CN110318617A - A kind of canopy bar-type lock system - Google Patents
A kind of canopy bar-type lock system Download PDFInfo
- Publication number
- CN110318617A CN110318617A CN201811496397.2A CN201811496397A CN110318617A CN 110318617 A CN110318617 A CN 110318617A CN 201811496397 A CN201811496397 A CN 201811496397A CN 110318617 A CN110318617 A CN 110318617A
- Authority
- CN
- China
- Prior art keywords
- rocker arm
- lock system
- handle
- canopy
- lock
- 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
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C19/00—Other devices specially designed for securing wings, e.g. with suction cups
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Lock And Its Accessories (AREA)
Abstract
The present invention relates to a kind of canopy lock system, especially a kind of canopy bar-type lock system belongs to Aircraft structural design field.A kind of canopy bar-type lock system, including handle set, rocker arm, handle and lock pull rod, handle set include interconnecting piece and tight lock part, and connecting rocker arm and handle on interconnecting piece, rocker arm and handle link and can rotate under external force around interconnecting piece；Tight lock part is hollow cylinder, and spherical parts, elastic component and fastener are disposed in tight lock part, and the groove that its end opens up when the top of spherical parts rotates position to terminal with rocker arm engages, and elastic component is limited in tight lock part by spherical parts, fastener；The lock pull rod body of rod connect with rocker arm and can slide on rocker arm, and both ends are connect with aircraft front and back cabin latch mechanism respectively.The present invention has the advantage that 1, canopy lock system coupling mechanism force meets aircraft overload flight and catapult-assisted take-off requirement.2, it may be implemented to limit the function that canopy is unlocked under each operating condition of aircraft, and coupling mechanism force is adjustable, front and back cabin can freely unlock.
Description
Technical field
The present invention relates to a kind of canopy lock system, especially a kind of canopy bar-type lock system belongs to Flight Vehicle Structure
Design field.
Background technique
Canopy lock system is used to lock canopy position, and the load that canopy is born in aircraft flight
Lotus passes to fuselage, guarantees Flight Safety.It is lock system that lock system firm locking, which is not in unexpected unlock in flight course,
System design key.All kinds of latch mechanisms are designed as hook-type lock, bar-type lock its execution unit latch hook, lock pin etc. using from locking,
Bear to be not in unlock, but the lock pull rod for connecting each latch mechanism is driving part when canopy load, its own there are weight,
Certain course overload power is had in flight course, is in-flight likely to occur and is moved and then latch mechanism is driven to unlock.It is general to use
This unlocking force is eliminated in two kinds of designs, first is that designing dead point in lock pull rod driving, i.e., lock can only be driven to draw by unlocking handle
Bar movement, the overload power that lock pull rod itself is born not will cause lock pull rod movement, this is that design is generally used for hook-type lock, bar-type lock
It is not applicable.Therefore use the lock pull rod of bar-type lock that need to design locking apparatus, for overcoming flight overload power, so that realizing can only pass through
Handle is locked to unlock, and overload power not will cause the movement of lock pull rod and unlock when flight.Aircraft is using rollover hatchcover, bar-type lock
System, the linkage of front and back cabin unlocking handle, to avoid lock system from surprisingly unlocking, design corresponding mechanism both can guarantee certain coupling mechanism force
It is able to maintain the ability that front and back cabin can freely unlock again.
Summary of the invention
Present invention aim to address problems of the prior art, and providing one kind may be implemented each operating condition lower limit of aircraft
The canopy bar-type lock system that canopy processed is unlocked.
To achieve the goals above, the present invention adopts the following technical scheme: a kind of canopy bar-type lock system, including handle
Seat, rocker arm, handle and lock pull rod, handle set includes interconnecting piece and tight lock part, connecting rocker arm and handle on interconnecting piece, rocker arm and hand
Handle links and can rotate under external force around interconnecting piece；Tight lock part is hollow cylinder, and ball is disposed in tight lock part
Shape part, elastic component and fastener, the groove that its end opens up when the top of spherical parts rotates position to terminal with rocker arm engage, ball
Elastic component is limited in tight lock part by shape part, fastener；The lock pull rod body of rod connect with rocker arm and can slide on rocker arm, both ends
It is connect respectively with aircraft front and back cabin latch mechanism.
Preferably, the fastener is holding screw, is spirally connected with the internal screw thread for being set to tight lock part hollow cylinder, is pushed up
Portion and elastic component bottom against.
Preferably, the end of the groove is arc-shaped transition.
Preferably, waist-shaped hole is provided on rocker arm, lock pull rod passes through waist-shaped hole by connector and realizes lock pull rod and shake
Arm is slidably connected.
Preferably, connecting shaft is provided on interconnecting piece, connecting shaft can rotate on interconnecting piece, the end of handle, rocker arm
It is connected and fixed respectively with connecting shaft.
Preferably, the tight lock part is hollow cylinder, and top is close to the bottom of rocker arm.
Preferably, the elastic component be spring, top and spherical parts against, bottom and fastener tip against.
Preferably, the spherical parts are steel ball.
Steel ball and spring are installed by increasing structure on lock system handle set, increased on the rocker arm of connection lock pull rod recessed
Slot makes spring by steel ball card in rocker arm groove, the coupling mechanism force of Lai Zengjia lock system；Holding screw holddown spring controls spring
Elastic force realizes coupling mechanism force regulatory function.
Compared with the prior art, the invention has the following advantages:
1, canopy lock system coupling mechanism force meets aircraft overload flight and catapult-assisted take-off requirement.
2, it may be implemented to limit the function that canopy is unlocked under each operating condition of aircraft, and coupling mechanism force is adjustable, front and back cabin can be certainly
By unlocking.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the embodiment of the present invention in the lockout condition；
In figure, 1, handle set；2, pull rod is locked；3, steel ball；4, spring；5, holding screw；6, rocker arm；7, handle.
Specific embodiment
It should be noted that in the present embodiment, noun of locality " top, bottom " etc. is retouched according to shown in attached drawing
It states, is not construed as limiting the invention.
1 couple of present invention is further described with reference to the accompanying drawing: as shown in Figure 1, a kind of canopy bar-type lock system, including
Handle set 1, rocker arm 6, handle 7 and lock pull rod 2.
Handle set 1 includes interconnecting piece and tight lock part, and interconnecting piece includes plate-like piece and auricle, and plate-like piece is connected to the bottom of auricle
3 auricles are connected in turn by portion, and the through-hole for holding bolt and passing through is opened up in a wherein outboard ear on piece, is used for hand
Handle seat 1, which is bolted, to be mounted on cockpit apperture fame, offers through-hole respectively in the corresponding position of 3 auricles, connecting shaft is worn
Through-hole is crossed, the end and handle 7 for being pierced by auricle are connected and fixed, and another end for being pierced by auricle is fixed using locking nut, and
It is locking using bolt；One end of rocker arm 6, which is provided with, holds the through-hole that connecting shaft passes through, and rocker arm 6 passes through through-hole and consolidates with axis connection is connect
Fixed, rocker arm 6 and handle 7 link and connecting shaft can be driven to rotate under external force, and the other end of rocker arm 6 offers waist type
Hole, bolt pass through lock pull rod 2 and waist-shaped hole and connect rocker arm 6, lock pull rod 2, to lock pull rod 2 under the effect of external force in rocker arm
Sliding in 6 waist-shaped hole；Tight lock part is hollow cylinder, positioned at the lower section of rocker arm 6, be disposed in tight lock part steel ball 3,
Spring 4 and holding screw 5, the groove that its end opens up when the top of steel ball 3 rotates position to terminal with rocker arm 6 engage, steel ball
3, holding screw 5 is spirally connected with the internal screw thread for being set to tight lock part hollow cylinder, and spring 4 is limited in tight lock part；Lock is drawn
2 both ends of bar are connect with aircraft front and back cabin latch mechanism respectively.
Since requirement of the aircraft under each operating conditions to coupling mechanism force is different, in order to meet its requirement, set inside tight lock part
It is long as far as possible to set internal thread partial-length, length setting is advisable with the maximum compressibility for reaching spring.
In order to which with steel ball 3 clamping stagnation does not occur during engaging or separating for rocker arm 6, the end of groove is designed as circular arc
Shape transition.
After lock system locking, rocker arm 6 rotates position to terminal, and steel ball 3 is stuck in rocker arm 6 under the action of spring 4 at this time
In groove.If lock system needs to unlock, the groove for needing that steel ball 3 is first made to be detached from rocker arm 6 realizes unlock.This mode can increase
The coupling mechanism force of lock system can overcome when spring force is enough and lock the overload that pull rod 2 is generated in course big overload
Power increases system reliability.Meanwhile as long as the power applied on front and back cabin handle 7 is sufficiently large, preceding backseat pilot can be free
Unlock.Steel ball 3, spring 4 and holding screw 5, when needing to adjust lock system releasing force, can pass through tune on handle set 1
Section holding screw 5 carrys out the compression degree of adjustment spring 4, to change lock system releasing force, realizes regulatory function.
Canopy bar-type lock system of the present invention may be implemented to limit the function that canopy is unlocked under each operating condition of aircraft, and lock
Clamp force is adjustable, and front and back cabin can freely unlock, and has good application value, and all kinds of rollover hatchcover lock systems are designed
Also there is biggish reference function.
What the embodiment of the present invention was announced is preferred embodiment, and however, it is not limited to this, the ordinary skill people of this field
Member, easily according to above-described embodiment, understands spirit of the invention, and make different amplification and variation, but as long as not departing from this
The spirit of invention, all within the scope of the present invention.
Claims (8)
1. a kind of canopy bar-type lock system, including handle set, rocker arm, handle and lock pull rod, it is characterised in that: handle set includes
Interconnecting piece and tight lock part, connecting rocker arm and handle on interconnecting piece, rocker arm and handle linkage and can be under external force around connection
Portion's rotation；Tight lock part is hollow cylinder, and spherical parts, elastic component and fastener, the top of spherical parts are disposed in tight lock part
The groove that its end opens up when portion rotates position to terminal with rocker arm engages, and elastic component is limited to locking by spherical parts, fastener
In portion；The lock pull rod body of rod connect with rocker arm and can slide on rocker arm, and both ends are connect with aircraft front and back cabin latch mechanism respectively.
2. canopy bar-type lock system according to claim 1, it is characterised in that: the fastener is holding screw, with
The internal screw thread for being set to tight lock part hollow cylinder is spirally connected, top with elastic component bottom against.
3. canopy bar-type lock system according to claim 1, it is characterised in that: the end of the groove is arc-shaped mistake
It crosses.
4. canopy bar-type lock system according to claim 1, it is characterised in that: be provided with waist-shaped hole on rocker arm, lock
Pull rod passes through waist-shaped hole by connector and realizes that lock pull rod and rocker arm are slidably connected.
5. canopy bar-type lock system according to claim 1, it is characterised in that: connecting shaft is provided on interconnecting piece,
Connecting shaft can rotate on interconnecting piece, handle, rocker arm end be connected and fixed respectively with connecting shaft.
6. canopy bar-type lock system according to claim 1, it is characterised in that: the tight lock part is hollow cylinder,
Its top is close to the bottom of rocker arm.
7. canopy bar-type lock system according to claim 1 or 2, it is characterised in that: the elastic component is spring, top
Portion and spherical parts against, bottom and fastener tip against.
8. canopy bar-type lock system according to claim 1, it is characterised in that: the spherical parts are steel ball.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811496397.2A CN110318617A (en) | 2018-12-07 | 2018-12-07 | A kind of canopy bar-type lock system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811496397.2A CN110318617A (en) | 2018-12-07 | 2018-12-07 | A kind of canopy bar-type lock system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110318617A true CN110318617A (en) | 2019-10-11 |
Family
ID=68112673
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811496397.2A Pending CN110318617A (en) | 2018-12-07 | 2018-12-07 | A kind of canopy bar-type lock system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110318617A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110863704A (en) * | 2019-11-26 | 2020-03-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Non-coaxial transmission device and hatch cover folding driving device with same |
| CN112593778A (en) * | 2020-12-17 | 2021-04-02 | 中国航空工业集团公司成都飞机设计研究所 | Large-scale integral side-turning type cabin cover driving system and method |
| CN114348233A (en) * | 2021-12-17 | 2022-04-15 | 江西洪都航空工业集团有限责任公司 | Aircraft cabin locking device |
| CN114671035A (en) * | 2022-03-04 | 2022-06-28 | 湖南山河科技股份有限公司 | Flight control pull rod control device, installation method and application |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0437984A1 (en) * | 1990-01-16 | 1991-07-24 | British Aerospace Public Limited Company | Canopy or panel locking assembly |
| US6874733B2 (en) * | 2003-02-13 | 2005-04-05 | The Boeing Company | Attachment apparatus for injected-molded frameless canopies |
| CN102561851A (en) * | 2011-12-14 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Aircraft cabin latch type lock |
| CN202509914U (en) * | 2011-12-16 | 2012-10-31 | 江西洪都航空工业集团有限责任公司 | Self-insurance type aircraft cabin hook lock |
| CN204299295U (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 door handle mechanism |
| CN107605292A (en) * | 2017-09-04 | 2018-01-19 | 江西洪都航空工业集团有限责任公司 | A kind of canopy latch mechanism |
| CN207725630U (en) * | 2017-07-04 | 2018-08-14 | 西安飞机工业（集团）有限责任公司 | A kind of opening mechanism of aircraft drag umbrella hatch door |
-
2018
- 2018-12-07 CN CN201811496397.2A patent/CN110318617A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0437984A1 (en) * | 1990-01-16 | 1991-07-24 | British Aerospace Public Limited Company | Canopy or panel locking assembly |
| US6874733B2 (en) * | 2003-02-13 | 2005-04-05 | The Boeing Company | Attachment apparatus for injected-molded frameless canopies |
| CN102561851A (en) * | 2011-12-14 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Aircraft cabin latch type lock |
| CN202509914U (en) * | 2011-12-16 | 2012-10-31 | 江西洪都航空工业集团有限责任公司 | Self-insurance type aircraft cabin hook lock |
| CN204299295U (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 door handle mechanism |
| CN207725630U (en) * | 2017-07-04 | 2018-08-14 | 西安飞机工业（集团）有限责任公司 | A kind of opening mechanism of aircraft drag umbrella hatch door |
| CN107605292A (en) * | 2017-09-04 | 2018-01-19 | 江西洪都航空工业集团有限责任公司 | A kind of canopy latch mechanism |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110863704A (en) * | 2019-11-26 | 2020-03-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Non-coaxial transmission device and hatch cover folding driving device with same |
| CN112593778A (en) * | 2020-12-17 | 2021-04-02 | 中国航空工业集团公司成都飞机设计研究所 | Large-scale integral side-turning type cabin cover driving system and method |
| CN114348233A (en) * | 2021-12-17 | 2022-04-15 | 江西洪都航空工业集团有限责任公司 | Aircraft cabin locking device |
| CN114348233B (en) * | 2021-12-17 | 2023-08-11 | 江西洪都航空工业集团有限责任公司 | Aircraft cabin lock device |
| CN114671035A (en) * | 2022-03-04 | 2022-06-28 | 湖南山河科技股份有限公司 | Flight control pull rod control device, installation method and application |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191011 |