CN115493827B - Device and method for detecting upper lock of nose landing gear of airplane - Google Patents
Device and method for detecting upper lock of nose landing gear of airplane Download PDFInfo
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- CN115493827B CN115493827B CN202211205813.5A CN202211205813A CN115493827B CN 115493827 B CN115493827 B CN 115493827B CN 202211205813 A CN202211205813 A CN 202211205813A CN 115493827 B CN115493827 B CN 115493827B
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- locking
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- 238000000034 method Methods 0.000 title claims abstract description 8
- 230000000149 penetrating effect Effects 0.000 claims abstract description 10
- 238000001514 detection method Methods 0.000 claims description 24
- 238000000926 separation method Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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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
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The invention discloses a device and a method for detecting an upper lock of an aircraft nose landing gear. Comprises a bracket component (1), wherein the front end of the bracket component (1) is provided with a rotating sleeve component (2), and the tail end is connected with a positioning component (3); the positioning assembly (3) comprises a connecting part (31), the connecting part (31) is connected with the arc-shaped groove (32), and the connecting part (31) is used for being connected with the tail end of the bracket assembly (1); waist-shaped guide grooves (33) are formed in groove walls on two sides of the arc-shaped groove (32), a detachable lock rod positioner (34) is arranged between the two waist-shaped guide grooves (33), and the lock rod positioner (34) can be connected with a positioning pin (35) penetrating through the waist-shaped guide grooves (33). The invention has the characteristics of simple structure, high reliability and easy operation.
Description
Technical Field
The invention belongs to the technical field of structural design of aviation technology, and particularly relates to an upper lock detection device and method for an aircraft nose landing gear.
Background
The landing gear up-lock is an important component of a landing gear retraction system, and the basic functional requirements are as follows: under a specified engineering environment, when the landing gear is retracted and operated to an extreme position, the buffer strut is locked and kept fixed at the specified retracted position; when put down, the function of pre-unlocking is completed. In order to simulate the movement of the upper lock of the landing gear, the locking data of the upper lock is mastered, and the landing gear needs to be retracted and extended for a plurality of times. At present, only naked eyes observe, the working efficiency is low, the operation and the observation are very inconvenient in a narrow space in a landing gear cabin, and the labor intensity is high.
Disclosure of Invention
The purpose of the invention is that: an aircraft nose landing gear uplock detection device and method are provided. The invention has the characteristics of simple structure, high reliability and easy operation.
The technical scheme of the invention is as follows: the upper lock detection device for the nose landing gear of the aircraft comprises a bracket assembly, wherein the front end of the bracket assembly is provided with a rotating sleeve assembly, and the tail end of the bracket assembly is connected with a positioning assembly; the positioning assembly comprises a connecting part, the connecting part is connected with the arc-shaped groove, and the connecting part is used for being connected with the tail end of the bracket assembly; the groove walls on two sides of the arc-shaped groove are provided with waist-shaped guide grooves, a detachable lock rod positioner is arranged between the two waist-shaped guide grooves, and the lock rod positioner can be connected with a positioning pin penetrating through the waist-shaped guide grooves.
In the detection device for the upper lock of the nose landing gear of the aircraft, the lock rod locator comprises a T-shaped piece, the bottom end of the T-shaped piece is provided with a locating clamping groove, two ends of the T-shaped piece are respectively and detachably connected with a connecting arm, one connecting arm is in threaded connection with a locking nut penetrating through a waist-shaped guide groove on one side, and locking and locating of the lock rod locator on the waist-shaped guide groove are completed; the locating pin penetrates through the kidney-shaped guide groove on one side and is connected with the inner hole of the locking nut in a threaded manner after penetrating out of the kidney-shaped guide groove on the other side.
In the above-mentioned aircraft nose landing gear upper lock detection device, the swivel assembly comprises a pair of semicircular bushings and a clamp which are oppositely arranged, and the clamp fixes the pair of semicircular bushings which are oppositely arranged at the front end of the bracket assembly.
In the detection device for the upper lock of the nose landing gear of the airplane, the bottom of the connecting part is also provided with a long guide groove; the tail end of the bracket component is provided with a guide post; the guide post can slide in the long guide groove.
In the detection device for the upper lock of the nose landing gear of the aircraft, the bracket component is provided with the lightening hole I.
In the detection device for the upper lock of the nose landing gear of the aircraft, the positioning assembly is provided with the lightening hole II.
The detection method of the detection device for the upper lock of the nose landing gear of the airplane comprises the following steps: the bracket component is rotationally connected to a rotating shaft of the landing gear actuating cylinder of the aircraft by utilizing the rotating sleeve component; rotating the bracket assembly to enable the lock rod of the upper lock to move between the two kidney-shaped guide grooves of the positioning assembly, then pulling the lock rod to the position to be detected, and locking the position to be detected of the lock rod at the moment by using the lock rod positioner; after locking, the lock rod is separated from the positioning component; after separation, the lock rod is replaced by the positioning pin at the position to be detected, and the positioning pin is locked between the two kidney-shaped guide grooves; after the replacement is completed, the rotating bracket component rotates the locating pin to the locking hook position of the upper lock of the landing gear of the aircraft.
In the detection method of the upper lock detection device of the nose landing gear of the aircraft, when the positioning pin can be clamped into the lock hook, the locking is proved to be effective when the lock rod is positioned at the position to be detected; when the locking is impossible, the locking hook is adjusted by the position of the positioning pin, so that the locking is ensured.
The invention has the advantages that: compared with the prior art, the invention provides the landing gear upper lock detection device, wherein the semicircular bushing is divided into two halves, so that the semicircular bushing is convenient to fix on the rotating shaft of the hydraulic actuator cylinder; the semicircular bushing is provided with a groove along the circumference, so that the clamp is convenient to fix, and the overall stability is convenient to maintain; the hanging frame is divided into a left part and a right part, so that the hanging frame is convenient to install in a narrow space in the landing gear cabin; the positioning component is provided with a circular arc waist-shaped guide groove, so that the movement track of the upper lock is fully considered; the locating pin is used for replacing the lock rod to carry out clamping detection, so that the real working state of the upper lock when the landing gear of the aircraft is retracted and released is simulated; the landing gear is prevented from being retracted and released for many times during detection, the working efficiency is improved, the labor intensity is reduced, and meanwhile, the operation is more convenient.
Drawings
FIG. 1 is a state diagram of the present invention;
FIG. 2 is an exploded view of the uplock detection apparatus;
FIG. 3 is a schematic diagram of a lock detection device;
FIG. 4 is a schematic view of a positioning assembly;
FIG. 5 is a schematic view of a rotor assembly;
FIG. 6 is a schematic diagram of a semi-circular bushing structure;
fig. 7 is a schematic view of a small clip structure.
Reference numerals: the device comprises a 1-bracket component, a 11-guide post, a 12-lightening hole I, a 2-rotating sleeve component, a 21-semicircular bushing, a 22-clamp, a 3-positioning component, a 31-connecting part, a 311-long guide groove, a 32-arc groove, a 33-waist-shaped guide groove, a 34-lock rod positioner, a 341-T-shaped piece, a 342-positioning clamping groove, a 343-connecting arm, a 344-locking nut, a 35-positioning pin, a 36-lightening hole II, a 4-lock rod, a 5-lock hook and a 6-landing gear.
Detailed Description
The invention is further illustrated by the following figures and examples, which are not intended to be limiting.
Example 1. 1-7, the detection device for the upper lock of the nose landing gear of the aircraft comprises a bracket assembly 1, wherein the front end of the bracket assembly 1 is provided with a rotating sleeve assembly 2, and the tail end of the bracket assembly is connected with a positioning assembly 3; the positioning assembly 3 comprises a connecting part 31, the connecting part 31 is connected with the arc-shaped groove 32, and the connecting part 31 is used for being connected with the tail end of the bracket assembly 1; waist-shaped guide grooves 33 are formed in groove walls on two sides of the arc-shaped groove 32, a detachable lock rod positioner 34 is arranged between the two waist-shaped guide grooves 33, and the lock rod positioner 34 can be connected with a positioning pin 35 penetrating through the waist-shaped guide grooves 33.
During detection, the bracket component 1 is rotationally connected to the rotating shaft of the landing gear actuator cylinder of the airplane by the rotating sleeve component 2; rotating the bracket component 1 to enable the lock rod 4 of the upper lock to move between the two kidney-shaped guide grooves 33 of the positioning component 3, then pulling the lock rod 4 to the position to be detected, and locking the position to be detected of the lock rod 4 at the moment by using the lock rod positioner 34; after locking, the lock rod 4 is separated from the positioning component 3; after separation, the lock rod 4 is replaced by the positioning pin 35 at the position to be detected, and the positioning pin 35 is locked between the two kidney-shaped guide grooves 33; after the replacement is completed, the rotating bracket assembly 1 rotates the positioning pin 35 to the position of the lock hook 5 of the upper lock of the landing gear of the aircraft; if the positioning pin 35 can be clamped into the lock hook 5, the locking is effective when the lock rod 4 is at the position to be detected; if the locking is impossible, the locking hook 5 is adjusted by the position of the positioning pin 35, so that the locking is ensured.
The lock rod positioner 34 includes a T-shaped member 341, a positioning slot 342 is formed at the bottom end of the T-shaped member 341, two ends of the T-shaped member 341 are detachably connected with a connecting arm 343, wherein one connecting arm 343 is in threaded connection with a locking nut 344 penetrating through one side of the kidney-shaped guide slot 33, so as to complete locking and positioning of the lock rod positioner 34 on the kidney-shaped guide slot 33; the positioning pin 35 is threaded into the kidney-shaped guide groove 33 on one side and is threaded into the inner hole of the locking nut 344 after passing through the kidney-shaped guide groove 33 on the other side.
The lock lever positioner 34 operates as follows: when the lock rod 4 is in the position to be tested, the positioning clamping groove 342 is leaned against the rod body of the lock rod 4, and then the lock nut 344 is used for penetrating through the kidney-shaped guide groove 33 on one side and is in threaded connection with the connecting arm 343 on one side to lock and fix the position of the lock rod positioner 34; then the lock rod 4 is removed, the positioning pin 35 passes through the kidney-shaped guide groove 33 and is in threaded connection with the inner hole of the locking nut 344 to lock and fix the positioning pin 35, at the moment, the positioning clamping groove 342 is leaned against the rod body of the positioning pin 35, and the process finishes the replacement of the lock rod 4 by the positioning pin 35; after the replacement is completed, the T-shaped piece 341 is removed, so that the interference of the positioning pin 35 to the locking hook 5 when the positioning pin 35 rotates to the locking hook 5 is avoided.
The swivel assembly 2 includes a pair of opposed semicircular bushings 21 and a clip 22, and the clip 22 fixes the pair of opposed semicircular bushings 21 to the front end of the bracket assembly 1. By this arrangement, the swivel assembly 2 is made more convenient to mount on the rotating shaft.
The bottom of the connecting part 31 is also provided with an elongated guide slot 311; the tail end of the bracket component 1 is provided with a guide post 11; the guide post 11 can slide in the elongated guide groove 311. Through this structure, can adjust the distance of locating component 3 from the axle center of rotation in radial according to the demand to improve the adaptability of device.
The bracket assembly 1 is provided with a lightening hole I12.
The positioning assembly 3 is provided with a lightening hole II 36. Since the rotation of the bracket assembly 1 is driven by manual work, the arrangement of the lightening holes is beneficial to reducing the labor intensity.
Claims (5)
1. The upper lock detection device for the nose landing gear of the aircraft is characterized by comprising a bracket assembly (1), wherein the front end of the bracket assembly (1) is provided with a rotating sleeve assembly (2), and the tail end of the bracket assembly is connected with a positioning assembly (3); the positioning assembly (3) comprises a connecting part (31), the connecting part (31) is connected with the arc-shaped groove (32), and the connecting part (31) is used for being connected with the tail end of the bracket assembly (1); waist-shaped guide grooves (33) are formed in groove walls on two sides of the arc-shaped groove (32), a detachable lock rod positioner (34) is arranged between the two waist-shaped guide grooves (33), and the lock rod positioner (34) can be connected with a positioning pin (35) penetrating through the waist-shaped guide grooves (33);
The locking rod positioner (34) comprises a T-shaped piece (341), a positioning clamping groove (342) is formed in the bottom end of the T-shaped piece (341), connecting arms (343) are detachably connected to the two ends of the T-shaped piece (341) respectively, one connecting arm (343) is in threaded connection with a locking nut (344) penetrating through one side of the kidney-shaped guide groove (33), and locking and positioning of the locking rod positioner (34) on the kidney-shaped guide groove (33) are completed; the positioning pin (35) penetrates through the kidney-shaped guide groove (33) on one side and is connected with the inner hole of the locking nut (344) in a threaded manner after penetrating out of the kidney-shaped guide groove (33) on the other side;
the rotating sleeve assembly (2) comprises a pair of semicircular bushings (21) and a clamp (22) which are oppositely arranged, and the clamp (22) is used for fixing the pair of semicircular bushings (21) which are oppositely arranged at the front end of the bracket assembly (1);
the bottom of the connecting part (31) is also provided with a long guide groove (311); the tail end of the bracket component (1) is provided with a guide post (11); the guide post (11) can slide in the long guide groove (311).
2. The aircraft nose landing gear uplock detection apparatus as set forth in claim 1, wherein: the bracket component (1) is provided with a lightening hole I (12).
3. The aircraft nose landing gear uplock detection apparatus as set forth in claim 1, wherein: the positioning component (3) is provided with a lightening hole II (36).
4. A method of detecting an aircraft nose landing gear uplock detection apparatus according to any one of claims 1 to 3, wherein: the bracket component (1) is rotationally connected to a rotating shaft of an aircraft landing gear actuator by the rotating sleeve component (2); rotating the bracket component (1) to enable the lock rod (4) of the upper lock to move between two kidney-shaped guide grooves (33) of the positioning component (3), then pulling the lock rod (4) to a position to be detected, and locking the position to be detected of the lock rod (4) at the moment by using the lock rod positioner (34); after locking, the lock rod (4) is separated from the positioning component (3); after separation, the lock rod (4) is replaced at the position to be detected by the positioning pin (35), and the positioning pin (35) is locked between the two kidney-shaped guide grooves (33); after the replacement is completed, the rotating bracket component (1) rotates the locating pin (35) to the position of the lock hook (5) of the upper lock of the landing gear of the aircraft.
5. The method for detecting an aircraft nose landing gear uplock detection apparatus according to claim 4, wherein: when the positioning pin (35) can be clamped into the lock hook (5), the locking is effective when the lock rod (4) is proved to be at the position to be detected; when the locking is impossible, the locking hook (5) is adjusted by the position of the positioning pin (35) to ensure the locking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211205813.5A CN115493827B (en) | 2022-09-30 | 2022-09-30 | Device and method for detecting upper lock of nose landing gear of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211205813.5A CN115493827B (en) | 2022-09-30 | 2022-09-30 | Device and method for detecting upper lock of nose landing gear of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115493827A CN115493827A (en) | 2022-12-20 |
| CN115493827B true CN115493827B (en) | 2024-07-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211205813.5A Active CN115493827B (en) | 2022-09-30 | 2022-09-30 | Device and method for detecting upper lock of nose landing gear of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115493827B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB202112388D0 (en) * | 2019-03-12 | 2021-10-13 | Airbus Operations Ltd | Landing gear system uplock arrangement |
| CN216375058U (en) * | 2021-11-12 | 2022-04-26 | 四川凌峰航空液压机械有限公司 | Aircraft landing gear uplock lock test device |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9927319B2 (en) * | 2013-10-01 | 2018-03-27 | C. Kirk Nance | Method for determining aircraft center of gravity independent of measuring the aircraft weight |
| GB2581793A (en) * | 2019-02-25 | 2020-09-02 | Airbus Operations Ltd | Aircraft landing gear uplock system |
| FR3102141B1 (en) * | 2019-10-17 | 2021-11-05 | Safran Landing Systems | Hanging box fitted with restraint detection means |
-
2022
- 2022-09-30 CN CN202211205813.5A patent/CN115493827B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB202112388D0 (en) * | 2019-03-12 | 2021-10-13 | Airbus Operations Ltd | Landing gear system uplock arrangement |
| CN216375058U (en) * | 2021-11-12 | 2022-04-26 | 四川凌峰航空液压机械有限公司 | Aircraft landing gear uplock lock test device |
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| Publication number | Publication date |
|---|---|
| CN115493827A (en) | 2022-12-20 |
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