CN106153319A - A kind of simulation 8 frame forebody load loaded member for aircraft slow test - Google Patents
A kind of simulation 8 frame forebody load loaded member for aircraft slow test Download PDFInfo
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- CN106153319A CN106153319A CN201610512814.2A CN201610512814A CN106153319A CN 106153319 A CN106153319 A CN 106153319A CN 201610512814 A CN201610512814 A CN 201610512814A CN 106153319 A CN106153319 A CN 106153319A
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- matrix
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- collar tie
- tie beam
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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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- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to aircraft slow test technology, relate to a kind of simulation 8 frame forebody load loaded member for aircraft slow test.It is characterized in that: it includes that matrix (1), 4 loading joints (2), vertical buttress brace (3), horizontal buttress brace (4), collar tie beams (5) are connected section bar (7) with ground board attachment-type material (6) and noselanding gear well.The present invention proposes kind the simulation 8 frame forebody load loaded member for aircraft slow test, is avoided that use origianl structure part, as testpieces, thus considerably reduces experimentation cost.
Description
Technical field
The invention belongs to aircraft slow test technology, relate to a kind of simulation 8 frame forebody for aircraft slow test and carry
Lotus loaded member.
Background technology
Aircraft full machine slow test, its 8 frame forebody is not examined position, is only played imposed load effect.At present
When aircraft full machine slow test, 8 frame forebodys employing origianl structure parts are as testpieces, after full machine slow test, and 8 frame forebodys
Can not re-use, owing to 8 frame forebody manufacturing costs are high, cause the cost of full machine slow test to remain high.
Summary of the invention
It is an object of the invention to: propose kind of the simulation 8 frame forebody load loaded member being used for aircraft slow test, in order to keep away
Exempt to use origianl structure part as testpieces, thus experimentation cost is greatly lowered.
The technical scheme is that a kind of simulation 8 frame forebody load loaded member for aircraft slow test, it is special
Levy and be: it includes 1,4 loading joints 2 of matrix, vertical buttress brace 3, horizontal buttress brace 4, collar tie beam 5 and ground board attachment-type material 6
Section bar 7 is connected with noselanding gear well；Matrix 1 is a plectane, has a circle to be uniformly distributed along the circumference at matrix 1 near the position of circumference
Circumference bolt hole, collar tie beam 5 be a cross section be the annulus of L-shaped, the anchor ring of collar tie beam 5 has the circle that a circle is uniformly distributed along the circumference
Beam bolt hole, the quantity of circumference bolt hole is identical and position is corresponding with on matrix 1 for the quantity of collar tie beam bolt hole, will by bolt
Collar tie beam 5 is fixed on the rear surface of matrix 1；Loading joint 2 cross section is that a cross section isThe component of shape, is loading joint
Have bolt hole in front and rear surfaces, 4 loading joints 2 are bolted on directly over matrix 1, underface, front-left and just right
Side, the position of 4 loading joints 2 is relative to the centrosymmetry of matrix 1；The front surface of matrix 1 there are 4～10 vertically add
Strong muscle 3, the quantity of vertical stiffeners 3 is even number, and the vertical center line of the relative matrix 1 of vertical stiffeners 3 is symmetrical, vertically adds
Strong muscle 3 is welded as entirety with the front surface of matrix 1；Having 2～8 horizontal stiffeners 4 on the front surface of matrix 1, level adds
The quantity of strong muscle 4 is even number, and the horizontal center line of the relative matrix 1 of horizontal stiffener 4 is symmetrical, horizontal stiffener 4 and matrix 1
Front surface be welded as entirety, the infall at horizontal stiffener 4 with vertical stiffeners 3 is also welded as entirety；After matrix 1
Position corresponding with fuselage floor height on surface have a horizontal stretching, cross section be the ground board attachment-type material 6 of L-shaped, ground
Board attachment-type material 6 is welded as entirety with the rear surface of matrix 1；On the rear surface of matrix 1 corresponding with noselanding gear well sidewall
Position have two vertical stretchings, cross section be L-shaped noselanding gear well connect section bar 7, noselanding gear well connect section bar 7 weld
On the rear surface of matrix 1, noselanding gear well connects the upper end of section bar 7 and docks with ground board attachment-type material 6.
The invention has the beneficial effects as follows: propose and plant the simulation 8 frame forebody load loaded member for aircraft slow test,
It is avoided that use origianl structure part, as testpieces, thus considerably reduces experimentation cost.One embodiment of the present of invention, through examination
Verifying bright, experimentation cost reduces more than 80%.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.In figure, the outer direction of paper is front, and in paper, direction is rear, up and down side
To constant.
Fig. 2 is the A-A sectional view of Fig. 1.
Detailed description of the invention
Below the present invention is described in further details.See Fig. 1,2, a kind of simulation 8 frame for aircraft slow test
Forebody load loaded member, it is characterised in that: it include 1,4 loading joints 2 of matrix, vertical buttress brace 3, horizontal buttress brace 4,
Collar tie beam 5 is connected section bar 7 with ground board attachment-type material 6 and noselanding gear well；Matrix 1 is a plectane, at matrix 1 near circumference
There is the circumferential bolt hole that a circle is uniformly distributed along the circumference position, collar tie beam 5 be a cross section be the annulus of L-shaped, at the anchor ring of collar tie beam 5
On have the collar tie beam bolt hole that a circle is uniformly distributed along the circumference, the quantity of collar tie beam bolt hole is identical with the quantity of circumference bolt hole on matrix 1
And position is corresponding, is fixed on the rear surface of matrix 1 by collar tie beam 5 by bolt；Loading joint 2 cross section is that a cross section isThe component of shape, has bolt hole on surface loading before and after joint, and 4 loading joints 2 are just being bolted on matrix 1
Top, underface, front-left and front-right, the position of 4 loading joints 2 is relative to the centrosymmetry of matrix 1；At matrix 1
Having 4～10 vertical stiffeners 3 on front surface, the quantity of vertical stiffeners 3 is even number, the relative matrix 1 of vertical stiffeners 3
Vertical center line is symmetrical, and vertical stiffeners 3 is welded as entirety with the front surface of matrix 1；The front surface of matrix 1 has 2
Root～8 horizontal stiffeners 4, the quantity of horizontal stiffener 4 is even number, the horizontal center line pair of the relative matrix 1 of horizontal stiffener 4
Distribution, horizontal stiffener 4 is claimed to be welded as entirety with the front surface of matrix 1, in intersecting of horizontal stiffener 4 and vertical stiffeners 3
Place is also welded as entirety；Position corresponding with fuselage floor height on the rear surface of matrix 1 has a horizontal stretching, horizontal
Cross section is the ground board attachment-type material 6 of L-shaped, and ground board attachment-type material 6 is welded as entirety with the rear surface of matrix 1；Rear table at matrix 1
Position corresponding with noselanding gear well sidewall on face have two vertical stretchings, cross section be the noselanding gear well connecting-type of L-shaped
Material 7, noselanding gear well connects section bar 7 and is welded on the rear surface of matrix 1, and noselanding gear well connects upper end and the floor of section bar 7
Connect section bar 6 to dock.
The operation principle of the present invention is: by the collar tie beam 5 and 8 frame rear body eyelid covering of 8 frame forebody load loaded member in test
Riveting, loads test load pressurized strut and is connected with the loading joint 2 of 8 frame forebody load loaded member, and load loads pressurized strut
8 frame forebody load are applied to loading joint 2 according to test requirements document.
One embodiment of the present of invention, has 6 vertical stiffeners 3, at the front surface of matrix 1 on the front surface of matrix 1
On have 2 horizontal stiffeners 4.
Claims (1)
1. the simulation 8 frame forebody load loaded member for aircraft slow test, it is characterised in that: it include matrix (1),
4 loading joints (2), vertical buttress brace (3), horizontal buttress brace (4), collar tie beam (5) and ground board attachment-type material (6) and before rise and fall
Frame cabin connects section bar (7)；Matrix (1) is a plectane, in the week that the position of the close circumference of matrix (1) has a circle to be uniformly distributed along the circumference
To bolt hole, collar tie beam (5) be a cross section be the annulus of L-shaped, the anchor ring of collar tie beam (5) has a circle be uniformly distributed along the circumference
Collar tie beam bolt hole, the quantity of collar tie beam bolt hole is identical with the quantity of matrix (1) upper circumference bolt hole and position is corresponding, passes through spiral shell
Collar tie beam (5) is fixed on the rear surface of matrix (1) by bolt；Loading joint (2) cross section is that a cross section isThe component of shape,
Load and have bolt hole on surface before and after joint, 4 loading joints (2) are bolted on directly over matrix (1), just under
Side, front-left and front-right, the position of 4 loading joints (2) is relative to the centrosymmetry of matrix (1)；Front table at matrix (1)
Having 4～10 vertical stiffeners (3) on face, the quantity of vertical stiffeners (3) is even number, vertical stiffeners (3) matrix relatively
(1) vertical center line is symmetrical, and vertical stiffeners (3) is welded as entirety with the front surface of matrix (1)；At matrix (1)
Having 2～8 horizontal stiffeners (4) on front surface, the quantity of horizontal stiffener (4) is even number, horizontal stiffener (4) base relatively
The horizontal center line of body (1) is symmetrical, and horizontal stiffener (4) is welded as entirety with the front surface of matrix (1), strengthens in level
Muscle (4) is also welded as entirety with the infall of vertical stiffeners (3)；On the rear surface of matrix (1) and fuselage floor height pair
The position answered have a horizontal stretching, cross section be ground board attachment-type material (6) of L-shaped, ground board attachment-type material (6) and matrix
(1) rear surface is welded as entirety；Position corresponding with noselanding gear well sidewall on the rear surface of matrix (1) has two to hang down
Straight noselanding gear well that stretch, that cross section is L-shaped connects section bar (7), and noselanding gear well connects section bar (7) and is welded on matrix
(1), on rear surface, noselanding gear well connects the upper end of section bar (7) and docks with ground board attachment-type material (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610512814.2A CN106153319B (en) | 2016-07-01 | 2016-07-01 | A kind of 8 frame forebody load loaded member of simulation for aircraft slow test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610512814.2A CN106153319B (en) | 2016-07-01 | 2016-07-01 | A kind of 8 frame forebody load loaded member of simulation for aircraft slow test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106153319A true CN106153319A (en) | 2016-11-23 |
| CN106153319B CN106153319B (en) | 2018-07-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610512814.2A Active CN106153319B (en) | 2016-07-01 | 2016-07-01 | A kind of 8 frame forebody load loaded member of simulation for aircraft slow test |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106596003A (en) * | 2016-11-29 | 2017-04-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite aircraft fuselage section pressurizing test method |
| CN107101811A (en) * | 2017-04-18 | 2017-08-29 | 西北工业大学 | A kind of aircraft main landing gear side brace bonding pad bearer properties experiment loading unit |
| CN107521721A (en) * | 2017-07-20 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test fuselage course load designing load method |
| CN110228603A (en) * | 2019-05-29 | 2019-09-13 | 陕西飞机工业（集团）有限公司 | It is a kind of for simulating the slow test end frame of Aircraft Air state |
| CN110803296A (en) * | 2019-10-15 | 2020-02-18 | 中国直升机设计研究所 | Helicopter full-mechanical static test lift force system dummy |
| WO2023123731A1 (en) * | 2021-12-31 | 2023-07-06 | 北京空间机电研究所 | Truss-type structure loading device and method for static test of spacecraft hull propulsion module |
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| WO2005043107A2 (en) * | 2003-10-30 | 2005-05-12 | Hottinger Baldwin Messtechnik Gmbh | Device for determining strains on fiber composite components |
| CN203350022U (en) * | 2013-01-05 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Restraint device of large airplane part test |
| CN203365124U (en) * | 2013-07-18 | 2013-12-25 | 连云港中复连众复合材料集团有限公司 | Full-dimension test system and platform for megawatt-level blower fan blade |
| CN103723285A (en) * | 2013-12-04 | 2014-04-16 | 中国飞机强度研究所 | Empennage load applying device used for plane structure strength tests |
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| RU2158909C1 (en) * | 2000-03-07 | 2000-11-10 | Лабзин Василий Васильевич | Stand for testing transmission mechanism of flying vehicle aerodynamic control surface actuator |
| WO2005043107A2 (en) * | 2003-10-30 | 2005-05-12 | Hottinger Baldwin Messtechnik Gmbh | Device for determining strains on fiber composite components |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106596003A (en) * | 2016-11-29 | 2017-04-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite aircraft fuselage section pressurizing test method |
| CN106596003B (en) * | 2016-11-29 | 2019-04-23 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of composite airplane frame sections pressurising test method |
| CN107101811A (en) * | 2017-04-18 | 2017-08-29 | 西北工业大学 | A kind of aircraft main landing gear side brace bonding pad bearer properties experiment loading unit |
| CN107101811B (en) * | 2017-04-18 | 2019-03-29 | 西北工业大学 | A kind of aircraft main landing gear side brace bonding pad bearer properties experiment loading unit |
| CN107521721A (en) * | 2017-07-20 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test fuselage course load designing load method |
| CN107521721B (en) * | 2017-07-20 | 2020-07-07 | 中国航空工业集团公司西安飞机设计研究所 | Full-size fatigue test fuselage course load loading design method |
| CN110228603A (en) * | 2019-05-29 | 2019-09-13 | 陕西飞机工业（集团）有限公司 | It is a kind of for simulating the slow test end frame of Aircraft Air state |
| CN110803296A (en) * | 2019-10-15 | 2020-02-18 | 中国直升机设计研究所 | Helicopter full-mechanical static test lift force system dummy |
| WO2023123731A1 (en) * | 2021-12-31 | 2023-07-06 | 北京空间机电研究所 | Truss-type structure loading device and method for static test of spacecraft hull propulsion module |
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| Publication number | Publication date |
|---|---|
| CN106153319B (en) | 2018-07-24 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Hanzhoung, Shaanxi Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |