CN109110152B - Lock adjusting mechanism - Google Patents
Lock adjusting mechanism Download PDFInfo
- Publication number
- CN109110152B CN109110152B CN201710480657.6A CN201710480657A CN109110152B CN 109110152 B CN109110152 B CN 109110152B CN 201710480657 A CN201710480657 A CN 201710480657A CN 109110152 B CN109110152 B CN 109110152B
- Authority
- CN
- China
- Prior art keywords
- screw
- aircraft
- lock system
- cushion
- connecting rod
- 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.)
- Active
Links
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
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- 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; ARRANGEMENT 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Braking Arrangements (AREA)
Abstract
The utility model provides a transfer lock mechanism, including the screw rod, the cushion, the connecting rod, screw one, the rocking arm, the round pin stick, the travel indicator, the slide caliper, screw three, screw four, screw five, the screw rod is zigzag screw thread portion front end and connecting rod connection, the cushion is the aerial internal thread and install on the emergent lock system of aircraft through screw five, screw thread portion and cushion internal thread connection, rocking arm one end is connected the other end through the round pin stick with the connecting rod through screw one and is connected with the travel indicator, the rocking arm passes through screw four and installs on the emergent lock system of aircraft, the slide caliper passes through screw three and installs on the emergent lock system of aircraft, the inside slide rail of slide caliper is passed to the travel indicator. The lock adjusting mechanism is simple in structure, convenient to operate and easy to carry, the problem that an emergency lock system cannot be adjusted due to the fact that an outfield is arranged is solved reliably, the efficiency of adjusting the emergency lock system of an aircraft by the outfield is improved, and the flight safety of the aircraft is guaranteed.
Description
Technical Field
The invention relates to the technical field of aircraft cabin cover emergency locks, in particular to a lock adjusting mechanism.
Background
The emergency lock system on the aircraft is connected with the aircraft cabin, and the cockpit cover emergency system directly influences the flight safety of the aircraft and the life safety of pilots, so the requirements on the cabin emergency system are very high, and errors cannot occur in the debugging process of the emergency system on the outfield aircraft. Because no reliable and portable test tool is used for adjustment, potential safety hazards exist in the aircraft.
Disclosure of Invention
In order to solve the technical problems, the invention provides a lock adjusting mechanism for adjusting an emergency lock system in an outfield, ensuring the normal emergency lock system on an aircraft and ensuring the flight safety of the aircraft.
The utility model provides a transfer lock mechanism, including the screw rod, the cushion, the connecting rod, screw one, the rocking arm, the round pin stick, the travel indicator, the slide caliper, screw three, screw four, screw five, the screw rod is zigzag screw thread portion front end and connecting rod connection, the cushion is the cavity internal thread and install on the emergent lock system of aircraft through screw five, screw thread portion and cushion internal thread connection, rocking arm one end is connected the other end through the round pin stick with the connecting rod through screw one and is connected with the travel indicator, the rocking arm passes through screw four and installs on the emergent lock system of aircraft, the slide caliper passes through screw three and installs on the emergent lock system of aircraft, the travel indicator passes the inside slide rail of slide caliper.
Further, the lock adjusting mechanism further comprises a second screw which penetrates into the vernier caliper and props against the travel indicator.
Further, the lock adjusting mechanism has a vernier caliper of 300 mm.
By adopting the technical means, the beneficial technical effects obtained by the invention are as follows: the lock adjusting mechanism is simple in structure, convenient to operate and easy to carry, the problem that an emergency lock system cannot be adjusted due to the fact that an outfield is arranged is solved reliably, the efficiency of adjusting the emergency lock system of an aircraft by the outfield is improved, and the flight safety of the aircraft is guaranteed.
Drawings
Fig. 1: is a schematic structural diagram of the invention.
In the figure: 1. a screw; 2. a cushion block; 3. a connecting rod; 4. a first screw; 5. a rocker arm; 6. a pin; 7. a second screw; 8. a travel indicator; 9. 300mm vernier caliper; 10. a third screw; 11. a screw IV; 12. screw five.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples being provided for illustration only and not for limitation of the scope of the invention.
The utility model provides a transfer lock mechanism, including screw rod 1, cushion 2, connecting rod 3, screw one 4, rocking arm 5, the round pin stick 6, travel indicator 8, slide caliper 9, screw three 10, screw four 11, screw five 12, screw 1 is zigzag screw thread portion front end and connecting rod 3 are connected, cushion 2 is the cavity internal thread and install on the emergency lock system of aircraft through screw five 12, screw 1 screw thread portion and cushion 2 internal thread connection, rocking arm 5 one end is connected the other end through screw one 4 and connecting rod 3 and is connected with travel indicator 8 through round pin stick 6, rocking arm 5 passes through screw four 11 and installs on the emergency lock system of aircraft, slide caliper 9 passes through screw three 10 and installs on the emergency lock system of aircraft, travel indicator 8 passes the inside slide rail of slide caliper 9.
To avoid the sway of the travel indicator 8, the reading is facilitated. The locking mechanism also comprises a second screw 7, and the second screw 7 penetrates into the vernier caliper 9 and props against the travel indicator 8.
In order to meet the debugging requirement, the debugging precision is improved. The vernier caliper 9 of the lock adjusting mechanism is a 300mm vernier caliper.
Before the test, the travel indicator 8 is aligned with the zero value of the vernier caliper 9, the screw rod 1 is rocked to push the connecting rod 3 to open an emergency lock on the aircraft, and the numerical value on the vernier caliper 9 at the moment is read out to enable the numerical value to meet the requirement. The emergency lock system on the aircraft is connected with the aircraft cabin, and the cockpit cover emergency system directly influences the flight safety of the aircraft and the life safety of pilots, so the requirements on the cockpit emergency system are very high. The lock adjusting mechanism is simple in structure, convenient to operate and easy to carry, and solves the problem that an emergent lock system cannot be adjusted due to the fact that an outgoing army is discharged.
The above technical solution only represents the preferred technical solution of the present invention, and some changes that may be made by those skilled in the art to some parts of the technical solution represent the principles of the present invention, and the technical solution falls within the scope of the present invention.
Claims (3)
1. The utility model provides a transfer lock mechanism which characterized in that: the utility model provides a quick-change type quick-change lock mechanism, including screw rod (1), cushion (2), connecting rod (3), screw one (4), rocking arm (5), round pin stick (6), travel indicator (8), slide caliper (9), screw three (10), screw four (11), screw five (12), screw rod (1) is zigzag screw thread portion front end and connecting rod (3) are connected, cushion (2) are hollow internal screw thread and install on the emergent lock system of aircraft through screw five (12), screw rod (1) screw thread portion and cushion (2) internal thread connection, rocking arm (5) one end is connected the other end through round pin stick (6) with connecting rod (3) through screw one (4) and is connected with travel indicator (8), rocking arm (5) are installed on the emergent lock system of aircraft through screw four (11), slide caliper (9) are installed on the emergent lock system of aircraft through screw three (10), slide caliper (8) pass slide rail inside slide caliper (9).
2. The lock adjustment mechanism of claim 1, wherein: the locking mechanism further comprises a second screw (7), and the second screw (7) penetrates into the vernier caliper (9) and props against the travel indicator (8).
3. The lock mechanism according to claim 1 or 2, wherein: the vernier caliper (9) is a 300mm vernier caliper.
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 CN109110152A (en) | 2019-01-01 |
| CN109110152B true 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) |
Families Citing this family (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 (6)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8744801B2 (en) * | 2007-10-05 | 2014-06-03 | Oceaneering International, Inc. | Controllable caliper |
-
2017
- 2017-06-22 CN CN201710480657.6A patent/CN109110152B/en active Active
Patent Citations (6)
| 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 |
| 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 (1)
| Title |
|---|
| 国外先进战斗机空中应急功能分析;唐正府等;《燃气涡轮试验与研究》;20130215(第01期);53-57 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109110152A (en) | 2019-01-01 |
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