CN112419832A - Upper rotor control mechanism for coaxial helicopter model rotor test - Google Patents
Upper rotor control mechanism for coaxial helicopter model rotor test Download PDFInfo
- Publication number
- CN112419832A CN112419832A CN202011316876.9A CN202011316876A CN112419832A CN 112419832 A CN112419832 A CN 112419832A CN 202011316876 A CN202011316876 A CN 202011316876A CN 112419832 A CN112419832 A CN 112419832A
- Authority
- CN
- China
- Prior art keywords
- hub
- support rod
- guide cylinder
- automatic
- rotor
- 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.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/46—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer the aircraft being a helicopter
Abstract
The invention belongs to the technical field of rotor wing tests, and discloses an upper rotor wing control mechanism for a coaxial helicopter model rotor wing test, which is arranged in an upper hub, a support rod is fixed on a non-rotating structure below the hub, and the lower end of a guide cylinder is fixed on a support rod base; the automatic inclinator is connected to the guide cylinder; the outer ring of the automatic inclinator is provided with a movable ring, the movable ring is provided with a plurality of U-shaped grooves, each U-shaped groove is connected with one end of a pull rod, and the other end of one pull rod is connected with one end of a paddle; the rotating ring is also provided with at least one connecting structure, the connecting structure is connected with one end of the anti-torsion arm, and the other end of the anti-torsion arm is connected to the propeller hub; the fixed end of the actuator is connected to the bottom of the guide cylinder, and the actuating end of the actuator is connected to the fixed ring of the automatic inclinator. The anti-torsion arm drives the automatic tilter to move together with the hub, and the rotor wing system is operated by different displacement states of the actuating cylinder, so that the purpose of operating the rotor wing is achieved.
Description
Technical Field
The invention belongs to the technical field of rotor wing tests, and particularly relates to an upper rotor wing control mechanism for a coaxial helicopter model rotor wing test.
Background
With the development of helicopter technology, various helicopter configurations are in progress, and coaxial helicopters are typical representatives of the new helicopter configurations.
In the flying process of the helicopter, due to the rotation of the rotor and the influence of the air flow flying forwards in the flying process, the rotor blades are in a periodic motion, and the periodic motion determines that the rotor of the helicopter can be used as a lifting surface and a control surface of the helicopter. The operating mechanism of the rotor is particularly important in order to realize the cyclic movement of the blades.
The conventional single-rotor helicopter is generally operated below the hub, and the helicopter rotor can be conveniently operated. The steering of the coaxial helicopter may be a stick-system steering, such as the russian ka series helicopters, but all of the stick-systems are in the wind field, increasing the hub drag.
Disclosure of Invention
In view of the above-mentioned problems in the prior art, it is an object of the present invention to provide an upper rotor manipulating mechanism for a helicopter model rotor test, which achieves the purpose of rotor manipulation by supporting and fixing an automatic tilter in a hub, driving the automatic tilter to move with the hub through an anti-torsion arm, and applying manipulation to a rotor system through different displacement states of a ram.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
An upper rotor operating mechanism for a coaxial helicopter model rotor test, the upper rotor operating mechanism disposed within an upper hub, said mechanism comprising: the device comprises a support rod 1, a guide cylinder 2, an actuator 3, an automatic inclinator 4, an anti-torsion arm 5 and a pull rod 6;
the lower end of the guide cylinder is fixedly connected to a base of the support rod 1 through a pin;
the automatic inclinator 4 is connected to the guide cylinder through a flat key; the outer ring of the automatic inclinator 4 is provided with a movable ring, the movable ring is provided with a plurality of U-shaped grooves, each U-shaped groove is connected with one end of a pull rod, and the other end of the pull rod is connected with one end of a paddle; the rotating ring is also provided with at least one connecting structure, the connecting structure is connected with one end of the anti-torsion arm 5, and the other end of the anti-torsion arm 5 is connected to the hub;
the fixed end of the actuator 3 is connected to the bottom of the guide cylinder, the actuating end of the actuator 3 is connected to the fixed ring of the automatic inclinator 4, and the fixed ring is arranged at the bottom of the automatic inclinator 4.
The upper rotor wing control mechanism is arranged in the upper propeller hub, so that the control of blades of the upper propeller hub is realized, the integral structure is compact, and the aerodynamic appearance of the helicopter is not influenced.
The technical scheme of the invention has the characteristics and further improvements that:
(1) the number of the actuating cylinders is three, and the three actuating cylinders are respectively connected to three fixed rings of the automatic inclinator 4.
(2) The automatic recliner 4 moves up and down along the flat keys on the guide cylinders under the common upward or common downward force of the three rams.
The attack angle of the blades is changed through the combined action of the actuating cylinders, so that the helicopter can complete the flight of various postures.
(3) The automatic tilter 4 is fixed in the propeller hub through the supporting rod 1, the automatic tilter is driven to move together with the propeller hub through the torsion-proof arm 5, and the blades of the upper rotor wing are operated through different displacement states of the actuating cylinder.
(4) The support rod 1 is a hollow structure for connecting a signal line on the blade to a test device.
(5) The upper part of the support rod 1 is provided with threads, and the upper part of the guide cylinder 2 is fixed on the support rod 1 through the threads.
The lower end of the guide cylinder is fixedly connected to the base of the support rod 1 through a pin; the upper part of the guide cylinder 2 is fixed on the support rod 1 through threads. The whole disassembly of the operating mechanism is facilitated.
(6) The same position of the bottom of the support rod 1 and the bottom of the guide cylinder 2 is provided with a through hole for leading a power supply and a control cable on the machine to an actuator.
(7) The mechanism further comprises: a cover plate; the cover plate is disposed on the hub.
The invention provides an upper rotor wing control mechanism device for a coaxial helicopter model rotor wing test, which mainly comprises a support rod, a guide cylinder, an actuator, an automatic tilter, an anti-torsion arm, a pull rod and the like. The automatic inclinator is placed inside the propeller hub, and the variable-pitch control of the rotor wing is realized by adding the non-rotating supporting rod.
Drawings
FIG. 1 is a schematic structural diagram of an upper rotor operating mechanism for a coaxial helicopter model rotor test according to an embodiment of the present invention;
the device comprises a support rod 1, a guide cylinder 2, an actuator 3, an automatic inclinator 4, a torsion-proof arm 5 and a pull rod 6.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
An embodiment of the present invention provides an upper rotor maneuvering mechanism for a helicopter model rotor test, where as shown in fig. 1, the upper rotor maneuvering mechanism is disposed inside an upper hub, and the mechanism includes: the device comprises a support rod 1, a guide cylinder 2, an actuator 3, an automatic inclinator 4, an anti-torsion arm 5 and a pull rod 6;
the lower end of the guide cylinder is fixedly connected to a base of the support rod 1 through a pin;
the automatic inclinator 4 is connected to the guide cylinder through a flat key; the outer ring of the automatic inclinator 4 is provided with a movable ring, the movable ring is provided with a plurality of U-shaped grooves, each U-shaped groove is connected with one end of a pull rod, and the other end of the pull rod is connected with one end of a paddle; the rotating ring is also provided with at least one connecting structure, the connecting structure is connected with one end of the anti-torsion arm 5, and the other end of the anti-torsion arm 5 is connected to the hub;
the fixed end of the actuator 3 is connected to the bottom of the guide cylinder, the actuating end of the actuator 3 is connected to the fixed ring of the automatic inclinator 4, and the fixed ring is arranged at the bottom of the automatic inclinator 4.
The upper rotor wing control mechanism is arranged in the upper propeller hub, so that the control of blades of the upper propeller hub is realized, the integral structure is compact, and the aerodynamic appearance of the helicopter is not influenced.
The number of the actuating cylinders is three, and the three actuating cylinders are respectively connected to three fixed rings of the automatic inclinator 4.
The automatic recliner 4 moves up and down along the flat keys on the guide cylinders under the common upward or common downward force of the three rams.
The attack angle of the blades is changed through the combined action of the actuating cylinders, so that the helicopter can complete the flight of various postures.
The automatic tilter 4 is fixed in the propeller hub through the supporting rod 1, the automatic tilter is driven to move together with the propeller hub through the torsion-proof arm 5, and the blades of the upper rotor wing are operated through different displacement states of the actuating cylinder.
The support rod 1 is a hollow structure for connecting a signal line on the blade to a test device.
The upper part of the support rod 1 is provided with threads, and the upper part of the guide cylinder 2 is fixed on the support rod 1 through the threads.
The lower end of the guide cylinder is fixedly connected to the base of the support rod 1 through a pin; the upper part of the guide cylinder 2 is fixed on the support rod 1 through threads. The whole disassembly of the operating mechanism is facilitated.
