CN104215442A - Tail rotor blade sleeve centrifugal force loading device - Google Patents
Tail rotor blade sleeve centrifugal force loading device Download PDFInfo
- Publication number
- CN104215442A CN104215442A CN201410424784.0A CN201410424784A CN104215442A CN 104215442 A CN104215442 A CN 104215442A CN 201410424784 A CN201410424784 A CN 201410424784A CN 104215442 A CN104215442 A CN 104215442A
- Authority
- CN
- China
- Prior art keywords
- spring
- centrifugal force
- oversleeve
- tail
- bearing
- 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.)
- Granted
Links
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a tail rotor blade sleeve centrifugal force loading device, and belongs to fatigue testing technologies for tail rotor blades of helicopters. The tail rotor blade sleeve centrifugal force loading device is characterized by comprising a spring, a spring connecting bolt, a spring connecting fork lug, a force measuring rod, an adjusting rod, a bearing with a handle, a connecting plate, bearing connecting bolts, a blade sleeve connecting plate, an adjusting nut and an intermediate bearing with a handle, wherein one end of the spring is connected with the spring connecting fork lug; the force measuring rod is connected with the spring connecting fork lug and the adjusting rod in a threaded manner; the adjusting rod is connected with the bearing with the handle in a threaded manner; a hole is formed in the connecting plate; the bearing with the handle is connected with the connecting plate through the bearing connecting bolts; the bearing with the handle can rotate around the bearing connecting bolt; one end of the intermediate bearing with the handle is inserted in the connecting plate and is connected with the connecting plate through the bearing connecting bolts; the other end of the intermediate bearing with the handle is connected with the blade sleeve connecting plate; and the magnitude of the blade sleeve centrifugal force can be adjusted through the adjusting nut. The stress state of a tail rotor blade sleeve is simulated; a testing load is applied to the sleeve through the spring; and the purpose of checking the fatigue performance of blades is achieved.
Description
Technical field
The invention belongs to helicopter tail rotor leaf fatigue test technology, relate to the design of a kind of helicopter tail rotor leaf oversleeve centrifugal force charger.
Background technology
Tail-rotor leaf is tail-rotor vitals, in order to grasp tail-rotor leaf fatigue behaviour, needs on ground in the face of tail-rotor leaf carries out torture test, grasp tail-rotor leaf fatigue properties, and then provides the life-span of tail-rotor leaf.Because helicopter is when flying, tail-rotor leaf oversleeve will bear the centrifugal force from tail-rotor leaf, therefore needs stress during simulated flight when torture test, adds centrifugal force to tail-rotor foliar spray.
At present, China does not have similar test unit, can not carry out this loading.Do not retrieve relevant open source literature abroad.
Summary of the invention
The technical problem to be solved in the present invention: design a kind of helicopter tail rotor leaf oversleeve centrifugal force charger, the stress during oversleeve installation of simulation tail-rotor leaf, to tail-rotor leaf oversleeve imposed load, can reach the object of examination tail-rotor leaf fatigue behaviour.
Technical scheme of the present invention: a kind of tail-rotor leaf oversleeve centrifugal force charger, technical scheme of the present invention comprises: spring, spring coupling bolt, spring yoke ear, dynamometer link, adjuster bar, band arbor hold, web joint, bearing coupling bolt, blade oversleeve web joint, setting nut, and Intermediate Gray arbor holds composition.Both ends of the spring has crotch, one end is fixed by crotch, and one end is connected with spring yoke ear by spring coupling bolt, and dynamometer link is threaded connection spring yoke ear and adjuster bar, by rotating dynamometer link, size tail-rotor leaf oversleeve applying centrifugal force can be changed.The adjuster bar other end has threaded hole, and band arbor holds one end screw thread, and adjuster bar holds with band arbor and is threaded connection.Porose on web joint, band arbor socket joint enters in web joint, and is connected with web joint by bearing coupling bolt.Band arbor holds and can rotate around bearing coupling bolt.Intermediate Gray arbor holds one end and inserts web joint, and is connected by bearing coupling bolt, and the other end is connected with blade oversleeve web joint, can be regulated the size of blade oversleeve centrifugal force by setting nut.
Described band arbor holds on the handle that holds with Intermediate Gray arbor external thread.
Beneficial effect of the present invention: simulation tail-rotor leaf oversleeve stress, applies test load by spring to oversleeve, reach the object of examination tail-rotor leaf fatigue behaviour.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Embodiment
Below the present invention is described in further details.
