CN112224404A - Oversleeve structure for foldable bearingless rotor wing - Google Patents
Oversleeve structure for foldable bearingless rotor wing Download PDFInfo
- Publication number
- CN112224404A CN112224404A CN202011114443.5A CN202011114443A CN112224404A CN 112224404 A CN112224404 A CN 112224404A CN 202011114443 A CN202011114443 A CN 202011114443A CN 112224404 A CN112224404 A CN 112224404A
- Authority
- CN
- China
- Prior art keywords
- section
- root
- typical
- flexible beam
- foldable
- 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
- 230000007704 transition Effects 0.000 claims abstract description 36
- 230000001681 protective effect Effects 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 7
- 238000005520 cutting process Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- 230000003247 decreasing effect Effects 0.000 claims 1
- 238000013461 design Methods 0.000 description 5
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/48—Root attachment to rotor head
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a cuff structure for a foldable bearingless rotor wing, which comprises a root connecting section, a typical section and an end connecting section, wherein the root connecting section is transited with the typical section through the root transition section, and the typical section is transited with the end connecting section through the end transition section; the root connecting section is symmetrically provided with first mounting interfaces for connecting with a shimmy damper, the front edge is provided with a second mounting interface for connecting with a variable-pitch rocker arm, and the cross section of the root connecting section is in a rounded rectangle shape; the cross section of the typical section is rectangular with two ends in arc structures, and the inner diameter of the typical section is determined by the maximum shape change of a flexible beam assembled in the typical section; the front end part of the end part connecting section is of a pair of plate-shaped structures arranged at intervals, and the upper surface and the lower surface of the end part connecting section are provided with a first connecting interface used for connecting the end part of the flexible beam and a second connecting interface used for connecting the paddle; the oversleeve structure has the characteristics of small size and small pneumatic resistance.
Description
Technical Field
The invention belongs to the technical field of structural design of helicopter rotor systems, and particularly relates to a sleeve configuration for a foldable bearingless rotor.
Background
In the prior art, the structure form of integrating a flexible beam, a sleeve and a blade is as that of an air passenger helicopter company H135; although the number of parts of the H135 is the minimum, the rotor wing can be folded at the root part of the flexible beam, the size of the folded rotor wing is larger, the integral structural form of the flexible beam, the sleeve and the blade is not easy to carry out visual inspection, the position for installing the dynamic balance weight needs to be additionally designed, the operation of workers needs to be considered for installing the dynamic balance weight, and the dynamic balance weight cannot be arranged at the side close to the blade tip with higher efficiency;
the structure form is that the flexible beam, the paddle and the sleeve are separated like the MD900, and the three pieces are connected together through two bolts; the MD900 connecting bolt needs to be compatible with the installation of the rotor dynamic balance weight plate, and is not beneficial to the development of folding. The flexible beams like Bell430 are designed into a pair and are directly arranged on the rotor shaft; the flexible beam form of Bell430, while reducing the number of parts, does not provide the folding function.
In recent years, in order to improve the folding performance of a bearingless rotor wing, a hollow straight company also adopts a structural form of split design of a flexible beam, a sleeve and a blade on the H145, the flexible beam and the blade are connected and loaded together through a hollow main bearing bolt capable of placing a counterweight, the connection form of a single bolt has certain risk, the structure of the H145 connection part is very complex, the processing requirement of the interface part is too high, and the production and maintenance are not facilitated; the folding of the paddle is convenient in implementation due to the structural form that the flexible beams are connected with the oversleeves through two bolts, the paddle is connected with the oversleeves through two pins, but the folding form of the AH-1Z is only two front and two back ways, and the size after folding is larger than that of a mode that 4 pieces are folded backwards.
Because of technical blockade, the sleeve of the foreign bearingless rotor is difficult to obtain the detailed technical details and obtain the substantive reference; some domestic bearingless sleeves cannot be used for foldable bearingless rotors, and the design requirements cannot be met.
Disclosure of Invention
The invention aims to provide a sleeve configuration for a foldable bearingless rotor wing, which is used for solving the problem that the existing bearingless sleeve cannot be used for the foldable bearingless rotor wing and cannot meet the design requirement.
In order to realize the task, the invention adopts the following technical scheme:
a cuff configuration for a foldable bearingless rotor, comprising a root connecting section, a typical section and an end connecting section, wherein the root connecting section is transited to the typical section through the root transition section, and the typical section is transited to the end connecting section through the end transition section;
the middle parts of the outer edges of the upper surface and the lower surface of the root connecting section are protruded towards one side of the root, and first mounting interfaces for connecting with a shimmy damper are symmetrically arranged; the front edge of the root connecting section is provided with a second mounting interface for connecting with a variable-pitch rocker arm, and the cross section of the root connecting section is in a rounded rectangle shape;
the cross section of the typical section is rectangular with two ends in arc structures, the inner diameter of the typical section is determined by the maximum shape change of a flexible beam assembled in the typical section, and the distance between the flexible beam and the inner wall of the typical section is not smaller than a set minimum gap and not larger than a maximum gap under any working condition;
the front end part of the end part connecting section is a pair of plate-shaped structures arranged at intervals, and the front edge and the rear edge of each plate-shaped structure are subjected to arc-shaped cutting treatment; the upper surface and the lower surface of the end connecting section are provided with a first connecting interface used for connecting the end part of the flexible beam and a second connecting interface used for connecting the paddle.
Further, the root transition section is in linear transition, the outer diameter of the root transition section is gradually reduced from the root to the end, and the cross section shape of the root transition section is changed to a rectangle with an arc-shaped structure at two ends and excellent pneumatic performance from a fillet rectangle convenient to mount from the root to the end.
Further, the cross section of the root part of the end transition section is rectangular with two ends in arc structures, and the end part of the end transition section is in smooth transition with the end connecting section.
Further, when the cuff configuration is installed on the rotor, from 0.04R to 0.06R is the root connection segment, from 0.06R to 0.07R is the root transition segment, from 0.07R to 0.18R is the typical segment, from 0.18R to 0.20R is the end transition segment, from 0.20R to 0.23R is the end connection segment;
where R denotes the blade radius of the rotor, and 0.04R denotes a distance of 0.04R from the center of rotation of the blade.
Furthermore, the height of the root connecting section is H, and the height of a typical section is 0.6-0.7H.
Further, the front edge and the rear edge of the root of the end connecting section are provided with interfaces for mounting an anti-collision sheet, and the front edge of the typical section is coated with a protective belt.
Furthermore, the oversleeve structure is internally used for penetrating through the flexible beam, two sides of a pair of first mounting interfaces on the root connecting section are respectively provided with a shimmy damper, the shimmy dampers are connected through a curved rod, and the curved rod penetrates through a damper mounting hole on the flexible beam; the end part of the flexible beam is fixed on the first connecting interface, and the other end of the flexible beam is finally connected to the central piece of the propeller hub after passing through the curved rod, so that the connection with the fuselage is realized.
Furthermore, when the pitch is changed, the pitch-changing pull rod transmits the load to the pitch-changing rocker arm, the pitch-changing rocker arm transmits the load to the oversleeve structure, and the oversleeve structure is a rigid structure, so that when the oversleeve is twisted, the paddle is driven to be twisted, and the twisting function is realized; meanwhile, in the sleeve twisting process, a twisting angle input is applied to the flexible beam through the first connecting interface connected with the flexible beam; the flexible beam part inside generates torsional deformation, realizes the function of torsional hinge, unloads the torque, and avoids the torque from being transmitted to the central piece.
Compared with the prior art, the invention has the following technical characteristics:
the present invention provides a high performance cuff configuration for a foldable bearingless rotor, which can be used with a foldable bearingless rotor with low aerodynamic drag. Reference may be made to the configuration of this cuff during the design of other bearingless rotor cuffs.
Drawings
FIG. 1 is a schematic overall structural view of a cuff configuration provided in accordance with one embodiment of the present invention;
FIG. 2 is a schematic top view of a cuff configuration according to an embodiment of the present invention;
figure 3 is a schematic view of the twist distribution of the cuff configuration provided by one embodiment of the present invention.
The reference numbers in the figures illustrate: the anti-collision device comprises a root connecting section 1, a first installation interface 2, a second installation interface 3, a root transition section 4, a typical section 5, a protective belt 6, an end transition section 7, an end connecting section 8, a first connection interface 9, a second connection interface 10 and an anti-collision sheet 11.
Detailed Description
Referring to fig. 1-3, the present invention discloses a cuff configuration for a foldable bearingless rotor for transmitting the operating force of a pitch link to a main blade, providing a flapping arm outer profile, transmitting part of the load of the main blade to a flexible beam, the relative motion of the cuff root and the flexible beam causing the damper to undergo shear deformation to provide damping, bearing all the load from the blade during blade folding. The cuff configuration proposed by the present invention comprises a root connection segment 1, a representative segment 5 and an end connection segment 8, wherein the root connection segment 1 and the representative segment 5 are transitioned by a root transition segment 4, and the representative segment 5 and the end connection segment 8 are transitioned by an end transition segment 7. Wherein:
the root attachment section 1 has a profile from 0.04R to 0.23R, where R denotes the blade radius of the rotor and 0.04R denotes a distance of 0.04R from the center of rotation of the blade, the same applies below. The middle parts of the outer edges of the upper surface and the lower surface of the root connecting section 1 are protruded towards one side of the root, the shape of the protrusion can adapt to the installation part of the rotor wing, and first installation interfaces 2 for connecting with a shimmy damper are symmetrically arranged at the protruded parts; the front edge of the root connecting section 1 is provided with a second mounting interface 3 for connecting with a variable-pitch rocker arm; the cross section of the root connecting section 1 is in a round corner rectangle, and the radius of the round corner is 28 mm; the root connecting section 1 has a chord-wise length of 0.0375R and a height of 0.0258R. The side wall of the root connecting section 1 is thin-walled and its thickness is less than 1/10 of its cross-sectional length (distance between the leading edge and the trailing edge).
The root transition section 4 is in linear transition from 0.06R to 0.07R, the outer diameter of the root transition section 4 is gradually reduced from the root to the end, the shape of the cross section is gradually changed from the root to the end, and the cross section is changed from a rounded rectangle convenient to mount to a rectangle (similar to an ellipse, two ends of the rectangle are replaced by two ends of the ellipse) with arc-shaped structures at two ends and excellent pneumatic performance, wherein the shape of the rectangle is similar to a standard runway; wherein, the chord-wise length of the end part of the root transition section 4 is 0.0379R, and the height thereof is 0.0222R.
The typical section 5 is from 0.07R to 0.18R, the cross section of the typical section 5 is rectangular with arc-shaped structures at two ends, the inner diameter of the typical section 5 is gradually increased from the root part to the end part, the chord length at the end part is 0.0322R, and the height is 0.0155R; the inner diameter of the typical section 5 is determined by the maximum shape change of a flexible beam assembled in the typical section, and the distance between the flexible beam and the inner wall of the typical section 5 is not less than the set minimum clearance and not more than the maximum clearance under any working condition; wherein the minimum clearance can be 3-5 mm; the maximum gap is 7-9 mm, so that the pneumatic resistance generated by the oversleeves is reduced as much as possible on the premise that the flexible beams and the oversleeves cannot generate movement interference under various working conditions; the shimmy and flap ranges of the flexible beam under different working conditions can be measured through experiments, tests and other modes, so that the structure of the typical section 5 is determined. A protective belt 6 is arranged at the front edge of the typical section 5, the protective belt 6 can be made of polyurethane, the front edge of the sleeve is protected (the length of the protective belt is basically consistent with that of the typical section 5), when the sleeve works in a sand environment, a protective screen is added, and the protective belt 6 can be replaced after being damaged. The height of the root connecting section 1 is recorded as H (the distance between the two first mounting interfaces 2), and the height of the typical section 5 is 0.6-0.7H.
The end transition section 7 is from 0.18R to 0.20R, the cross section of the root part of the end transition section 7 is rectangular with arc-shaped structures at two ends, and the end part of the end transition section is in smooth transition with the end connecting section 8; i.e. from the oval-like configuration of the exemplary section 5 to a flat configuration with suitably joined ends.
The end connecting section 8 is from 0.20R to 0.23R, the front end part of the end connecting section 8 is a pair of plate-shaped structures which are arranged at intervals, and the front edge and the rear edge of each plate-shaped structure are subjected to arc-shaped cutting treatment to optimize the appearance, reduce the weight of the structure and also play a role in facilitating connection and installation; the upper surface and the lower surface of the end connecting section 8 are provided with a first connecting interface 9 for connecting the end of the flexible beam and a second connecting interface 10 for connecting the blade. The front edge and the rear edge of the root part of the end connecting section 8 are both provided with interfaces for mounting the anti-collision sheet 11, and after the anti-collision sheet 11 is mounted, the anti-collision sheet 11 can play a role in buffering and anti-collision after the oversleeve is folded; the bumper plate 11 may be made of a material such as rubber.
