CN107757945A - A kind of measurement apparatus for aircraft nose landing gear uplock emergent unlocking - Google Patents
A kind of measurement apparatus for aircraft nose landing gear uplock emergent unlocking Download PDFInfo
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- CN107757945A CN107757945A CN201710817150.5A CN201710817150A CN107757945A CN 107757945 A CN107757945 A CN 107757945A CN 201710817150 A CN201710817150 A CN 201710817150A CN 107757945 A CN107757945 A CN 107757945A
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- steel wire
- screw rod
- wire rope
- emergent
- measurement apparatus
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Abstract
The invention belongs to aircraft mounting technology field, discloses a kind of measurement apparatus for aircraft nose landing gear uplock emergent unlocking.Including bearing (1), screw rod (2), flexible handle (3), pulley assembly (4), steel wire rope (5)；The device transmits the principles such as force value using leading screw regulation height, fixed pulley, ensure that steel wire rope is in same level height with preceding emergent handle, it is simple in construction, solve after nose-gear receives and lock, preceding uplock under emergency conditions unlocking force value can not test problems, and dual lock force value carries out dominant quantization, it is easy to use, have a wide range of application, improve measurement accuracy and product quality, ensured flight safety.
Description
Technical field
The invention belongs to aircraft mounting technology field, is related to a kind of survey for aircraft nose landing gear uplock emergent unlocking
Measure device.
Background technology
Undercarriage layout uses first three point type, fuselage is inwardly closed at, in order in various air strip landings, aircraft landing
During, can landing gear uplock reliably unlock-put down and lock, due to by structure, installation form, product performance
Restrict, nose-gear uplock emergent unlocking power can not detect, and only pass through artificially fuzzy carry out functional trial, emergent unlocking
Force value is not energetic, and using the method for " about estimating ", mass defect is caused to Aircraft Production.
On preceding upper lock support, preceding uplock is in turn mounted at upper lock support for the preceding emergent unlocking system integration
On, support is connected with airframe structure section bar again.It is whole that this is a set of (nose-gear, preceding uplock, upper lock support, preceding
Emergent unlocking system) all in noselanding gear well.After undercarriage tightens up noselanding gear well completely, whole nose-gear
Cabin space is extremely narrow and small, so when with preceding emergent unlocking system blow the gear down, by structure, intensity, construction space, finished product
The restriction of itself assembly properties, operating personnel can only one man operation, because will be from floor under floor during operation, operating personnel
The position of emergent unlocking handle can only be seen clearly in advance, then on one knee, a hand is used for supporting the weight of body, grasps body
Balance, the other hand is put in by the emergent mouth of the Φ 300mm on front deck floor has led cabin with feeling to find red emergent unlocking hand
Handle, 23mm is stretched with 490N~980N power towards aircraft outside perpendicular to upper lock support, passes through emergent unlocking handle and drives steel
Uplock is played before Suo Lakai, nose-gear is slowly fallen with deadweight and then uses emergent lock system again by nose-gear down lock
Pin, in drawing process, limited by locus, easily come off, force-detecting position position inaccurate.
The content of the invention
Goal of the invention：Instant invention overcomes in the prior art can not dynamometry the shortcomings that, there is provided one kind installation is accurate, operation
Simply, service precision is high, and directly acts on the emergent unlocking measurement apparatus of nose-gear uplock.
Technical scheme：In order to solve the above-mentioned technical problem, the present invention is achieved by the following technical solutions：One kind is used for
The measurement apparatus of aircraft nose landing gear uplock emergent unlocking, it is characterized in that, including bearing 1, screw rod 2, flexible handle 3, pulley
Component 4, steel wire rope 5；The upper end of screw rod 2 is connected with flexible handle 3, and lower end is connected through the screwed hole of bearing 1 with component 4, steel wire rope 5
One end is designed to form of hooks, and the other end is designed to suspension ring shape, and form of hooks one end is passed down through bearing 1 and bypasses the chute of pulley assembly 4
It is connected with preposition red handle on aircraft, suspension ring shape one end is connected with dynamometer.
The bearing 1 is flange dish type, has the swivel nut uniformly supported by 3 legs, swivel nut hole and method directly over center
Blue disk female coaxial.
The main body of screw rod 2 is shaft-like, and there is through hole upper end, and flexible handle 3 is arranged in through hole, and lower end is pitched for triangle
There is coaxial aperture ear, termination, and pulley assembly 4 is in triangle fork ear.
The pulley assembly 4 includes aluminium alloy single-grooved pulleys 6, hinge axis 7, plain washer 8, split pin 9；Hinge axis 7 passes through
The lower end triangle fork ear coaxial aperture of screw rod 2 and aluminium alloy single-grooved pulleys 6, plain washer 8 are connected with split pin 9.
The bearing 1 is flange dish type, has the swivel nut uniformly supported by 3 legs, swivel nut hole and method directly over center
Blue disk female coaxial, screw rod 2 is in swivel nut and ring flange.
Beneficial effect
Compared with prior art, the beneficial effects of the invention are as follows：
The invention provides one kind installation accurately, simple to operate, service precision is high, and it is upper to directly act on nose-gear
The emergent unlocking measurement apparatus of lock.The measurement apparatus quantifies emergent unlocking force value, and dynamometry is convenient, is examined in time in assembling stage
Survey, prevent the generation of quality problems；The connected mode of form of hooks, during the twisting of force-detecting position is found, easily avoid locked groove not
Come off, while certain adjustment amount is provided for the accumulated error of aircraft assembling, and without other objective influence factors, ensure
The accuracy of measurement force value；Technological equipment performance and product quality are improved, has saved manpower, material resources and financial resources, is shortened
Production cycle.
Brief description of the drawings
Fig. 1 is the structural representation of measurement apparatus of the present invention；
Fig. 2 is bearing structure illustration of the present invention；
Fig. 3 is screw-rod structure schematic diagram of the present invention；
Fig. 4 is pulley block structure diagrammatic elevation view of the present invention；
Fig. 5 is pulley block structure schematic sectional view of the present invention；
Fig. 6 is steel cord structure schematic diagram of the present invention.
Wherein：1 is bearing, and 2 be screw rod, and 3 be flexible handle, and 4 be pulley assembly, and 5 be steel wire rope, and 6 be aluminium alloy single groove
Pulley, 7 be hinge axis, and 8 be plain washer, and 9 be split pin.
Embodiment
The present invention is described in further detail with embodiment below in conjunction with the accompanying drawings：
A kind of measurement apparatus for aircraft nose landing gear uplock emergent unlocking, as shown in figure 1, including bearing 1, screw rod
2nd, flexible handle 3, pulley assembly 4, steel wire rope 5.The upper end of screw rod 2 is connected with flexible handle 3, passes through the rotation of flexible handle 3, band
Dynamic the moving up and down in bearing 1 of screw rod 2, carry out adjustable pulley height, and then ensure that steel wire rope 5 is in together with preceding emergent handle
One level height, be advantageous to the positioning of force-detecting position, facilitate accurate dynamometry；The lower end of screw rod 2 is connected through the screwed hole of bearing 1 and pulley
Component 4 connects, and the one end of steel wire rope 5 is designed to form of hooks, and the other end is designed to suspension ring shape, and form of hooks one end is passed down through bearing 1
It is connected around the chute of pulley assembly 4 with red handle on aircraft, suspension ring shape one end is connected with dynamometer.Steel wire rope 5 passes through dynamometer
Tense, ensure that steel wire rope 5 is brought into close contact with the chute of aluminium alloy single-grooved pulleys 6, and then ensure at steel wire rope 5 and preceding emergent handle
In same level height.
As shown in Fig. 2 bearing 1 is flange dish type, there are the swivel nut uniformly supported by 3 legs, swivel nut directly over center
Hole and ring flange female coaxial, screw rod 2 is in swivel nut and ring flange.
As shown in figure 3, the main body of screw rod 2 is shaft-like, there is through hole upper end, and lower end is that triangle pitches ear, and termination has coaxially
Hole, pulley assembly 4 is in triangle fork ear.
As shown in Figure 4, Figure 5, the pulley assembly 4 includes aluminium alloy single-grooved pulleys 6, hinge axis 7, plain washer 8, split pin
9；Hinge axis 7 is pitched ear, aluminium alloy single-grooved pulleys 6, plain washer 8 by the lower end triangle of screw rod 2 and is connected with split pin 9.
As shown in fig. 6, the steel wire rope 5 is designed to one end of form of hooks and the preceding emergent preposition red handle of lock be connected,
It is designed to that one end of suspension ring shape is connected with dynamometer；Tensed by dynamometer, ensure that steel wire rope 5 is slided with aluminium alloy single-grooved pulleys 6
Groove is brought into close contact, and then ensures that steel wire rope 5 is in same level height with preceding emergent handle.
The present apparatus is the nose-gear uplock emergent unlocking measuring appliance to match with aeroplane performance, and the measuring appliance is using cunning
Wheeled exchanging structure, pulley ensure that switching height is in same level with preceding emergent handle using leading screw regulation height and position
Highly, dynamometry process, can be easy to find unlocking force-detecting position with flexible rotating, so as to improve the preceding precision for playing emergent unlocking measurement.
Using this form, in measurement process, operating personnel can not have to measure in preceding cabin, pass through front deck floor φ
300mm emergent mouth, measuring appliance is put down, and one end is connected with the preceding emergent preposition red handle of lock, and one end is connected with dynamometer, is entered
Row dynamometry, institute's dynamometry value play the size of emergent unlocking power before being
Operating process is as follows：
1. all parts in the manufacture present invention；
2. the measurement apparatus of the present invention is installed aboard；
3. the structure by the rotation of flexible handle, drives screw rod moving up and down in the holder, carry out adjustable pulley height,
And then ensure that steel wire rope is in same level height, and fine rotation with preceding emergent handle, the position of force-detecting position is determined, is entered
Row dynamometry.
