CN104198113A - Double-end calibration device and calibration method - Google Patents

Double-end calibration device and calibration method Download PDF

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Publication number
CN104198113A
CN104198113A CN201410476414.1A CN201410476414A CN104198113A CN 104198113 A CN104198113 A CN 104198113A CN 201410476414 A CN201410476414 A CN 201410476414A CN 104198113 A CN104198113 A CN 104198113A
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measuring force
end device
loading
load
calibration
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CN104198113B (en
Inventor
谢斌
向光伟
赵忠良
吴军强
王超
李�浩
陶洋
杨海泳
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High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
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High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
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  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention relates to a double-end calibration device and a calibration method and belongs to the technical field of aerodynamic force measurement of aerospace force test. The double-end calibration device with the middle fixed and two ends free is used for calibration during force test of wind tunnel aerodynamic/kinematic coupling research. The double-end calibration device mainly comprises two sets of L-shaped sliders and loading heads which are used cooperatively, one end of the front L-shaped slider is connected with the front loading head while the other end of the same is connected with the front end of a double-end force measurement device, and the rear L-shaped slider is connected with the rear loading head while the other end of the same is connected with the rear end of the double-end force measurement device; the loading heads are four-point type frame loading heads, do not interference with each other in space and are used for applying longitudinal load; the L-shaped sliders are connecting pieces between the force measurement device and the loading heads, do not interference with each other in space, are provided with a pair of longitudinally-symmetrical resistance loading points, and are used for applying axial load. The problem about calibration of the double-end force measurement device in special test is solved, six components can be calibrated at most, and the device and the method are simple and feasible special force measurement device calibration schemes indeed.

Description

A kind of both-end calibrating installation and calibration steps
Technical field
The invention belongs to wind-tunnel aerodynamic force measurement mechanism technical field, be specifically related to a kind of both-end calibrating installation and calibration steps.
Background technology
At present, in extraordinary wind tunnel force measurement test, need to design special device for measuring force with size, direction and the application point of the suffered aerodynamic loading of measurement model.Device for measuring force all needs by calibrating installation imposed load before test, and according to certain step method calibration, to obtain the relational matrix of output signal and load, i.e. the composition error of computing formula, and definite device for measuring force.Conventional calibration cartridge is equipped with slide block type, telescopic two kinds, and different with load according to the design feature of device for measuring force, general large load rod-type device for measuring force is selected telescopic calibrating installation, and little load device for measuring force is selected slide block type calibrating installation.Extraordinary device for measuring force generally will design corresponding charger and explore corresponding new calibration steps, to meet test needs.Both-end device for measuring force for extraordinary test cannot complete calibration with existing calibrating installation and calibration steps, main cause is that this device for measuring force is fixedly two ends special construction freely of middle part, and generic calibration device and calibration steps can only calibrate that one end is fixed, other end device for measuring force freely.
Summary of the invention
The present invention, in order to solve the static calibration problem of both-end device for measuring force, provides a kind of both-end calibrating installation and calibration steps.
Adopt for achieving the above object following technical scheme:
A both-end calibrating installation, comprises the web members that two opposition arrange, and the upper end of each web member is provided with for the fixing connecting hole of tested device, and web member upper end is provided with Resistance-load point for loading axial load; The lower end of each web member is provided with loading head, and the loading head of two web member lower end settings is spatially non-interference.
In technique scheme, the connecting hole symmetric coaxial on described two web members arranges.
In technique scheme, the Resistance-load point on described two connecting holes is longitudinally symmetrical.
In technique scheme, described loading head is square, on each angle at four angles of loading head, by vertical connecting line, connects a loading disc.
In technique scheme, described two web members are " L " shape.
The present invention also provides a kind of calibration steps of both-end device for measuring force, and the method is:
The first step, by the adjustment level of tested both-end device for measuring force and stiff end is fixed, installs respectively the web member of two " L " shapes, and two links of tested both-end device for measuring force are inserted in the connecting hole on web member;
Second step, the moment of adjusting respectively two loading heads loads center, and projection on surface level overlaps with two, the stiff end both sides electrical centre of both-end device for measuring force to make it, connects all loading discs;
The 3rd step, each loading disc of web member and loading head imposed load repeatedly therein, gathers the important voltage output value of both-end device for measuring force, calculates major event coefficient and distracter coefficient;
The 4th step, at each loading disc of another web member and loading head imposed load repeatedly, gathers the important voltage output value of both-end device for measuring force, calculates major event coefficient and distracter coefficient;
The 5th step, respectively around axial force direction rotation both-end device for measuring force 180 degree, 90 degree, 270 degree, repeat the first step, the 3rd step, the 4th step, calibrate successively the positive and negative direction of device for measuring force vertical and horizontal, finally obtain the Voltage-output of both-end device for measuring force and the compute matrix of load relation;
The 6th step, the composition error of checking compute matrix, repeatedly, error of calculation index, obtains both-end device for measuring force and measures accuracy the check load that all load(ing) points load respectively stochastic distribution by size at vertical and horizontal.
In said method, described second step and the 3rd step load separately the two ends of both-end device for measuring force successively, try to achieve respectively the mutual interference coefficient in both-end device for measuring force two ends.
In said method, the 6th described step is all directions that simultaneously load both-end device for measuring force leading portion and back segment, to obtain the composition error of both-end device for measuring force.
In said method, it is calibration steps that the calibration steps of described both-end device for measuring force adopts the earth's axis.
The present invention has following characteristics:
1, both-end calibrating installation of the present invention can be realized the fixedly two ends simulation loading of extraordinary device for measuring force freely of middle part, be applicable to play class model pneumatic/the ground static calibration of the front device for measuring force of the extraordinary test of sports coupling dynamometry.
2, having broken through conventional calibration device, can only to calibrate one end be that stiff end, the other end are free-ended device for measuring force, adopts two cover loading heads to be used in conjunction with, and counterweight loads on time space does not interfere mutually.
3, both-end calibrating installation of the present invention is simple in structure, utilizes framed structure to optimize loss of weight, and rigidity is lightweight greatly, has both been easy to processing and assembling, has reduced again the impact of loading head weight on calibration result.
4, the calibration steps of both-end device for measuring force of the present invention is simple, adopts the mode of single-ended calibration and both-end integrated correction, has to utilize to obtain calibration calculations formula accurately.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the front view of both-end calibrating installation of the present invention;
Fig. 2 is the vertical view of both-end calibrating installation of the present invention.
In figure: the 1st, both-end device for measuring force, the 11st, leading portion electrical centre, the 12nd, back segment electrical centre, the 13rd, stiff end, the 21st, before " L " shape slide block, the 22nd, front loading head, the 31st, after " L " shape slide block, the 32nd, rear loading head.
Embodiment
Fig. 1 is the front view of both-end calibrating installation of the present invention, both-end calibrating installation of the present invention, mainly comprises two covers " L " shape slide block and loading head, is used in conjunction with each other, wherein, " L " shape slide block one end is connected with front loading head, and the other end is connected with both-end device for measuring force front end; " L " shape slide block one end is connected with rear loading head afterwards, and the other end is connected with both-end device for measuring force rear end; Described " L " shape slide block is the web member between device for measuring force and loading head, and be provided with the Resistance-load point of a pair of longitudinal symmetry, this Resistance-load point is in the surface level at device for measuring force axial force direction place, by applying axial load with the tangent many groups pulley of this surface level.
Fig. 2 is the vertical view of both-end calibrating installation of the present invention, in conjunction with Fig. 1, loading head of the present invention is four-point framework loading head, adopts layout type one in front and one in back, one on the other, make to load code-disc spatially non-interference, be convenient to utilize standard test weight imposed load; Described both-end calibrating installation is longitudinally symmetrical, the mushing error of introducing to reduce unsymmetric structure.
This example is calibrated to example with the both-end device for measuring force of four components (lift, pitching moment, side force and yawing, totally 8 groups of differential voltage output signals), and concrete implementation step is described:
(1) stiff end of both-end device for measuring force is fixed on calibrated mount, normal force positive dirction upwards, need if desired to connect by suitable joint, guarantee to connect reliable, by optical instruments such as spirit-leveling instrument, inclinators, make the axis of both-end device for measuring force in surface level, 8 groups of differential voltage output signals of both-end device for measuring force are connected with acquisition system, guarantee that sense is consistent with the coordinate system direction of regulation, initial reading is stable;
(2) install before " L " shape slide block and front loading head to both-end device for measuring force front end, after installing, " L " shape slide block and rear loading head are to both-end device for measuring force rear end, by optical instruments such as spirit-leveling instrument, inclinators, make longitudinally symmetrical load(ing) point in same level, do not have roll angle, flange connects, screw tension;
(3) by loading the method for lift and pitching moment, determine the distance of loading head center of moment skew electrical centre, and adjust respectively accordingly forward and backward loading head moment and load center, it is overlapped with leading portion electrical centre and the projection of back segment electrical centre on surface level of both-end device for measuring force, error is no more than 0.2mm, and measure respectively forward and backward loading head center of moment apart from the distance of both-end device for measuring force 1 end face, as calibration center moment reference length;
(4) on four loading discs of front loading head, repeatedly apply step loading, gather the important voltage output value of both-end device for measuring force, calculate the leading portion major event coefficient of both-end device for measuring force and to back segment distracter coefficient;
(5) on four loading discs of rear loading head, repeatedly apply step loading, gather the important voltage output value of both-end device for measuring force, calculate the back segment major event coefficient of both-end device for measuring force and to leading portion distracter coefficient;
For four component force devices, often carry out the sing1e unit calibration of one-component, after utilizing least square fitting to calculate, can obtain the major event coefficient of current calibration component and calibrate component to other seven groups of voltage signals interference coefficient.
(6) respectively around axial force direction rotation both-end device for measuring force 180 degree, 90 degree, 270 degree, repetition (1), (2), (4), (5) step, calibrate successively the longitudinal positive dirction of device for measuring force and horizontal positive and negative direction, for each coefficients by using method of average of positive negative direction, obtain final coefficient.
The final Voltage-output of both-end device for measuring force and the compute matrix of load relation of obtaining, as shown in table 1;
Certain four component both-end device for measuring force calibration formula of table 1
? Y1 Mz1 Y2 Mz2 Z1 My1 Z2 My2
U-Uo 173.65 3.6726 225.65 3.7278 368.61 1.5785 460.55 2.0101
Y1 - 0.06499 -0.07066 -0.002546 0.08900 -0.0002905 0.008688 -9.185E-06
Mz1 -0.5318 - 0.7802 0.02520 0.1275 0.002553 -0.09546 -0.0005781
Y2 -0.07800 0.002433 - -0.06551 0.004347 9.010E-05 0.1303 0.0001293
Mz2 -0.7418 0.01740 1.272 - 0.5341 -0.001773 -0.1436 0.001574
Z1 0.002940 -0.0004797 0.004877 0.0002779 - -0.06683 -0.06411 0.001789
My1 -0.1281 -0.01732 0.002760 0.0003628 -1.738 - -0.9222 0.02631
Z2 0.002128 -0.0001325 0.0007873 -4.915E-05 -0.03560 -0.0005834 - 0.06717
My2 -0.02678 0.001074 0.2619 -0.007292 0.6095 0.01209 -2.7623 -
(7) composition error of checking compute matrix, all load(ing) points adopt orthogonal method that 15 groups of check load are set, at vertical and horizontal, load respectively by check load and load, calculate each component measurement value and load the error between counterweight, and the root mean square of the error of calculation, obtain both-end device for measuring force composite measurement error.
When wind tunnel test, each component calculates the aerodynamic resultant of forward and backward two segment models by following formula:
F i = K i 1 ΔU i 1 + K i 2 ΔU i 2 + Σ j = 1 7 R ij .
The Computing Principle of six component force devices of similar structures and step, with four component both-end device for measuring force in above-mentioned example, are not just described one by one at this.
The technology that the unspecified part of the present invention is known to the skilled person.
The present invention is not limited to aforesaid embodiment.The present invention expands to any new feature or any new combination disclosing in this manual, and the arbitrary new method disclosing or step or any new combination of process.

Claims (9)

1. a both-end calibrating installation, is characterized in that the web members that comprise that two opposition arrange, the upper end of each web member are provided with for the fixing connecting hole of tested device, and web member upper end is provided with Resistance-load point for loading axial load; The lower end of each web member is provided with loading head, and the loading head of two web member lower end settings is spatially non-interference.
2. a kind of both-end calibrating installation according to claim 1, is characterized in that the connecting hole symmetric coaxial setting on described two web members.
3. a kind of both-end calibrating installation according to claim 1, is characterized in that the Resistance-load point of described two web member upper ends is longitudinally symmetrical.
4. a kind of both-end calibrating installation according to claim 1, is characterized in that described loading head is square, on each angle at four angles of loading head, by vertical connecting line, connects a loading disc.
5. a kind of both-end calibrating installation according to claim 1, is characterized in that described two web members are " L " shape.
6. a calibration steps for both-end device for measuring force, is characterized in that the method is:
The first step, by tested both-end device for measuring force adjustment level and stiff end is fixed, the web member of two " L " shapes is installed respectively, two links of tested both-end device for measuring force are inserted in the connecting hole on web member, after adjustment level, use bolted;
Second step, the moment of adjusting respectively two loading heads loads center, and projection on surface level overlaps with two, the stiff end both sides electrical centre of both-end device for measuring force to make it, connects all loading discs;
The 3rd step, each loading disc of web member and loading head imposed load repeatedly therein, gathers the important voltage output value of both-end device for measuring force, calculates major event coefficient and distracter coefficient;
The 4th step, at each loading disc of another web member and loading head imposed load repeatedly, gathers the important voltage output value of both-end device for measuring force, calculates major event coefficient and distracter coefficient;
The 5th step, respectively around axial force direction rotation both-end device for measuring force 180 degree, 90 degree, 270 degree, repeat the first step, the 3rd step, the 4th step, calibrate successively the positive and negative direction of device for measuring force vertical and horizontal, finally obtain the Voltage-output of both-end device for measuring force and the compute matrix of load relation;
The 6th step, the composition error of checking compute matrix, repeatedly, error of calculation index, obtains both-end device for measuring force and measures accuracy the check load that all load(ing) points load respectively stochastic distribution by size at vertical and horizontal.
7. the calibration steps of a kind of both-end device for measuring force according to claim 6, is characterized in that: described second step and the 3rd step load separately the two ends of both-end device for measuring force successively, tries to achieve respectively the mutual interference coefficient in both-end device for measuring force two ends.
8. the calibration steps of a kind of both-end device for measuring force according to claim 6, is characterized in that: the 6th described step is all directions that simultaneously load both-end device for measuring force leading portion and back segment, to obtain the composition error of both-end device for measuring force.
9. the calibration steps of a kind of both-end device for measuring force according to claim 6, is characterized in that: it is calibration steps that the calibration steps of described both-end device for measuring force adopts the earth's axis.
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Cited By (9)

* Cited by examiner, † Cited by third party
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CN107091726A (en) * 2017-05-27 2017-08-25 中国空气动力研究与发展中心高速空气动力研究所 A kind of device and method for improving balance measurement uncertainty
CN107782492A (en) * 2017-12-12 2018-03-09 哈尔滨工业大学 A kind of modular mechanical shoulder joint torque sensor calibrating platform
CN110567639A (en) * 2019-07-31 2019-12-13 中国航天空气动力技术研究院 Multi-axis force sensor calibration method and calibration device
CN110836748A (en) * 2019-11-27 2020-02-25 中国航发沈阳黎明航空发动机有限责任公司 Engine blade static torque meter calibration system and calibration method
CN112098036A (en) * 2020-11-23 2020-12-18 中国空气动力研究与发展中心高速空气动力研究所 Interference force calibration device and method for wind tunnel test blade supporting device
CN112504554A (en) * 2020-10-19 2021-03-16 中国空气动力研究与发展中心高速空气动力研究所 Calibration method of six-component high-precision micro-rolling torque 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
CN115574914A (en) * 2022-09-26 2023-01-06 中国航空工业集团公司哈尔滨空气动力研究所 Calibration device and calibration method for low-speed wind tunnel external air bridge balance
CN117091800A (en) * 2023-10-17 2023-11-21 中国空气动力研究与发展中心高速空气动力研究所 Full-automatic six-degree-of-freedom balance calibration system for low-temperature balance calibration

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1293765A2 (en) * 2001-09-18 2003-03-19 DEUTZ Aktiengesellschaft Procedure for calibrating a power brake used in an internal combustion engine test bench
CN202582832U (en) * 2012-05-02 2012-12-05 浙江省计量科学研究院 Couple type torque standardizing machine
CN103616157A (en) * 2013-12-23 2014-03-05 中国航天空气动力技术研究院 Wind-tunnel balance body shafting static correction system and wind-tunnel balance body shafting static correction method
CN103625655A (en) * 2013-12-23 2014-03-12 中国航天空气动力技术研究院 Strain balance temperature influence calibration system
CN203688149U (en) * 2014-01-02 2014-07-02 深圳乐行天下科技有限公司 Correction device of pressure sensor
CN204085784U (en) * 2014-09-18 2015-01-07 中国空气动力研究与发展中心高速空气动力研究所 A kind of both-end calibrating installation

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1293765A2 (en) * 2001-09-18 2003-03-19 DEUTZ Aktiengesellschaft Procedure for calibrating a power brake used in an internal combustion engine test bench
CN202582832U (en) * 2012-05-02 2012-12-05 浙江省计量科学研究院 Couple type torque standardizing machine
CN103616157A (en) * 2013-12-23 2014-03-05 中国航天空气动力技术研究院 Wind-tunnel balance body shafting static correction system and wind-tunnel balance body shafting static correction method
CN103625655A (en) * 2013-12-23 2014-03-12 中国航天空气动力技术研究院 Strain balance temperature influence calibration system
CN203688149U (en) * 2014-01-02 2014-07-02 深圳乐行天下科技有限公司 Correction device of pressure sensor
CN204085784U (en) * 2014-09-18 2015-01-07 中国空气动力研究与发展中心高速空气动力研究所 A kind of both-end calibrating installation

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107091726A (en) * 2017-05-27 2017-08-25 中国空气动力研究与发展中心高速空气动力研究所 A kind of device and method for improving balance measurement uncertainty
CN107091726B (en) * 2017-05-27 2023-06-23 中国空气动力研究与发展中心高速空气动力研究所 Device and method for improving measurement uncertainty of balance
CN107782492A (en) * 2017-12-12 2018-03-09 哈尔滨工业大学 A kind of modular mechanical shoulder joint torque sensor calibrating platform
CN107782492B (en) * 2017-12-12 2019-11-05 哈尔滨工业大学 A kind of modular mechanical shoulder joint torque sensor calibrating platform
CN110567639B (en) * 2019-07-31 2021-09-07 中国航天空气动力技术研究院 Multi-axis force sensor calibration method and calibration device
CN110567639A (en) * 2019-07-31 2019-12-13 中国航天空气动力技术研究院 Multi-axis force sensor calibration method and calibration device
CN110836748B (en) * 2019-11-27 2021-03-02 中国航发沈阳黎明航空发动机有限责任公司 Engine blade static torque meter calibration system and calibration method
CN110836748A (en) * 2019-11-27 2020-02-25 中国航发沈阳黎明航空发动机有限责任公司 Engine blade static torque meter calibration system and calibration method
CN112504554A (en) * 2020-10-19 2021-03-16 中国空气动力研究与发展中心高速空气动力研究所 Calibration method of six-component high-precision micro-rolling torque measuring device
CN112098036A (en) * 2020-11-23 2020-12-18 中国空气动力研究与发展中心高速空气动力研究所 Interference force calibration device and method for wind tunnel test blade supporting 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
CN115574914A (en) * 2022-09-26 2023-01-06 中国航空工业集团公司哈尔滨空气动力研究所 Calibration device and calibration method for low-speed wind tunnel external air bridge balance
CN115574914B (en) * 2022-09-26 2023-04-14 中国航空工业集团公司哈尔滨空气动力研究所 Calibration device and calibration method for low-speed wind tunnel external air bridge balance
CN117091800A (en) * 2023-10-17 2023-11-21 中国空气动力研究与发展中心高速空气动力研究所 Full-automatic six-degree-of-freedom balance calibration system for low-temperature balance calibration
CN117091800B (en) * 2023-10-17 2024-01-02 中国空气动力研究与发展中心高速空气动力研究所 Full-automatic six-degree-of-freedom balance calibration system for low-temperature balance calibration

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