In the scheme, the torsion ratio of a linear transition section between the 0.06R section and the 0.18R section is 72.9 degrees/R.
The oversleeve structure is internally used for penetrating through the flexible beam, two sides of a pair of first mounting interfaces 2 on the root connecting section 1 are respectively provided with a shimmy damper, the shimmy dampers are connected through a curved rod, and the curved rod penetrates through a damper mounting hole on the flexible beam; the end of the flexible beam is fixed to the first connection interface 9, and the other end of the flexible beam passes through the curved rod and is finally connected to the central part of the hub, so that the connection with the fuselage is realized.
When the pitch is changed, the pitch-changing pull rod transmits the load to the pitch-changing rocker arm, the pitch-changing rocker arm transmits the load to the oversleeve configuration, and the oversleeve configuration is a rigid structure, so that when the oversleeve is twisted, the paddle is driven to be twisted, and the twisting function is realized; meanwhile, in the sleeve twisting process, a twisting angle input is applied to the flexible beam through the first connecting interface 9 connected with the flexible beam; the flexible beam part inside generates torsional deformation, realizes the function of torsional hinge, unloads the torque, and avoids the torque from being transmitted to the central piece.
According to the oversleeve structure provided by the invention, the core component flexible beam of the bearingless rotor wing is arranged in the cavity inside the oversleeve structure, so that the aerodynamic resistance of the whole rotor wing can be reduced in the aspect of aerodynamics; considering from the structure self, can accomplish the size minimum under the prerequisite of guaranteeing not to take place to interfere with flexible roof beam.
The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equally replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application, and are intended to be included within the scope of the present application.
Claims (8)
1. A cuff configuration for a foldable bearingless rotor, characterized by comprising a root connection section (1), a typical section (5) and an end connection section (8), wherein the root connection section (1) transitions with the typical section (5) through a root transition section (4) and the typical section (5) transitions with the end connection section (8) through an end transition section (7);
the middle parts of the outer edges of the upper surface and the lower surface of the root connecting section (1) are protruded towards one side of the root, and first mounting interfaces (2) for connecting with a shimmy damper are symmetrically arranged; the front edge of the root connecting section (1) is provided with a second mounting interface (3) for connecting with a variable-pitch rocker arm, and the cross section of the root connecting section (1) is in a round-corner rectangle shape;
the cross section of the typical section (5) is rectangular with two ends in arc structures, the inner diameter of the typical section (5) is determined by the maximum shape change of a flexible beam assembled in the typical section, and the distance between the flexible beam and the inner wall of the typical section (5) is not smaller than the set minimum clearance and not larger than the maximum clearance under any working condition;
the front end part of the end part connecting section (8) is a pair of plate-shaped structures arranged at intervals, and the front edge and the rear edge of each plate-shaped structure are subjected to arc-shaped cutting treatment; the upper surface and the lower surface of the end connecting section (8) are provided with a first connecting interface (9) for connecting the end part of the flexible beam and a second connecting interface (10) for connecting the blade.
2. A cuff configuration for a foldable bearingless rotor according to claim 1, wherein said root transition section (4) is a linear transition with a decreasing outer diameter from root to tip, and a cross-sectional shape from root to tip from a rounded rectangle for easy installation to a rectangle with an arc-shaped configuration at both ends with excellent aerodynamic performance.
3. A cuff configuration for a foldable bearingless rotor according to claim 1, wherein the cross-sectional shape of the root of the end transition section (7) is rectangular with two ends in an arc configuration, the ends of which transition smoothly with the end connection section (8).
4. A cuff configuration for a foldable bearingless rotor according to claim 1, characterized in that when the cuff configuration is mounted on the rotor, from 0.04R to 0.06R is the root connecting section (1), from 0.06R to 0.07R is the root transition section (4), from 0.07R to 0.18R is the typical section (5), from 0.18R to 0.20R is the end transition section (7), from 0.20R to 0.23R is the end connecting section (8);
where R denotes the blade radius of the rotor, and 0.04R denotes a distance of 0.04R from the center of rotation of the blade.
