CN109018428A - A kind of engine installation structure load-carrying properties test device - Google Patents
A kind of engine installation structure load-carrying properties test device Download PDFInfo
- Publication number
- CN109018428A CN109018428A CN201810426321.6A CN201810426321A CN109018428A CN 109018428 A CN109018428 A CN 109018428A CN 201810426321 A CN201810426321 A CN 201810426321A CN 109018428 A CN109018428 A CN 109018428A
- Authority
- CN
- China
- Prior art keywords
- load
- engine
- bogusware
- installation structure
- engine installation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to a kind of engine installation structure load-carrying properties test devices, including engine bogusware, aircraft hangs bogusware, actuator, load bearing floor and load wall, engine installation structure to be tested connects the aircraft hanging bogusware and the engine bogusware, described actuator one end is connect with the engine bogusware, the other end is connect with load bearing floor, the actuator exports scheduled load, apply the load of horizontal simulated engine thrust to engine bogusware respectively, the inertial load of vertical direction, the inertial load of horizontal direction, load passes to engine installation structure by engine bogusware, engine installation structure transfers load to hanging bogusware again.By the bearer properties for the sensor measurements engine installation structure such as straining, being displaced.
Description
Technical field
The present invention relates to Aeroengine Design fields, test more particularly, to a kind of engine installation structure load-carrying properties
Device.
Background technique
Aero-engine mounting structure plays the role of connecting aero-engine with aircraft hanging structure, to hold in work
By the load in three directions of engine, so to consider that engine installation structure undertakes the performance of load in design.
Chinese patent CN103868633B discloses a kind of engine overhead air distribution camshaft contact stress test method, packet
It includes following steps: determining duty cycle cam ring-corresponding camshaft degree of driven member Max.contact stress with emulation mode；It borrows
Help the crankshaft fillets stress under bench test dynamic test cam Max.contact stress corner；Then cam-follower contact force is determined
With the linear relationship of cam root fillet stress, can then convert to obtain the maximum unilateral force of cam-follower；Final basis
Hertz formula solves to obtain contact stress.But the patent still can not detect the load of engine in three directions.
Summary of the invention
It is an object of the present invention to overcome the above-mentioned drawbacks of the prior art and provide one kind can test three
The engine installation structure load-carrying properties test device of direction load.
The purpose of the present invention can be achieved through the following technical solutions:
A kind of engine installation structure load-carrying properties test device, including engine bogusware, aircraft hang bogusware, actuation
Device, load bearing floor and load wall,
Engine installation structure to be tested connects the aircraft hanging bogusware and the engine bogusware, the actuator
One end is connect with the engine bogusware, and the other end is connect with load bearing floor, which exports scheduled load, respectively to hair
Motivation bogusware applies load, the inertial load of vertical direction, the inertial load of horizontal direction of horizontal simulated engine thrust,
Load passes to engine installation structure by engine bogusware, and engine installation structure transfers load to hanging bogusware again,
Pass through the strain that is installed on engine installation structure, displacement sensor its bearer properties.
The aircraft hanging bogusware and the engine bogusware lean against on load wall.
The engine bogusware is by load-carrying construction after fancase load-carrying construction, fancase and rear housing load-carrying construction group
It is fixed on after fancase on load-carrying construction at, the fancase load-carrying construction and rear housing load-carrying construction.
The fan-shaped shape of fancase load-carrying construction, is arranged in one end of load-carrying construction after the fancase；Institute
Load-carrying construction is I-shaped steel construction after stating fancase, in the slide plate that upper surface is equipped with sliding slot and slides along the chute；It is described
The other end of load-carrying construction after the fancase is arranged in rear housing load-carrying construction.
The fancase load-carrying construction and the rear housing load-carrying construction are equipped with to be connect with engine installation structure
Mounting hole.
Aircraft hanging bogusware by hanger, the crossbeam that is connected to hanger front end, the lifting lug for being connected to below the crossbeam and
The rear suspension centre composition of hanger lower part is set.
The hanger is connect with the load wall.
The both ends of crossbeam are arranged in the lifting lug.
The rear end of the hanger is equipped with the mounting hole connecting with engine installation structure.
Compared with prior art, the present invention is by applying forward thrust load, vertical direction to the simulation of engine bogusware
Inertial load, horizontal cross inertial load by engine bogusware by various load transmission engine installation structures passing through peace
Assembling structure passes to hanging bogusware.Engine bogusware includes main engine load-carrying construction, reflects its true load transmission
Characteristic, therefore reasonable load can be applied to mounting structure to be tested, examine its performance under real bearing state.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of engine installation structure load-carrying properties test device；
Fig. 2 is the structural schematic diagram of engine bogusware；
Fig. 3 is the structural schematic diagram of engine bogusware；
Fig. 4 is the structural schematic diagram that aircraft hangs bogusware；
In figure, 1- engine structure bogusware, 11- fancase load-carrying construction, load-carrying construction after 12- fancase, after 13-
Casing load-carrying construction, 2- aircraft hang bogusware, 21- hanger, 22- crossbeam, 23- front lifting lug, suspension centre after 24-, the installation of 3- engine
Structure, 4- actuator, 5- load bearing floor, 6- load wall.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
Embodiment
A kind of engine installation structure load-carrying properties test device, structure is as shown in Figure 1, including engine bogusware 1, flying
Machine hangs bogusware 2, actuator 4, load bearing floor 5 and load wall 6.It is false that engine installation structure 3 to be tested connects aircraft hanging
Part 2 and engine bogusware 1,4 one end of actuator are connect with engine bogusware 1, and the other end and load bearing floor 5 and dependency structure connect
It connects.Actuator 4 exports scheduled load, applies the load, vertical of horizontal simulated engine thrust to engine bogusware 1 respectively
Inertial load, the inertial load of horizontal direction in direction, load pass to engine installation structure 3 by engine bogusware 1, send out
Motivation mounting structure 3 transfers load to hanging bogusware 2 again, is passed by the strain, the displacement that are installed on engine installation structure
Sensor measures its bearer properties.Above-mentioned engine bogusware 1 and aircraft hanging bogusware 2 lean against on load wall 6.Engine bogusware 1 by
Load-carrying construction 12 and rear housing load-carrying construction 13 form after fancase load-carrying construction 11, fancase, fancase load knot
Structure 11 and rear housing load-carrying construction 13 are fixed on after fancase on load-carrying construction 12.The fan-shaped shape of fancase load-carrying construction 11
One end of load-carrying construction 12 after fancase is arranged in shape；Load-carrying construction 12 is I-shaped steel construction after fancase, upper
The slide plate that surface is equipped with sliding slot and slides along the chute；The another of load-carrying construction 12 after fancase is arranged in rear housing load-carrying construction 13
One end.Fancase load-carrying construction 12 and rear housing load-carrying construction 13 are equipped with the mounting hole connecting with engine installation structure 3.
Aircraft hang bogusware 2 by hanger 21, the crossbeam 22 that is connected to 21 front end of hanger, the lifting lug 23 for being connected to 22 lower section of crossbeam and set
Set the composition of rear suspension centre 24 in 21 lower part of hanger.Hanger 21 is connect with load wall 6.The both ends of crossbeam 22 are arranged in lifting lug 23.It hangs
The rear end of frame 21 is equipped with the mounting hole connecting with engine installation structure 3, can connect with 3 corresponding component of engine installation structure.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (9)
1. a kind of engine installation structure load-carrying properties test device, which is characterized in that the device includes engine bogusware, aircraft
Bogusware, actuator, load bearing floor and load wall are hung,
Engine installation structure to be tested connects the aircraft hanging bogusware and the engine bogusware, described actuator one end
It is connect with the engine bogusware, the other end is connect with load bearing floor, which exports scheduled load, gives engine respectively
Bogusware applies load, the inertial load of vertical direction, the inertial load of horizontal direction of horizontal simulated engine thrust, load
Engine installation structure is passed to by engine bogusware, engine installation structure transfers load to hanging bogusware again, passes through
It is installed on strain on engine installation structure, displacement sensor its bearer properties.
2. a kind of engine installation structure load-carrying properties test device according to claim 1, which is characterized in that described to fly
Machine hanging bogusware and the engine bogusware lean against on load wall.
3. a kind of engine installation structure load-carrying properties test device according to claim 1 or 2, which is characterized in that institute
It states engine bogusware to be made of load-carrying construction after fancase load-carrying construction, fancase and rear housing load-carrying construction, the wind
Fan casing load-carrying construction and rear housing load-carrying construction are fixed on after fancase on load-carrying construction.
4. a kind of engine installation structure load-carrying properties test device according to claim 3, which is characterized in that the wind
The fan-shaped shape of casing load-carrying construction is fanned, one end of load-carrying construction after the fancase is set；It is held after the fancase
Power structure is I-shaped steel construction, in the slide plate that upper surface is equipped with sliding slot and slides along the chute；The rear housing load-carrying construction
The other end of load-carrying construction after the fancase is set.
5. a kind of engine installation structure load-carrying properties test device according to claim 3, which is characterized in that the wind
Fan casing load-carrying construction and the rear housing load-carrying construction are equipped with the mounting hole connecting with engine installation structure.
6. a kind of engine installation structure load-carrying properties test device according to claim 1 or 2, which is characterized in that institute
State aircraft hanging bogusware by hanger, the crossbeam that is connected to hanger front end, the lifting lug for being connected to below the crossbeam and be arranged in hanger
The rear suspension centre of lower part forms.
7. a kind of engine installation structure load-carrying properties test device according to claim 6, which is characterized in that described to hang
Frame is connect with the load wall.
8. a kind of engine installation structure load-carrying properties test device according to claim 6, which is characterized in that described to hang
The both ends of crossbeam are arranged in ear.
9. a kind of engine installation structure load-carrying properties test device according to claim 6, which is characterized in that described to hang
The rear end of frame is equipped with the mounting hole connecting with engine installation structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810426321.6A CN109018428A (en) | 2018-05-07 | 2018-05-07 | A kind of engine installation structure load-carrying properties test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810426321.6A CN109018428A (en) | 2018-05-07 | 2018-05-07 | A kind of engine installation structure load-carrying properties test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109018428A true CN109018428A (en) | 2018-12-18 |
Family
ID=64611603
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810426321.6A Pending CN109018428A (en) | 2018-05-07 | 2018-05-07 | A kind of engine installation structure load-carrying properties test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109018428A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595750A (en) * | 2019-09-19 | 2019-12-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Loading device for wing hanging joint |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5396791A (en) * | 1993-08-13 | 1995-03-14 | General Electric Company | Engine testing mounting adaptor |
| CN102680236A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Structural strength test loading device for aircraft wing-mounted engine |
| CN103630347A (en) * | 2013-11-26 | 2014-03-12 | 成都发动机（集团）有限公司 | Motor substitution equipment for static force test of airplane wing |
| CN104280242A (en) * | 2013-07-01 | 2015-01-14 | 现代自动车株式会社 | Engine test device |
| CN204964197U (en) * | 2015-06-29 | 2016-01-13 | 上海交通大学 | Engine compression ratio on line measurement automation equipment |
| FR3046235A1 (en) * | 2015-12-29 | 2017-06-30 | Snecma | INTERCHANGEABLE SUPPORT FOR FASTENING A TURBOMACHINE |
| CN206937145U (en) * | 2017-07-05 | 2018-01-30 | 中国航空工业集团公司西安飞机设计研究所 | A kind of engine hanging joint test fixture |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN207197796U (en) * | 2017-07-05 | 2018-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Engine hanger slow test charging assembly and engine hanger slow test system |
| CN207197819U (en) * | 2017-07-05 | 2018-04-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of engine bogusware and engine hang slow test system |
| CN207318099U (en) * | 2017-10-18 | 2018-05-04 | 深圳光启空间技术有限公司 | Engine and propeller integral type test device |
| US10183759B2 (en) * | 2013-12-06 | 2019-01-22 | Safran Power Units | Adjustable engine suspension for positioning the engine relative to the mount thereof |
-
2018
- 2018-05-07 CN CN201810426321.6A patent/CN109018428A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5396791A (en) * | 1993-08-13 | 1995-03-14 | General Electric Company | Engine testing mounting adaptor |
| CN102680236A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Structural strength test loading device for aircraft wing-mounted engine |
| CN104280242A (en) * | 2013-07-01 | 2015-01-14 | 现代自动车株式会社 | Engine test device |
| CN103630347A (en) * | 2013-11-26 | 2014-03-12 | 成都发动机（集团）有限公司 | Motor substitution equipment for static force test of airplane wing |
| US10183759B2 (en) * | 2013-12-06 | 2019-01-22 | Safran Power Units | Adjustable engine suspension for positioning the engine relative to the mount thereof |
| CN204964197U (en) * | 2015-06-29 | 2016-01-13 | 上海交通大学 | Engine compression ratio on line measurement automation equipment |
| FR3046235A1 (en) * | 2015-12-29 | 2017-06-30 | Snecma | INTERCHANGEABLE SUPPORT FOR FASTENING A TURBOMACHINE |
| CN206937145U (en) * | 2017-07-05 | 2018-01-30 | 中国航空工业集团公司西安飞机设计研究所 | A kind of engine hanging joint test fixture |
| CN207197796U (en) * | 2017-07-05 | 2018-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Engine hanger slow test charging assembly and engine hanger slow test system |
| CN207197819U (en) * | 2017-07-05 | 2018-04-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of engine bogusware and engine hang slow test system |
| CN207318099U (en) * | 2017-10-18 | 2018-05-04 | 深圳光启空间技术有限公司 | Engine and propeller integral type test device |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
Non-Patent Citations (3)
| Title |
|---|
| 夏佳莹，李诗哲，于哲峰，周翔，汪海: "某种翼吊发动机安装结构应力分析方法研究", 《科学技术与工程》 * |
| 李卫平，谭伟，薛彩军，聂宏: "民用飞机发动机吊挂部段静力试验与静强度分析", 《南京航空航天大学学报》 * |
| 李春刚: "某型飞机发动机安装架强度分析", 《燃气涡轮试验与研究》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595750A (en) * | 2019-09-19 | 2019-12-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Loading device for wing hanging joint |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104062104B (en) | Aero-engine compressor blade fatigue circulation test device | |
| CN202420858U (en) | Durability test stand for brake pedals of automobile | |
| CN109490113B (en) | Test piece and test method for fatigue test of hanging thrust pin of aircraft engine | |
| CN102680236B (en) | Structural strength test loading device for aircraft wing-mounted engine | |
| CN109018428A (en) | A kind of engine installation structure load-carrying properties test device | |
| CN108910080B (en) | Helicopter tail rotor pneumatic load environment simulation test device | |
| CN107607391A (en) | A kind of multi-grade lever loading experimental apparatus | |
| CN112378608A (en) | Prestress-loaded rocket-borne equipment vibration test system and test method | |
| CN205809193U (en) | A kind of pantograph dynamic characteristic test laboratory table | |
| CN207472655U (en) | A kind of multi-grade lever loading experimental apparatus | |
| CN203929356U (en) | Large scale Segment Model test unit | |
| CN107480355B (en) | Method for verifying bearing capacity of engine mounting joint | |
| CN106568562B (en) | The test method and device of power transmission tower crossarm bolt anti-loosening property | |
| CN106065898A (en) | The crankshaft structure of straight-eight engine | |
| CN104101534B (en) | A kind of engine crankshaft fatigue test clamper | |
| Shim et al. | Passive control of pitch-break of a BWB UCAV model using vortex generator | |
| CN205785840U (en) | Fork truck service brake test-bed | |
| CN112729734A (en) | Method for measuring transfer characteristics of series-type vibration isolator | |
| CN106122688A (en) | A kind of snubber base | |
| CN102954887A (en) | Testing device for measuring damping effect of working blades of high-pressure turbine | |
| CN203824828U (en) | Device for reducing frictional force of piston rod of high-tonnage horizontal fatigue testing machine | |
| Kouris et al. | Damage detection of an unreinforced stone masonry two storeys building based on damping estimate | |
| CN209485878U (en) | A kind of target plate three-dimensional confining pressure cabinet for body depth penetration experiment | |
| CN207366195U (en) | In the air by the experimental rig of oily feeler lever damper | |
| CN208220855U (en) | Hydraulic tappet with safety valve and the engine with the hydraulic tappet |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181218 |