The same position of the bottom of the support rod 1 and the bottom of the guide cylinder 2 is provided with a through hole for leading a power supply and a control cable on the machine to an actuator.
The mechanism further comprises: a cover plate; the cover plate is disposed on the hub.
The upper rotor wing control mechanism device for the coaxial helicopter model rotor wing test mainly comprises a support rod, a guide cylinder, an actuator, an automatic tilter, a torsion-proof arm, a pull rod and the like, wherein the automatic tilter is fixed in a hub through the support, the automatic tilter is driven to move together with the hub through the torsion-proof arm, and the control is applied to a rotor wing system through different displacement states of the actuator cylinder, so that the aim of controlling the coaxial upper rotor wing is fulfilled.
When the rotor rotates, the three actuating cylinders are fixed on the non-rotating supporting rod, the actuating cylinders generate different displacements to enable the fixed ring of the tilter to tilt according to a set angle, the movable ring of the automatic tilter is connected with the hub through the anti-torsion arm, the hub drives the blades to move in a set angle plane, and the pull rod connected with the movable ring drives the blades to perform periodic variable pitch motion in a rotation period, so that the control of the rotor is realized. The supporting rod is connected with the rotating shaft through a bearing, so that the relative motion between the rotating shaft and the irrotational shaft is ensured, and the purpose of rotor operation is realized.
The invention has the advantages that: according to the upper rotor wing control mechanism device for the coaxial helicopter model rotor wing test, the automatic tilter is placed in the propeller hub, and the variable-pitch control of the rotor wing is realized by adding the non-rotating supporting rod.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. An upper rotor operating mechanism for a coaxial helicopter model rotor test, wherein the upper rotor operating mechanism is disposed within an upper hub, said mechanism comprising: the device comprises a support rod (1), a guide cylinder (2), an actuator (3), an automatic inclinator (4), a torsion-proof arm (5) and a pull rod (6);
the lower end of the guide cylinder is fixedly connected to a base of the support rod (1) through a pin;
the automatic inclinator (4) is connected to the guide cylinder through a flat key; the outer ring of the automatic inclinator (4) is provided with a movable ring, the movable ring is provided with a plurality of U-shaped grooves, each U-shaped groove is connected with one end of a pull rod, and the other end of the pull rod is connected with one end of a paddle; the movable ring is also provided with at least one connecting structure, the connecting structure is connected with one end of the anti-torsion arm (5), and the other end of the anti-torsion arm (5) is connected to the propeller hub;
the fixed end of the actuator (3) is connected to the bottom of the guide cylinder, the actuating end of the actuator (3) is connected to the fixed ring of the automatic inclinator (4), and the fixed ring is arranged at the bottom of the automatic inclinator (4).
2. An upper rotor operating mechanism for a coaxial helicopter model rotor test according to claim 1 wherein there are three rams connected to the three stationary rings of the automatic tilter (4).
3. An upper rotor operating mechanism for a coaxial helicopter model rotor test according to claim 2 wherein the automatic tilter (4) moves up and down along the flat key on the guide tube under the common upward or common downward force of the three rams.
4. An upper rotor operating mechanism for a coaxial helicopter model rotor test according to claim 3 characterized in that the autotilter (4) is fixed in the hub by the support rod (1) and is moved with the hub by the anti-twist arm (5) imparting manipulation to the blades of the upper rotor through different displacement states of the ram.
5. An upper rotor steering mechanism for a coaxial helicopter model rotor test according to claim 1 characterized in that the support rod (1) is a hollow structure used to connect the signal wires on the blades to the test fixture.
6. The upper rotor operating mechanism for the coaxial helicopter model rotor test is characterized in that the upper part of the support rod (1) is provided with threads, and the upper part of the guide cylinder (2) is fixed on the support rod (1) through the threads.
7. The upper rotor operating mechanism for the coaxial helicopter model rotor test is characterized in that the bottom parts of the support rod (1) and the guide cylinder (2) are provided with through holes at the same position for leading the power supply and the control cable on the helicopter to the actuator.
8. An upper rotor operating mechanism for a coaxial helicopter model rotor test according to claim 1 further comprising: a cover plate; the cover plate is disposed on the hub.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011316876.9A CN112419832A (en) | 2020-11-20 | 2020-11-20 | Upper rotor control mechanism for coaxial helicopter model rotor test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011316876.9A CN112419832A (en) | 2020-11-20 | 2020-11-20 | Upper rotor control mechanism for coaxial helicopter model rotor test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112419832A true CN112419832A (en) | 2021-02-26 |
Family
ID=74777939
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011316876.9A Pending CN112419832A (en) | 2020-11-20 | 2020-11-20 | Upper rotor control mechanism for coaxial helicopter model rotor test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112419832A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2890375A1 (en) * | 2005-09-08 | 2007-03-09 | Conservatoire Nat Arts | ROTARY VESSEL CONTROL ASSEMBLY |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN105070003A (en) * | 2015-05-18 | 2015-11-18 | 北京航空航天大学 | Coaxial helicopter rotor measurement signal transmission system |
| CN105217025A (en) * | 2015-11-09 | 2016-01-06 | 德奥通用航空股份有限公司 | A kind of aircraft coaxial double-rotary wing system |
| CN106915457A (en) * | 2017-02-22 | 2017-07-04 | 北京航空航天大学 | A kind of variable co-axial helicopter steerable system of upper and lower rotor inclinator depth of parallelism |
| CN209581869U (en) * | 2019-02-22 | 2019-11-05 | 江西希德防务系统技术有限公司 | A kind of coaxial double-rotary wing unmanned helicopter rotor mechanism |
-
2020
- 2020-11-20 CN CN202011316876.9A patent/CN112419832A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2890375A1 (en) * | 2005-09-08 | 2007-03-09 | Conservatoire Nat Arts | ROTARY VESSEL CONTROL ASSEMBLY |
| CN105070003A (en) * | 2015-05-18 | 2015-11-18 | 北京航空航天大学 | Coaxial helicopter rotor measurement signal transmission system |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN105217025A (en) * | 2015-11-09 | 2016-01-06 | 德奥通用航空股份有限公司 | A kind of aircraft coaxial double-rotary wing system |
| CN106915457A (en) * | 2017-02-22 | 2017-07-04 | 北京航空航天大学 | A kind of variable co-axial helicopter steerable system of upper and lower rotor inclinator depth of parallelism |
| CN209581869U (en) * | 2019-02-22 | 2019-11-05 | 江西希德防务系统技术有限公司 | A kind of coaxial double-rotary wing unmanned helicopter rotor mechanism |
Non-Patent Citations (1)
| Title |
|---|
| 李科伟等: "共轴直升机操纵技术与微小型化发展", 《无人系统技术》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5284794B2 (en) | Retractable lift blade for aircraft | |
| US7674091B2 (en) | Rotor blade pitch control | |
| JPH04502594A (en) | Helicopter individual blade control device | |
| US2818123A (en) | Rotary wing aircraft | |
| EP2851294B1 (en) | Rotorcraft rotor including primary pitch horns and secondary horns | |
| CN103534169B (en) | The method of work of flapping wing device and flapping wing device | |
| CN113386954A (en) | Upper and lower rotor independent control device of coaxial double-rotor helicopter | |
| US11053003B2 (en) | Cyclorotor thrust control, transmission and mounting system | |
| CN108438209B (en) | Cycloidal propeller eccentric circle control mechanism | |
| CN112419832A (en) | Upper rotor control mechanism for coaxial helicopter model rotor test | |
| KR100558462B1 (en) | A vertical takeoff and landing aircraft | |
| US3232348A (en) | Rotary wing aircraft | |
| KR100558463B1 (en) | A vertical takeoff and landing aircraft | |
| CN106168531A (en) | A kind of wind tunnel test rotor control mechanism | |
| CN113772118B (en) | Method for operating rotor mechanism of coaxial rigid double-rotor test bed | |
| CN215285253U (en) | Upper and lower rotor independent control device of coaxial double-rotor helicopter | |
| CN107031835B (en) | Rotor unmanned aerial vehicle becomes oar radius variable pitch device | |
| US2684212A (en) | Disk rotor with retracting blades for convertible aircraft | |
| CN107856849B (en) | Gyro disk propeller type vertical take-off and landing aircraft | |
| GB936789A (en) | Blade pitch control mechanism for a helicopter | |
| GB800890A (en) | Directional control system for rotary wing aircraft | |
| CN113734437B (en) | Automatic tilting device of electric helicopter | |
| US11958594B2 (en) | Cyclic pitch angle adjustment apparatus | |
| CN216916275U (en) | Top direct-drive rotor wing device | |
| CN116443296A (en) | Rotor wing variable-pitch control device based on 2-PUU+PSR parallel driving |
Legal Events
| 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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210226 |
|
| RJ01 | Rejection of invention patent application after publication |