Claims (6)
1. a kind of measurement apparatus for aircraft nose landing gear uplock emergent unlocking, it is characterized in that, including bearing (1), screw rod
(2), flexible handle (3), pulley assembly (4), steel wire rope (5)；Screw rod (2) upper end is connected with flexible handle (3), and lower end passes through branch
Seat (1) screwed hole is connected with component (4), and steel wire rope (5) one end is designed to form of hooks, and the other end is designed to suspension ring shape, form of hooks
One end is passed down through bearing (1) and is connected around pulley assembly (4) chute with preposition red handle on aircraft, suspension ring shape one end and dynamometry
Meter connection.
2. it is used for the measurement apparatus of aircraft nose landing gear uplock emergent unlocking as claimed in claim 1, it is characterized in that, it is described
Bearing (1) is flange dish type, has the swivel nut uniformly supported by 3 legs directly over center, swivel nut hole and ring flange endoporus are same
Axle, screw rod (2) is in swivel nut and ring flange.
3. it is used for the measurement apparatus of aircraft nose landing gear uplock emergent unlocking as claimed in claim 1 or 2, it is characterized in that,
Screw rod (2) main body is screw rod, and there is through hole upper end, and lower end is that triangle pitches ear, and there is coaxial aperture termination, and pulley assembly 4 is mounted in
In triangle fork ear.
4. it is used for the measurement apparatus of aircraft nose landing gear uplock emergent unlocking as claimed in claim 3, it is characterized in that, it is described
Pulley assembly (4) includes aluminium alloy single-grooved pulleys (6), hinge axis (7), plain washer (8), split pin (9)；Hinge axis (7) passes through
Screw rod (2) lower end triangle fork ear, aluminium alloy single-grooved pulleys (6), plain washer (8) are connected with split pin (9).
5. it is used for the measurement apparatus of aircraft nose landing gear uplock emergent unlocking as claimed in claim 4, it is characterized in that, it is described
The device drives screw rod (2) moving up and down in bearing (1), carrys out adjustable pulley height by the rotations of flexible handle (3),
Ensure that steel wire rope (5) is in same level height with preceding emergent handle.
6. it is used for the measurement apparatus of aircraft nose landing gear uplock emergent unlocking as claimed in claim 4, it is characterized in that, it is described
Steel wire rope (5) is tensed by dynamometer, is ensured that steel wire rope (5) is brought into close contact with aluminium alloy single-grooved pulleys (6) chute, is ensured steel wire
Rope (5) is in same level height with preceding emergent handle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817150.5A CN107757945B (en) | 2017-09-12 | 2017-09-12 | Measuring device for emergency unlocking of uplock of nose landing gear of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817150.5A CN107757945B (en) | 2017-09-12 | 2017-09-12 | Measuring device for emergency unlocking of uplock of nose landing gear of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107757945A true CN107757945A (en) | 2018-03-06 |
| CN107757945B CN107757945B (en) | 2020-01-10 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710817150.5A Active CN107757945B (en) | 2017-09-12 | 2017-09-12 | Measuring device for emergency unlocking of uplock of nose landing gear of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107757945B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110056197A1 (en) * | 2007-12-21 | 2011-03-10 | Messier-Dowty Inc. | Landing gear uplock mechanism employing thermal phase-change actuation |
| CN102139760A (en) * | 2011-01-13 | 2011-08-03 | 陕西飞机工业（集团）有限公司 | Airplane undercarriage emergence extension steel cable system |
| CN103523213A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Landing gear uplock |
| CN204210730U (en) * | 2014-09-18 | 2015-03-18 | 中国商用飞机有限责任公司 | Landing gear uplock mechanism |
| CN204433026U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | A kind of hatch door is received and is put in place and lock detection device |
| CN104890862A (en) * | 2015-06-24 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Undercarriage emergency putting control system |
| CN107036745A (en) * | 2017-04-24 | 2017-08-11 | 西北工业大学 | Latch hook staring torque measurement apparatus and method for uplock reliability test |
-
2017
- 2017-09-12 CN CN201710817150.5A patent/CN107757945B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110056197A1 (en) * | 2007-12-21 | 2011-03-10 | Messier-Dowty Inc. | Landing gear uplock mechanism employing thermal phase-change actuation |
| CN102139760A (en) * | 2011-01-13 | 2011-08-03 | 陕西飞机工业（集团）有限公司 | Airplane undercarriage emergence extension steel cable system |
| CN103523213A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Landing gear uplock |
| CN204210730U (en) * | 2014-09-18 | 2015-03-18 | 中国商用飞机有限责任公司 | Landing gear uplock mechanism |
| CN204433026U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | A kind of hatch door is received and is put in place and lock detection device |
| CN104890862A (en) * | 2015-06-24 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Undercarriage emergency putting control system |
| CN107036745A (en) * | 2017-04-24 | 2017-08-11 | 西北工业大学 | Latch hook staring torque measurement apparatus and method for uplock reliability test |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107757945B (en) | 2020-01-10 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |