CN104773305B - A kind of asymmetric aircraft fuel system simulator stand structure and method for designing thereof - Google Patents
A kind of asymmetric aircraft fuel system simulator stand structure and method for designing thereof Download PDFInfo
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- CN104773305B CN104773305B CN201510097167.9A CN201510097167A CN104773305B CN 104773305 B CN104773305 B CN 104773305B CN 201510097167 A CN201510097167 A CN 201510097167A CN 104773305 B CN104773305 B CN 104773305B
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Abstract
The invention discloses a kind of asymmetric aircraft fuel system simulator stand structure and method for designing thereof, including ground supports, drive end one, testing stand housing, bearing one, pivot center one, right half housing of testing stand, left half housing of testing stand, load and testing stand center of gravity etc..This test platform structure method for designing is to use computer 3D software to be modeled, and all of load of simulator stand, the load produced including structure itself and load quality and the inertial load etc. produced due to rotation, modeling software will obtain the center of gravity of testing stand automatically, Optimum Experiment platform structure on this basis, make this weight of testing stand and load quality carry out all or as far as possible to balance, the rod member of left half housing is lengthened under meeting intensity and rigidity condition, making testing stand housing be integrally formed asymmetrically shaped, testing stand center of gravity is close to pivot center one.It is little that test platform structure of the present invention not only has unbalanced moments, advantage rational in infrastructure, reduces the cost building testing stand.
Description
Technical field
The invention belongs to Aviation Test field of mechanical structure design, relate to a kind of asymmetric aircraft fuel system simulation examination
Test platform structure and method for designing thereof.
Background technology
According to the regulation of aircraft industry standard (HB7169-1995), aircraft fuel system is in development process, it is necessary to carry out
Ground simulation test, required equipment is to have the aircraft fuel system ground simulation test platform of 2DOF rotation direction (below
It is called for short testing stand).
Currently known test platform structure is all symmetrical expression, i.e. relative to the test platform structure distribution of pivot center motion
It it is symmetrical expression.As shown in Figure 1.Symmetrical expression distributed architecture is simple, is typically due to load deviation of gravity center symmetrical expression distributed architecture
Center, makes the unbalanced moments of testing stand increase, and the consequence thus brought is that the driving moment of testing stand must increase accordingly, as
This brings the irrationality of design.
Summary of the invention
In order to overcome the irrationality of above-mentioned design, the present invention proposes a kind of asymmetric aircraft fuel system simulation examination
Test platform structure and method for designing thereof, and use computer 3D software that testing stand is modeled, all of load of simulator stand,
The load produced including the quality of structure own and load etc., calculate test platform position of centre of gravity, due to the most symmetrical
In the case of test platform center of gravity deflection pivot center one the right, by more Mass Distribution in the left side of axis, by a left side
Half housing is optimized design, makes left half housing expand formation to the left asymmetrically shaped, and now test platform center of gravity will be to rotation
Axis one is close, has thus reached to reduce the purpose of testing stand unbalanced moments.
The technical scheme is that 1. 1 kinds of asymmetric aircraft fuel system simulator stand structures, including ground
Support, right half housing of drive end one, testing stand housing, bearing one, pivot center one, drive end two, testing stand, testing stand left half
Housing, testing stand inside casing, pivot center two, bearing two, load and testing stand center of gravity, described drive end one is arranged on ground supports
On, described testing stand housing one end is arranged on drive end one, and the other end is installed on the bearing one in ground supports, described test
Platform housing can rotate around pivot center one under the driving of drive end one, and described drive end two is arranged on right half housing of testing stand
On, described testing stand inside casing one end is arranged on drive end two, and the other end is arranged on the bearing two on left half housing of testing stand,
Described testing stand inside casing can rotate around pivot center two under the driving of drive end two, and described load is arranged on testing stand inside casing
On, it is characterised in that: testing stand is modeled by root Ju computer 3D software, simulation calculates, optimize the result of design, to a described left side half
The rod member of housing lengthens under meeting intensity and rigidity condition, makes described testing stand housing be integrally formed asymmetrically shaped,
Described testing stand center of gravity is close to pivot center one, until testing stand center of gravity and the eccentric throw value of pivot center one are null value or most
May be close to null value.
2. an asymmetric aircraft fuel system simulator stand construction design method, it is characterised in that: described test
Platform construction design method is to use computer 3D software to be modeled testing stand, and all of load of simulator stand, including
Load that structure itself and load quality produce and owing to rotating the inertial load produced, Optimum Experiment platform knot on this basis
Structure, makes this weight of testing stand and load quality carry out all or as far as possible and balances, and is meeting intensity and rigidity Design ginseng simultaneously
On the basis of number, design determines new test platform structure.
It is little that test platform structure of the present invention not only has unbalanced moments, advantage rational in infrastructure, and method for designing is simple
Feasible.The more important thing is the driving moment that thus can greatly reduce testing stand, reduce the cost building testing stand.
Accompanying drawing explanation
Fig. 1 is former symmetrical expression distributed architecture schematic diagram；
Fig. 2 is present configuration schematic diagram；
In figure: 1-ground supporting, 2-drive end one, 3-testing stand housing 4-bearing one, 5-pivot center one, 6-drives
End one, right half housing of 7-testing stand, left half housing of 8-testing stand, 9-testing stand inside casing, 10-pivot center two, 11-bearing two,
12 loads, 13-testing stand center of gravity.
Detailed description of the invention
Below in conjunction with the accompanying drawings and the present invention is described in further detail by detailed description of the invention.
As shown in Figure 2, a kind of asymmetric aircraft fuel system ground simulation test platform structure, including ground supporting 1,
Right half housing 7 of drive end 1, testing stand housing 3, bearing 1, pivot center 1, drive end 26, testing stand, testing stand are left
Half housing 8, testing stand inside casing 9, pivot center 2 10, bearing 2 11, load 12 and testing stand center of gravity 13.Use computer 3D
The softwares such as modeling software such as CATIA, UG testing stand entire infrastructure is included structural body and load 12 carry out one to one true
Real modeling, and give real material behavior to Each part, now, modeling software will obtain the center of gravity of testing stand automatically
13, owing under usual symmetric case, test platform center of gravity 13 is partial on the right of pivot center 1, left half housing 8 structure is carried out excellent
Change design, by more Mass Distribution in the left side of axis, such as to the rod member of left half housing 8 under the conditions of meeting intensity and toughness
Carry out lengthening (this enforcement row are preferably) or overstriking, or do not affecting load i.e. aircraft fuel system injection ground simulation test system peace
To the right thick stick part shortening etc. on the premise of dress, now test platform center of gravity 13 will be close to pivot center 1, until eccentric throw value
For null value or as close possible to null value.Now the quality of the test platform structure left and right sides the most wholly or largely balances, thus
Reach to reduce the purpose of testing stand unbalanced moments, simultaneously on the basis of meeting the design parameters such as intensity and rigidity, determined
New test platform structure scheme.
Claims (2)
1. an asymmetric aircraft fuel system simulator stand structure, including ground supports (1), drive end one (2), test
Outside right half housing (7) of platform housing (3), bearing one (4), pivot center one (5), drive end two (6), testing stand, testing stand left half
Frame (8), testing stand inside casing (9), pivot center two (10), bearing two (11), load (12) and testing stand center of gravity (13), described in drive
Moved end one (2) is arranged in ground supports (1), and described testing stand housing (3) one end is arranged on drive end one (2), the other end
Installing on the bearing one (4) in ground supports (1), described testing stand housing (3) can be around rotation under the driving of drive end one (2)
Axis one (5) rotates, and described drive end two (6) is arranged on right half housing (7) of testing stand, described testing stand inside casing (9) one end
Being arranged on drive end two (6), the other end is arranged on the bearing two (11) on left half housing (8) of testing stand, described testing stand
Inside casing (9) can rotate around pivot center two (10) under the driving of drive end two (6), and described load (12) is arranged in testing stand
On frame (9), it is characterised in that: testing stand is modeled by root Ju computer 3D software, simulation calculates, optimize the result of design, to institute
The rod member stating left half housing (8) lengthens under meeting intensity, rigidity condition, makes described testing stand housing (3) be integrally formed
Asymmetrically shaped, described testing stand center of gravity (13) is close to pivot center one (5), until testing stand center of gravity (13) and pivot center
The eccentric throw value of one (5) is null value or as close possible to null value.
2. an asymmetric aircraft fuel system simulator stand construction design method, it is characterised in that: described testing stand is tied
Structure method for designing is to use computer 3D software to be modeled testing stand, and all of load of simulator stand, including structure
The load produced with load quality own and the inertial load produced due to rotation, modeling software will obtain testing stand automatically
Center of gravity, on this basis Optimum Experiment platform structure, make this weight of testing stand and load quality carry out all or as far as possible and balance,
Simultaneously on the basis of meeting intensity and rigidity Design parameter, design determines new test platform structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510097167.9A CN104773305B (en) | 2015-03-05 | 2015-03-05 | A kind of asymmetric aircraft fuel system simulator stand structure and method for designing thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510097167.9A CN104773305B (en) | 2015-03-05 | 2015-03-05 | A kind of asymmetric aircraft fuel system simulator stand structure and method for designing thereof |
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| CN104773305A CN104773305A (en) | 2015-07-15 |
| CN104773305B true CN104773305B (en) | 2016-08-24 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468851A (en) * | 2015-11-26 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining aircraft dynamic weight characteristic |
| CN110895201B (en) * | 2019-12-04 | 2021-07-09 | 中国直升机设计研究所 | Helicopter fuel system normal overload ground simulation device and method |
| CN112706912B (en) * | 2020-12-29 | 2022-11-22 | 中国航空工业集团公司西安飞机设计研究所 | Force transmission structure of asymmetric ellipsoid |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202703895U (en) * | 2012-07-02 | 2013-01-30 | 江西洪都航空工业集团有限责任公司 | Airplane fuel system ground simulator stand with universal joint pin mechanism |
| EP2214962B1 (en) * | 2007-11-29 | 2013-07-03 | Airbus Operations GmbH | Apparatus and method for testing an aircraft tank system |
| CN203335628U (en) * | 2013-06-09 | 2013-12-11 | 江西洪都航空工业集团有限责任公司 | Slewing bearing structure for aircraft fuel system test turntable |
| CN203612227U (en) * | 2013-12-20 | 2014-05-28 | 中国科学院沈阳自动化研究所 | Three-axis turntable capable of moving in all directions |
-
2015
- 2015-03-05 CN CN201510097167.9A patent/CN104773305B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2214962B1 (en) * | 2007-11-29 | 2013-07-03 | Airbus Operations GmbH | Apparatus and method for testing an aircraft tank system |
| CN202703895U (en) * | 2012-07-02 | 2013-01-30 | 江西洪都航空工业集团有限责任公司 | Airplane fuel system ground simulator stand with universal joint pin mechanism |
| CN203335628U (en) * | 2013-06-09 | 2013-12-11 | 江西洪都航空工业集团有限责任公司 | Slewing bearing structure for aircraft fuel system test turntable |
| CN203612227U (en) * | 2013-12-20 | 2014-05-28 | 中国科学院沈阳自动化研究所 | Three-axis turntable capable of moving in all directions |
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| CN104773305A (en) | 2015-07-15 |
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