As shown in Figure 1, the present invention is a kind of tail-rotor leaf oversleeve centrifugal force charger, comprise: spring 1, spring coupling bolt 2, spring yoke ear 3, dynamometer link 4, adjuster bar 5, band arbor holds 6, web joint 7, bearing coupling bolt 8, blade oversleeve web joint 9, setting nut 10, Intermediate Gray arbor holds 11 compositions, there is crotch at spring 1 two ends, one end is fixed by crotch, one end is connected with spring yoke ear 3 by spring coupling bolt 2, dynamometer link 4 is threaded connection spring yoke ear 3 and adjuster bar 5, by rotating dynamometer link 4, size tail-rotor leaf oversleeve applying centrifugal force can be changed.Adjuster bar 5 other end has threaded hole, and band arbor holds one end screw thread, and adjuster bar 5 holds 6 with band arbor and is threaded connection.Porose on web joint 7, band arbor holds in 6 insertion web joints, and is connected with web joint 7 by bearing coupling bolt 8.Band arbor holds 6 and can rotate around bearing coupling bolt 8.Intermediate Gray arbor holds 11 one end and inserts web joint 7, and is connected by bearing coupling bolt 8, and setting nut 10 holds 11 with Intermediate Gray arbor and is threaded, and setting nut 10 regulates the size of blade oversleeve centrifugal force.
Concrete, the mode that described dynamometer link 4 is threaded connection spring yoke ear 3 and adjuster bar 5 is: dynamometer link 4 one end is left-hand thread hole, and one end is right-hand thread hole, and there is right-hand thread spring yoke ear 3 one end, and there is left-hand thread adjuster bar 5 one end.
Or the mode that described dynamometer link 4 is threaded connection spring yoke ear 3 and adjuster bar 5 is: dynamometer link 4 one end is left-hand thread hole, one end is right-hand thread hole, and there is left-hand thread spring yoke ear 3 one end, and there is right-hand thread adjuster bar 5 one end.
Described web joint 7 can be veneer or many plates.
Described dynamometer link 4 is straight-bar or knee.
Described adjuster bar 5 is straight-bar or knee.
Described band arbor hold 6 and Intermediate Gray arbor hold 11 handle on have external thread.
Claims (8)
1. a tail-rotor leaf oversleeve centrifugal force charger, it is characterized in that, comprise spring (1), spring coupling bolt (2), spring yoke ear (3), dynamometer link (4), adjuster bar (5), band arbor holds (6), web joint (7), bearing coupling bolt (8), blade oversleeve web joint (9), setting nut (10) and Intermediate Gray arbor hold (11), spring (1) one end is connected with spring yoke ear (3) by spring coupling bolt (2), dynamometer link (4) is threaded connection spring yoke ear (3) and adjuster bar (5), adjuster bar (5) holds (6) with band arbor and is threaded connection, web joint (7) is upper porose, and band arbor is held (6) and is connected with web joint (7) by bearing coupling bolt (8), band arbor holds (6) and can rotate around bearing coupling bolt (8), Intermediate Gray arbor holds (11) one end and inserts web joint (7), and connected by bearing coupling bolt (8), the other end is connected with blade oversleeve web joint (9), setting nut (10) holds (11) and is threaded with Intermediate Gray arbor, setting nut (10) regulates the size of blade oversleeve centrifugal force.
2. tail-rotor leaf oversleeve centrifugal force charger according to claim 1, it is characterized in that, described spring (1) two ends are all with crotch, and the other end is fixed by crotch.
3. tail-rotor leaf oversleeve centrifugal force charger according to claim 1, it is characterized in that, the version that described dynamometer link (4) is threaded connection spring yoke ear (3) and adjuster bar (5) is: dynamometer link (4) one end is left-hand thread hole, one end is right-hand thread hole, there is right-hand thread spring yoke ear (3) one end, and there is left-hand thread adjuster bar (5) one end.
4. tail-rotor leaf oversleeve centrifugal force charger according to claim 1, it is characterized in that, the version that described dynamometer link (4) is threaded connection spring yoke ear (3) and adjuster bar (5) is: dynamometer link (4) one end is left-hand thread hole, one end is right-hand thread hole, there is left-hand thread spring yoke ear (3) one end, and there is right-hand thread adjuster bar (5) one end.
5. tail-rotor leaf oversleeve centrifugal force charger according to claim 1, it is characterized in that, described web joint (7) can be veneer or many plates.
6. tail-rotor leaf oversleeve centrifugal force charger according to claim 1, it is characterized in that, described dynamometer link (4) is straight-bar or knee.
7. tail-rotor leaf oversleeve centrifugal force charger according to claim 1, it is characterized in that, described adjuster bar (5) is straight-bar or knee.
