CN206990215U - Aircraft engine test stand frame - Google Patents
Aircraft engine test stand frame Download PDFInfo
- Publication number
- CN206990215U CN206990215U CN201720749170.9U CN201720749170U CN206990215U CN 206990215 U CN206990215 U CN 206990215U CN 201720749170 U CN201720749170 U CN 201720749170U CN 206990215 U CN206990215 U CN 206990215U
- Authority
- CN
- China
- Prior art keywords
- moving frame
- support
- base
- torsion
- frame
- 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.)
- Active
Links
Abstract
The utility model discloses a kind of aircraft engine test stand frame, including running support base, moving frame device, for providing moving frame device support and enabling moving frame support meanss that moving frame device swings, be arranged on moving frame device and the survey torquer for being tested moment of torsion caused by aero-engine and the device for measuring force for being tested pulling force caused by aero-engine or thrust, moving frame support meanss and device for measuring force are arranged on running support base.Aircraft engine test stand frame of the present utility model, the measurement of the steady-state behaviour parameters such as thrust or pulling force and the moment of torsion of aero-engine can be realized, measurement result precision is high, Experiment Result can take a flight test for the installation of aero-engine and provide reference frame, reduce scientific research to take a flight test workload, evade developing risk.
Description
Technical field
The utility model belongs to technical field of experiment equipment, specifically, the utility model is related to a kind of aero-engine
Its Test Rig.
Background technology
Aircraft is that the mankind are most quick and convenient transport facility, and its power set --- aero-engine is aircraft
One of determinant of energy, it is described as the heart of aircraft.Heart of the engine as aircraft, for airborne vehicle flight provide it is dynamic
Power.The performance of engine directly affects the Performance And Reliability and economy of aircraft.Engine and other plant equipment phases
Than structure is more complicated, and condition of work is more severe, once being broken down in flight course, will result in serious consequence.Aviation
With the change of working depth and rotating speed, the parameter such as its pulling force, thrust and moment of torsion, oil consumption very great Cheng can also occur for engine therewith
The fluctuation of degree.These changes will also tend to the productions such as the internal structure to engine in itself, vibration parameters, structural strength, intake and exhaust
Raw large effect., can be to pulling force, thrust and moment of torsion caused by propeller when the output power of aero-engine is affected
Indirect, serious influence is produced, this directly affects the safe to use of aircraft.While the stability of control of engine speed,
The quality of acceleration and deceleration characteristic also directly affects the handling and stability of aircraft.Therefore, in order to ensure the normal of engine
Work and the stabilized flight of aircraft also need to provide accordingly a kind of, it is necessary to effectively obtain the characteristic of engine in test phase
Aircraft engine test stand frame.
Utility model content
The utility model is intended at least solve one of technical problem present in prior art.Therefore, the utility model carries
For a kind of aircraft engine test stand frame, it is therefore an objective to realize the performance test of aero-engine.
To achieve these goals, the technical scheme that the utility model is taken is：Aircraft engine test stand frame, including examination
Vehicle frame base, moving frame device, for providing moving frame device support and enabling moving frame support meanss that moving frame device swings, set
It is placed on moving frame device and for the survey torquer tested moment of torsion caused by aero-engine and for sending out aviation
The device for measuring force that pulling force caused by motivation or thrust are tested, moving frame support meanss and device for measuring force are arranged at running support base
On.
The moving frame support meanss include the moving frame column being arranged on the running support base and are rotatably arranged on
Rocking arm on moving frame column, rocking arm is connected with the moving frame device and the rotation centerline of rocking arm is in horizontal plane.
One end of the rocking arm is connected by axle on rocking arm with the moving frame column, and the other end of rocking arm passes through rocking arm lower axle
It is connected with the moving frame device.
The moving frame support meanss set multiple and multiple moving frame support meanss right in two rows on the running support base
Claim arrangement.
The moving frame device includes the moving frame base above the running support base, the examination being arranged on moving frame base
Platform support frame and the changeover base being arranged on testing stand support frame are tested, moving frame base is connected with the rocking arm, the survey moment of torsion
Device is arranged in changeover base.
The moving frame device also includes being connected and being obliquely installed with the testing stand support frame and the moving frame base
Diagonal brace.
It is described survey torquer include be arranged in the changeover base torsion pass axle support base, be rotatably arranged on biography
Turn round on axle support base and for receiving the motor support torsion pass axle of moment of torsion caused by aero-engine, being arranged at motor support
Moment of torsion jacking block and the pressure sensor of the pressure for receiving to survey the application of moment of torsion jacking block are surveyed on torsion pass axle.
Described aircraft engine test stand frame also includes being used for the engine installation for installing aero-engine to be tested
Frame, the engine support surveyed torquer and also include being connected with the motor support torsion pass axle and motor mounts.
The motor mounts are located at the side of the testing stand support frame, the axis of the motor support torsion pass axle
It is in the center of gravity of aero-engine to be tested in same vertical plane.
The device for measuring force includes dynamometry rod bearing, the dynamometry push rod being arranged on dynamometry rod bearing and is arranged at moving frame bottom
The pressure sensor of the pressure applied on seat and for receiving dynamometry push rod.
Aircraft engine test stand frame of the present utility model, thrust or pulling force and moment of torsion of aero-engine etc. can be realized
The measurement of steady-state behaviour parameter, Experiment Result can take a flight test for the installation of aero-engine and provide reference frame, reduce scientific research examination
Fly workload, evade developing risk.
Brief description of the drawings
This specification includes the following drawings, and shown content is respectively：
Fig. 1 is the front view of the utility model aircraft engine test stand frame；
Fig. 2 is the top view of the utility model aircraft engine test stand frame；
In figure mark for：
1st, running support base；
2nd, moving frame support meanss；201st, moving frame column；202nd, bearing cover；203rd, axle on rocking arm；204th, rocking arm；205th, shake
Arm lower axle；
3rd, device for measuring force；301st, pressure sensor；302nd, dynamometry rod bearing；303rd, dynamometry push rod；304th, adaptor；
4th, moving frame device；401st, changeover base；402nd, connecting plate；403rd, testing stand support frame；404th, diagonal brace；405th, moving frame
Base；
5th, torquer is surveyed；501st, torsion pass axle support base；502nd, moment of torsion protection bearing；503rd, torque support is surveyed；504th, send out
Motivation supports torsion pass axle；505th, engine support；506th, blind flange；507th, pressure sensor；508th, moment of torsion jacking block is surveyed；509th, it is pre-
Moment of torsion is added to adjust bearing；
6th, shock absorbing part；601st, beam；602nd, beam installation sheet；
7th, motor mounts；8th, pin.
Embodiment
Below against accompanying drawing, by the description to embodiment, specific embodiment of the present utility model is made further detailed
Thin explanation, it is therefore an objective to help those skilled in the art have to design of the present utility model, technical scheme it is more complete, accurate and
Deep understanding, and contribute to its implementation.
As depicted in figs. 1 and 2, the utility model provides a kind of aircraft engine test stand frame, including running support base
1st, moving frame device 4, for providing moving frame device 4 support and enabling moving frame support meanss 2 that moving frame device 4 swings, set
In on moving frame device 4 and for the survey torquer 5 tested moment of torsion caused by aero-engine and for sending out aviation
The device for measuring force 3 that thrust caused by motivation or pulling force are tested, moving frame support meanss 2 and device for measuring force 3 are arranged at running support
On base 1.
Specifically, as depicted in figs. 1 and 2, running support base 1 is horizontally disposed that moving frame device 4 is arranged at running support bottom
The top of seat 1, moving frame device 4 are connected by moving frame support meanss 2 with running support base 1, and moving frame support meanss 2 fill moving frame
Put 4 tops for hanging on running support base 1 so that moving frame device 4 can be along the length direction of running support base 1 after stress
Swing.Moving frame device 4 includes the moving frame base 405 positioned at the top of running support base 1, is fixedly installed on moving frame base 405
Testing stand support frame 403 and the changeover base 401 being arranged on testing stand support frame 403.Moving frame base 405 fills with moving frame support
Put 2 to be connected, for testing stand support frame 403 to be vertically arranged on moving frame base 405, changeover base 401 is fixedly installed on experiment
The upper end of platform support frame 403, the lower end of testing stand support frame 403 are fixedly connected with moving frame base 405, are surveyed torquer 5 and are set
In in changeover base 401.
As depicted in figs. 1 and 2, moving frame device 4 also includes being connected with testing stand support frame 403 and moving frame base 405 and being
The diagonal brace 404 being obliquely installed, diagonal brace 404 are arranged at the relative both sides of testing stand support frame 403, the upper end of diagonal brace 404 and experiment
Platform support frame 403 is fixedly connected, and the lower end of diagonal brace 404 is fixedly connected with moving frame base 405.In the present embodiment, testing stand branch
Support 403 is bolted on moving frame base 405, with four diagonal braces between testing stand support frame 403 and moving frame base 405
404 are strengthened, and to improve the strength and stability of moving frame part, it is relative that four diagonal braces 404 are distributed in testing stand support frame 403
Both sides and each side of testing stand support frame 403 two parallel diagonal braces 404 are set respectively.
As depicted in figs. 1 and 2, moving frame device 4 also includes being used to fix changeover base 401 and testing stand support frame 403
Connecting plate 402 together, connecting plate 402 are fixedly connected with testing stand support frame 403 and changeover base 401.
As depicted in figs. 1 and 2, moving frame support meanss 2 include the moving frame column 201 being vertically arranged on running support base 1
With the rocking arm 204 being rotatably arranged on moving frame column 201, rocking arm 204 is connected with moving frame device 4 and the rotation of rocking arm 204
Centerline is in horizontal plane.The rotation centerline of rocking arm 204 is parallel with the width of running support base 1,204, rocking arm
Between moving frame column 201 and moving frame base 405, the upper end of rocking arm 204 is rotated by axle on rocking arm 203 and moving frame column 201
Connection, the lower end of rocking arm 204 is rotatablely connected by rocking arm lower axle 205 and moving frame base 405.Moving frame support meanss 2 are in running support
Multiple and multiple moving frame support meanss 2 are set to be arranged symmetrically in two rows on base 1, at the moving frame support meanss 2 of same row
In on the same straight line parallel with the length direction of running support base 1, the rocking arm 204 and moving frame of multiple moving frame support meanss 2
Base 405 connects, and makes moving frame base 405 parallel with the running support base 1 of lower section, makes moving frame device 4 and survey moment of torsion thereon
Device 5 can be swung after stress relative to running support base 1.
As depicted in figs. 1 and 2, in the present embodiment, moving frame support meanss 2 set four, and four moving frame support meanss 2 are pressed
Two rows are arranged symmetrically, and moving frame base 405 is rectangular configuration, and four moving frame support meanss 2 turn at the one of moving frame base 405 respectively
It is rotatablely connected at angle with moving frame base 405.Moving frame device 4 and running support base 1 are connected by four moving frame support meanss 2, shape
Into a kind of suspended structure, stability is improved, reduces frictional resistance so that in the pulling force or thrust of measurement aero-engine
When, measurement result accuracy is higher.
As depicted in figs. 1 and 2, the torsion pass axle support base that torquer 5 includes being vertically arranged in changeover base 401 is surveyed
501st, it is rotatably arranged on torsion pass axle support base 501 and is used for the motor support for receiving moment of torsion caused by aero-engine
Torsion pass axle 504, the moment of torsion being arranged on torsion pass axle support base 501 protection bearing 502, it is arranged at motor support torsion pass axle 504
On survey moment of torsion jacking block 508, pressure sensor 507, pretorque regulation for receiving to survey the pressure that moment of torsion jacking block 508 applies
Bearing 509, the adjusting screw surveyed torque support 503 and be arranged at pretorque regulation bearing 509.The He of torsion pass axle support base 501
Moment of torsion protection bearing 502 is bolted in changeover base 401, and torsion pass axle support base 501 is set in changeover base 401
Two and two torsion pass axle support bases 501 provide a supporting role for motor support torsion pass axle 504 jointly, moment of torsion protection bearing
502 between two torsion pass axle support bases 501, and pretorque regulation bearing 509 and survey torque support 503 are bolted
On moment of torsion protection bearing 502.Motor support torsion pass axle 504 is cylinder, the axis of motor support torsion pass axle 504 and examination
The parallel motor support torsion pass axle 504 of length direction of vehicle frame base 1 is arranged on torsion pass axle support base 501 by bearing,
Motor support torsion pass axle 504 simultaneously can be rotatable around its axis.Pressure sensor 507, which is installed on, to be surveyed in torque support 503.Engine
Support torsion pass axle 504 is provided with a groove, surveys moment of torsion jacking block 508 and is arranged in the groove and is connected therewith by interference fit
Connect, motor support torsion pass axle 504 can drive when rotating surveys the synchronous axial system of moment of torsion jacking block 508, and pressure sensor 507 is with surveying
Moment of torsion jacking block 508 is engaged, and pressure sensor 507 is in the side for surveying moment of torsion jacking block 508, in motor support torsion pass axle 504
Drive to survey after moment of torsion jacking block 508 rotates and can make the squeeze pressure sensor 507 of survey moment of torsion jacking block 508.In order that pressure sensor 507
Initial pressure value be zero, contact condition need to be kept with pressure sensor 507 by surveying moment of torsion jacking block 508, by being adjusted in pretorque
The adjusting screw that the position of moment of torsion jacking block 508 is surveyed in regulation is provided on section bearing 509, adjusting screw and pretorque bearing are spiral shell
Line connects and the axle of the axis and motor support torsion pass axle 504 of adjusting screw is perpendicular, and adjusting screw is located at motor support
The top of torsion pass axle 504, moment of torsion jacking block 508 is surveyed between pressure sensor 507 and adjusting screw, the end of adjusting screw is supported
Touch and survey moment of torsion jacking block 508, the position for surveying moment of torsion jacking block 508 can be adjusted by turning adjusting screw so that survey moment of torsion jacking block 508
Contact condition is kept with pressure sensor 507.
As depicted in figs. 1 and 2, aircraft engine test stand frame of the present utility model also includes being used to install boat to be tested
The motor mounts 7 of empty engine, surveying torquer 5 also includes and motor support torsion pass axle 504 and motor mounts 7
The engine support 505 of connection, engine support 505 are fixed on the end of motor support torsion pass axle 504, engine support
505 are connected with motor support torsion pass axle 504 by spline.In order to improve resistance to axial force, strengthen connecting with blind flange 506
Connect.
As depicted in figs. 1 and 2, motor mounts 7 are located at the side of testing stand support frame 403 and are located at motor support
The lower section of torsion pass axle 504, then by aero-engine to be tested be arranged on motor mounts 7 on after, aero-engine suspension
In the outside of testing stand support frame 403, it by the rotation of motor support torsion pass axle 504, can install aero-engine
Automatic center-of-gravity regulating position after good, and then cause the axis of motor support torsion pass axle 504 and aero-engine to be tested
Center of gravity is in same vertical plane, can so reduce during the torque measurement because aero-engine own wt and caused by by mistake
Difference.
As depicted in figs. 1 and 2, aircraft engine test stand frame of the present utility model also includes being arranged at engine support
Multiple beams 601 between 505 and motor mounts 7, beam 601 can reach the effect of damping, each beam
601 are connected in an opening position with engine support 505 and motor mounts 7 respectively.
As depicted in figs. 1 and 2, device for measuring force 3 is arranged at the side of moving frame base 405 and common with motor mounts 7
In the same side of testing stand support frame 403, the device for measuring force 3 in this position can make aero-engine of the present utility model
Its Test Rig meets the requirement of the tensile test of aero-engine.The device for measuring force 3 includes being fixedly installed on running support base 1
Adaptor 304, the dynamometry rod bearing 302 being fixedly installed on adaptor 304, the dynamometry that is arranged on dynamometry rod bearing 302
The pressure sensor 303 of push rod 303 and the pressure for being arranged on moving frame base 405 and applying for receiving dynamometry push rod 303.Survey
The length direction of power push rod 303 is parallel with the axis of motor support torsion pass axle 504, and dynamometry push rod 303 is located at running support bottom
The top of seat 1, the end face for facing dynamometry push rod 303 that pressure sensor 303 is arranged at moving frame base 405 (is now moving frame bottom
The front end surface of seat 405) on.
When device for measuring force 3 is arranged at the opposite side of moving frame base 405 and is respectively at testing stand branch with motor mounts 7
During the side of support 403, the device for measuring force 3 in this position can meet aircraft engine test stand frame of the present utility model
The requirement of the thrust test of aero-engine, the structure of the device for measuring force 3 when the structure of the device for measuring force 3 is with surveying pulling force is identical,
3 end faces for facing dynamometry push rod 303 that pressure sensor 303 is disposed on moving frame base 405 (are now moving frame base 405
Rear end end face, front-end and back-end are two ends on the length direction of moving frame base 405) on.
As depicted in figs. 1 and 2, aircraft engine test stand frame of the present utility model also includes pin 8, running support base 1
With the first pin-and-hole for allowing pin 8 to be embedded in, moving frame base 405 has the second pin-and-hole for allowing pin 8 to be embedded in, and pin 8 is to set vertically
It is placed between running support base 1 and moving frame base 405, the lower end of pin 8 is inserted in the first pin-and-hole, the upper end insertion of pin 8 the
In two pin-and-holes.First pin-and-hole is the circular hole being arranged on the top surface of running support base 1, and the second pin-and-hole is to be arranged at moving frame base
Circular hole on 405 bottom surface, the first pin-and-hole is located at the lower section of the second pin-and-hole and both are coaxial, the first pin-and-hole and the second pin-and-hole it is straight
Footpath is equal in magnitude, and the diameter of pin 8 is less than the diameter of the first pin-and-hole and the second pin-and-hole.The effect of pin 8 is to be used to fill moving frame
Put 4 and enter row constraint, avoid moving frame device 4 because significantly swing and caused by sensor destruction.In the present embodiment, the first pin-and-hole and
A diameter of 22mm of second pin-and-hole, a diameter of 20mm of pin 8.
The operation principle of aircraft engine test stand frame of the present utility model is as follows：
1st, when the aero-engine tested can produce pulling force (or thrust) at work, drawn caused by aero-engine
Power (or thrust) can be delivered on moving frame device 4 by motor mounts 7 and survey torquer 5, moving frame device 4 is had one
The trend of (or backward) motion forward, now, moving frame device 4 passes to power installed in the front end of moving frame base 405 (or rear end)
On pressure sensor 303, pressure sensor 303 contacts with dynamometry push rod 303, pressure sensor 303 is pressurized, and can then lead to
Cross the pressure suffered by sensor display reading pressure sensor 303, the as pulling force (or thrust) of engine (before testing
The fixing screws of sensor are adjusted, zero) it is sensor is withstood on the side of moving frame base 405 and initial pressure value.
2nd, caused moment of torsion can make aero-engine drive engine installation to the aero-engine tested at work
Frame 7 and motor support torsion pass axle 504 produce the trend of the axis rotation around motor support torsion pass axle 504, the final moment of torsion
The pressure acted on by surveying moment of torsion jacking block 508 on pressure sensor 507 is converted into, is read by the display of pressure sensor 507
The pressure gone out multiplied by with survey the contact point of moment of torsion jacking block 508 and pressure sensor 507 to the axis of motor support torsion pass axle 504 it
Between distance, as aero-engine moment of torsion (to adjust the fixing screws of sensor before testing, make sensor withstand on survey turn round
Zero) side of square jacking block 508 and initial pressure value are.
The utility model is exemplarily described above in association with accompanying drawing.Obviously, the utility model implements not
Limited by aforesaid way.As long as employ the various unsubstantialities that methodology and technical scheme of the present utility model are carried out
Improvement；Or it is not improved, above-mentioned design of the present utility model and technical scheme are directly applied into other occasions, at this
Within the protection domain of utility model.
Claims (10)
1. aircraft engine test stand frame, it is characterised in that：Including running support base, moving frame device, for being carried to moving frame device
For supporting and enabling moving frame support meanss that moving frame device swings, be arranged on moving frame device and for being produced to aero-engine
The survey torquer and the dynamometry for being tested pulling force caused by aero-engine or thrust that raw moment of torsion is tested
Device, moving frame support meanss and device for measuring force are arranged on running support base.
2. aircraft engine test stand frame according to claim 1, it is characterised in that：The moving frame support meanss include setting
The moving frame column being placed on the running support base and the rocking arm being rotatably arranged on moving frame column, rocking arm and the moving frame
Device is connected and the rotation centerline of rocking arm is in horizontal plane.
3. aircraft engine test stand frame according to claim 2, it is characterised in that：One end of the rocking arm passes through rocking arm
Upper axle is connected with the moving frame column, and the other end of rocking arm is connected by rocking arm lower axle with the moving frame device.
4. the aircraft engine test stand frame according to Claims 2 or 3, it is characterised in that：The moving frame support meanss exist
Multiple and multiple moving frame support meanss are set to be arranged symmetrically in two rows on the running support base.
5. aircraft engine test stand frame according to claim 2, it is characterised in that：The moving frame device includes being located at institute
State the moving frame base above running support base, the testing stand support frame being arranged on moving frame base and be arranged at testing stand support frame
On changeover base, moving frame base is connected with the rocking arm, and the survey torquer is arranged in changeover base.
6. aircraft engine test stand frame according to claim 5, it is characterised in that：The moving frame device also includes and institute
Testing stand support frame is stated to connect with the moving frame base and the diagonal brace to be obliquely installed.
7. the aircraft engine test stand frame according to claim 5 or 6, it is characterised in that：The survey torquer includes
The torsion pass axle support base that is arranged in the changeover base, it is rotatably arranged on torsion pass axle support base and for receiving aviation
The motor support torsion pass axle of moment of torsion caused by engine, the survey moment of torsion jacking block being arranged on motor support torsion pass axle and it is used for
Receive the pressure sensor for the pressure that survey moment of torsion jacking block applies.
8. aircraft engine test stand frame according to claim 7, it is characterised in that：Also include to be tested for installing
The motor mounts of aero-engine, the survey torquer also include pacifying with the motor support torsion pass axle and engine
Shelve the engine support of connection.
9. aircraft engine test stand frame according to claim 8, it is characterised in that：The motor mounts are located at institute
The side of testing stand support frame is stated, the axis and the center of gravity of aero-engine to be tested of the motor support torsion pass axle are in
In same vertical plane.
10. aircraft engine test stand frame according to claim 5, it is characterised in that：The device for measuring force includes dynamometry
Rod bearing, the dynamometry push rod being arranged on dynamometry rod bearing and it is arranged on moving frame base and for receiving the application of dynamometry push rod
The pressure sensor of pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720749170.9U CN206990215U (en) | 2017-06-26 | 2017-06-26 | Aircraft engine test stand frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720749170.9U CN206990215U (en) | 2017-06-26 | 2017-06-26 | Aircraft engine test stand frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206990215U true CN206990215U (en) | 2018-02-09 |
Family
ID=61399782
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720749170.9U Active CN206990215U (en) | 2017-06-26 | 2017-06-26 | Aircraft engine test stand frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206990215U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109374166A (en) * | 2018-12-10 | 2019-02-22 | 中国航发四川燃气涡轮研究院 | A kind of distributed measurement device and method |
| CN109406150A (en) * | 2018-12-13 | 2019-03-01 | 中科航空动力(株洲)装备制造研究院有限公司 | A kind of Used For Turbojet Engine Test Bench rack |
| CN109781423A (en) * | 2018-12-09 | 2019-05-21 | 西安航天动力试验技术研究所 | It is a kind of can it is multi-faceted adjust engine location running support |
| CN110346145A (en) * | 2019-07-16 | 2019-10-18 | 中国航发四川燃气涡轮研究院 | A kind of boat form aeroengine thrust dynamometry rack |
| CN110535852A (en) * | 2019-08-28 | 2019-12-03 | 象限空间（天津）科技有限公司 | A kind of General Aviation piston engine TT&C system |
| CN110793782A (en) * | 2019-09-19 | 2020-02-14 | 中国科学院力学研究所 | Small turbine shaft engine test and test device |
| CN113252346A (en) * | 2021-04-13 | 2021-08-13 | 西安法士特汽车传动有限公司 | Self-adaptive movable test run rack and method |
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
| CN115683415A (en) * | 2022-11-10 | 2023-02-03 | 南通市航天机电自动控制有限公司 | Dynamometer rack for aircraft engine |
-
2017
- 2017-06-26 CN CN201720749170.9U patent/CN206990215U/en active Active
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109781423B (en) * | 2018-12-09 | 2020-11-10 | 西安航天动力试验技术研究所 | Test frame capable of adjusting position of engine in multiple directions |
| CN109781423A (en) * | 2018-12-09 | 2019-05-21 | 西安航天动力试验技术研究所 | It is a kind of can it is multi-faceted adjust engine location running support |
| CN109374166A (en) * | 2018-12-10 | 2019-02-22 | 中国航发四川燃气涡轮研究院 | A kind of distributed measurement device and method |
| CN109406150A (en) * | 2018-12-13 | 2019-03-01 | 中科航空动力(株洲)装备制造研究院有限公司 | A kind of Used For Turbojet Engine Test Bench rack |
| CN110346145A (en) * | 2019-07-16 | 2019-10-18 | 中国航发四川燃气涡轮研究院 | A kind of boat form aeroengine thrust dynamometry rack |
| CN110346145B (en) * | 2019-07-16 | 2021-03-19 | 中国航发四川燃气涡轮研究院 | Boat type aero-engine thrust force measurement rack |
| CN110535852A (en) * | 2019-08-28 | 2019-12-03 | 象限空间（天津）科技有限公司 | A kind of General Aviation piston engine TT&C system |
| CN110793782B (en) * | 2019-09-19 | 2020-10-27 | 中国科学院力学研究所 | Small turbine shaft engine test and test device |
| CN110793782A (en) * | 2019-09-19 | 2020-02-14 | 中国科学院力学研究所 | Small turbine shaft engine test and test device |
| CN113252346A (en) * | 2021-04-13 | 2021-08-13 | 西安法士特汽车传动有限公司 | Self-adaptive movable test run rack and method |
| CN113252346B (en) * | 2021-04-13 | 2024-02-06 | 西安法士特汽车传动有限公司 | Self-adaptive movable test bed and method |
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
| CN115436065B (en) * | 2022-11-08 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
| CN115683415A (en) * | 2022-11-10 | 2023-02-03 | 南通市航天机电自动控制有限公司 | Dynamometer rack for aircraft engine |
| CN115683415B (en) * | 2022-11-10 | 2023-12-29 | 合肥奕谦信息科技有限公司 | Dynamometer rack for aircraft engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206990215U (en) | Aircraft engine test stand frame | |
| CN105277375B (en) | A kind of Electric Motor Wheel is comprehensive performance test bed | |
| CN102175420B (en) | Two-degrees-of-freedom supporting system for wind tunnel test of airplane | |
| CN208751852U (en) | A kind of torsion bar type steering engine torque loading device | |
| CN109018430B (en) | Rotorcraft blade performance test bench | |
| CN211347313U (en) | Two-degree-of-freedom dynamic test supporting device for open wind tunnel | |
| CN102494908A (en) | Servo-motor aerodynamic load analog device of aircraft landing gear folding and unfolding | |
| CN107472519A (en) | A kind of device for coaxial double-rotor helicopter ground resonance test | |
| CN113252285B (en) | Vertical wind tunnel model pitching-rolling test device and use method | |
| CN103943004B (en) | Coriolis acceleration device | |
| CN104843177B (en) | Aircraft | |
| CN210852954U (en) | Four-frame four-axis photoelectric pod vibration reduction structure | |
| CN102998082A (en) | Device for wind tunnel dynamic derivative pitch vibration test | |
| CN106525404A (en) | Tail rotor stand | |
| CN104198152B (en) | Bionic flapping-wing flying vehicle rises force test device and method of testing thereof | |
| CN212556849U (en) | High-precision double-shaft simulation turntable with no shielding of clearance of pitching shaft | |
| CN106005458A (en) | Self-stabilizing platform for high-attitude shooting of unmanned aerial vehicle | |
| CN207365823U (en) | A kind of Free Modal pilot system under guided missile autorotation | |
| CN107168389B (en) | Two-dimensional ultra-high speed rotating platform | |
| CN208070050U (en) | A kind of driving of rudder face and rudder face angle measuring mechanism | |
| CN209209065U (en) | The two-way Test System of Dynamic Balance of unmanned plane rotor | |
| CN111044221B (en) | Three-dimensional inertia testboard adjusting device of unmanned aerial vehicle | |
| CN114166496B (en) | Tilt rotor wing test device | |
| CN115754710A (en) | Coaxial motor testing mechanism and brushless motor | |
| CN205718900U (en) | A kind of automatic counterweight apparatus for pole coordinate measuring apparatus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |