CN201362366Y - Cowling lock mechanism of helicopter nacelle - Google Patents
Cowling lock mechanism of helicopter nacelle Download PDFInfo
- Publication number
- CN201362366Y CN201362366Y CNU2009200004613U CN200920000461U CN201362366Y CN 201362366 Y CN201362366 Y CN 201362366Y CN U2009200004613 U CNU2009200004613 U CN U2009200004613U CN 200920000461 U CN200920000461 U CN 200920000461U CN 201362366 Y CN201362366 Y CN 201362366Y
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- China
- Prior art keywords
- lock
- boss
- helicopter
- cowling
- pin
- 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.)
- Expired - Lifetime
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Abstract
The utility model belongs to the technical field of aviation, which relates to a cowling lock mechanism of a helicopter nacelle. The lock shell of the cowling lock mechanism is fixed on a cowling of a helicopter nacelle, the side of a boss positioned on one side of the center of the helicopter on the lock shell is equipped with a lock hole, a lock pin is inserted into the lock hole of the lock shell, the top portion of the boss is provided with a waist-shaped hole, a small wheel is fixed onto the lock pin through a pin bolt, one end of a swinging arm is fixed onto the lock pin, a cylindrical boss is arranged on the side opposite to the boss of the lock shell, a torsion spring and a big wheel are installed on the cylindrical boss, the other end of the swinging ring is fixed onto the big wheel, a gasket and a self-lock nut are pressed on the swinging arm, one end of the torsion spring is connected with the lock shell, the other end of the torsion spring is inserted into a pin bolt installed on the swinging arm, and an anti-false-locking device is arranged on the side of the cylindrical boss. The cowling lock mechanism of a helicopter nacelle completes locking action through leading the lock pin to be inserted inside the lock hole of the lock shell, and has reliable locking state. Besides, the anti-false-locking device can indicate whether the nacelle cowling is closed in place or not, and the safety of the lock is effectively improved.
Description
Technical field
The utility model belongs to the aeronautical technology field, relates to a kind of helicopter piggyback pod fairing latch mechanism.
Background technology
At present, helicopter piggyback pod fairing lock is rolled by latch hook, extension spring, lock to be formed, groundwork is the rotor switch handle, drive latch hook, itself and lock are hooked together reach closed condition, when closing, the latch hook point need overcome bigger power just can be made latch hook root and lock roll seat to hook together and put in place, because trace is closed easy deformation under fairing and the hi-heat condition improper, cause locking mechanism to produce false lock phenomenon easily, cause fairing in the helicopter flight process, to be subjected to air resistance and flick, have a strong impact on helicopter flight safety.
Summary of the invention
The utility model purpose provides a kind of at the improper helicopter piggyback pod fairing latch mechanism that is not easy to cause the false lock of locking mechanism generation phenomenon under fairing and the hi-heat condition of closing.Technical solution of the present utility model is, lock housing is fixed on the helicopter piggyback pod fairing, and the side that is positioned at the boss of helicopter center one side on the lock housing has lockhole, and lock pin inserts in the lockhole of lock housing; The top of boss has waist shaped hole, and on lock pin, an end of swing arm is fixed on the lock pin trundle with dowel fixes; A relative side with boss is provided with cylinder boss on the lock housing, and torsion spring and big roller are housed on the cylinder boss, and the other end of swing arm is fixed on the big roller; Be pressed with pad and self-locking mother Luo in the swing arm; Torsion spring one end is connected with lock housing, and the other end inserts in the bolt axle of installing in the swing arm; One side of cylinder boss is provided with the anti-false locking device; The anti-false locking device comprises spring strut, Luo bolt, slide block, spring, and the Luo bolt joins by spring strut and the slide block that is embedded on the boss, and spring housing is connected on the spring strut inner bolt.Advantage that the utlity model has and beneficial effect, the utility model adopts lock pin to insert the lock housing lockhole and finishes the locking action, this form locking state is firm, and can reflect whether the piggyback pod fairing closes by the anti-false locking device puts in place, promptly when the slide block in anti-false locking device when complete opening does not put in place, lock pin can't pass the lockpin hole of lock housing, this information feeds back in the handle mechanism by the connecting rod in the locking mechanism, make the handle can't clickwise, fairing was not closed and was put in place this moment, and safe reliability is effectively improved.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is the lateral plan of Fig. 1.
The specific embodiment
Claims (1)
1. helicopter piggyback pod fairing latch mechanism, it is characterized in that, lock housing (1) is fixed on the helicopter piggyback pod fairing, and the side that is positioned at the boss (2) of helicopter center one side on the lock housing (1) has lockhole (3), and lock pin (4) inserts in the lockhole (3) of lock housing (1); The top of boss (2) has waist shaped hole (5), and trundle (6) is fixed on the lock pin (4) with pin (8), and an end of swing arm (7) is fixed on the lock pin (4); Lock housing (1) goes up a relative side with boss (2) and is provided with cylinder boss (9), and torsion spring (10) and big roller (11) are housed on the cylinder boss (9), and the other end of swing arm (7) is fixed on the big roller (11); Be pressed with pad (12) and self lock nut (13) in the swing arm (7); Torsion spring (10) one ends are connected with lock housing (1), and the other end inserts swing arm (7) and goes up in the bolt axle of installing (14); One side of cylinder boss (9) is provided with the anti-false locking device; The anti-false locking device comprises spring strut (16), bolt (17), slide block (18), spring (15), and bolt (17) joins by spring strut (16) and the slide block (18) that is embedded on the boss (2), and spring (15) is socketed on spring strut (16) inner bolt (17).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CNU2009200004613U CN201362366Y (en) | 2009-01-08 | 2009-01-08 | Cowling lock mechanism of helicopter nacelle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CNU2009200004613U CN201362366Y (en) | 2009-01-08 | 2009-01-08 | Cowling lock mechanism of helicopter nacelle |
Publications (1)
Publication Number | Publication Date |
---|---|
CN201362366Y true CN201362366Y (en) | 2009-12-16 |
Family
ID=41473025
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CNU2009200004613U Expired - Lifetime CN201362366Y (en) | 2009-01-08 | 2009-01-08 | Cowling lock mechanism of helicopter nacelle |
Country Status (1)
Country | Link |
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CN (1) | CN201362366Y (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102826218A (en) * | 2012-09-11 | 2012-12-19 | 江西洪都航空工业集团有限责任公司 | Afterbody rectification structure of twin-engine aircraft |
CN103129740A (en) * | 2013-02-07 | 2013-06-05 | 玉环县天润航空机械制造厂 | Locking mechanism of engine compartment fairing |
CN106428579A (en) * | 2016-11-30 | 2017-02-22 | 中国直升机设计研究所 | Locking mechanism for fairing |
CN109533283A (en) * | 2018-11-12 | 2019-03-29 | 中国直升机设计研究所 | A kind of foldable radome fairing and the helicopter with it |
CN113291648A (en) * | 2021-05-17 | 2021-08-24 | 大连中集特种物流装备有限公司 | Tray box |
-
2009
- 2009-01-08 CN CNU2009200004613U patent/CN201362366Y/en not_active Expired - Lifetime
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102826218A (en) * | 2012-09-11 | 2012-12-19 | 江西洪都航空工业集团有限责任公司 | Afterbody rectification structure of twin-engine aircraft |
CN102826218B (en) * | 2012-09-11 | 2016-06-15 | 江西洪都航空工业集团有限责任公司 | A kind of Afterbody rectification structure of twin-engine aircraft |
CN103129740A (en) * | 2013-02-07 | 2013-06-05 | 玉环县天润航空机械制造厂 | Locking mechanism of engine compartment fairing |
CN103129740B (en) * | 2013-02-07 | 2015-07-15 | 玉环天润航空机械制造有限公司 | Locking mechanism of engine compartment fairing |
CN106428579A (en) * | 2016-11-30 | 2017-02-22 | 中国直升机设计研究所 | Locking mechanism for fairing |
CN109533283A (en) * | 2018-11-12 | 2019-03-29 | 中国直升机设计研究所 | A kind of foldable radome fairing and the helicopter with it |
CN109533283B (en) * | 2018-11-12 | 2020-09-25 | 中国直升机设计研究所 | Collapsible radome fairing and have its helicopter |
CN113291648A (en) * | 2021-05-17 | 2021-08-24 | 大连中集特种物流装备有限公司 | Tray box |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
CX01 | Expiry of patent term | ||
CX01 | Expiry of patent term |
Granted publication date: 20091216 |