5. A cuff configuration for a foldable bearingless rotor according to claim 1, characterized in that the height of the root connecting section (1) is H, whereas the height of a typical section (5) is 0.6-0.7H.
6. A cuff configuration for a foldable bearingless rotor according to claim 1, characterized in that the leading edge, the trailing edge of the root of said end connection section (8) is provided with an interface for mounting of a fender (11), the leading edge of said typical section (5) is coated with a protective strip (6).
7. A cuff configuration for a foldable bearingless rotor according to claim 1, wherein the cuff configuration is internally used for passing through a flexible beam, a shimmy damper is respectively arranged at two sides of a pair of first mounting interfaces (2) on the root connecting section (1), the shimmy dampers are connected through a curved rod, and the curved rod passes through a damper mounting hole on the flexible beam; the end of the flexible beam is fixed to the first connecting interface (9), and the other end of the flexible beam is connected to a central piece of the hub after passing through the curved rod, so that the connection with the fuselage is realized.
8. The cuff configuration for a foldable bearingless rotor of claim 1 wherein during the pitch change, the pitch link transfers the load to the pitch change rocker, which transfers the load to the cuff configuration, which, because the cuff configuration is a rigid structure, drives the blades to twist when the cuff twists, achieving the twisting function; meanwhile, in the sleeve twisting process, a twisting angle input is applied to the flexible beam through a first connecting interface (9) connected with the flexible beam; the flexible beam part inside generates torsional deformation, realizes the function of torsional hinge, unloads the torque, and avoids the torque from being transmitted to the central piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011114443.5A CN112224404A (en) | 2020-10-16 | 2020-10-16 | Oversleeve structure for foldable bearingless rotor wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011114443.5A CN112224404A (en) | 2020-10-16 | 2020-10-16 | Oversleeve structure for foldable bearingless rotor wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112224404A true CN112224404A (en) | 2021-01-15 |
Family
ID=74118822
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011114443.5A Pending CN112224404A (en) | 2020-10-16 | 2020-10-16 | Oversleeve structure for foldable bearingless rotor wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112224404A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928552A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter bearingless rotor oversleeve with light weight |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1172750A (en) * | 1996-07-18 | 1998-02-11 | 西科尔斯基飞机公司 | Optimized composite flexbeam for helicopter rotors |
| EP1238906A1 (en) * | 2001-03-06 | 2002-09-11 | Bell Helicopter Textron Inc. | Multi-bladed tail rotor hub design for Coriolis relief |
| KR20130078482A (en) * | 2011-12-30 | 2013-07-10 | 한국항공우주연구원 | Bearingless main rotor hub system |
| EP2653385A1 (en) * | 2012-04-18 | 2013-10-23 | Eurocopter Deutschland GmbH | Aerodynamic blade attachment for a bearingless rotor of a helicopter |
| CN103373467A (en) * | 2012-04-18 | 2013-10-30 | 尤洛考普特德国有限公司 | Blade attachment for a bearingless rotor of a helicopter |
| EP2727861A1 (en) * | 2012-11-06 | 2014-05-07 | Takraf GmbH | Method for adjusting the position of the electric motor to the position of the drive drum of a direct drive for a belt conveyor assembly |
| US20140241885A1 (en) * | 2013-02-27 | 2014-08-28 | Airbus Helicopters Deutschland GmbH | Partly cruciform flexbeam and method of manufacturing such a flexbeam |
| CN104691755A (en) * | 2013-12-10 | 2015-06-10 | 空客直升机德国有限公司 | Beam for a rotorcraft rotor and rotorcraft rotor |
| EP2894093A1 (en) * | 2014-01-14 | 2015-07-15 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Flexbeam unit for a hingeless or a hinge- and bearingless multi-blade rotor of a rotary wing aircraft |
| EP2949579A1 (en) * | 2014-05-28 | 2015-12-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Flexbeam unit with at least one twisted flexbeam element |
| CN106741860A (en) * | 2016-12-30 | 2017-05-31 | 中航维拓（天津）科技有限公司 | A kind of oil based on composite moves many rotor flexible rotor systems |
| CN109506862A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | A kind of flexible beam tail-rotor leaf stiffness test device |
| CN109533317A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of rigid rotor propeller shank configuration |
-
2020
- 2020-10-16 CN CN202011114443.5A patent/CN112224404A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1172750A (en) * | 1996-07-18 | 1998-02-11 | 西科尔斯基飞机公司 | Optimized composite flexbeam for helicopter rotors |
| EP1238906A1 (en) * | 2001-03-06 | 2002-09-11 | Bell Helicopter Textron Inc. | Multi-bladed tail rotor hub design for Coriolis relief |
| KR20130078482A (en) * | 2011-12-30 | 2013-07-10 | 한국항공우주연구원 | Bearingless main rotor hub system |
| EP2653385A1 (en) * | 2012-04-18 | 2013-10-23 | Eurocopter Deutschland GmbH | Aerodynamic blade attachment for a bearingless rotor of a helicopter |
| CN103373467A (en) * | 2012-04-18 | 2013-10-30 | 尤洛考普特德国有限公司 | Blade attachment for a bearingless rotor of a helicopter |
| EP2727861A1 (en) * | 2012-11-06 | 2014-05-07 | Takraf GmbH | Method for adjusting the position of the electric motor to the position of the drive drum of a direct drive for a belt conveyor assembly |
| US20140241885A1 (en) * | 2013-02-27 | 2014-08-28 | Airbus Helicopters Deutschland GmbH | Partly cruciform flexbeam and method of manufacturing such a flexbeam |
| CN104691755A (en) * | 2013-12-10 | 2015-06-10 | 空客直升机德国有限公司 | Beam for a rotorcraft rotor and rotorcraft rotor |
| EP2894093A1 (en) * | 2014-01-14 | 2015-07-15 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Flexbeam unit for a hingeless or a hinge- and bearingless multi-blade rotor of a rotary wing aircraft |
| EP2949579A1 (en) * | 2014-05-28 | 2015-12-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Flexbeam unit with at least one twisted flexbeam element |
| CN106741860A (en) * | 2016-12-30 | 2017-05-31 | 中航维拓（天津）科技有限公司 | A kind of oil based on composite moves many rotor flexible rotor systems |
| CN109506862A (en) * | 2018-11-12 | 2019-03-22 | 中国直升机设计研究所 | A kind of flexible beam tail-rotor leaf stiffness test device |
| CN109533317A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of rigid rotor propeller shank configuration |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928552A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter bearingless rotor oversleeve with light weight |
| CN113928552B (en) * | 2021-11-19 | 2023-04-28 | 中国直升机设计研究所 | Lightweight bearingless rotor sleeve of helicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4189121A (en) | Variable twist leading edge flap | |
| US6024325A (en) | Rotor for rotary wing aircraft | |
| US9453516B2 (en) | Blade rotary assembly with aerodynamic outer toroid spoiler for a shrouded propulsion rotary assembly | |
| CN103373467B (en) | Blade attachment for helicopter bearingless rotor | |
| CN104129499B (en) | For duct rotor and the rotor craft of aircraft | |
| US10625847B2 (en) | Split winglet | |
| US20050133672A1 (en) | Wing tip device | |
| GB2533413A (en) | Lifting Surfaces | |
| JPH0523240B2 (en) | ||
| CN109533317B (en) | Rigid rotor blade root structure | |
| WO1998030446A2 (en) | Variable pitch aircraft propeller | |
| WO1998030446A9 (en) | Variable pitch aircraft propeller | |
| GB2425998A (en) | Low noise airfoil, eg cascade rotor blade for helicopters | |
| EP1531126A1 (en) | Wing tip device | |
| KR20120118427A (en) | Active gurney flap | |
| KR102055015B1 (en) | Active gurney flap | |
| CN103770939B (en) | Divided blade attachment for the bearingless rotor of helicopter | |
| JPH04293695A (en) | Low noise type tail section rotor | |
| CN105966600B (en) | One kind can continuous modification drag rudder | |
| CN112224404A (en) | Oversleeve structure for foldable bearingless rotor wing | |
| CN112224445A (en) | Oversleeve of perspective inspection flexible beam | |
| CN216536915U (en) | Blade tip structure, rotor blade, wind turbine, wind farm and aircraft | |
| CN116848319A (en) | Pitch control wind turbine with blade connection members | |
| CN108216572A (en) | A kind of more bent shaft-driven flexible aerofoil component and with its wing | |
| CN102700711A (en) | Layout for hydraulic shimmy damper of rotor wing of helicopter |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210115 |