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 PDF

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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
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CN
China
Prior art keywords
load
engine
bogusware
installation structure
engine installation
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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
Application number
CN201810426321.6A
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Chinese (zh)
Inventor
于哲峰
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Shanghai Jiaotong University
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Shanghai Jiaotong University
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Publication date
Application filed by Shanghai Jiaotong University filed Critical Shanghai Jiaotong University
Priority to CN201810426321.6A priority Critical patent/CN109018428A/en
Publication of CN109018428A publication Critical patent/CN109018428A/en
Pending legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND 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
    • B64F5/00Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60Testing or inspecting aircraft components or systems
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00Testing of engines

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  • 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

A kind of engine installation structure load-carrying properties test device
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.
CN201810426321.6A 2018-05-07 2018-05-07 A kind of engine installation structure load-carrying properties test device Pending CN109018428A (en)

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

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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

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Cited By (1)

* Cited by examiner, † Cited by third party
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

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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
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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
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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
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US5396791A (en) * 1993-08-13 1995-03-14 General Electric Company Engine testing mounting adaptor
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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
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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

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Cited By (1)

* Cited by examiner, † Cited by third party
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

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Application publication date: 20181218