CN104344930A - Rotor head angle contact ball bearing variable-pitch propeller hub for helicopter blade dynamic balance test table - Google Patents
Rotor head angle contact ball bearing variable-pitch propeller hub for helicopter blade dynamic balance test table Download PDFInfo
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- CN104344930A CN104344930A CN201310337470.2A CN201310337470A CN104344930A CN 104344930 A CN104344930 A CN 104344930A CN 201310337470 A CN201310337470 A CN 201310337470A CN 104344930 A CN104344930 A CN 104344930A
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- propeller hub
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- ball bearing
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Abstract
The invention relates to the technical field of helicopter test, in particular to a rotor head angle contact ball bearing variable-pitch propeller hub for a helicopter blade dynamic balance test table. The propeller hub comprises a radial ball bearing (1), six angle contract ball bearings (2), a variable-pitch hinge casing (3) and a variable-pitch hinge shaft neck (4), wherein one end of the variable-pitch hinge shaft neck (4) is connected with a swinging hinge, the other end of the variable-pitch hinge shaft neck (4) is arranged inside the variable-pitch hinge casing (3) through the radial ball bearing (1) and the six angle contract ball bearings (2) in a sleeving way, the radial ball bearing (1) is positioned at one side near the rotating center, and the angle contract ball bearings (2) are positioned at one side far away from the rotating center. Through the propeller hub, the stress concentration phenomenon of a propeller hub variable-pitch bearing can be reduced, the service life of the propeller hub variable-pitch bearing can be prolonged, the appearance dimension of the propeller hub structure is reduced, the hinge moment measuring precision of the test table rotor head propeller hub is improved, and the use completeness rate of the test table rotor head propeller hub is improved.
Description
Technical field
The invention belongs to helicopter experimental technique field, particularly relate to a kind of Helicopter Blade Dynamic Balance Test platform rotor head angular contact ball bearing displacement propeller hub.
Background technology
Existing Helicopter Blade Dynamic Balance Test platform rotor head propeller hub has two profiles formula, one utilizes resilient bearing to realize propeller hub displacement, resilient bearing major part is formed by stacking by rubber and bowl-type stalloy, the advantage of resilient bearing is used to be that propeller hub does not need lubrication, safeguard very convenient, but simultaneously there is obvious defect is that resilient bearing has elasticity of torsion moment, and along with environment temperature change greatly and unstable, to the hinge moment of transient equilibrium blade, there is considerable influence.Another kind realizes propeller hub displacement by the mode that end face bearing adds needle bearing, end face bearing bears centrifugal force, and needle bearing realizes rotating relative to displacement of propeller hub pitch hinge housing and axle journal, because end face bearing stock size is larger, there is physical dimension by this way large, overall propeller hub weightening finish is more.
Due to above-mentioned two kinds of existing helicopter blade dynamic balance bench rotor head propeller hub patterns, there is the poor shortcoming of hinge moment precision in the first pattern, requires higher type, just can not adopt this mode for hinge moment measuring accuracy.The second pattern due to the force of rolling friction of metal bearing less, therefore hinge moment measuring accuracy is higher, but because end face bearing size is comparatively large, be unfavorable for the layout of testing table propeller hub parameter measurement equipment as hinge moment sensor, propeller pitch angle adjustment linear actuator.
Summary of the invention
The technical problem to be solved in the present invention:
Based on above reason, the present invention adopts and a kind ofly uses metal bearing and the little and compact displacement propeller hub of structure, can substitute aforementioned two profiles formula testing table rotor head propeller hub.
Technical scheme of the present invention:
A kind of Helicopter Blade Dynamic Balance Test platform rotor head angular contact ball bearing displacement propeller hub, this propeller hub comprises 1 radial ball bearing 1,6 angular contact ball bearings 2, pitch hinge housing 3, pitch hinge axle journal 4, wherein, pitch hinge axle journal 4 one end is connected with flapping hinge, and one end is sleeved on pitch hinge housing 3 inside by 1 radial ball bearing 1 and 6 angular contact ball bearings 2 in addition, radial ball bearing 1 is positioned near rotation center side, and angular contact bearing 2 is positioned at away from rotation center side.
Beneficial effect of the present invention:
The stress concentration phenomenon of propeller hub pitch bearing can be reduced by the present invention, improve the life-span of propeller hub pitch bearing, reduce the physical dimension of propeller hub structure, improve the hinge moment measuring accuracy of testing table rotor head propeller hub, improve testing table rotor head propeller hub use availability ratio.
Accompanying drawing explanation
Fig. 1 is Helicopter Blade Dynamic Balance Test corner of table contact ball bearing displacement propeller hub pitch hinge structural representation, and in figure, 1 is radial ball bearing, and 2 is angular contact ball bearing, 3 is pitch hinge housing, 4 is pitch hinge axle journal, and 5 is pitch hinge housing locking big nut, and 6 is pitch hinge axle journal locking big nut.
Embodiment
A kind of Helicopter Blade Dynamic Balance Test platform rotor head angular contact ball bearing displacement propeller hub, this propeller hub comprises 1 radial ball bearing 1,6 angular contact ball bearings 2, pitch hinge housing 3, pitch hinge axle journal 4, wherein, pitch hinge axle journal 4 one end is connected with flapping hinge, and one end is sleeved on pitch hinge housing 3 inside by 1 radial ball bearing 1 and 6 angular contact ball bearings 2 in addition, radial ball bearing 1 is positioned near rotation center side, and angular contact bearing 2 is positioned at away from rotation center side.
The pattern of Helicopter Blade Dynamic Balance Test platform rotor head angular contact bearing displacement propeller hub as shown in Figure 1, wherein comprises 1 radial ball bearing 1 and 6 angular contact ball bearings 2, jointly forms the pitch hinge of propeller hub with pitch hinge housing 3, pitch hinge axle journal 4.Bearing 1 and 2 can realize relatively rotating between pitch hinge housing and pitch hinge axle journal, and the centrifugal force of blade born by 6 angular contact ball bearings 2, and the centrifugal force of 1/6th only born by each angular contact ball bearing.Comparatively speaking, the propeller hub structure comparison of this kind of pattern is compact, is suitable for the needs that blade dynamic balance test stand rotor head adds repacking survey sensor and adjustment equipment.And due to this kind of type approval test platform rotor head propeller hub use pitch bearing be metal bearing, its friction force is less, can meet the requirement that degree of precision measures blade hinge moment.Bearing 1 and 2 can realize relatively rotating between pitch hinge housing and pitch hinge axle journal, and bearing 2 can also bear the centrifugal force of blade.
Claims (1)
1. a Helicopter Blade Dynamic Balance Test platform rotor head angular contact ball bearing displacement propeller hub, it is characterized in that, this propeller hub comprises 1 radial ball bearing (1), 6 angular contact ball bearings (2), pitch hinge housing (3), pitch hinge axle journal (4), wherein, pitch hinge axle journal (4) one end is connected with flapping hinge, one end is sleeved on pitch hinge housing (3) inside by 1 radial ball bearing (1) and 6 angular contact ball bearings (2) in addition, radial ball bearing (1) is positioned near rotation center side, and angular contact bearing (2) is positioned at away from rotation center side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310337470.2A CN104344930A (en) | 2013-08-05 | 2013-08-05 | Rotor head angle contact ball bearing variable-pitch propeller hub for helicopter blade dynamic balance test table |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310337470.2A CN104344930A (en) | 2013-08-05 | 2013-08-05 | Rotor head angle contact ball bearing variable-pitch propeller hub for helicopter blade dynamic balance test table |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104344930A true CN104344930A (en) | 2015-02-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310337470.2A Pending CN104344930A (en) | 2013-08-05 | 2013-08-05 | Rotor head angle contact ball bearing variable-pitch propeller hub for helicopter blade dynamic balance test table |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104344930A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107640306A (en) * | 2017-08-25 | 2018-01-30 | 珠海磐磊智能科技有限公司 | Marine propulsion, ship and its travel control method |
| CN108105363A (en) * | 2017-11-29 | 2018-06-01 | 中国直升机设计研究所 | A kind of seesaw type unmanned helicopter pitch hinge |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB546510A (en) * | 1940-04-16 | 1942-07-16 | Walter Scott Hoover | Improvements in or relating to propeller blade supports |
| GB606524A (en) * | 1945-10-03 | 1948-08-16 | Curtiss Wright Corp | Improvements in or relating to propeller assemblies |
| GB2244525A (en) * | 1990-04-04 | 1991-12-04 | Dowty Aerospace Gloucester | Propeller blade hub assembly |
| CN103085971A (en) * | 2011-10-28 | 2013-05-08 | 贝尔直升机泰克斯特龙公司 | Increased Capacity Spherical Lined Bearing |
-
2013
- 2013-08-05 CN CN201310337470.2A patent/CN104344930A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB546510A (en) * | 1940-04-16 | 1942-07-16 | Walter Scott Hoover | Improvements in or relating to propeller blade supports |
| GB606524A (en) * | 1945-10-03 | 1948-08-16 | Curtiss Wright Corp | Improvements in or relating to propeller assemblies |
| GB2244525A (en) * | 1990-04-04 | 1991-12-04 | Dowty Aerospace Gloucester | Propeller blade hub assembly |
| CN103085971A (en) * | 2011-10-28 | 2013-05-08 | 贝尔直升机泰克斯特龙公司 | Increased Capacity Spherical Lined Bearing |
Non-Patent Citations (1)
| Title |
|---|
| 覃海鹰等: "直8型机主尾桨毂滑油渗漏问题分析与处理", 《直升机技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107640306A (en) * | 2017-08-25 | 2018-01-30 | 珠海磐磊智能科技有限公司 | Marine propulsion, ship and its travel control method |
| CN108105363A (en) * | 2017-11-29 | 2018-06-01 | 中国直升机设计研究所 | A kind of seesaw type unmanned helicopter pitch hinge |
| CN108105363B (en) * | 2017-11-29 | 2021-03-30 | 中国直升机设计研究所 | Seesaw type distance-variable hinge of unmanned helicopter |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150211 |
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| RJ01 | Rejection of invention patent application after publication |