CN113942640B - Inner control rotor wing supporting piece structure - Google Patents
Inner control rotor wing supporting piece structure Download PDFInfo
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- CN113942640B CN113942640B CN202111177064.5A CN202111177064A CN113942640B CN 113942640 B CN113942640 B CN 113942640B CN 202111177064 A CN202111177064 A CN 202111177064A CN 113942640 B CN113942640 B CN 113942640B
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 31
- 238000013461 design Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The application belongs to rotor support structural design field, discloses an interior manipulation rotor support structure. The method comprises the following steps of: hollow cylinder section, taper section, reinforcing rib section and circular ring section; the hollow cylindrical section is connected with the inner rotor shaft; the ring section is connected with the guide cylinder; the ring section is also connected with a torque arm assembly; the reinforcing rib section is connected with the rocker component. The lower end of the hollow cylindrical section is provided with a plurality of first bolt holes along the radial direction, and a shoulder bushing is arranged in each first bolt hole; the hollow cylindrical section is connected with the inner rotor shaft through bolts; the thickness of the bolt hole area of the hollow cylindrical section is thickest, the thickness of the annular area of the hollow cylindrical section close to the upper end face is inferior, and the thickness of the rest part of the hollow cylindrical section is thinnest. The support structure has a multifunctional structure: the rotor shaft connecting device has the advantages of realizing the functions of quick and simple connection with a rotor shaft, connection with a rocker assembly, connection with a guide cylinder and connection with a torque arm assembly.
Description
Technical Field
The invention belongs to the field of rotor support structure design, and discloses an inner control rotor support structure.
Background
The coaxial double-rotor helicopter has the characteristics of high flying speed, high hovering efficiency, good maneuverability, low noise and the like, can effectively enhance the overall combat capability of armies, improve the maneuvering assault capability in the air and improve the battlefield survivability, and is an important direction for the future development of the helicopter. The coaxial helicopter has two rotors, and two sets of automatic inclinators are used for respectively operating the two sets of rotors. The upper rotor wing automatic inclinator of the coaxial helicopter is of an inner control structure. The whole control system is positioned in the rotor shaft of the helicopter, compared with the conventional external control helicopter, the pneumatic interference of the external control variable-pitch pull rod is eliminated, the windward area is smaller, the waste resistance of the rotor system in flight can be effectively reduced, and the performance of the helicopter is improved, so that the internal control configuration is widely applied to coaxial helicopters of different models.
The steering gear of the upper rotor is located outside the rotor shaft, and the steering command needs to be transmitted in the inner rotor shaft, so that the steering command outside the rotor shaft needs to be transmitted into the rotor shaft in order to realize the inner steering of the rotor, and therefore, a support piece for the inner steering rotor needs to be designed. The support piece and the rotor shaft of conventional rotor are in spline connection and single in function, spline connection is adopted, the spline is firstly designed on the support piece and the rotor shaft, and the spline connection needs structures such as a conical ring, a spindle screw, a bearing plate, an anti-loosening plate, a locking screw and the like, so that the connection structure is more. And the design, processing and assembly of the spline are difficult. Therefore, the conventional support member has a single function, and cannot realize a plurality of connection functions. The present invention therefore provides a support structure for a bearing rotor, which has a plurality of connection functions and is connected with other structures only by bolts, and which is simple and reliable in connection and convenient in inspection and maintenance.
Disclosure of Invention
The present invention provides an inner steering rotor support structure, which is characterized in that the inner steering rotor of a coaxial helicopter needs to transmit steering command of steering engine from the outside of a rotor shaft to the inside of the rotor shaft and then to an upper rotor hub pitch horn, so that the inner steering rotor support structure is needed to be connected with the steering structure to transmit steering command.
An inner control rotor support structure is divided into from top to bottom in proper order: hollow cylinder section, taper section, reinforcing rib section and circular ring section;
the hollow cylindrical section is connected with the inner rotor shaft;
the circular ring section is connected with the guide cylinder; the ring section is also connected with a torque arm component
The reinforcing rib section is connected with the rocker component.
Further, the lower end of the hollow cylindrical section is provided with a plurality of first bolt holes along the radial direction, and a shoulder bushing is arranged in each first bolt hole; the hollow cylindrical section is connected with the inner rotor shaft through bolts;
the thickness of the bolt hole area of the hollow cylindrical section is thickest, the thickness of the annular area of the hollow cylindrical section close to the upper end face is inferior, and the thickness of the rest part of the hollow cylindrical section is thinnest.
Further, the bottom of the inner side wall of the hollow cylindrical section is provided with an annular flange for limiting the inner rotary wing shaft.
Further, the reinforcing rib section comprises eight reinforcing ribs, and the eight reinforcing ribs are connected with the conical section and the circular ring section;
every two reinforcing ribs are in a group, and each group is distributed at 90 degrees;
a second bolt hole is formed in the middle of each reinforcing rib, and a shoulder bushing is arranged in each second bolt hole;
and each group of reinforcing ribs is connected with a rocker assembly through bolts.
Further, eight straight lining holes are formed in the circular ring, and each straight lining hole is internally provided with a straight lining; the bolt passes through the straight bushing and is connected with the guide cylinder.
Further, every two straight lining holes are in one group, and each group of straight lining holes is distributed between two groups of reinforcing ribs.
Further, two groups of torque arm lugs are symmetrically arranged on the lower end face of the circular ring section and are connected with the torque arm through bolts.
Further, the reinforcing ribs are greatest in thickness at the bolt holes.
Further, the bottom of the outer side wall of the conical section is provided with a step surface for positioning.
The beneficial effects are that:
1. the support structure has a multifunctional structure: the rotor shaft is quickly and simply connected with the rotor shaft, the rocker assembly, the guide cylinder and the torque arm assembly;
2. the support piece structure is a multifunctional integrated design structure, so that the number of parts is reduced, the weight of the structure can be reduced, and the design for reducing the weight is realized;
3. the support member structure is connected only through bolts, has an installation positioning surface, is convenient to install and detach, is simple to maintain, and can reduce maintenance cost.
Drawings
Figure 1 is a schematic view of the mounting of a support with a rotor shaft;
FIG. 2 is a schematic view of a support structure;
FIG. 3 is a cross-sectional view of support structure A-A;
FIG. 4 is a top view of the support member
The three-dimensional rotor comprises a support piece assembly 1, a connecting bolt 2, an inner rotor shaft 3, a rocker assembly 4, a square arm assembly 5 with a torque arm, a guide cylinder 6, a first shoulder bushing 11, a straight bushing 12, a second shoulder bushing 13, a support piece part 14 and a third shoulder bushing 15.
Detailed Description
The invention is further illustrated by the following embodiments:
the invention discloses a support piece structure 1 of a coaxial rotor wing, which comprises a support piece 14, a first shoulder bush 11, a second shoulder bush 13, a third shoulder bush 15 and a straight bush 12, wherein the first shoulder bush 11, the second shoulder bush 13, the third shoulder bush 15 and the straight bush 12 are in interference fit with the support piece 14.
The structure has a plurality of connection functions: the device is connected with the inner rotor shaft 3, the rocker assembly 4, the square arm of the torque arm 5 and the guide cylinder 6;
the structural part is a cylindrical section and is used for being connected with the cylindrical surface of the inner rotor shaft. The cylindrical section is a cylinder with unequal thickness, and the wall thickness of the bolt connection area is the largest, so that the main bearing is changed; the wall thickness of the uppermost ring body is secondary, and the thicker ring body is used for preventing the cylindrical section from generating larger deformation during processing; the middle area of the cylinder is thin in wall and used for reducing weight; the small step surface is designed at the lower side of the inner cylindrical surface in the connection area with the rotor shaft, so that the small step surface can play a role in positioning when being installed with the rotor shaft, and is convenient to install with an inner rotor shaft bolt;
the inner rotor shaft is connected with the inner rotor shaft through 8 bolt holes, the 8 bolt holes are unevenly distributed, and the positions of the connecting holes avoid the positions of the middle reinforcing ribs of the supporting piece;
the inner rotor shaft 3 is connected with the inner rotor shaft through bolts, the direction of the bolts is that the bolts are at the inner side, and the nuts are at the outer side, so that the nuts are convenient. The rotor shaft is in spline connection with a conventional helicopter rotor shaft, and the structure such as a spline structure, a spindle nut, a bearing plate, an anti-loosening plate, a locking screw and the like is omitted in bolt connection, so that the whole connection structure is simpler, and the maintenance is more convenient;
the middle part of the support piece is a conical section, the lower part of the support piece is a circular ring, the conical section is connected with the circular ring through 8 reinforcing ribs, every two reinforcing ribs are in a group, 4 groups are distributed uniformly. Four step surfaces are designed on the outer surface of the upper circular section, and the upper circular section has a weight reduction effect for a process clamping surface. The inner and outer contours of the reinforcing ribs are arc-shaped, each group of reinforcing ribs is provided with a bolt mounting hole, the wall thickness of the reinforcing ribs in the mounting hole area is maximum, large open space holes are formed between each group of reinforcing ribs, and the open space is the mounting space of the connecting bolts and is designed for reducing the weight of the whole supporting piece;
the middle area of each group of reinforcing ribs is connected with a rocker assembly rod 4, and the rocker assembly plays a role of leverage, and can transmit an off-axis operating command into the rotor shaft so as to realize on-axis operation of the whole upper rotor automatic inclinator;
2 straight lining holes are designed on a ring body between each group of reinforcing ribs on the lower circular ring of the support piece, 8 straight lining holes are formed in total, a straight lining 12 is arranged in each straight lining hole, and the support piece and the guide cylinder are connected by bolts;
two torque arm lug structures are designed on the ring body at the lower part of the support piece, the square torque arm assembly 5 can be directly connected, the torque arm lug plays a role of a torque arm flange, a torque arm flange plate is omitted, and the structure is designed as a whole, so that the support piece has a complete structure.
The foregoing is merely a detailed description of the invention, which is not a matter of routine skill in the art. However, the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present invention should be included in the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (7)
1. An internally piloted rotor support structure, characterized by: the support piece structure is divided into from top to bottom in proper order: hollow cylinder section, taper section, reinforcing rib section and circular ring section;
the lower end of the hollow cylindrical section is provided with a plurality of first bolt holes along the radial direction, and a shoulder bushing is arranged in each first bolt hole; the hollow cylindrical section is connected with the inner rotor shaft through bolts; the bottom of the inner side wall of the hollow cylindrical section is provided with an annular flange for limiting the inner rotary wing shaft;
the circular ring section is connected with the guide cylinder; the ring section is also connected with a torque arm assembly;
the reinforcing rib section is connected with the rocker assembly and comprises eight reinforcing ribs, and the eight reinforcing ribs are connected with the conical section and the circular ring section; every two reinforcing ribs are in a group, a second bolt hole is formed in the middle of each reinforcing rib, and a shoulder bushing is arranged in each second bolt hole; each group of reinforcing ribs is connected with a rocker component through a bolt;
eight straight bushing holes are formed in the circular ring, and each straight bushing hole is internally provided with a straight bushing; the bolt passes through the straight bushing and is connected with the guide cylinder.
2. An internally piloted rotor support structure according to claim 1, wherein:
the thickness of the bolt hole area of the hollow cylindrical section is thickest, the thickness of the annular area of the hollow cylindrical section close to the upper end face is inferior, and the thickness of the rest part of the hollow cylindrical section is thinnest.
3. An internally piloted rotor support structure according to claim 2, wherein: the eight reinforcing ribs are distributed at 90 degrees to each other in each group.
4. An internally piloted rotor support structure according to claim 3, wherein: every two straight lining holes are in a group, and each group of straight lining holes is distributed between two groups of reinforcing ribs.
5. An internally piloted rotor support structure according to claim 1, wherein: the lower end face of the ring section is symmetrically provided with two groups of torque arm lugs, and the torque arm lugs are connected with the torque arm through bolts.
6. An internally piloted rotor support structure according to claim 1, wherein: the thickness of the reinforcing rib is the largest at the bolt hole.
7. An internally piloted rotor support structure according to claim 1, wherein: the bottom of the outer side wall of the conical section is provided with a step surface for positioning.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111177064.5A CN113942640B (en) | 2021-10-09 | 2021-10-09 | Inner control rotor wing supporting piece structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111177064.5A CN113942640B (en) | 2021-10-09 | 2021-10-09 | Inner control rotor wing supporting piece structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113942640A CN113942640A (en) | 2022-01-18 |
| CN113942640B true CN113942640B (en) | 2023-04-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111177064.5A Active CN113942640B (en) | 2021-10-09 | 2021-10-09 | Inner control rotor wing supporting piece structure |
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| CN (1) | CN113942640B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE9400258U1 (en) * | 1994-01-12 | 1995-05-18 | Schwarze, Hans-Otto, 45665 Recklinghausen | Device for stripping dirt from belt straps in the area of a drive or deflection roller |
| SE0104391D0 (en) * | 2001-12-27 | 2001-12-27 | Scania Cv Abp | Bushing arrangement for an anti-roll bar |
| CN104129498A (en) * | 2014-07-23 | 2014-11-05 | 中国航天空气动力技术研究院 | Rotor wing control mechanism for coaxial helicopter |
| CN205060011U (en) * | 2015-10-27 | 2016-03-02 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle rotor - control system of displacement |
| CN106477040A (en) * | 2016-11-30 | 2017-03-08 | 中国直升机设计研究所 | Rotor driver is manipulated in a kind of axle |
| CN108116673A (en) * | 2017-12-22 | 2018-06-05 | 中国兵器工业计算机应用技术研究所 | A pitch control system for a coaxial twin-propeller helicopter |
| WO2019049752A1 (en) * | 2017-09-05 | 2019-03-14 | 株式会社ブリヂストン | Bush |
| CN109969388A (en) * | 2019-04-19 | 2019-07-05 | 北京海空行科技有限公司 | A kind of steerable system for coaxial unmanned helicopter |
| CN111605702A (en) * | 2020-06-09 | 2020-09-01 | 湖南优玄科技有限公司 | Control system for coaxial double-rotor unmanned helicopter and operation method |
| CN112478154A (en) * | 2020-12-05 | 2021-03-12 | 北京航空航天大学 | Rotor propeller suitable for tilt-rotor aircraft |
-
2021
- 2021-10-09 CN CN202111177064.5A patent/CN113942640B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE9400258U1 (en) * | 1994-01-12 | 1995-05-18 | Schwarze, Hans-Otto, 45665 Recklinghausen | Device for stripping dirt from belt straps in the area of a drive or deflection roller |
| SE0104391D0 (en) * | 2001-12-27 | 2001-12-27 | Scania Cv Abp | Bushing arrangement for an anti-roll bar |
| CN104129498A (en) * | 2014-07-23 | 2014-11-05 | 中国航天空气动力技术研究院 | Rotor wing control mechanism for coaxial helicopter |
| CN205060011U (en) * | 2015-10-27 | 2016-03-02 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle rotor - control system of displacement |
| CN106477040A (en) * | 2016-11-30 | 2017-03-08 | 中国直升机设计研究所 | Rotor driver is manipulated in a kind of axle |
| WO2019049752A1 (en) * | 2017-09-05 | 2019-03-14 | 株式会社ブリヂストン | Bush |
| CN108116673A (en) * | 2017-12-22 | 2018-06-05 | 中国兵器工业计算机应用技术研究所 | A pitch control system for a coaxial twin-propeller helicopter |
| CN109969388A (en) * | 2019-04-19 | 2019-07-05 | 北京海空行科技有限公司 | A kind of steerable system for coaxial unmanned helicopter |
| CN111605702A (en) * | 2020-06-09 | 2020-09-01 | 湖南优玄科技有限公司 | Control system for coaxial double-rotor unmanned helicopter and operation method |
| CN112478154A (en) * | 2020-12-05 | 2021-03-12 | 北京航空航天大学 | Rotor propeller suitable for tilt-rotor aircraft |
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| Publication number | Publication date |
|---|---|
| CN113942640A (en) | 2022-01-18 |
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