CN105416580A - Method for avoiding shifting of frequency adapter side plates through bushes - Google Patents
Method for avoiding shifting of frequency adapter side plates through bushes Download PDFInfo
- Publication number
- CN105416580A CN105416580A CN201510861012.8A CN201510861012A CN105416580A CN 105416580 A CN105416580 A CN 105416580A CN 201510861012 A CN201510861012 A CN 201510861012A CN 105416580 A CN105416580 A CN 105416580A
- Authority
- CN
- China
- Prior art keywords
- side plate
- mounting holes
- frequency match
- match device
- lower side
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- 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
- B64C11/02—Hub construction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a helicopter rotor hub system, and provides a method for avoiding shifting of frequency adapter side plates through bushes. The method includes the steps that (a) when three mounting holes in the upper side plate (8) and three mounting holes in the lower side plate (8) of each frequency adapter of a star-shaped flexible hub are enlarged and deformed, the frequency adapters are dismounted from the hub; (b) the three mounting holes in the upper side plate (8) and the three mounting holes in the lower side plate (8) of each frequency adapter are machined to be expanded to 18 mm, and it is guaranteed that the three mounting holes in the upper side plate (8) and the three mounting holes in the lower side plate (8) of each frequency adapter are coaxial with three mounting holes of an outer connector (7); (c) then the corresponding LY11 aluminum bushes are embedded in the three mounting holes of the upper side plate (8) and the three mounting holes of the lower side plate (8) of each frequency adapter respectively, the outer diameter of each aluminum bush is 18 mm, and the inner diameter of each aluminum bush is phi14.6+/-0.1 mm; and (d) the frequency adapters are mounted on the hub again.
Description
Technical field
The present invention relates to lifting airscrew rotor hub system, particularly relate to a kind of method that lining overcomes the skew of frequency match device side plate.
Background technology
The present age, a kind of relatively more conventional pattern of Helicopter Main Hub was star Flexible Main propeller hub (see Fig. 1), its main feature is exactly be provided with frequency match device (i.e. shimmy-damper between the upper and lower clamping plate of propeller hub, its structure is shown in Fig. 2), for providing shimmy damping, avoiding the interphase interaction of rotor and fuselage and occurring resonating.
Starflex hub frequency match device rubber bodies 4 produces shearing motion between type star polygon work 1, clamping plate 3, provides lagging motion damping.The side plate up and down 8 of frequency match device and coupling 7 to be fixed on propeller hub between lower plate 3 by three frequency match device bolts 5.
The defect of prior art:
The original dimension of three mounting holes of the upper and lower side plate 8 of frequency match device is Φ 14.6 ± 0.1mm.Due to Long-Time Service, three mounting holes of the upper and lower side plate 8 of frequency match device there will be distortion, side plate is caused to produce skew, and then cause frequency match device damping silicon rubber 4 to produce twisting motion outside shear deformation, cause the shimmy power exception acted on propeller hub, increase the vibration of helicopter body.
Summary of the invention
The technical problem to be solved in the present invention: a kind of lining overcomes the method for frequency match device side plate skew, avoid star Flexible Main propeller hub frequency match device upper and lower side plate that skew distortion occurs, and then avoid the shimmy power of propeller hub abnormal, ensure that helicopter body vibration is in rational scope, ensures the traveling comfort of passenger riding.
Technical scheme of the present invention: a kind of lining overcomes the method for frequency match device side plate skew, comprising:
A frequency match device, when three mounting holes of the upper and lower side plate of starflex hub frequency match device (8) occur increasing distortion, decomposes from propeller hub by ();
B () utilizes machine adding method to expand upper and lower for frequency match device side plate (8) three mounting holes to 18mm, make three mounting holes of upper and lower side plate (8) ensure coaxial with three mounting holes of coupling (7);
C () then inlays a LY11 aluminium cover respectively in the upper and lower side plate of frequency match device (8) three mounting holes, the external diameter of aluminium cover is 18mm, and the internal diameter of aluminium cover is Φ 14.6 ± 0.1mm;
D frequency match device is arranged on propeller hub by () again.
Beneficial effect of the present invention: after the invention process, Helicopter Main Hub frequency match device upper and lower side plate skew inconsistent phenomenon no longer occurs, can ensure the normal use of helicopter.
Accompanying drawing explanation
Fig. 1 is helicopter starflex hub schematic diagram.
Fig. 2 is frequency match device schematic diagram.
Detailed description of the invention
The invention provides a kind of method that lining overcomes the skew of frequency match device side plate, as shown in Figure 1, 2, Fig. 1 is helicopter starflex hub schematic diagram, starflex hub forms primarily of type star polygon work 1, ball-bearing casing 2, upper and lower clamping plate 3, frequency match device 4, frequency match device is fixed between upper and lower clamping plate 3 by hold-down bolt 5, the nipple of frequency match device 4 and the support arm end bearing fit of type star polygon work 1.Fig. 2 is frequency match device schematic diagram, and frequency match device forms primarily of aluminum nipple 6, aluminum coupling 7, up and down side plate 8, damping silicon rubber 9.In rotor wing rotation process, frequency match device damping silicon rubber 9 produces shearing motion, for the shimmy of rotor provides damping.
The embodiment of the present invention comprises:
A frequency match device, when three mounting holes of the upper and lower side plate 8 of starflex hub frequency match device occur increasing distortion, decomposes from propeller hub by ().
B () utilizes machine adding method to expand upper and lower for frequency match device side plate 8 three mounting holes to 18mm, make three mounting holes of upper and lower side plate 8 ensure coaxial with three mounting holes of coupling 7.
C () then inlays a LY11 aluminium cover respectively in the upper and lower side plate of frequency match device 8 three mounting holes, the external diameter of aluminium cover is 18mm, and the internal diameter of aluminium cover is Φ 14.6 ± 0.1mm.
D frequency match device is arranged on propeller hub by () again.
Like this, the tolerance clearance between upper and lower side plate 8 and frequency match device bolt of rear end plate 5 has returned to initial condition, can ensure that the upper and lower side plate 8 of frequency match device there will not be dislocation, distortion.
Note: the size of frequency match device upper and lower side plate 8 reaming also can strengthen as one sees fit, will ensure greatly to closely cooperate between three linings inlaying and upper and lower side plate, so need certain magnitude of interference, interference fit dimension limit is chosen as H7/p6.
Claims (1)
1. overcome a method for frequency match device side plate skew with lining, it is characterized in that, comprising:
A frequency match device, when three mounting holes of the upper and lower side plate of starflex hub frequency match device (8) occur increasing distortion, decomposes from propeller hub by ();
B () utilizes machine adding method to expand upper and lower for frequency match device side plate (8) three mounting holes to 18mm, make three mounting holes of upper and lower side plate (8) ensure coaxial with three mounting holes of coupling (7);
C () then inlays a LY11 aluminium cover respectively in the upper and lower side plate of frequency match device (8) three mounting holes, the external diameter of aluminium cover is 18mm, and the internal diameter of aluminium cover is Φ 14.6 ± 0.1mm;
D frequency match device is arranged on propeller hub by () again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510861012.8A CN105416580A (en) | 2015-11-30 | 2015-11-30 | Method for avoiding shifting of frequency adapter side plates through bushes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510861012.8A CN105416580A (en) | 2015-11-30 | 2015-11-30 | Method for avoiding shifting of frequency adapter side plates through bushes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105416580A true CN105416580A (en) | 2016-03-23 |
Family
ID=55495220
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510861012.8A Pending CN105416580A (en) | 2015-11-30 | 2015-11-30 | Method for avoiding shifting of frequency adapter side plates through bushes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105416580A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107933955A (en) * | 2017-12-01 | 2018-04-20 | 中国直升机设计研究所 | A kind of radially fixed loading device of frequency adaptation |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101850490A (en) * | 2010-05-31 | 2010-10-06 | 南通中远船务工程有限公司 | Rudder pintle bearing body repairing process based on metal repairing agent casting |
| CN201925299U (en) * | 2010-12-30 | 2011-08-10 | 河南三建建设集团有限公司 | Device for fixing self-tapping screw in wall |
| CN103831574A (en) * | 2013-12-10 | 2014-06-04 | 贵州黎阳航空动力有限公司 | Process for repairing hollow turbine blade body blocking cover |
| CN104880277A (en) * | 2015-05-15 | 2015-09-02 | 哈尔滨飞机工业集团有限责任公司 | Main blade connecting arm for test table |
-
2015
- 2015-11-30 CN CN201510861012.8A patent/CN105416580A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101850490A (en) * | 2010-05-31 | 2010-10-06 | 南通中远船务工程有限公司 | Rudder pintle bearing body repairing process based on metal repairing agent casting |
| CN201925299U (en) * | 2010-12-30 | 2011-08-10 | 河南三建建设集团有限公司 | Device for fixing self-tapping screw in wall |
| CN103831574A (en) * | 2013-12-10 | 2014-06-04 | 贵州黎阳航空动力有限公司 | Process for repairing hollow turbine blade body blocking cover |
| CN104880277A (en) * | 2015-05-15 | 2015-09-02 | 哈尔滨飞机工业集团有限责任公司 | Main blade connecting arm for test table |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107933955A (en) * | 2017-12-01 | 2018-04-20 | 中国直升机设计研究所 | A kind of radially fixed loading device of frequency adaptation |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160323 |