8. tail-rotor leaf oversleeve centrifugal force charger according to claim 1, is characterized in that, described band arbor holds on handle that (6) and Intermediate Gray arbor hold (11) external thread.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424784.0A CN104215442B (en) | 2014-08-26 | 2014-08-26 | A kind of tail-rotor leaf oversleeve is centrifuged force loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424784.0A CN104215442B (en) | 2014-08-26 | 2014-08-26 | A kind of tail-rotor leaf oversleeve is centrifuged force loading device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104215442A true CN104215442A (en) | 2014-12-17 |
| CN104215442B CN104215442B (en) | 2017-07-07 |
Family
ID=52097165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410424784.0A Active CN104215442B (en) | 2014-08-26 | 2014-08-26 | A kind of tail-rotor leaf oversleeve is centrifuged force loading device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104215442B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644450A (en) * | 2017-01-10 | 2017-05-10 | 北京强度环境研究所 | Anti-rotation adjusting device for centrifugal tests |
| CN110411722A (en) * | 2019-07-26 | 2019-11-05 | 中国航发沈阳发动机研究所 | A kind of structural static and fatigue experimental device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2028591C1 (en) * | 1990-07-02 | 1995-02-09 | Московский вертолетный завод им.М.Л.Миля | Stand for member dynamic tests |
| RU2034257C1 (en) * | 1991-06-24 | 1995-04-30 | Вертолетный научно-технический комплекс им.Н.И.Камова | Method of testing the helicopter rotor members and test stand for its realization |
| CN101363770A (en) * | 2008-10-08 | 2009-02-11 | 燕山大学 | Fatigue-tesing machine for ball socket bearing of helicopter main rotor |
| CN103439096A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | Helicopter tail rotor booster fatigue test system |
-
2014
- 2014-08-26 CN CN201410424784.0A patent/CN104215442B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2028591C1 (en) * | 1990-07-02 | 1995-02-09 | Московский вертолетный завод им.М.Л.Миля | Stand for member dynamic tests |
| RU2034257C1 (en) * | 1991-06-24 | 1995-04-30 | Вертолетный научно-технический комплекс им.Н.И.Камова | Method of testing the helicopter rotor members and test stand for its realization |
| CN101363770A (en) * | 2008-10-08 | 2009-02-11 | 燕山大学 | Fatigue-tesing machine for ball socket bearing of helicopter main rotor |
| CN103439096A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | Helicopter tail rotor booster fatigue test system |
Non-Patent Citations (1)
| Title |
|---|
| 夏国旺等: "直升机球柔性尾桨桨毂连接件疲劳试验技术研究", 《直升机技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644450A (en) * | 2017-01-10 | 2017-05-10 | 北京强度环境研究所 | Anti-rotation adjusting device for centrifugal tests |
| CN106644450B (en) * | 2017-01-10 | 2023-10-10 | 北京强度环境研究所 | Anti-rotation adjusting device for centrifugal test |
| CN110411722A (en) * | 2019-07-26 | 2019-11-05 | 中国航发沈阳发动机研究所 | A kind of structural static and fatigue experimental device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104215442B (en) | 2017-07-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104697753B (en) | A kind of tail-rotor leaf fatigue experimental device | |
| CN104215443B (en) | One kind has led rocking arm joint torque loading device | |
| CN204495559U (en) | A kind of resilient bearing torsional rigidity proving installation | |
| CN201852741U (en) | Special fixture for bolt tension test | |
| CN204439326U (en) | A kind of test rudder face actuator simulator | |
| WO2011131922A3 (en) | System and method for a surface strain gauge | |
| CN104215442A (en) | Tail rotor blade sleeve centrifugal force loading device | |
| CN104236880B (en) | A kind of torsional arm component fatigue experimental device | |
| CN107515094A (en) | A kind of diverging space rod-type parachute wind tunnel test support meanss | |
| CN204640137U (en) | A kind of bolt disassembly instrument | |
| CN207106941U (en) | Helicopter pitch-change-link joint replacing specific purpose tool | |
| CN203657955U (en) | Connecting sleeve used for measuring shaft static braking torque | |
| CN203622341U (en) | Gear or bearing disassembling tool | |
| CN104502020A (en) | Balance tool for detecting static balance state of blade | |
| CN202987529U (en) | Length-adjustable soft connecting piece | |
| CN205483563U (en) | Single -point supports joint bearing performance test machine | |
| CN204666060U (en) | A kind of variator bonnet comprehensively tests tool | |
| CN105014592A (en) | Self-centering sleeve head | |
| CN104977113A (en) | Fixed-wing aircraft operating force test sensor | |
| CN105527103A (en) | Single-point support knuckle bearing performance testing machine | |
| CN204649412U (en) | A kind of screw fastener head toughness test device and test tool | |
| CN203248481U (en) | Expansion pin for fixing propeller blade | |
| CN105716836B (en) | A kind of main blade equal bending moments load maintainer of anti-deicing | |
| CN204330212U (en) | Detect the balance tooling of blade static-balance state | |
| CN204195696U (en) | A kind of jackscrew device of quick release shaft coupling taper bolt |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |