CN106628206A - Lightning protection structure with small rotating torque - Google Patents
Lightning protection structure with small rotating torque Download PDFInfo
- Publication number
- CN106628206A CN106628206A CN201611161200.0A CN201611161200A CN106628206A CN 106628206 A CN106628206 A CN 106628206A CN 201611161200 A CN201611161200 A CN 201611161200A CN 106628206 A CN106628206 A CN 106628206A
- Authority
- CN
- China
- Prior art keywords
- weathercock
- rotating torque
- lightning protection
- housing
- shell
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/02—Lightning protectors; Static dischargers
Abstract
The invention belongs to the aircraft lightning protection technology, and particularly relates to a lightning protection structure with small rotating torque. The structure with the small rotating torque includes a weather vane (1), shafts (2), ceramic bearings (3), a shell (4) and conductive pins (5). The ceramic bearings (3) are installed in bearing holes of the shell (4), the conductive pins (5) are fixed on the shell (4), and the weather vane (1) is fixed on the shafts (2), connected with the shafts (2) and then fixed on the ceramic bearings (3). The structure is simple, the ceramic bearings are easy to rotate, so that the rotation torque of the weather vane is small, when an attack-angle sensor is attacked by thunder, point discharging is formed between the shell (4) and the conductive pins (5), electric currents thus reach a plane body after passing through the weather vane (1), the conductive pins (5) and the shell (4), it is avoided that lightning stroke energy is thus gathered on the weather vane and the weather vane is then damaged, and the structure has great practical application value.
Description
Technical field
The invention belongs to aircraft shocking preventing technology, and in particular to a kind of little rotating torque lightning protection for incidence vane is tied
Structure.
Background technology
Incidence vane, in the survey aircraft angle of attack, is to ensure that the rotating torque of its weathercock is little, typically using metal bearing
Supporting construction.And incidence vane belongs to the exposed equipment of aircraft, be subject to thunderbolt, thunder-strike current just via weathercock-axle-
Metal bearing-housing is to airframe.Because the ball of metal bearing is big with its raceway contact resistance, according to formula, generate heat
Power P=I2R, when thunder-strike current flows through its contact surface, because caloric value causes greatly contact surface to melt between ball and raceway, makes rolling
Road is welded together with ball, it is impossible to relatively rotate, so that weathercock can not be rotated, incidence vane failure.
In order to avoid bearing fails in thunderbolt, conventional method be the part that will contact with bearing inner race and with bearing outside
The part use of circle contact can bear the ground strap connection of thunder-strike current, good conduction is formed between bearing inner race and outer ring and is led to
Road, will bearing inner race and outer ring short circuit, when being struck by lightning, make via ground strap connection thunder-strike current is guided to aircraft machine
On body, so as to protect metal bearing, it is to avoid raceway is welded together with ball.But the structure increases the rotating torque for making bearing
Greatly, in not being suitable for the little incidence vane of requirement rotating torque.
The content of the invention
The purpose of the present invention is：A kind of little rotating torque lightning protection structure for incidence vane is provided, for solving to attack
Angle transducer be struck by lightning after a disabler difficult problem.
The technical scheme is that：A kind of little rotating torque lightning protection structure, it include weathercock 1, axle 2, ceramic bearing 3,
Housing 4 and conductive pin 5, wherein, weathercock 1 is fixed on ceramic bearing 3 after being connected with axle 2, and ceramic bearing 3 installs the axle of housing 4
In bearing bore, weathercock 1 is set to form insulation system with housing 4, conductive pin 5 is arranged on housing 4, forms good conductive structure, and
There is certain gap between weathercock 1.
Gap between the conductive pin 5 and weathercock 1 is between 0.1mm～0.3mm.
The conductive pin 5 is cutting-edge structure.
It is fastening assembling between the conductive pin 5 and housing 4.
It is an advantage of the invention that：The ceramic bearing 3 of the little rotating torque lightning protection structure of the present invention makes weathercock 1 be formed with housing 4
Insulation system, can avoid metal bearing in thunderbolt using ceramic bearing 3, and thunder-strike current makes raceway be welded together with ball
And fail, meanwhile, ceramic bearing 3 is easy to rotate so that the rotating torque of weathercock is less.Formed between conductive pin 5 and housing 4 simultaneously
Good conductive structure, makes electric current via on weathercock 1, conductive pin 5, housing 4 to airframe, it is to avoid the energy of thunderbolt is in weathercock
On gather, damage weathercock.The simple structure, changes little to the version of the former angle of attack, is adapted in existing incidence vane
Carry out popularization and application.
Description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the cutting-edge structure schematic diagram of conductive pin.
Specific embodiment
The present invention is described in further details below.
With reference to Fig. 1～Fig. 2.The little rotating torque lightning protection structure of the present invention includes weathercock 1, axle 2, ceramic bearing 3, the and of housing 4
Conductive pin 5.Wherein, weathercock 1 is fixed on ceramic bearing 3 after being connected with axle 2, and ceramic bearing 3 is installed in the dead eye of housing 4.
The ceramic bearing 3 is easy to rotate in dead eye, and rotating torque is less, so as to facilitate the rotation of weathercock.The conductive pin 5 with
Housing 4 is fixed on housing 4 by interference fit, a good conductive structure of formation.
After the completion of assembling, the bottom of the weathercock 1 sees there is certain gap with surface of shell, and between conductive pin 5
Gap be 0.1mm～0.3mm between, and the conductive pin be top for spheroid cutting-edge structure, when being struck by lightning, conductive pin
Gap between 5 and weathercock 1 can form point discharge effect.Produced electric current is via weathercock 1, conductive pin 5, housing 4 to aircraft
On body.And ceramic bearing 3 makes weathercock 1 form insulation system with housing 4, it is to avoid the energy of thunderbolt gathering on weathercock, make
Weathercock is damaged.The electric current of the isolation of ceramic bearing 3 simultaneously, can avoid metal bearing in thunderbolt, and thunder-strike current makes raceway and ball
It is welded together and fails.
The simple structure of the little rotating torque lightning protection structure of the present invention, cancels existing connected mode of making contact, using conductive pin
Discharged with the point discharge effect of weathercock, little is changed to the version of the former angle of attack, and due to being provided without making contact, therefore wind
Mark can be rotated with bearing is convenient, and rotating torque is little, is adapted to carry out popularization and application in existing incidence vane, with larger reality
Border using value.
Claims (4)
1. a kind of little rotating torque lightning protection structure, is characterized in that, including weathercock (1), axle (2), ceramic bearing (3), housing (4) and
Conductive pin (5), wherein, weathercock (1) is fixed on ceramic bearing (3) after being connected with axle (2), and ceramic bearing (3) installs housing (4)
Dead eye in, make weathercock (1) and housing (4) form insulation system, conductive pin (5) is formed good on housing (4)
Conductive structure, and there is certain gap between weathercock (1).
2. little rotating torque lightning protection structure according to claim 1, is characterized in that, between the conductive pin (5) and weathercock (1)
Gap be 0.1mm～0.3mm between.
3. little rotating torque lightning protection structure according to claim 1, is characterized in that, the conductive pin (5) is cutting-edge structure.
4. little rotating torque lightning protection structure according to claim 1, is characterized in that, the conductive pin (5) and housing (4) it
Between for fastening assembling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161200.0A CN106628206B (en) | 2016-12-15 | 2016-12-15 | A kind of small rotating torque lightning protection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161200.0A CN106628206B (en) | 2016-12-15 | 2016-12-15 | A kind of small rotating torque lightning protection structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628206A true CN106628206A (en) | 2017-05-10 |
| CN106628206B CN106628206B (en) | 2019-01-15 |
Family
ID=58823656
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611161200.0A Active CN106628206B (en) | 2016-12-15 | 2016-12-15 | A kind of small rotating torque lightning protection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628206B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10393766B2 (en) | 2017-08-17 | 2019-08-27 | Rosemount Aerospace Inc. | Water management system for angle of attack sensors |
| US10730637B2 (en) | 2017-09-29 | 2020-08-04 | Rosemount Aerospace Inc. | Integral vane base angle of attack sensor |
| US11162970B2 (en) | 2019-06-17 | 2021-11-02 | Rosemount Aerospace Inc. | Angle of attack sensor |
| US11181545B2 (en) | 2017-08-17 | 2021-11-23 | Rosemount Aerospace Inc. | Angle of attack sensor with thermal enhancement |
| US11649057B2 (en) | 2019-12-13 | 2023-05-16 | Rosemount Aerospace Inc. | Static plate heating arrangement |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204007586U (en) * | 2014-06-10 | 2014-12-10 | 中国商用飞机有限责任公司 | Microminiature angle of attack sensor |
| CN204297107U (en) * | 2014-11-19 | 2015-04-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft incidence vane protective device |
| CN104986355A (en) * | 2015-07-14 | 2015-10-21 | 中航飞机股份有限公司西安飞机分公司 | Giving method and giving device of aircraft incidence angle |
| US20150364887A1 (en) * | 2014-06-12 | 2015-12-17 | Kamatics Corporation | Electrically conductive bearing system and method |
| CN106032169A (en) * | 2015-03-13 | 2016-10-19 | 空客(北京)工程技术中心有限公司 | Static discharger, aircraft, and installation method for static discharger |
-
2016
- 2016-12-15 CN CN201611161200.0A patent/CN106628206B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204007586U (en) * | 2014-06-10 | 2014-12-10 | 中国商用飞机有限责任公司 | Microminiature angle of attack sensor |
| US20150364887A1 (en) * | 2014-06-12 | 2015-12-17 | Kamatics Corporation | Electrically conductive bearing system and method |
| CN204297107U (en) * | 2014-11-19 | 2015-04-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft incidence vane protective device |
| CN106032169A (en) * | 2015-03-13 | 2016-10-19 | 空客(北京)工程技术中心有限公司 | Static discharger, aircraft, and installation method for static discharger |
| CN104986355A (en) * | 2015-07-14 | 2015-10-21 | 中航飞机股份有限公司西安飞机分公司 | Giving method and giving device of aircraft incidence angle |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10393766B2 (en) | 2017-08-17 | 2019-08-27 | Rosemount Aerospace Inc. | Water management system for angle of attack sensors |
| US11181545B2 (en) | 2017-08-17 | 2021-11-23 | Rosemount Aerospace Inc. | Angle of attack sensor with thermal enhancement |
| US11768219B2 (en) | 2017-08-17 | 2023-09-26 | Rosemount Aerospace Inc. | Angle of attack sensor with thermal enhancement |
| US10730637B2 (en) | 2017-09-29 | 2020-08-04 | Rosemount Aerospace Inc. | Integral vane base angle of attack sensor |
| US11162970B2 (en) | 2019-06-17 | 2021-11-02 | Rosemount Aerospace Inc. | Angle of attack sensor |
| US11649057B2 (en) | 2019-12-13 | 2023-05-16 | Rosemount Aerospace Inc. | Static plate heating arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106628206B (en) | 2019-01-15 |
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