopter inertia pitch rotor configuration provided by an embodiment of the present invention;
FIG. 3 is a schematic view of a structure of a further helicopter inertia variable pitch rotor according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a pitch gearset according to an embodiment of the present invention;
FIG. 5 is a schematic view of motor acceleration provided by an embodiment of the present invention;
FIG. 6 is a schematic illustration of motor deceleration provided by an embodiment of the present invention;
the system comprises a motor 1, a central propeller hub 2, a forward variable-pitch gear set 3, a reverse variable-pitch gear set 4, a propeller clamp 5, a blade 6, a phase sensor 7, a first gear 8, a second gear 9 and a third gear 10.
Detailed Description
Referring to fig. 1-6, the present invention provides an inertia variable-pitch rotor and a control method thereof.
The inertia variable-pitch rotor wing comprises a motor 1, a central hub 2, a forward variable-pitch gear set 3, a reverse variable-pitch gear set 4, a paddle clamp 5, blades 6, a phase sensor 7, a first gear 8, a second gear 9, a third gear 10 and a rotating speed controller.
In the embodiment of the application, the central hub is arranged on the motor, and one end of the variable pitch gear set is arranged on the central hub; the paddle is arranged on the paddle clamp; the paddle clamp is connected with the variable pitch gear set and can rotate along with the variable pitch gear set. The pitch-variable gear set includes: a first gear fixedly connected with the hub and non-rotatable; and the second gear is meshed with the first gear.
In the embodiment of the application, in the process that the motor rotates at a constant speed according to the basic rotating speed required by the lift force, the blades drive the pitch-variable gear set to keep static relative to the central propeller hub under the action of centrifugal force, the blade pitches on two sides are the same, the lift force is consistent, and the lift force direction is parallel to the main shaft.
In the embodiment of the application, when the motor tends to accelerate, the variable pitch gear set and the blades connected with the variable pitch gear set are accelerated and lagged behind the motor under the action of inertia. In the forward pitch-variable gear set, the forward pitch-variable gear set rotates backwards relative to the motor, and because the first gear is meshed with the second gear and fixedly connected with the propeller hub, the second gear rotates under the action of the first gear to drive the pitch to be increased, and the third gear rotates along with the second gear without influencing the pitch variation. In the reverse pitch-variable gear set, the reverse pitch-variable gear set rotates backwards relative to the motor, and because the first gear is meshed with the second gear and is fixedly connected with the propeller hub, the second gear rotates under the action of the first gear to drive the pitch to be reduced, and the third gear rotates along with the second gear without influencing the pitch variation.
In the embodiment of the application, when the motor tends to rotate at a reduced speed, the pitch gear set and the blades connected thereto are decelerated and lagged behind the motor by inertia. In the positive pitch-variable gear set, the positive pitch-variable gear set rotates forwards relative to the motor, and because the first gear is meshed with the second gear and fixedly connected with the propeller hub, the second gear rotates under the action of the first gear to drive the pitch to be reduced, and the third gear rotates along with the second gear without influencing the pitch variation. In the reverse pitch-variable gear set, the reverse pitch-variable gear set rotates forwards relative to the motor, and because the first gear is meshed with the second gear and is fixedly connected with the propeller hub, the second gear rotates under the action of the first gear to drive the pitch to increase, and the third gear rotates along with the second gear without influencing the pitch change.
The phase sensor arranged at the bottom of the motor detects the rotating phase of the paddle in real time and sends an acceleration and deceleration signal to the rotating speed controller. When the lift force needs to be generated to deflect in a specific direction, the rotating phase of the blade takes a lift force deflection moment axis as a bisector, and when the phase sensor detects that the blade connected with the positive pitch-variable gear set is in the first half-circle phase, an acceleration signal is sent to the rotating speed controller, and the motor accelerates to rotate. When the phase sensor detects the phase of the rear half circle of the paddle connected with the forward pitch-variable gear set, a speed reduction signal is sent to the rotating speed controller, and the motor rotates in a speed reduction mode. The motor is subjected to acceleration and deceleration control periodically, so that the pitch is always increased in the phase of the front half circle and decreased in the phase of the rear half circle no matter the blades connected with the forward variable-pitch gear set or the blades connected with the reverse variable-pitch gear set, the lift force is deflected in the preset direction, and the periodic variable-pitch control is realized.
Meanwhile, the acceleration and deceleration amplitude of the motor is based on the basic rotating speed of the motor, and the acceleration and deceleration are completed within one rotation of the motor, so that the average rotating speed of the motor is kept unchanged, and the average rotating speed of the rotor wing is not influenced.
Through the structure and the control mode, the invention can realize the periodic variable pitch control of the paddle only by slightly changing the rotating speed of the motor at a specific phase according to a specific frequency.
The inertia variable-pitch rotor wing can be electrically driven or fuel-powered.
Further, the pitch-variable wave box is essentially used for converting the inertial rotating motion of the blade into the pitch-variable rotating motion of the blade, and the form of the pitch-variable wave box is not limited to gear transmission as long as the same effect is achieved.
Furthermore, the inertia variable-pitch rotor blade can be two blades or even blades larger than the two blades, and the blades are symmetrically arranged in pairs.
Furthermore, the inertia variable-pitch rotor wing can be used independently or in combination.
As shown in fig. 1, 2, and 3, the main components of the structure include: the system comprises a motor, a central propeller hub, a forward variable-pitch gear set, a reverse variable-pitch gear set, a propeller clamp, a propeller blade and a phase sensor.
As shown in fig. 4, the first gear of the forward and reverse pitch gear sets is in the opposite position and is fixed and non-rotatable with the hub; the third gear is opposite in position and can rotate freely, so that the lifting capacity balancing function is realized; the second gear is fixed with the paddle clamp and meshed with the first gear and the third gear. It is understood that when the paddle swings, the second gear rotates under the action of the first gear, the paddle clamp is driven to rotate to achieve the pitch changing effect, and the third gear does not influence the pitch changing movement.
As shown in fig. 5, when the motor tends to accelerate, the pitch gear set and the blades connected thereto are accelerated by inertia to lag behind the motor. In the forward pitch-variable gear set, the forward pitch-variable gear set rotates backwards relative to the motor, and because the first gear is meshed with the second gear and fixedly connected with the propeller hub, the second gear rotates under the action of the first gear to drive the pitch to be increased, and the third gear rotates along with the second gear without influencing the pitch variation. In the reverse pitch gear set, the reverse pitch gear set rotates backwards relative to the motor, and since the first gear is meshed with the second gear and the first gear is fixedly connected with the hub, the second gear rotates under the action of the first gear, and the driving pitch is reduced.
As shown in fig. 6, when the motor tends to rotate at a reduced speed, the pitch gearset and the blades attached thereto slow down behind the motor under the influence of inertia. In the positive pitch-variable gear set, the positive pitch-variable gear set rotates forwards relative to the motor, and because the first gear is meshed with the second gear and fixedly connected with the propeller hub, the second gear rotates under the action of the first gear to drive the pitch to be reduced, and the third gear rotates along with the second gear without influencing the pitch variation. In the reverse pitch gear set, the reverse pitch gear set rotates forwards relative to the motor, and as the first gear is meshed with the second gear and the first gear is fixedly connected with the propeller hub, the second gear rotates under the action of the first gear, and the pitch of the driving propeller is increased.
The phase sensor arranged at the bottom of the motor detects the rotating phase of the paddle in real time and sends an acceleration and deceleration signal to the rotating speed controller. When the lift force needs to be generated to deflect in a specific direction, the rotating phase of the blade takes a lift force deflection moment axis as a bisector, and when the phase sensor detects that the blade connected with the positive pitch-variable gear set is in the first half-circle phase, an acceleration signal is sent to the rotating speed controller, and the motor accelerates to rotate. When the phase sensor detects the phase of the rear half circle of the paddle connected with the forward pitch-variable gear set, a speed reduction signal is sent to the rotating speed controller, and the motor rotates in a speed reduction mode. Therefore, the motor is periodically subjected to acceleration and deceleration control, no matter the blades connected with the forward variable-pitch gear set or the blades connected with the reverse variable-pitch gear set, the blade pitch is always increased in the phase of the front half circle, and the blade pitch is reduced in the phase of the rear half circle, so that the lift force deflects according to the preset value, and the periodic variable-pitch control is realized.
Meanwhile, the acceleration and deceleration amplitude of the motor is based on the basic rotating speed of the motor, and the acceleration and deceleration are completed within one rotation of the motor, so that the average rotating speed of the motor is kept unchanged, and the average rotating speed of the rotor wing is not influenced.
The inertia variable-pitch rotor wing is simple and reliable in structure and low in manufacturing cost, is a simple and effective method for realizing periodic variable-pitch control, can simply and conveniently realize the periodic variable-pitch control through the inertia variable-pitch rotor wing structure and the control method, greatly reduces the difficulty of the periodic variable-pitch technology, reduces the difficulty of using and maintaining a helicopter, and is beneficial to popularization and application of the helicopter.
Claims (8)
1. A helicopter inertia pitch rotor, comprising:
a motor disposed on the top of the helicopter;
a central hub connected to a rotor of the motor;
a variable pitch gear set connected to the central hub;
the phase sensor is arranged at the bottom of the motor and used for detecting the phase of the blade;
and the rotating speed controller is connected with the motor and is used for controlling the rotating speed of the motor.
2. A helicopter inertia pitch rotor as claimed in claim 1, wherein said pitch gear set comprises:
a first gear fixedly connected to the central hub;
and the second gear is meshed with the first gear and is used for driving the blades to change the pitch.
3. A helicopter inertia pitch rotor as claimed in claim 2, wherein said pitch gear set further comprises:
and the third gear is meshed with the second gear and can rotate freely.
4. A helicopter inertia pitch rotor as claimed in claim 3, wherein said pitch gear set comprises:
a positive pitch gearset connected to one end of the central hub;
and the reverse variable pitch gear set is connected with the other end of the central hub.
5. A helicopter inertia pitch rotor as claimed in claim 4, further comprising:
one end of the paddle clamp is connected with the second gear, and the other end of the paddle clamp is connected with the paddle;
a paddle blade connected with the paddle clip.
6. A helicopter inertia pitch rotor according to claim 1, wherein said speed controller is coupled to said phase sensor; the rotating speed controller controls the rotating speed of the motor in real time according to the phase signals detected by the phase sensor.
7. A helicopter inertia pitch rotor according to claim 2, wherein a central axis of said first gear is parallel to a rotational axis of said motor and is fixedly disposed on said central hub; the central axis of the second gear is perpendicular to the rotation axis of the motor.
8. A helicopter inertia pitch rotor according to claim 3, wherein said third gear is disposed opposite said first gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111391773.3A CN113928540B (en) | 2021-11-19 | 2021-11-19 | Helicopter inertia displacement rotor wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111391773.3A CN113928540B (en) | 2021-11-19 | 2021-11-19 | Helicopter inertia displacement rotor wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113928540A true CN113928540A (en) | 2022-01-14 |
| CN113928540B CN113928540B (en) | 2023-10-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111391773.3A Active CN113928540B (en) | 2021-11-19 | 2021-11-19 | Helicopter inertia displacement rotor wing |
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2090214A (en) * | 1980-08-13 | 1982-07-07 | Mckrill Nigel Howard | Controlling Helicopter Rotors |
| CN101376433A (en) * | 2008-10-10 | 2009-03-04 | 南京航空航天大学 | Helicopter rotor operation method and system |
| CN104139860A (en) * | 2014-04-23 | 2014-11-12 | 李晓宇 | Multi-shaft rotor aircraft and transmission mechanism thereof |
| FR3040687A3 (en) * | 2015-09-04 | 2017-03-10 | Hung-Fu Lee | HELICOPTER WITH MULTIPLE ROTORS OF NOT VARIABLE |
| CN108995793A (en) * | 2018-09-03 | 2018-12-14 | 南京航空航天大学 | A kind of rotary wing changing is away from system |
| CN208544421U (en) * | 2018-06-14 | 2019-02-26 | 南京航空航天大学 | A kind of independent pitch is away from rotor system |
| CN110816814A (en) * | 2019-12-09 | 2020-02-21 | 北京海空行科技有限公司 | Coaxial helicopter control-transmission system based on single automatic inclinator |
| CN111003164A (en) * | 2019-12-05 | 2020-04-14 | 吴佳艺 | Coaxial tilting three-rotor-blade helicopter |
| CN111065577A (en) * | 2017-08-23 | 2020-04-24 | 维曼机器人股份有限公司 | Driving mechanism |
| CN111252238A (en) * | 2020-03-17 | 2020-06-09 | 南京韬讯航空科技有限公司 | Variable-pitch rotor system module controlled by electric regulation and helicopter |
| CN111268096A (en) * | 2020-03-25 | 2020-06-12 | 湖南韬讯航空科技有限公司 | Steering engine-free variable-pitch rotor system module and helicopter |
| CN112173080A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Variable-pitch rotor wing structure and control method thereof |
-
2021
- 2021-11-19 CN CN202111391773.3A patent/CN113928540B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2090214A (en) * | 1980-08-13 | 1982-07-07 | Mckrill Nigel Howard | Controlling Helicopter Rotors |
| CN101376433A (en) * | 2008-10-10 | 2009-03-04 | 南京航空航天大学 | Helicopter rotor operation method and system |
| CN104139860A (en) * | 2014-04-23 | 2014-11-12 | 李晓宇 | Multi-shaft rotor aircraft and transmission mechanism thereof |
| FR3040687A3 (en) * | 2015-09-04 | 2017-03-10 | Hung-Fu Lee | HELICOPTER WITH MULTIPLE ROTORS OF NOT VARIABLE |
| CN111065577A (en) * | 2017-08-23 | 2020-04-24 | 维曼机器人股份有限公司 | Driving mechanism |
| CN208544421U (en) * | 2018-06-14 | 2019-02-26 | 南京航空航天大学 | A kind of independent pitch is away from rotor system |
| CN108995793A (en) * | 2018-09-03 | 2018-12-14 | 南京航空航天大学 | A kind of rotary wing changing is away from system |
| CN111003164A (en) * | 2019-12-05 | 2020-04-14 | 吴佳艺 | Coaxial tilting three-rotor-blade helicopter |
| CN110816814A (en) * | 2019-12-09 | 2020-02-21 | 北京海空行科技有限公司 | Coaxial helicopter control-transmission system based on single automatic inclinator |
| CN111252238A (en) * | 2020-03-17 | 2020-06-09 | 南京韬讯航空科技有限公司 | Variable-pitch rotor system module controlled by electric regulation and helicopter |
| CN111268096A (en) * | 2020-03-25 | 2020-06-12 | 湖南韬讯航空科技有限公司 | Steering engine-free variable-pitch rotor system module and helicopter |
| CN112173080A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Variable-pitch rotor wing structure and control method thereof |
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| Publication number | Publication date |
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| CN113928540B (en) | 2023-10-27 |
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