CN109110152A - A kind of tune latch mechanism - Google Patents
A kind of tune latch mechanism Download PDFInfo
- Publication number
- CN109110152A CN109110152A CN201710480657.6A CN201710480657A CN109110152A CN 109110152 A CN109110152 A CN 109110152A CN 201710480657 A CN201710480657 A CN 201710480657A CN 109110152 A CN109110152 A CN 109110152A
- Authority
- CN
- China
- Prior art keywords
- screw
- aircraft
- lock system
- tune
- connect
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- 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
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
A kind of tune latch mechanism, including screw rod, cushion block, connecting rod, screw one, rocker arm, sell stick, travel indicator, vernier caliper, screw three, screw four, screw five, screw rod is that zigzag threaded portion front end is connect with connecting rod, cushion block is aerial internal screw thread and is mounted in the emergency lock system of aircraft by screw five, screw flight portions are connect with cushion block internal screw thread, one end connect the other end with connecting rod by screw one and is connect by pin stick with travel indicator, rocker arm is mounted in the emergency lock system of aircraft by screw four, vernier caliper is mounted in the emergency lock system of aircraft by screw three, travel indicator is transmitted through the sliding rail inside vernier caliper.The tune latch mechanism structure is simple, easy to operate, is easy to carry about with one, and reliable operation solves the problems, such as that outfield troubleshooting can not debug emergency lock system, improves outfield to the emergency lock system debugging efforts efficiency of aircraft, has ensured Flight Safety.
Description
Technical field
The present invention relates to aircraft hatchcover emergency lock technology fields, more particularly to a kind of tune latch mechanism.
Background technique
Emergency lock system on aircraft is connected with aircraft cockpit, and canopy emergency system directly affects the flight peace of aircraft
Complete and pilot life security, so the requirement to cockpit emergency system is very high, and the emergency system on the aircraft of outfield
In debugging process, there can be no faults.Since not reliable, portable test instrument is adjusted, aircraft is often led to
There are security risks.
Summary of the invention
In order to solve the above technical problems, the present invention provides adjust emergency lock system in a kind of outfield, it is ensured that on aircraft
Lock system of meeting an urgent need is normal, ensures the tune latch mechanism of Flight Safety.
A kind of tune latch mechanism, including screw rod, cushion block, connecting rod, screw one, rocker arm, pin stick, travel indicator, vernier caliper,
Screw three, screw four, screw five, screw rod are that zigzag threaded portion front end is connect with connecting rod, and cushion block is aerial internal screw thread and passes through spiral shell
Nail five is mounted in the emergency lock system of aircraft, and screw flight portions are connect with cushion block internal screw thread, and one end passes through screw one
It connect the other end with connecting rod to connect by pin stick with travel indicator, rocker arm is mounted on the emergency lock system of aircraft by screw four
On, vernier caliper is mounted in the emergency lock system of aircraft by screw three, and travel indicator is transmitted through the cunning inside vernier caliper
Rail.
Further, which further includes screw two, and screw two is passed to vernier caliper and withstands travel indicator.
Further, the tune latch mechanism, vernier caliper are 300mm vernier caliper.
By using the technological means, advantageous effects that the present invention obtains are as follows: the tune latch mechanism structure is simple, operation
It is convenient, it is easy to carry about with one, reliable operation solves the problems, such as that outfield troubleshooting can not debug emergency lock system, improves outfield to aircraft
Emergency lock system debugging efforts efficiency, ensured Flight Safety.
Detailed description of the invention
Fig. 1: for structural schematic diagram of the invention.
In figure: 1, screw rod；2, cushion block；3, connecting rod；4, screw one；5, rocker arm；6, stick is sold；7, screw two；8, stroke refers to
Show device；9,300mm vernier caliper；10, screw three；11, screw four；12, screw five.
Specific embodiment
The principle and features of the present invention will be described below with reference to the accompanying drawings, and example is served only for explaining invention, not
For limiting the scope of the invention.
A kind of tune latch mechanism, including screw rod 1, cushion block 2, connecting rod 3, screw 1, Rocker arm 5, pin stick 6, travel indicator 8, trip
Slide calliper rule 9, screw 3 10, screw 4 11, screw 5 12 are marked, screw rod 1 is that zigzag threaded portion front end is connect with connecting rod 3, and cushion block 2 is
Aerial internal screw thread is simultaneously mounted in the emergency lock system of aircraft by screw 5 12, and 1 threaded portion of screw rod and 2 internal screw thread of cushion block connect
It connects, Rocker arm 5 one end connect the other end with connecting rod 3 by screw 1 and connect by pin stick 6 with travel indicator 8, and Rocker arm 5 passes through
Screw 4 11 is mounted in the emergency lock system of aircraft, and vernier caliper 9 is mounted on the emergency lock system of aircraft by screw 3 10
On, travel indicator 8 is transmitted through the sliding rail inside vernier caliper 9.
To avoid travel indicator 8 from shaking, convenient for reading.The tune latch mechanism further includes screw 27, the incoming trip of screw 27
Mark slide calliper rule 9 simultaneously withstand travel indicator 8.
To meet commissioning requirements, adjustment accuracy is improved.The vernier caliper 9 of the tune latch mechanism is 300mm vernier caliper.
Travel indicator 8 is aligned to the zero of vernier caliper 9 before test, screw rod 1 is shaken and connecting rod 3 is pushed to make answering on aircraft
Anxious lock is opened, and is read the numerical value on vernier caliper 9 at this time, is reached requirement.Emergency lock system and aircraft cockpit on aircraft
It is connected, canopy emergency system directly affects the flight safety of aircraft and the life security of pilot, so meeting an urgent need to cockpit
The requirement of system is very high.The tune latch mechanism structure is simple, easy to operate, is easy to carry about with one, and solving outgoing army's troubleshooting can not
The problem of debugging emergency lock system.
Above-mentioned technical proposal only embodies the optimal technical scheme of technical solution of the present invention, those skilled in the art
The principle of the present invention is embodied to some variations that some of them part may be made, belongs to the scope of protection of the present invention it
It is interior.
Claims (3)
1. a kind of tune latch mechanism, it is characterised in that: the tune latch mechanism includes screw rod (1), cushion block (2), connecting rod (3), screw one
(4), rocker arm (5), pin stick (6), travel indicator (8), vernier caliper (9), screw three (10), screw four (11), screw five
(12), the screw rod (1) is that zigzag threaded portion front end is connect with connecting rod (3), and the cushion block (2) is aerial internal screw thread and passes through
Screw five (12) is mounted in the emergency lock system of aircraft, and screw rod (1) threaded portion is connect with cushion block (2) internal screw thread, institute
State rocker arm (5) one end by screw one (4) connect with connecting rod (3) other end pass through pin stick (6) connect with travel indicator (8),
The rocker arm (5) is mounted in the emergency lock system of aircraft by screw four (11), and the vernier caliper (9) passes through screw three
(10) it is mounted in the emergency lock system of aircraft, the travel indicator (8) is transmitted through the internal sliding rail of vernier caliper (9).
2. tune latch mechanism according to claim 1, it is characterised in that: the tune latch mechanism further includes screw two (7), described
Screw two (7) is passed to vernier caliper (9) and withstands travel indicator (8).
3. tune latch mechanism according to claim 1 or 2, it is characterised in that: the vernier caliper (9) is 300mm vernier calliper
Ruler.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710480657.6A CN109110152B (en) | 2017-06-22 | 2017-06-22 | Lock adjusting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710480657.6A CN109110152B (en) | 2017-06-22 | 2017-06-22 | Lock adjusting mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109110152A true CN109110152A (en) | 2019-01-01 |
| CN109110152B CN109110152B (en) | 2023-08-04 |
Family
ID=64732649
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710480657.6A Active CN109110152B (en) | 2017-06-22 | 2017-06-22 | Lock adjusting mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109110152B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113636102A (en) * | 2021-08-06 | 2021-11-12 | 大连长丰实业总公司 | Debugging and ranging device for emergency lock system of aircraft canopy |
| CN113911386A (en) * | 2021-09-29 | 2022-01-11 | 大连长丰实业总公司 | Debugging and ranging device for emergency lock system of aircraft canopy |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB566794A (en) * | 1943-04-13 | 1945-01-15 | Joseph Harold Marshall | A new or improved gauging or marking-out instrument |
| CN1244652A (en) * | 1998-08-12 | 2000-02-16 | 陈其良 | Caliper with locking button |
| US20090093910A1 (en) * | 2007-10-05 | 2009-04-09 | Grosz Gregory C | Controllable Caliper |
| CN205049071U (en) * | 2015-10-13 | 2016-02-24 | 苏州耕源电子科技有限公司 | Testing fixture |
| CN105929327A (en) * | 2016-06-18 | 2016-09-07 | 中航华东光电有限公司 | Key travel testing device and method |
| CN206073882U (en) * | 2016-09-21 | 2017-04-05 | 陕西重型汽车有限公司 | Altitude valve idle stroke region detection frock |
| CN110313234B (en) * | 2014-12-30 | 2017-04-19 | 中国人民解放军第五七〇六工厂 | A kind of aircraft seat She San mechanism locks bullet machine and assembles corner measuring tool |
-
2017
- 2017-06-22 CN CN201710480657.6A patent/CN109110152B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB566794A (en) * | 1943-04-13 | 1945-01-15 | Joseph Harold Marshall | A new or improved gauging or marking-out instrument |
| CN1244652A (en) * | 1998-08-12 | 2000-02-16 | 陈其良 | Caliper with locking button |
| US20090093910A1 (en) * | 2007-10-05 | 2009-04-09 | Grosz Gregory C | Controllable Caliper |
| CN110313234B (en) * | 2014-12-30 | 2017-04-19 | 中国人民解放军第五七〇六工厂 | A kind of aircraft seat She San mechanism locks bullet machine and assembles corner measuring tool |
| CN205049071U (en) * | 2015-10-13 | 2016-02-24 | 苏州耕源电子科技有限公司 | Testing fixture |
| CN105929327A (en) * | 2016-06-18 | 2016-09-07 | 中航华东光电有限公司 | Key travel testing device and method |
| CN206073882U (en) * | 2016-09-21 | 2017-04-05 | 陕西重型汽车有限公司 | Altitude valve idle stroke region detection frock |
Non-Patent Citations (2)
| Title |
|---|
| 唐正府等: "国外先进战斗机空中应急功能分析", 《燃气涡轮试验与研究》 * |
| 杨桦: "游标卡尺附件", 《计量技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113636102A (en) * | 2021-08-06 | 2021-11-12 | 大连长丰实业总公司 | Debugging and ranging device for emergency lock system of aircraft canopy |
| CN113911386A (en) * | 2021-09-29 | 2022-01-11 | 大连长丰实业总公司 | Debugging and ranging device for emergency lock system of aircraft canopy |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109110152B (en) | 2023-08-04 |
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