CN106153319B - A kind of 8 frame forebody load loaded member of simulation for aircraft slow test - Google Patents
A kind of 8 frame forebody load loaded member of simulation for aircraft slow test Download PDFInfo
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- CN106153319B CN106153319B CN201610512814.2A CN201610512814A CN106153319B CN 106153319 B CN106153319 B CN 106153319B CN 201610512814 A CN201610512814 A CN 201610512814A CN 106153319 B CN106153319 B CN 106153319B
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- matrix
- section bar
- connection section
- load
- collar tie
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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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to aircraft slow test technologies, are related to a kind of 8 frame forebody load loaded member of simulation for aircraft slow test.It is characterized in that：It includes matrix (1), 4 load connectors (2), vertical reinforcing beam (3), lateral reinforcing beam (4), collar tie beam (5) and floor connection section bar (6) and noselanding gear well connection section bar (7).The present invention proposes kind of the 8 frame forebody load loaded member of simulation for being used for aircraft slow test, is avoided that using origianl structure part as testpieces, to considerably reduce experimentation cost.
Description
Technical field
The invention belongs to aircraft slow test technologies, are related to a kind of 8 frame forebody of simulation load for aircraft slow test
Lotus loaded member.
Background technology
The full machine slow test of aircraft, 8 frame forebodys do not examine position, only play the role of applying load.At present
In the full machine slow test of aircraft, 8 frame forebodys are using origianl structure part as testpieces, after full machine slow test, 8 frame forebodys
It cannot reuse, since 8 frame forebody manufacturing costs are high, cause the cost of full machine slow test high.
Invention content
The purpose of the present invention is：Kind of the 8 frame forebody load loaded member of simulation for being used for aircraft slow test is proposed, to keep away
Exempt to use origianl structure part as testpieces, to which experimentation cost be greatly lowered.
The technical scheme is that：A kind of 8 frame forebody load loaded member of simulation for aircraft slow test, it is special
Sign is：It includes 1,4 load connector 2 of matrix, vertical stiffeners 3, horizontal stiffener 4, collar tie beam 5 and floor connection section bar 6
With noselanding gear well connection section bar 7；Matrix 1 is a plectane, has a circle to be uniformly distributed along the circumference close to the position of circumference in matrix 1
Circumferential bolt hole, collar tie beam 5 are that a cross section is L-shaped annulus, there is the circle that a circle is uniformly distributed along the circumference on the anchor ring of collar tie beam 5
Beam bolt hole, the quantity of collar tie beam bolt hole with the circumferential quantity of bolt hole is identical on matrix 1 and position is correspondings, pass through bolt general
Collar tie beam 5 is fixed in the rear surface of matrix 1；It is that a cross section is to load 2 section of connectorThe component of shape, in load connector
There are bolt hole, 4 load connectors 2 to be bolted on 1 surface of matrix, underface, front-left and the positive right side in front and rear surfaces
Just, central symmetry of the position of 4 load connectors 2 relative to matrix 1；There are 4~10 vertically to add in the front surface of matrix 1
The quantity of strengthening tendons 3, vertical stiffeners 3 is even number, and vertical stiffeners 3 are symmetrical with respect to the vertical center line of matrix 1, vertical to add
Strengthening tendons 3 and the front surface of matrix 1 are welded as entirety；There are 2~8 horizontal stiffeners 4, level to add in the front surface of matrix 1
The quantity of strengthening tendons 4 is even number, and horizontal stiffener 4 is symmetrical with respect to the horizontal center line of matrix 1, horizontal stiffener 4 and matrix 1
Front surface be welded as entirety, be also welded as entirety in the infall of horizontal stiffener 4 and vertical stiffeners 3；After matrix 1
On surface, with the fuselage floor corresponding position of height there are one horizontal stretching, cross section be L-shaped floor connection section bar 6, ground
Board attachment-type material 6 and the rear surface of matrix 1 are welded as entirety；In the rear surface of matrix 1, it is corresponding with noselanding gear well side wall
Position there are two vertical stretching, cross section be L-shaped noselanding gear well connection section bar 7, noselanding gear well connection section bar 7 weld
In the rear surface of matrix 1, the upper end of noselanding gear well connection section bar 7 is docked with floor connection section bar 6.
The beneficial effects of the invention are as follows：Kind of the 8 frame forebody load loaded member of simulation for being used for aircraft slow test is proposed,
It is avoided that and uses origianl structure part as testpieces, to considerably reduce experimentation cost.One embodiment of the present of invention, through examination
Verify bright, experimentation cost reduces 80% or more.
Description of the drawings
Fig. 1 is the structural schematic diagram of the present invention.In figure, paper outside direction is front, and direction is rear in paper, up and down side
To constant.
Fig. 2 is the A-A sectional views of Fig. 1.
Specific implementation mode
The present invention is described in further details below.Referring to Fig. 1,2, a kind of 8 frame of simulation for aircraft slow test
Forebody load loaded member, it is characterised in that：It include 1,4 load connector 2 of matrix, vertical stiffeners 3, horizontal stiffener 4,
Collar tie beam 5 and floor connection section bar 6 and noselanding gear well connection section bar 7；Matrix 1 is a plectane, in matrix 1 close to circumference
There is the circumferential bolt hole that a circle is uniformly distributed along the circumference in position, and collar tie beam 5 is that a cross section is L-shaped annulus, in the anchor ring of collar tie beam 5
On have a collar tie beam bolt hole that a circle is uniformly distributed along the circumference, the quantity of collar tie beam bolt hole is identical as the circumferential quantity of bolt hole on matrix 1
And position corresponds to, and collar tie beam 5 is fixed in the rear surface of matrix 1 by bolt；It is that a cross section is to load 2 section of connectorThe component of shape has a bolt hole in the front and rear surfaces of load connector, 4 load connectors 2 be bolted on matrix 1 just on
Side, underface, front-left and front-right, the central symmetry of the positions of 4 load connectors 2 relative to matrix 1；Before matrix 1
There are 4~10 vertical stiffeners 3 on surface, the quantity of vertical stiffeners 3 is even number, and vertical stiffeners 3 hang down with respect to matrix 1
Straight center line is symmetrical, and vertical stiffeners 3 and the front surface of matrix 1 are welded as entirety；There are 2 in the front surface of matrix 1
The quantity of~8 horizontal stiffeners 4, horizontal stiffener 4 is even number, and horizontal stiffener 4 is symmetrical with respect to the horizontal center line of matrix 1
Distribution, horizontal stiffener 4 and the front surface of matrix 1 are welded as entirety, in the infall of horizontal stiffener 4 and vertical stiffeners 3
Also it is welded as entirety；In the rear surface of matrix 1, there are one horizontal stretching, transversal for position corresponding with fuselage floor height
Face is L-shaped floor connection section bar 6, and floor connection section bar 6 and the rear surface of matrix 1 are welded as entirety；In the rear surface of matrix 1
Position upper, corresponding with noselanding gear well side wall there are two vertical stretching, cross section be L-shaped noselanding gear well connection section bar
7, noselanding gear well connection section bar 7 is welded in the rear surface of matrix 1, and upper end and the floor of noselanding gear well connection section bar 7 connect
Direct type material 6 docks.
The present invention operation principle be：By the collar tie beam 5 and 8 frame rear body coverings of 8 frame forebody load loaded members in experiment
Test load load pressurized strut is connect by riveting with the load connector 2 of 8 frame forebody load loaded members, and load loads pressurized strut
8 frame forebody load are applied to load connector 2 according to test requirements document.
One embodiment of the present of invention has 6 vertical stiffeners 3, in the front surface of matrix 1 in the front surface of matrix 1
On have 2 horizontal stiffeners 4.
Claims (1)
1. a kind of 8 frame forebody load loaded member of simulation for aircraft slow test, it is characterised in that：It include matrix (1),
4 load connectors (2), vertical stiffeners (3), horizontal stiffener (4), collar tie beam (5), with floor connection section bar (6) and before rise and fall
Frame cabin connection section bar (7)；Matrix (1) is a plectane, has the week that a circle is uniformly distributed along the circumference close to the position of circumference in matrix (1)
To bolt hole, collar tie beam (5) is that a cross section is L-shaped annulus, has a circle to be uniformly distributed along the circumference on the anchor ring of collar tie beam (5)
Collar tie beam bolt hole, the quantity of collar tie beam bolt hole with the circumferential quantity of bolt hole is identical on matrix (1) and position is corresponding, pass through spiral shell
Collar tie beam (5) is fixed in the rear surface of matrix (1) by bolt；It is that a cross section is to load connector (2) sectionThe component of shape,
Loading in the front and rear surfaces of connector has a bolt hole, 4 load connectors (2) are bolted on right over matrix (1), just under
Side, front-left and front-right, the central symmetry of the positions of 4 load connectors (2) relative to matrix (1)；In the preceding table of matrix (1)
There are 4~10 vertical stiffeners (3) on face, the quantity of vertical stiffeners (3) is even number, and vertical stiffeners (3) are with respect to matrix
(1) vertical center line is symmetrical, and vertical stiffeners (3) and the front surface of matrix (1) are welded as entirety；In matrix (1)
There are 2~8 horizontal stiffeners (4) in front surface, the quantity of horizontal stiffener (4) is even number, and horizontal stiffener (4) is with respect to base
The horizontal center line of body (1) is symmetrical, and horizontal stiffener (4) and the front surface of matrix (1) are welded as entirety, reinforces in level
Muscle (4) and the infall of vertical stiffeners (3) are also welded as entirety；In the rear surface of matrix (1), with fuselage floor height pair
The position answered there are one horizontal stretching, cross section be L-shaped floor connection section bar (6), floor connection section bar (6) and matrix
(1) rear surface is welded as entirety；In the rear surface of matrix (1), there are two hang down for position corresponding with noselanding gear well side wall
Directly stretch, cross section is L-shaped noselanding gear well connection section bar (7), and noselanding gear well connection section bar (7) is welded on matrix
(1) in rear surface, the upper end of noselanding gear well connection section bar (7) is docked with floor connection section bar (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 CN106153319A (en) | 2016-11-23 |
| CN106153319B true 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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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| CN110228603B (en) * | 2019-05-29 | 2022-11-18 | 陕西飞机工业（集团）有限公司 | Static test end frame for simulating 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 |
| CN114295401B (en) * | 2021-12-31 | 2022-11-01 | 北京空间机电研究所 | Static test truss type structure loading device and method for spacecraft cabin propulsion module |
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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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10350974B4 (en) * | 2003-10-30 | 2014-07-17 | Hottinger Baldwin Messtechnik Gmbh | Transducer element, device for detecting loads on fiber composite components and method of manufacturing the device |
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2016
- 2016-07-01 CN CN201610512814.2A patent/CN106153319B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2158909C1 (en) * | 2000-03-07 | 2000-11-10 | Лабзин Василий Васильевич | Stand for testing transmission mechanism of flying vehicle aerodynamic control surface actuator |
| 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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| Publication number | Publication date |
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| CN106153319A (en) | 2016-11-23 |
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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. |