CN108106812A - A kind of dynamometric system for thrust calibration - Google Patents
A kind of dynamometric system for thrust calibration Download PDFInfo
- Publication number
- CN108106812A CN108106812A CN201810006747.6A CN201810006747A CN108106812A CN 108106812 A CN108106812 A CN 108106812A CN 201810006747 A CN201810006747 A CN 201810006747A CN 108106812 A CN108106812 A CN 108106812A
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- Prior art keywords
- drum
- dynamometric system
- measurement
- dynamometric
- thrust calibration
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Classifications
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L27/00—Testing or calibrating of apparatus for measuring fluid pressure
- G01L27/002—Calibrating, i.e. establishing true relation between transducer output value and value to be measured, zeroing, linearising or span error determination
-
- 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
- G01M15/02—Details or accessories of testing apparatus
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses a set of dynamometric systems for thrust calibration, dynamometric system does not have independent fixed frame and floating frame, floating frame is structure as a whole with drum, its flat elements is using drum as floating frame, it is made of drag direction measurement member, lateral force orientation measurement member and lift orientation measurement member, three groups of drag direction measurement members are set along drum axis direction on drum side wall, two groups of lateral force orientation measurement members are set on the drum side wall of drum axis, and one group of lift orientation measurement member is connected on drum side wall；The present invention is made measuring system reference center be overlapped with drum central axis, realizes and measure without acceptance of persons, solved the problems, such as that traditional external balance misalignment measurement influences the accurate measurement of Mz components using dynamometric system and drum integrated design；The method pre-tightened by increasing load cells, during solving system debug, drum deforms under negative pressure condition, causes load cells zero passage.
Description
Technical field
The present invention relates to aerodynamic scopes, are specifically related to a kind of dynamometric system for thrust bridge standard.
Background technology
The air inlet of aircraft fanjet and jet flow cause the flowing of aircraft wing and fuselage to change, and the liter of aircraft are hindered special
Property and stability generate very important influence.Jet cutting car flow also has apparent influence to the efficiency of rudder, elevator, from
And influence the manipulation characteristic of aircraft.Therefore, it is particularly significant on the influence research of aircraft aerodynamic characteristic to carry out engine charge and jet flow.
Common research means are wind- tunnel investigations, and current state-of-the-art dynamic effect wind tunnel test methods are short in engine mockup
Turbo-power simulator is installed in cabin（TPS, Turbofan Powered Simulator）, it is short that this nacelle is known as TPS
Cabin.
TPS nacelles are used for before wind tunnel test, it is necessary to it be calibrated, therefore high-precision TPS calibrator (-ter) units are
Carry out the key of TPS experiments.The basic function of TPS calibrator (-ter) units is the air inlet and spray for simulating TPS nacelles in wind tunnel test state
Environment is flowed, and the parameters such as flow to TPS nacelles and thrust are accurately measured, to give flow coefficient and velocity coeffficient.But
It is that there is presently no TPS calibrating installations in China, it is impossible to which the autonomous calibration for completing TPS nacelles causes China's TPS power simulation wind
Hole experiment forms complete test capability not yet.In order to further improve the TPS test capabilities in China, meet China's aircraft and grind
Demand processed has carried out the development work of TPS nacelle calibrating installations.
The effect of TPS calibrating tank dynamometric systems is accurately to be measured for the thrust to TPS nacelles, TPS calibrating tanks
The measurement accuracy of dynamometric system directly affects calibration accuracy of the TPS calibrating tanks to experiment nacelle.Therefore, TPS calibrating tanks dynamometry
System development is the key that the development of TPS calibrating tanks and emphasis.
TPS calibrating tank dynamometric systems are a six component force measuring systems of strain-type.Strain-type force system extensive use
In wind tunnel test, simple component or multi -components force cell therein is generally termed balance.According to test model and balance
Relative installation is different, and wind-tunnel balance can be divided into internal balance and external balance, and according to structure type, wind-tunnel balance can divide again
For rod-type balance, box type balance, chip day equality.As domestic air force cause flourishes, wind-tunnel balance technology obtains
Rapid advances.The usual calibration accuracy of wind-tunnel balance of the country such as Chinese aerodynamic investigation and centre of development unit development
0.05% can be reached, accuracy can reach 0.3%, they can meet wind tunnel test measurement needs substantially.But when measurement accuracy will
When asking very high, conventional balance technical solution is difficult often to meet the requirements.Needs, determination of six components of foree system are developed according to TPS calibrating tanks
Each component measurement accuracy requirement of system implements relatively difficult within 0.1%.
One of main purpose of TPS experiments is to obtain interference drag, and engine installation interference drag coefficient magnitude is about
0.004.8m × 6m wind-tunnel transporter model reference areas are typically about 2.5 ㎡, and during wind speed 70m/s, interference drag is about 30N.
This resistance is evaluated, it is necessary to accurately deduct the thrust of TPS nacelles, this requires the error of the axial force of dynamometric system is not more than
3N.In addition, calibration test not only needs to measure the thrust of nacelle, it is also necessary to which the nacelle normal force accurately measured obtains thrust angle.
It can be seen that TPS experiments are very high to the accurate dynamometry requirement of dynamometric system.Therefore, TPS calibrating tanks dynamometric system accurately measures that there are all
More technological difficulties.
A. drum weight normal force（Y-component）Accurate measurement.
Dynamometric system needs to carry the weight of entire drum and TPS nacelles, according to external experience, the weight of entire drum
Close to 1.5 tons, and the normal force of TPS nacelles is usually less than 1200N, only accounts for the 1/10 of drum weight, to the standard of balance normal force
Really measurement brings very big difficulty.If not using counterweight measure, the normal force load design value of balance will at least reach 15000N,
To accurately measure the thrust angle of nacelle（Error is not more than 0.1 °）, the precision of balance is at least up to 0.02% level, existing
Balance technical merit be difficult to reach.
B. the high-acruracy survey and long term stability problem of dynamometric system.
The domestic strain gauge barbola work technology and measuring circuit compensation technique degree that becomes more meticulous is not high, it is difficult to reach TPS
Calibrating tank dynamometric system high-precision and measurement request steady in a long-term.
C. misalignment measurement influences the accurate measurement of Mz components.
In existing scheme, position is measured（Nacelle center）There is larger bias apart from balance system.Drum diameter is about
For 1 meter, balance（X-component）Bias is at least at 0.5 meter or more.The additional Mz load maximum that so resistance generates can reach
More than 1500Nm is approximately Mz component ranges（500N·m）3 times, leverage the measurement accuracy of balance.
The content of the invention
Present invention aim to address the high-acruracy survey problems of side crops industry in TPS calibrating installation calibration experiments, develop one
Set meets the wind tunnel tests demands such as TPS nacelles calibration for the dynamometric system of thrust calibration.
To achieve these goals, the present invention adopts the following technical scheme that：
A set of dynamometric system for thrust calibration, the dynamometric system do not have independent fixed frame and floating frame, the floating
Frame is structure as a whole with drum, the fixed frame and loading device, the braced frame integral structure of counter weight device；Its flat elements with
Drum is floating frame, is made of drag direction measurement member, lateral force orientation measurement member and lift orientation measurement member, along drum axis
Line direction sets three groups of drag direction measurement members on drum side wall, and two groups of sides are set on the drum side wall of drum axis
Member is measured to force direction, one group of lift orientation measurement member is connected on drum side wall.
In the above-mentioned technical solutions, every group of measurement member difference of the drag direction measurement member and lateral force orientation measurement member
It is arranged in parallel by two sensors are opposite on the same line.
In the above-mentioned technical solutions, the structure being arranged in parallel includes a connecting seat, at the both ends of connecting seat each
A connecting rod is connected, the other end of two connecting rods is connected with sensor.
In the above-mentioned technical solutions, elastic hinge is used between the connecting rod and sensor, between connecting rod and connecting seat
Bar connects.
In the above-mentioned technical solutions, the connecting seat has the function of to pre-tighten, and preload work is carried out to the sensor being attached thereto
With.
In the above-mentioned technical solutions, three groups of measurement members of the drag direction along drum central axis in circumferential uniform cloth
It puts, three groups of measuring cells and centerline axis parallel.
In the above-mentioned technical solutions, one group of measuring cell in the lift direction includes two standalone sensors, each
Sensor is attached by suspending way and drum.
In the above-mentioned technical solutions, it is attached between the sensor and drum by pre-tightening connector, pre-tightens connection
The pretightning force of device is generated by the dead weight of drum.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
The present invention is in order to evade the high-acruracy survey of balance and long-time stability this unfavorable factors, it is proposed that is passed based on high-precision
The balance measurement scheme of sensor.Meanwhile sensor is applied and is pre-tightened, it is made to always work in linear best range ability (20%
~100%) measurement accuracy, is not only increased, also improves the structural stability of system；
The present invention uses dynamometric system and drum integrated design, and measuring system reference center is made to be overlapped with drum central axis,
It realizes and measures without acceptance of persons, solve the problems, such as that traditional external balance misalignment measurement influences the accurate measurement of Mz components；
The method pre-tightened by increasing load cells, during solving system debug, drum deforms under negative pressure condition, causes
Load cells zero passages.
Description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is the structure diagram of the system；
Fig. 2 is balance component placement schematic diagram；
Fig. 3 is sensor connection diagram；
Wherein：1 is drum, and 2 be Fx drag directions measurement member, and 3 be Fy side force measurements member, and 4 be that Fz lift orientation measurement is first, 5
It is counter weight device, 6 be braced frame, and 7 be loading device, and 8 be a day flat elements, and 9 be to pre-tighten connecting seat, and 10 be elastic hinge, 11
It is connecting rod, 12 be sensor.
Specific embodiment
All features or disclosed all methods disclosed in this specification or in the process the step of, except mutually exclusive
Feature and/or step beyond, can combine in any way.
It is calibrating tank dynamometric system structure total figure, mainly by braced frame, day flat elements, loading device as shown in Fig. 1
With the compositions such as counter weight device.Dynamometric system does not have independent a fixed frame and floating frame in structure, but by floating frame and drum
Design is integral, and fixed frame is then integral with the design of the braced frame of loading device, counter weight device, this is conducive to greatest extent
Improve the rigidity of balance.Wherein, braced frame is weldment, is big rigidity frame, for sensor, normal direction loading pulley, just
Lift weighted lever is installed；Calibrating installation mainly includes counterweight, steel band charging assembly, pulley etc., and load(ing) point is directly installed on drum
On disk；Counter weight device is divided to two groups of positive normal, while for Fy and Mz trims；Negative two groups of normal direction, for Mx trims.Its flat elements with
Drum is floating frame, installation sensor, draw-bar seat, load(ing) point etc..Wherein, day flat elements are core component, by Fx measurements member, Fy
Measurement member and Fz measurement member compositions, arrange 10 sensors, topology layout is as shown in Figure 2 altogether.In the most key x (gas
The direction of flow or thrust of stream) direction, three groups of measuring cells have been laid out, and compared with drum central axis in circumferential uniform
Arrangement（Layout radius of circle is 600mm, the arm of force Lmy=1040mm, Lmz=600mm）, for measuring Fx, Mz, My component of balance；
In y directions, two groups of measuring cells are laid out, relative distance (arm of force Lmx) is 1140mm, for measuring Fy, Mx of balance points
Amount；In z directions, one group of measuring cell is laid out, for measuring the Fz components of balance.Wherein, drag direction, lateral force direction
Every group of measuring cell is arranged in parallel respectively by two sensors are opposite on the same line, and main purpose is assembled in sensor
Behind position, preload adjustment is carried out to force transmitting link.By adjusting making sensor load not zero passage and in preferable line at work
Property region in, this not only makes sensor have preferable using effect, but also force transmitting link is avoided to be pressurized, and improves balance rigidity
And structural stability.In lift direction, every group of measuring cell then arranges that lift direction is because drum by a sensor hanging
Disc system conducts oneself with dignity and generates pretensioning effect.
Fx/Fy/Fz measurement assemblies mainly by sensor, sensor holder, elastic hinge bar, connecting rod and pre-tighten seat etc. 5
It is grouped into, detailed construction is as shown in Figure 3.Wherein, sensor holder is installed in the relatively infinitely great braced frame of rigidity, pre-tightens seat
Then it is installed on drum.After the completion of assembling, exported by adjusting the adjusting nut on preload seat to adjust the zero of sensor load.
The invention is not limited in foregoing specific embodiments.The present invention, which expands to, any in the present specification to be disclosed
The step of new feature or any new combination and any new method or process disclosed or any new combination.
Claims (8)
1. a set of dynamometric system for thrust calibration, it is characterised in that the dynamometric system does not have independent fixed frame and floating
Frame, the floating frame are structure as a whole with drum, and the braced frame of the fixed frame and loading device, counter weight device is integrally tied
Structure；Its flat elements is using drum as floating frame, by drag direction measurement member, lateral force orientation measurement member and lift orientation measurement tuple
Into three groups of drag directions measurement members being set on drum side wall along drum axis direction, perpendicular to the drum side of drum axis
Two groups of lateral force orientation measurement members are set on wall, and one group of lift orientation measurement member is connected on drum side wall.
2. a set of dynamometric system for thrust calibration according to claim 1, it is characterised in that the drag direction is surveyed
Every group of measurement member of amount member and lateral force orientation measurement member is arranged in parallel respectively by two sensors are opposite on the same line.
3. a set of dynamometric system for thrust calibration according to claim 2, it is characterised in that described to be arranged in parallel
Structure includes a connecting seat, a connecting rod is each connected at the both ends of connecting seat, the other end of two connecting rods is connected with sensing
Device.
4. a set of dynamometric system for thrust calibration according to claim 3, it is characterised in that the connecting rod and sensing
It is connected between device, between connecting rod and connecting seat using elastic hinge bar.
5. a set of dynamometric system for thrust calibration according to claim 3, it is characterised in that the connecting seat has
Function is pre-tightened, preload effect is carried out to the sensor being attached thereto.
6. a set of dynamometric system for thrust calibration according to claim 1, it is characterised in that the drag direction
Three groups of measurement members are in be arranged circumferentially along drum central axis, three groups of measuring cells and centerline axis parallel.
7. a set of dynamometric system for thrust calibration according to claim 1, it is characterised in that the lift direction
One group of measuring cell includes two standalone sensors, each sensor is attached by suspending way and drum.
8. a set of dynamometric system for thrust calibration according to claim 7, it is characterised in that the sensor and drum
It is attached between disk by pre-tightening connector, the pretightning force for pre-tightening connector is generated by the dead weight of drum.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810006747.6A CN108106812A (en) | 2018-01-04 | 2018-01-04 | A kind of dynamometric system for thrust calibration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810006747.6A CN108106812A (en) | 2018-01-04 | 2018-01-04 | A kind of dynamometric system for thrust calibration |
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| Publication Number | Publication Date |
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| CN108106812A true CN108106812A (en) | 2018-06-01 |
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ID=62219573
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| CN201810006747.6A Pending CN108106812A (en) | 2018-01-04 | 2018-01-04 | A kind of dynamometric system for thrust calibration |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109357837A (en) * | 2018-11-22 | 2019-02-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Integral type balance calibration device and calibration method |
| CN109974962A (en) * | 2019-04-25 | 2019-07-05 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of scaling method of the effective forced area of labyrinth seal |
| CN112747892A (en) * | 2020-12-25 | 2021-05-04 | 中国航天空气动力技术研究院 | In-situ calibration device and method for measuring micro aerodynamic force air floatation platform |
| CN112985750A (en) * | 2020-12-23 | 2021-06-18 | 中国航天空气动力技术研究院 | Air-floating type wind tunnel force measuring device |
| CN113253606A (en) * | 2021-06-11 | 2021-08-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Calibration box high-pressure air supply and vacuum air suction combined control system and method |
| CN114216688A (en) * | 2021-11-12 | 2022-03-22 | 南京航空航天大学 | Thrust measuring device of miniature turbine engine |
| CN115046723A (en) * | 2022-08-15 | 2022-09-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Loading device for preparing force measurement test and test method |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109357837A (en) * | 2018-11-22 | 2019-02-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Integral type balance calibration device and calibration method |
| CN109357837B (en) * | 2018-11-22 | 2023-07-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Integrated balance calibration device and calibration method |
| CN109974962A (en) * | 2019-04-25 | 2019-07-05 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of scaling method of the effective forced area of labyrinth seal |
| CN109974962B (en) * | 2019-04-25 | 2023-10-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Calibration method for effective stress area of labyrinth seal |
| CN112985750A (en) * | 2020-12-23 | 2021-06-18 | 中国航天空气动力技术研究院 | Air-floating type wind tunnel force measuring device |
| CN112747892A (en) * | 2020-12-25 | 2021-05-04 | 中国航天空气动力技术研究院 | In-situ calibration device and method for measuring micro aerodynamic force air floatation platform |
| CN113253606A (en) * | 2021-06-11 | 2021-08-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Calibration box high-pressure air supply and vacuum air suction combined control system and method |
| CN114216688A (en) * | 2021-11-12 | 2022-03-22 | 南京航空航天大学 | Thrust measuring device of miniature turbine engine |
| CN114216688B (en) * | 2021-11-12 | 2023-08-04 | 南京航空航天大学 | Miniature turbine engine thrust measuring device and application method thereof |
| CN115046723A (en) * | 2022-08-15 | 2022-09-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Loading device for preparing force measurement test and test method |
| CN115046723B (en) * | 2022-08-15 | 2022-10-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Loading device for preparing force measurement test and test method |
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