CN107757945B - Measuring device for emergency unlocking of uplock of nose landing gear of airplane - Google Patents
Measuring device for emergency unlocking of uplock of nose landing gear of airplane Download PDFInfo
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- CN107757945B CN107757945B CN201710817150.5A CN201710817150A CN107757945B CN 107757945 B CN107757945 B CN 107757945B CN 201710817150 A CN201710817150 A CN 201710817150A CN 107757945 B CN107757945 B CN 107757945B
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- landing gear
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- uplock
- screw
- wire rope
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Abstract
The invention belongs to the technical field of airplane assembly and discloses a measuring device for emergency unlocking of an uplock of a nose landing gear of an airplane. Comprises a support (1), a screw (2), a movable handle (3), a pulley component (4) and a steel wire rope (5); the device utilizes principles such as lead screw height-adjusting, fixed pulley transmission power value, guarantees that wire rope and the emergent handle of leading-up are in same level, and simple structure has solved the undercarriage and has received the back of locking, and the unable problem that detects of the power value of unblanking under the emergent condition of the lock on the leading-up to carry out the dominance to the power value of unblanking and quantizing, convenient to use, the range of application is wide, has improved measurement accuracy and product quality, has ensured flight safety.
Description
Technical Field
The invention belongs to the technical field of airplane assembly, and relates to a measuring device for emergency unlocking of an uplock of a nose landing gear of an airplane.
Background
The landing gear layout adopts three points in front, and the landing gear is inwards accommodated in the fuselage, so that in the taking-off and landing process of various simple runways, and in the landing process of an airplane, whether the landing gear uplock can be reliably unlocked, put down and locked cannot be detected, because of the restriction of the structure, the installation form and the product characteristics, the emergency unlocking force of the landing gear uplock cannot be detected, only the functional test is carried out through artificial fuzziness, the emergency unlocking force value cannot be quantized, and the quality defect is caused to the airplane production by adopting an 'approximate estimation' method.
The front-lift emergency unlocking system is integrated on a front-lift upper lock bracket, the front-lift upper lock is arranged on the upper lock bracket, and the bracket is connected with the structural section of the machine body. The whole set (nose landing gear, a front lifting uplock, an uplock bracket and a front lifting emergency unlocking system) is completely arranged in the nose landing gear cabin. When the landing gear is completely tightened up in the nose landing gear cabin, the space of the whole nose landing gear cabin is extremely narrow, so when the landing gear is placed by the nose-up emergency unlocking system, under the restriction of structure, strength, construction space and the self-assembly characteristic of a finished product, an operator can only operate by one person, when in operation, the operator can only see the position of the emergency unlocking handle in advance from the floor to the under the floor, then the operator can only hold down the emergency unlocking handle by one knee, one hand is used for supporting the weight of the body and mastering the balance of the body, the other hand extends into the main cabin through an emergency opening with the diameter of 300mm on the floor of the nose cabin and finds the red emergency unlocking handle by feeling, the bracket perpendicular to the upper lock is stretched by the force of 490N-980N towards the outer side of the airplane, the steel cable is driven by the emergency unlocking handle to pull the nose-up upper lock, so that the nose landing gear slowly falls along with the dead, in the stretching process, the stretching device is limited by the spatial position, is easy to fall off, and the location of the force measuring point is inaccurate.
Disclosure of Invention
The purpose of the invention is as follows: the invention overcomes the defect that the force can not be measured in the prior art, and provides the emergency unlocking measuring device which is accurate in installation, simple in operation, high in use precision and directly acts on the uplock of the nose landing gear.
The technical scheme is as follows: in order to solve the technical problems, the invention is realized by the following technical scheme: a measuring device for emergency unlocking of an uplock of a nose landing gear of an airplane is characterized by comprising a support 1, a screw rod 2, a movable handle 3, a pulley assembly 4 and a steel wire rope 5; the upper end of the screw rod 2 is connected with the movable handle 3, the lower end of the screw rod passes through a threaded hole of the support 1 to be connected with the component 4, one end of the steel wire rope 5 is designed into a hook shape, the other end of the steel wire rope is designed into a hanging ring shape, one end of the hook shape downwards passes through the support 1 to bypass a sliding groove of the pulley component 4 to be connected with a front red handle on the airplane, and one end of the hanging ring shape.
The support 1 is in a flange disc shape, a threaded sleeve which is uniformly supported by 3 support legs is arranged right above the center, and a threaded sleeve hole is coaxial with an inner hole of the flange plate.
The main body of the screw rod 2 is rod-shaped, the upper end of the screw rod is provided with a through hole, the movable handle 3 is arranged in the through hole, the lower end of the screw rod is provided with a triangular fork lug, the end of the screw rod is provided with a coaxial hole, and the pulley component 4 is arranged in the triangular fork lug.
The pulley component 4 comprises an aluminum alloy single-groove pulley 6, a hinge shaft 7, a flat washer 8 and a cotter pin 9; the hinge shaft 7 is connected with a cotter pin 9 through a triangular fork ear coaxial hole at the lower end of the screw rod 2, an aluminum alloy single-groove pulley 6 and a flat washer 8.
The support 1 is in a flange disc shape, a threaded sleeve which is uniformly supported by 3 support legs is arranged right above the center, a threaded sleeve hole is coaxial with an inner hole of the flange disc, and the screw rod 2 is arranged in the threaded sleeve and the flange disc.
Advantageous effects
Compared with the prior art, the invention has the beneficial effects that:
the invention provides the emergency unlocking measuring device which is accurate in installation, simple in operation and high in use precision and directly acts on the uplock of the nose landing gear. The measuring device quantifies the emergency unlocking force value, is convenient to measure the force, and can detect in time in the assembly stage to avoid the quality problem; the hook-shaped connection mode is easy to avoid the lock groove from falling off in the twisting process of searching the force measuring point, provides a certain adjustment amount for the accumulated error of airplane assembly, has no other objective influence factors, and ensures the accuracy of the force measuring value; the performance of the process equipment and the product quality are improved, the manpower, material resources and financial resources are saved, and the production period is shortened.
Drawings
FIG. 1 is a schematic view of the structure of the measuring device of the present invention;
FIG. 2 is a schematic view of the stand-off structure of the present invention;
FIG. 3 is a schematic view of the screw configuration of the present invention;
figure 4 is a schematic elevational view of the sheave assembly of the present invention;
figure 5 is a schematic cross-sectional view of the sheave assembly of the present invention;
fig. 6 is a schematic view of the construction of the steel cord according to the invention.
Wherein: the device comprises a support 1, a screw rod 2, a movable handle 3, a pulley assembly 4, a steel wire rope 5, an aluminum alloy single-groove pulley 6, a hinge shaft 7, a flat washer 8 and a cotter pin 9.
Detailed Description
The invention is described in further detail below with reference to the following detailed description and accompanying drawings:
a measuring device for emergency unlocking of an uplock of a nose landing gear of an airplane is shown in figure 1 and comprises a support 1, a screw rod 2, a movable handle 3, a pulley assembly 4 and a steel wire rope 5. The upper end of the screw rod 2 is connected with the movable handle 3, the screw rod 2 is driven to move up and down in the support 1 through the rotation of the movable handle 3, the height of the pulley is adjusted, and the steel wire rope 5 and the front emergency handle are ensured to be at the same horizontal height, so that the positioning of a force measuring point is facilitated, and the force measurement is convenient and accurate; the lower end of the screw rod 2 penetrates through a threaded hole of the support 1 to be connected with the pulley assembly 4, one end of the steel wire rope 5 is designed into a hook shape, the other end of the steel wire rope is designed into a hanging ring shape, one end of the hook shape downwards penetrates through the support 1 to bypass a sliding groove of the pulley assembly 4 to be connected with an airplane upper red handle, and one end of the hanging ring shape is connected with the dynamometer. The steel wire rope 5 is tensioned through the dynamometer, the steel wire rope 5 is tightly attached to the sliding groove of the aluminum alloy single-groove pulley 6, and the steel wire rope 5 and the front emergency handle are located at the same horizontal height.
As shown in figure 2, the support 1 is in the shape of a flange plate, a threaded sleeve which is uniformly supported by 3 support legs is arranged right above the center, a threaded sleeve hole is coaxial with an inner hole of the flange plate, and the screw rod 2 is arranged in the threaded sleeve and the flange plate.
As shown in fig. 3, the main body of the screw 2 is rod-shaped, the upper end of the screw is provided with a through hole, the lower end of the screw is provided with a triangular fork lug, the end of the screw is provided with a coaxial hole, and the pulley component 4 is arranged in the triangular fork lug.
As shown in fig. 4 and 5, the pulley assembly 4 comprises an aluminum alloy single-groove pulley 6, a hinge shaft 7, a flat washer 8 and a cotter pin 9; the hinge shaft 7 is connected with a cotter pin 9 through a triangular fork lug at the lower end of the screw rod 2, an aluminum alloy single-groove pulley 6 and a flat washer 8.
As shown in fig. 6, one end of the steel wire rope 5 which is designed to be in a hook shape is connected with a front red handle of the front lifting emergency lock, and one end which is designed to be in a suspension loop shape is connected with the dynamometer; through the dynamometer tensioning, guarantee that wire rope 5 and 6 spouts of aluminum alloy list groove pulley are closely laminated, and then guarantee that wire rope 5 and the emergent handle of having just risen are in same level.
The device is an emergency unlocking measurer of a nose landing gear uplock matched with the performance of an airplane, the measurer adopts a pulley type switching structure, the pulley utilizes a lead screw to adjust the height and position, the switching height and a front lifting emergency handle are guaranteed to be at the same horizontal height, the force measuring process can be flexibly rotated, an unlocking force measuring point is convenient to find, and therefore the precision of front lifting emergency unlocking measurement is improved. By adopting the form, in the measuring process, an operator can measure without the need of a front lifting cabin, the measurer is put down through an emergency opening with the diameter of 300mm on the floor of the front cabin, one end of the measurer is connected with a front red handle of the front lifting emergency lock, the other end of the measurer is connected with a dynamometer for measuring force, and the measured force value is the magnitude of the front lifting emergency unlocking force
The operation process is as follows:
1. all parts in the invention are manufactured;
2. the measuring device is installed on an airplane;
3. the structure drives the screw rod to move up and down in the support through the rotation of the movable handle to adjust the height of the pulley, so that the steel wire rope and the front emergency handle are ensured to be positioned at the same horizontal height, and slightly rotate to determine the position of a force measuring point for measuring force.
Claims (6)
1. A measuring device for emergency unlocking of an uplock of a nose landing gear of an airplane is characterized by comprising a support (1), a screw (2), a movable handle (3), a pulley assembly (4) and a steel wire rope (5); the upper end of the screw rod (2) is connected with the movable handle (3), the lower end of the screw rod penetrates through a threaded hole of the support (1) to be connected with the component (4), one end of the steel wire rope (5) is designed into a hook shape, the other end of the steel wire rope is designed into a hanging ring shape, one end of the hook shape downwards penetrates through the support (1) to bypass a sliding groove of the pulley component (4) to be connected with a front emergency handle on an airplane, and one end of the hanging ring shape is connected.
2. The device for measuring the emergency unlocking of the uplock of the nose landing gear of the airplane as claimed in claim 1, wherein said support (1) is in the shape of a flange disk, a threaded sleeve is uniformly supported by 3 support legs right above the center, the threaded sleeve hole is coaxial with the inner hole of the flange disk, and the screw rod (2) is arranged in the threaded sleeve and the flange disk.
3. The device for measuring the emergency unlocking of the uplock on the nose landing gear of an aircraft according to claim 1 or 2, characterized in that the body of the screw (2) is a screw, the upper end of the screw is provided with a through hole, the lower end of the screw is provided with a triangular fork lug, the end of the screw is provided with a coaxial hole, and the pulley assembly 4 is arranged in the triangular fork lug.
4. The device for measuring the emergency unlocking of the uplock of the nose landing gear of an aircraft according to claim 3, characterized in that said pulley assembly (4) comprises an aluminum alloy single-groove pulley (6), a hinge shaft (7), a flat washer (8), a cotter pin (9); the hinge shaft (7) is connected with a cotter pin (9) through a triangular fork lug at the lower end of the screw rod (2), an aluminum alloy single-groove pulley (6) and a flat washer (8).
5. The device for measuring the emergency unlocking of the uplock on the nose landing gear of an airplane as claimed in claim 4, characterized in that the device drives the screw (2) to move up and down in the support (1) by the rotation of the movable handle (3) to adjust the height of the pulley, so as to ensure that the steel cable (5) and the emergency handle are at the same level.
6. The measuring device for the emergency unlocking of the uplock of the nose landing gear of the airplane as claimed in claim 4, wherein the steel wire rope (5) is tensioned by a dynamometer, so that the steel wire rope (5) is tightly attached to the sliding groove of the aluminum alloy single-groove pulley (6), and the steel wire rope (5) and the front emergency handle are at the same horizontal height.
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 CN107757945A (en) | 2018-03-06 |
| CN107757945B true CN107757945B (en) | 2020-01-10 |
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| 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 |
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| Country | Link |
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| CN (1) | CN107757945B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8567716B2 (en) * | 2007-12-21 | 2013-10-29 | Messier-Dowty Inc. | Landing gear uplock mechanism employing thermal phase-change actuation |
-
2017
- 2017-09-12 CN CN201710817150.5A patent/CN107757945B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| Publication number | Publication date |
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| CN107757945A (en) | 2018-03-06 |
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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. |
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