CN109374166A - A kind of distributed measurement device and method - Google Patents
A kind of distributed measurement device and method Download PDFInfo
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- CN109374166A CN109374166A CN201811503049.3A CN201811503049A CN109374166A CN 109374166 A CN109374166 A CN 109374166A CN 201811503049 A CN201811503049 A CN 201811503049A CN 109374166 A CN109374166 A CN 109374166A
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- combined engine
- measurement device
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- 238000005259 measurement Methods 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title claims description 16
- 239000013307 optical fiber Substances 0.000 claims description 45
- 238000009434 installation Methods 0.000 description 40
- 239000011159 matrix material Substances 0.000 description 12
- 239000013598 vector Substances 0.000 description 7
- 238000012360 testing method Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000005096 rolling process Methods 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 241001347978 Major minor Species 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011068 loading method Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L1/00—Measuring force or stress, in general
- G01L1/24—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet
- G01L1/242—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet the material being an optical fibre
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/16—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force
- G01L5/166—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force using photoelectric means
-
- 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
Abstract
Disclose a kind of distributed measurement device, the distributed measurement device is used to measure the vectored thrust of combined engine, combined engine includes two or more aero-engines, the distributed measurement device includes support component, mounting assembly and measurement component, in which: combined engine is mounted and fixed to support component by mounting assembly；Measurement component is arranged in mounting assembly, and measurement component acquires the thrust generated when the operating of two or more aero-engines, and the vectored thrust of combined engine is obtained using thrust collected.
Description
Technical field
The invention belongs to aero-engine technology fields, and in particular to a kind of for measuring combined engine vectored thrust
Distributed measurement device and method.
Background technique
Thrust is to evaluate the major parameter of aircraft and engine performance.With the raising of fighter plane technical indicator, thrust arrow
Amount technology becomes one of the significant technology of Fourth Generation Fighters, and Thrust Vectoring Technology imparts aircraft with fault speed super maneuver
Property, high agility, short take-off and landing performance, low detectivity and supersonic cruise ability, substantially increase the operation effect of fighter plane
Energy and survival ability.And equipped with vector spray aircraft flight control system design in, with greater need for by calculate thrust size come
The diversification control of engine and aircraft is carried out, therefore, how effectively directly measuring motor power has become a general character
Technical problem.
Currently, widest vectored thrust measurement method is vectored thrust test bay, major function is exactly by engine
The vectored thrust generated when test, which accurately measures, to be come, and all directions component of vectorial force is obtained by thrust rack, and to vector
The assessment of power progress position, action direction and size.Its principle is: rigid body equilibrium principle utilized, suitably arranges several constraints,
6 freedom degrees (3 one-movement-freedom-degrees and 3 rotational freedoms) for limiting engine are allowed to be in static determinacy or indeterminate flat
Weighing apparatus state measures thrust component size and azimuth.
The capital equipment that vectored thrust test bay is evaluated as vectored thrust engine, there are dynamometry assembly layout form is more
The features such as sample, complicated thrust transfer route, state of the art are most important for the performance for evaluating vectored thrust engine.But
It is that vectored thrust test bay versatility is insufficient, is designed generally directed to a certain model engine, construction, transformation and debugging cycle are long,
Economic cost is high.For assembly power engine, thrust measurement, difficulty are carried out using conventional vector thrust measurement rack
It is bigger.Since the mismachining tolerance of dynamometry component, installation error and rack stress act on the factors such as lower deformation, thrust measurement is caused
The dynamometry component in non-pusher direction generates coupling output error in journey, will seriously affect vectorial force measurement accuracy.
Summary of the invention
Goal of the invention
An object of the present invention is to provide a kind of distributed vectored thrust measuring device for aero-engine and
Method, to solve the problems, such as at least one in above-mentioned technical background or at least provide the useful business of one kind to select.
Technical solution
Distributed measurement device through the invention realizes above-mentioned purpose, and the distributed measurement device is for measuring combination
The vectored thrust of engine, combined engine include two or more aero-engines, and the distributed measurement device includes
Support component, mounting assembly and measurement component, in which: combined engine is mounted and fixed to by support group by mounting assembly
Part；Measurement component be arranged in mounting assembly, measurement component acquire two or more aero-engines operating when generate push away
Power, and utilize the vectored thrust of thrust collected acquisition combined engine.
In above-mentioned distributed measurement device, in conjunction with the space layout of measurement component, thrust acquisition group collected is utilized
Close the vectored thrust of engine.
In above-mentioned distributed measurement device, measure component space layout include measure component spatial position and/or
Orientation angle.
In above-mentioned distributed measurement device, measurement component includes optical fiber load cell, and the measurement of optical fiber load cell is simultaneously defeated
The stress of mounting assembly out obtains the vectored thrust of combined engine by the stress of mounting assembly.
Additionally provide a kind of method for measuring combined engine vectored thrust, the combined engine include two or
More aero-engines, the method use distributed measurement device, and the distributed measurement device includes support component, peace
Arrangement and measurement component, the method comprise the steps that combined engine is mounted and fixed to support group by mounting assembly
Part；Measurement component is arranged in mounting assembly；Production when acquiring the operating of two or more aero-engines by measuring component
Raw thrust；And the vectored thrust of combined engine is obtained using thrust collected.
In the method for the invention, in conjunction with the space layout of measurement component, combination is obtained using thrust collected and is started
The vectored thrust of machine.
In the method for the invention, the space layout for measuring component includes spatial position and/or the deflection for measuring component
Degree.
Beneficial effect
The distributed vectored thrust measuring device and method for aero-engine that the present invention designs, using in engine
Arrange that the mode of optical fiber load cell carries out engine vectored thrust measurement, core in the major-minor installation section structure of fluidic vectoring nozzle
Intracardiac appearance is to export the electric signal that the stress check calculation of major-minor fulcrum is optical fiber load cell, and combine nominal data by multiple electricity
Signal output result is converted to the thrust of engine.It solves the assembly power with the unilateral expansion fluidic vectoring nozzle of binary to start
Machine can not carry out the problem of vectored thrust measurement using conventional vector thrust rack, while logical for conventional vector thrust bed
With property deficiency, the construction problem that debugging cycle is long, economic cost is high, new thinking is proposed.
Detailed description of the invention
Fig. 1 is the schematic diagram of distributed measurement device of the invention；
Fig. 2 shows the first main installation sections of distributed measurement device of the invention；
Fig. 2 a shows the cross-sectional view of the interception of the line A-A in Fig. 2；
Fig. 3 shows the first auxiliary installation section of distributed measurement device of the invention；
Fig. 3 a shows the cross-sectional view of the interception of the line B-B in Fig. 3.
Specific embodiment
In Fig. 1, upper engine 1, combination spray pipe 5, lower engine 9 form combined engine, generate axial direction by combination spray pipe 5
The vectored thrust of power Fx, vertical force Fy, pitching moment Mz and rolling moment Mx composition.Upper engine 1 passes through the first main installation section
3, before the first auxiliary installation section 4 is fixed on mounting rack 2；Lower engine 9 passes through the main installation section 8 of third, third auxiliary installation section
10 are fixed on preceding mounting rack 2；Combination spray pipe 5 is fixed on rear mounting rack by second main installation section the 11, second auxiliary installation section 7
On 6.
The load such as engine axial thrust Fx, vertical thrust Fy, gravity G and motor-driven overload save and assist installation by main installation
Section passes to rack.Main installation point constrains engine axial thrust, vertical force, gravity, belongs to cantilever beam structure；Assist installation point
For Tiebar structure, the gravity and vertical force of engine are constrained, only in pull rod stress, belongs to two power rod structures.Wherein, the first main peace
The main 8 realization main thrust Fx and vertical force Fy measurement of installation section of the main installation section 11 of dress section 3, second, third, the first auxiliary installation section 4,
Second auxiliary installation section 7, third auxiliary installation section 10 realize pitching moment Mz and rolling moment Mx measurement.
In Fig. 2, core bar 31, mounting base 32, adjusting nut 33, spring beam 34, the main installation section 3 of the composition of conical head 35 first.
Before mounting base 32 is fixed on mounting rack 2, core bar 31 passes through mounting base 32, changes the position of core bar 31 by adjusting nut 33,
Conical head 35 is inserted into the ball-and-socket on upper engine 1 with fixed upper engine 1.It is spring beam 34 between core bar 31 and conical head 35,
It is circumferentially evenly distributed with four optical fiber load cells, the first vertical force optical fiber load cell 36 and the second vertical force optical fiber load cell 39
For measuring vertical force Fy, it is located at 34 top and bottom of spring beam, first axial force optical fiber load cell 37 and the second axis
To power optical fiber load cell 38 for measuring main thrust Fx, it is located at the front-end and back-end of spring beam 34.
The bad environments as locating for combined engine, temperature change is big, hangs down to eliminate temperature to spring beam 34, first
It is vertical to power optical fiber load cell 36, first axial force optical fiber load cell 37, the second axial force optical fiber load cell 38, second
The influence of power optical fiber load cell 39, improves measurement accuracy, and the first vertical force optical fiber load cell 36, first axial force optical fiber are surveyed
Power unit 37, the second axial force optical fiber load cell 38, the second vertical force optical fiber load cell 39 are all made of full-bridge connection, together
Shi Zengjia temperature compensation means.
The output of first vertical force optical fiber load cell 36 is R36, the output of first axial force optical fiber load cell 37 is R37, the
The output of two axial force optical fiber load cells 38 is R38, the output of the second vertical force optical fiber load cell 39 is R39。
Similarly, the second main installation section 11, the main installation section 8 of third are similar with the first main installation 3 structure types of section, do not do herein
It is described in detail.Wherein, four optical fiber load cells output of the second main installation section 11 is respectively R116、R117、R118、R119, the main peace of third
Four optical fiber load cells output of dress section 8 is respectively R86、R87、R88、R89。
In Fig. 3, fixing seat 41, first connecting rod 42, dynamometer link 43, the composition of second connecting rod 44 first auxiliary installation section.It is fixed
Before seat 41 is mounted on mounting rack 2,42 one end of first connecting rod is fixed on fixing seat 41, one end is connected with dynamometer link 43, and second connects
44 one end of bar is connected with dynamometer link 43, the other end is connected with upper engine 1, for fixed upper engine 1.Dynamometer link 43 is circumferential
Four optical fiber load cells of cloth, the first pulling force optical fiber load cell 45, the second pulling force optical fiber load cell 46, third pulling force optical fiber
Load cell 47, the 4th pulling force optical fiber load cell 48 form coupling circuit, for measuring pitching moment Mz and rolling moment Mx.
Similarly, in order to eliminate temperature to dynamometer link 43, the first pulling force optical fiber load cell 45, the second pulling force optical fiber dynamometry list
The influence of member 46, third pulling force optical fiber load cell 47, the 4th pulling force optical fiber load cell 48 improves measurement accuracy, and first draws
Power optical fiber load cell 45, the second pulling force optical fiber load cell 46, third pulling force optical fiber load cell 47, the 4th pulling force optical fiber are surveyed
Power unit 48 is all made of full-bridge connection, while increasing temperature compensation means.
The output of first pulling force optical fiber load cell 45 is R45, the output of the second pulling force optical fiber load cell 46 is R46, third drawing
The output of power optical fiber load cell 47 is R47, the output of the 4th pulling force optical fiber load cell 48 is R48。
Similarly, the second auxiliary installation section 7, third auxiliary installation section 10 are similar with the first auxiliary installation 4 structure types of section,
This is not detailed.Wherein, four optical fiber load cells output of the second auxiliary installation section 7 is respectively R75、R76、R77、R78, third
Four optical fiber load cells output of auxiliary installation section 10 is respectively R105、R106、R107、R108。
The stress condition of 3 groups of main installation sections and 3 groups of auxiliary installation sections is obtained by 48 groups of optical fiber load cells, in next step
Work is exactly the spatial position and orientation angle according to main and auxiliary installation section, and the power of each installation section is calculated resultant force with respect to reference point.
The stress of first main installation section 3 is respectively as follows:
The stress of second main installation section 11 is respectively as follows:
The stress of the main installation section 8 of third is respectively as follows:
The stress of first auxiliary installation section 4 is respectively as follows:
The stress of second auxiliary installation section 7 is respectively as follows:
The stress of third auxiliary installation section 10 is respectively as follows:
Therefore the vectored thrust measurement result of combined engine are as follows:
In order to realize the decoupling of measurement data, needs to test advance rower and determine, obtain decoupling matrices.According to selected calibration
Loading method and calibration test data, using the static decoupling algorithm of solution matrix generalized inverse, to vectored thrust measuring system into
Row decoupling computation, the validity of assessment system coupling error and static decoupling algorithm.
The matrix column vectors of dimension (12) that one group of calibration loading force is constituted is indicated with F, then K group loaded load data can be with
Constitute the matrix [F] of a 12*KN；Matrix (the m that the measurement indicating value of one group of vectored thrust measurement rack is constituted is indicated with matrix R
The column vector of dimension), then it can obtain the matrix R of a m × K.According to linear theory calibrating patterns, available following matrix side
Journey:
F=AR+E
In formula, E indicates that residual error, the error which meets front are assumed.According to the principle of least square, to be
The unbiased esti-mator of matrix number AE must be enabled to be equal to 0, it may be assumed that
Or
If the matrix R's of construction is full rank, order m, then matrix RTThe determinant of R is not equal to 0, thenMust have
Unique solution.The matrix expression of the calibration factor matrix solution of any component:
Claims (7)
1. a kind of distributed measurement device, the distributed measurement device is used to measure the vectored thrust of combined engine, combination
Engine includes two or more aero-engines, and the distributed measurement device includes support component, mounting assembly and survey
Measure component, in which:
Combined engine is mounted and fixed to support component by mounting assembly；
Measurement component be arranged in mounting assembly, measurement component acquire two or more aero-engines operating when generate push away
Power, and utilize the vectored thrust of thrust collected acquisition combined engine.
2. distributed measurement device according to claim 1, wherein in conjunction with the space layout of measurement component, using being adopted
The thrust of collection obtains the vectored thrust of combined engine.
3. distributed measurement device according to claim 2, wherein the space layout for measuring component includes measurement component
Spatial position and/or orientation angle.
4. distributed measurement device according to claim 1 or 2, wherein measurement component includes optical fiber load cell, optical fiber
Load cell measures and exports the stress of mounting assembly, and the vectored thrust of combined engine is obtained by the stress of mounting assembly.
5. a kind of method for measuring combined engine vectored thrust, the combined engine includes two or more aviations
Engine, the method use distributed measurement device, and the distributed measurement device includes support component, mounting assembly and survey
Component is measured, the method comprise the steps that
Combined engine is mounted and fixed to support component by mounting assembly；
Measurement component is arranged in mounting assembly；
The thrust generated when the operating of two or more aero-engines is acquired by measuring component；And
The vectored thrust of combined engine is obtained using thrust collected.
6. according to the method described in claim 5, wherein, in conjunction with the space layout of measurement component, being obtained using thrust collected
Obtain the vectored thrust of combined engine.
7. according to the method described in claim 6, wherein, the space layout for measuring component includes measuring the spatial position of component
And/or orientation angle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811503049.3A CN109374166B (en) | 2018-12-10 | 2018-12-10 | Distributed measuring device and method |
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| CN201811503049.3A CN109374166B (en) | 2018-12-10 | 2018-12-10 | Distributed measuring device and method |
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| CN109374166B CN109374166B (en) | 2021-08-03 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114166510A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Measuring device for transverse rigidity of force measuring assembly |
| CN114923617A (en) * | 2022-07-21 | 2022-08-19 | 中国航发四川燃气涡轮研究院 | Engine lift force measuring device |
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| CN106500902A (en) * | 2016-12-03 | 2017-03-15 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of strain-type multidimensional force sensor with from decoupling function |
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| CN108168774A (en) * | 2017-12-27 | 2018-06-15 | 中国航发四川燃气涡轮研究院 | A kind of space vector force calibration method |
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2018
- 2018-12-10 CN CN201811503049.3A patent/CN109374166B/en active Active
Patent Citations (6)
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| CN202693314U (en) * | 2012-06-15 | 2013-01-23 | 北京中陆航星机械动力科技有限公司 | Turbojet engine test bed |
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| CN114166510A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Measuring device for transverse rigidity of force measuring assembly |
| CN114923617A (en) * | 2022-07-21 | 2022-08-19 | 中国航发四川燃气涡轮研究院 | Engine lift force measuring device |
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| CN109374166B (en) | 2021-08-03 |
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