CN206399626U - The measurement apparatus of wing flexibility matrix - Google Patents
The measurement apparatus of wing flexibility matrix Download PDFInfo
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- CN206399626U CN206399626U CN201621280671.9U CN201621280671U CN206399626U CN 206399626 U CN206399626 U CN 206399626U CN 201621280671 U CN201621280671 U CN 201621280671U CN 206399626 U CN206399626 U CN 206399626U
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Abstract
The utility model provides a kind of measurement apparatus of wing flexibility matrix.The measurement apparatus of the wing flexibility matrix includes：Deformation measuring device, model supporting device, workbench, mobile device, force application mechanism and numerical control alignment system, mobile device is arranged on workbench, force application mechanism is set on the mobile device, and numerical control positioning system is electrically connected with mobile device and force application mechanism respectively；Model supporting device is fixed on the end of workbench, and numerical control positioning system control mobile device is moved on workbench, so that mobile device drives force application mechanism movement, and controls force application mechanism to apply pressure to the diverse location of wing；Deformation measuring device is fixedly installed at the position of workbench, measures the deflection of wing.Its is simple in construction for the measurement apparatus of the wing flexibility matrix, and measurement is accurate, and measurement process is easily operated, and then while the accuracy of wing flexibility matrix measurement is improved, reduces the workload of staff.
Description
Technical field
The utility model is related to Flight Vehicle Structure flexibility e measurement technology, more particularly to a kind of measurement of wing flexibility matrix is filled
Put.
Background technology
Aeroelastic effect is that aircraft produces elastic deformation under aerodynamic effect and causes its aerodynamic characteristic to change
A kind of phenomenon.In live flying, due to the effect of aerodynamic loading, the lift member particularly wing of aircraft can produce elastic change
Shape, i.e. lifting surface produce bending and reversed, and cause its load to redistribute, and change aerodynamic characteristic.Wing flexibility according to measurement
Matrix, can carry out the aeroelastic effect influence amendment of aircraft, improve the flight safety of aircraft.
Fig. 1 a are the schematic diagram of the measurement apparatus of existing wing flexibility matrix, as shown in Figure 1a, traditional measurement wing
The device of flexibility matrix includes model supporting device 2, loading device 10 and deformation measuring device 1.Wherein, loading device 10 is used
Loading pressurized strut or extension counterweight are loaded to wing 5, and deformation measuring device 1 is using dial gauge, amesdial or displacement transducer
Gather the deflection of wing 5.
But existing measurement apparatus, its measurement efficiency is low, workload is big.
Utility model content
The utility model provides a kind of measurement apparatus of wing flexibility matrix, to overcome existing measurement apparatus, and it is measured
The problem of efficiency is low, workload is big.
The utility model provides a kind of measurement apparatus of wing flexibility matrix, including：
Deformation measuring device, model supporting device, workbench, mobile device, force application mechanism and numerical control alignment system, institute
State mobile device to be arranged on the workbench, the force application mechanism is arranged in the mobile device, the numerical control positioning
System is electrically connected with the mobile device and the force application mechanism respectively；
The model supporting device is fixed on the end of the workbench, for fixing the wing；
The numerical control positioning system, for controlling the mobile device to be moved on the workbench, so that described move
Dynamic device drives the force application mechanism movement, and, for controlling the force application mechanism to apply to the diverse location of the wing
Pressure；
The deformation measuring device is fixedly installed at the position of the workbench, is existed for measuring the wing
Deflection under the force application mechanism pressure applied.
Further, the model supporting device includes side plate and the groove being arranged on the surface of side plate；
The side plate is fixedly installed on the end of the workbench, and the wing is fixedly installed on the default of the groove
At position.
Further, the force application mechanism includes force termination and servo electric jar, and the force termination is arranged on described
The top of servo electric jar, the servo electric jar is electrically connected with the numerical control positioning system.
Further, the force application mechanism also includes：Pressure sensor, the pressure sensor is fixed with the numerical control respectively
Position system, force termination electrical connection；
The pressure sensor, for gathering force termination pressure applied, and by the pressure output to institute
State numerical control positioning system.
Further, the surface of the workbench sets X to line slideway, and the mobile device is included along the X
The first moving carriage for being moved to line slideway, the Y-direction line slideway being arranged on first moving carriage, along the Y
The second moving carriage for being moved to line slideway, X are to servomotor and Y-direction servomotor；
The X is connected with first moving carriage and the numerical control positioning system respectively to servomotor, and the Y-direction is watched
Take motor to be connected with second moving carriage and the numerical control positioning system respectively, the servo electric jar is fixedly installed on institute
State on the second moving carriage.
Further, the X is provided with to X is provided with to displacement transducer on line slideway on the Y-direction line slideway
Y-direction displacement transducer；
The X is electrically connected with the numerical control positioning system respectively to displacement transducer, the Y-direction displacement transducer；
The X is used to measure the present bit of the force application mechanism to displacement transducer and the Y-direction displacement transducer
Put, and the current location is exported to the numerical control positioning system.
Further, the numerical control positioning system includes host computer and slave computer；
The host computer and the next mechatronics, the slave computer is respectively with the X to displacement transducer, the Y
It is electric to displacement transducer, the X to servomotor, the Y-direction servomotor, the servo electric jar and the pressure sensor
Connection.
Optionally, the deformation measuring device is three coordinate measuring machine, and the three coordinate measuring machine includes measurement probe；
The three coordinate measuring machine, for when the force application mechanism applies pressure to the wing, according to default many
The X of individual measurement point, Y-coordinate, to measure the Z coordinate value of each measurement point.
Optionally, the X to displacement transducer and the Y-direction displacement transducer be grating scale.
The measurement apparatus for the wing flexibility matrix that the utility model is provided, by the way that mobile device is arranged on into workbench
On, force application mechanism is set on the mobile device, and numerical control positioning system is electrically connected with mobile device and force application mechanism.Model
Support meanss are fixed on the end of the workbench, for fixing the wing；The numerical control positioning system, for controlling
Mobile device is stated to move on the workbench, so that the mobile device drives the force application mechanism movement, and, it is used for
The force application mechanism is controlled to apply pressure to the diverse location of the wing；The deformation measuring device is fixedly installed on close to institute
State at the position of workbench, for measuring deflection of the wing under the force application mechanism pressure applied, and then
Realize the accurate measurement to wing deflection.Its is simple in construction for the measurement apparatus of the present embodiment, and measurement is accurate, and measurement process is easy
Operation, and then while the accuracy of wing flexibility matrix measurement is improved, reduce the workload of staff.
Brief description of the drawings
, below will be to embodiment or existing in order to illustrate more clearly of the utility model or technical scheme of the prior art
The accompanying drawing used required in technology description is briefly described, it should be apparent that, drawings in the following description are this practicalities
Some new embodiments, for those of ordinary skill in the art, without having to pay creative labor, may be used also
To obtain other accompanying drawings according to these accompanying drawings.
Fig. 1 a are the schematic diagram of the measurement apparatus of existing wing flexibility matrix；
Fig. 1 is the front view of the measurement apparatus for the wing flexibility matrix that the utility model embodiment one is provided；
Fig. 1 b are the top view of the measurement apparatus for the wing flexibility matrix that the utility model embodiment one is provided；
Fig. 1 c are that the left view of the measurement apparatus for the wing flexibility matrix that the utility model embodiment one is provided (eliminates change
Shape measurement apparatus)；
The structural representation of the measurement apparatus embodiment two for the wing flexibility matrix that Fig. 2 provides for the utility model；
The structural representation of the measurement apparatus embodiment three for the wing flexibility matrix that Fig. 3 provides for the utility model；
The structural representation of the measurement apparatus example IV for the wing flexibility matrix that Fig. 4 provides for the utility model；
The structural representation of the measurement apparatus embodiment five for the wing flexibility matrix that Fig. 5 provides for the utility model.
Accompanying drawing identifier declaration：
1：Deformation measuring device；
101：Measure probe；
2：Model supporting device；
201：Side plate；
202：Groove；
203：Pedestal；
10：Loading device；
3：Workbench；
301：X is to line slideway；
4：Vibration-proof foundation；
5：Wing；
6：Mobile device；
7：Force application mechanism；
701：Exert a force termination；
702：Servo electric jar；
703：Pressure sensor；
601：First moving carriage；
602：Y-direction line slideway；
603：Second moving carriage；
80：Numerical control positioning system；
8：Host computer；
9：Slave computer；
901：XY coordinate acquisition modules；
902：Controller；
903：Servomotor drive module；
904：Exert a force acquisition module；
905：Communication module.
Embodiment
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Accompanying drawing in type embodiment, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that retouched
The embodiment stated is a part of embodiment of the utility model, rather than whole embodiments.Based on the implementation in the utility model
Example, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made is belonged to
The scope of the utility model protection.
The measurement apparatus for the wing flexibility matrix that the utility model is provided, it is adaptable to the aircraft of disposable type, for measuring
The flexibility matrix of wing, can be used for the aerofoil flexibility matrix of survey aircraft empennage and other types aircraft.
Below, the technical scheme shown in the application is described in detail by specific embodiment.It should be noted that under
These specific embodiments of face can be combined with each other, may be in certain embodiments for same or analogous concept or process
Repeat no more.
Fig. 1 is the front view of the measurement apparatus for the wing flexibility matrix that the utility model embodiment one is provided, and Fig. 1 b are this
The top view of the measurement apparatus for the wing flexibility matrix that utility model embodiment one is provided, Fig. 1 c are the utility model embodiment one
The left view (eliminating deformation measuring device) of the measurement apparatus of the wing flexibility matrix of offer.The wing flexibility square of the present embodiment
The measurement apparatus of battle array can include deformation measuring device 1, model supporting device 2, workbench 3, mobile device 6, force application mechanism 7
With numerical control alignment system (not shown), mobile device 6 is provided with the workbench 3, the force application mechanism 7 is arranged on
In the mobile device 6, the numerical control positioning system is electrically connected with the mobile device 6 and the force application mechanism 7 respectively；It is described
Model supporting device 2 is fixed on the end of the workbench 3, for fixing the wing 5；The numerical control positioning system, is used
In controlling the mobile device 6 to be moved on the workbench 3, so that the mobile device 6 drives the force application mechanism 7 to move
It is dynamic, and, for controlling diverse location application pressure of the force application mechanism 7 to the wing 5；The deformation measuring device 1
It is fixedly installed at the position of the workbench 3, is applied for measuring the wing 5 in the force application mechanism 7
Deflection under pressure.
Specifically, as shown in figure 1, the measurement apparatus of the present embodiment mainly includes deformation measuring device 1, model supporting device
2nd, workbench 3, mobile device 6, force application mechanism 7 and numerical control alignment system.Wherein, mobile device 6 is arranged on workbench 3
On, and can be moved on workbench 3.Force application mechanism 7 is fixedly installed on a mobile platform, and model supporting device 2 is set
In the end of workbench 3, meanwhile, numerical control positioning system is electrically connected with mobile device 6 and force application mechanism 7 respectively.The present embodiment
In, model supporting device 2 is used to fix wing 5 (being specially wing model), and mobile device 6 is under the control of numerical control positioning system
Force application mechanism 7 is driven to be moved to the underface of the point to be measured of wing 5.When positioned at the underface of the model of wing 5, numerical control positioning
System controls force application mechanism 7 to the pressure pressure of wing 5 (i.e. loading force) so that wing 5 deforms under the effect of the pressure.
Deformation measuring device 1 measures the deflection of now wing 5, specifically measures the Z coordinate value of wing 5.
It should be noted that the present embodiment is before measuring, it is necessary first in numerical control positioning system and deformation measuring device 1
In set the point for needing to measure, and the corresponding pressure value of each point to be measured.Numerical control positioning system can be treated according to above-mentioned
The position coordinates of measurement point controls the mobile device 6 to be moved to the underface of point to be measured, and controls force application mechanism 7 to wing
5 apply its corresponding pressure.Meanwhile, deformation measuring device 1 can respectively be treated according to the position coordinates of point to be measured to measure successively
The Z coordinate value of measurement point.
Wherein, the deformation measuring device 1 of the present embodiment is positioned close at the position of workbench 3, and is filled with mobile
The coordinate for putting 6 is identical, and then ensures that the measurement point that force application mechanism 7 is acted on is identical with the measurement point that deformation measuring device 1 is measured.
In actual use, wing 5 is fixedly installed on to the predetermined position of model supporting device 2.In numerical control positioning system
System pressure value corresponding with position coordinates and each measurement point that measurement point is set in deformation measuring device 1.For example, measurement point A：
(X, Y)=(10,20), its corresponding pressure value is 2KN, measurement point B：(X, Y)=(15,30), its corresponding pressure value is
1KN.Numerical control positioning system control mobile device 6 is moved so that the force application mechanism 7 being fixed in mobile device 6 is shifted along
The movement of device 6 and move, when force application mechanism 7 be located at measurement point A underface when, numerical control positioning system control force application mechanism 7
To measurement point A pressures 2KN pressure, wing 5 deforms under the pressure of the 2KN.Deformation measuring device 1 is moved to measurement point
A surface, the Z coordinate values of measurement measurement point A now, and preserve the Z coordinate value of the A points.Then, deformation measuring device 1 is moved
Move to measurement point B surface, the Z coordinate values of measurement measurement point B now, and preserve the Z coordinate value of B points.Deformation measuring device 1
Z coordinate value before measurement point A and B Z coordinate value now and measurement is compared, you can obtain the measurement point A of wing 5 and measurement
Point B deflection.Further, numerical control positioning system control force application mechanism 7 is recalled, and controls mobile device 6 to measurement point B's
Underface is moved, and when force application mechanism 7 is located at measurement point B underface, numerical control positioning system controls force application mechanism 7 to measurement point
B pressures 1KN pressure.Then, deformation measuring device 1 is moved to measurement point A and measurement point B, measurement measurement point A and measurement successively
Point B is in the deflection pressed to measurement point B under 1KN pressure.
It should be noted that model supporting device 2 can be removably attached to the end of workbench 3 in the present embodiment
Portion, such as bolt connection.Optionally, model supporting device 2 can also be welded on to the end of workbench 3, the present embodiment
Model supporting device 2 is not limited with the mode that is fixedly connected of workbench 3.
The workbench 3 and deformation measuring device 1 of the present embodiment can be arranged on shockproofly by parallels and fot screw
On base 4, it is to avoid influence the accuracy of measurement due to vibrations in measurement process.
The measurement apparatus for the wing flexibility matrix that the utility model is provided, by the way that mobile device is arranged on into workbench
On, force application mechanism is set on the mobile device, and numerical control positioning system is electrically connected with mobile device and force application mechanism.Model
Support meanss are fixed on the end of the workbench, for fixing the wing；The numerical control positioning system, for controlling
Mobile device is stated to move on the workbench, so that the mobile device drives the force application mechanism movement, and, it is used for
The force application mechanism is controlled to apply pressure to the diverse location of the wing；The deformation measuring device is fixedly installed on close to institute
State at the position of workbench, for measuring deflection of the wing under the force application mechanism pressure applied, and then
Realize the accurate measurement to wing deflection.Its is simple in construction for the measurement apparatus of the present embodiment, and measurement is accurate, and measurement process is easy
Operation, and then while the accuracy of wing flexibility matrix measurement is improved, reduce the workload of staff.
The structural representation of the measurement apparatus embodiment two for the wing flexibility matrix that Fig. 2 provides for the utility model.Upper
State on the basis of embodiment, the model supporting device 2 of the present embodiment can also include side plate 201 and be arranged on the side plate 201
Groove 202 on surface；The side plate 201 is fixedly installed on the end of the workbench 3, and the wing 5 is fixedly installed
In the predetermined position of the groove 202.
Specifically, as shown in Fig. 2 the model supporting device 2 of the present embodiment includes side plate 201, along dampening on side plate 201
Square to being provided with groove 202.One end of side plate 201 is fixed on to the end of workbench 3, now side plate 201 and work are flat
Platform 3 is vertical, and groove 202 is parallel with workbench 3.Wing 5 (being specifically the root of wing 5) is fixed on the default of groove 202
At position, and then realize the fixation to wing 5.
Optionally, wing 5 can be fixed in groove 202 by the present embodiment by bolt clamping or other manner.
Optionally, the present embodiment can set multiple grooves 202 on side plate 201, and then realize to wing 5 in different height
Positioning on degree.Wherein, the distance between particular number and adjacent two groove 202 of the groove 202 that side plate 201 is set can
To be set according to actual needs, the present embodiment is without limitation.
In order to improve the stability maintenance of side plate 201 and workbench 3, the model supporting device 2 of the present embodiment is in side plate
201 bottom is provided with a pedestal 203 by iron casting, and the pedestal 203 is fixed on workbench 3, and then
Implementation model support meanss 2 and the firm connection of workbench 3.
The measurement apparatus for the wing flexibility matrix that the utility model is provided, by being set on the side plate of model supporting device
Multiple grooves, realize the fixation to wing on different height, and then improve the controllability in test process to wing position.
The structural representation of the measurement apparatus embodiment three for the wing flexibility matrix that Fig. 3 provides for the utility model.Upper
On the basis of stating embodiment, as shown in figure 3, the force application mechanism 7 of the present embodiment can include force termination 701 and servo electric jar
702, the force termination 701 is arranged on the top of the servo electric jar 702, the servo electric jar 702 and the numerical control
Alignment system is electrically connected.
Specifically, as shown in figure 3, the force application mechanism 7 of the present embodiment includes force termination 701 and servo electric jar 702, its
Middle servo electric jar 702 is fixedly installed in mobile device 6, and force termination 701 is arranged on the top of servo electric jar 702, watches
Electric cylinder 702 is taken to electrically connect with numerical control positioning system.Numerical control positioning system is by controlling servo electric jar 702 to act, to realize
Control to the loading force of termination 701 that exerts a force.
In actual use, force termination 701 is moved to the underface of the underface, such as measurement point A of measurement point, and A
The corresponding pressure of point is 2KN.Now, numerical control positioning system control servo electric jar 702 is acted, and is pressed to force termination 701
2KN pressure so that force termination 701 to measurement point A press 2KN pressure.
Further, the force application mechanism 7 of the present embodiment can also include pressure sensor 703, the pressure sensor 703
Electrically connected respectively with the numerical control positioning system, the force termination 701；The pressure sensor 703, for gathering described apply
The pressure applied of power termination 701, and give the numerical control positioning system by the pressure output.
Specifically, as shown in figure 3, setting a pressure sensor 703,703 points of the pressure sensor on force application mechanism 7
Do not electrically connected with numerical control positioning system and force termination 701, for gathering the pressure that force termination 701 is pressed to each measurement point
Value, and the pressure value collected is sent to numerical control positioning system so that numerical control positioning system realizes the reality to the termination 701 that exerts a force
The monitoring of border loading procedure.
Optionally, as shown in figure 3, the pressure sensor 703 of the present embodiment can be arranged on servo electric jar 702 just under
Side, pressure sensor 703 is arranged in mobile device 6.Optionally, pressure sensor 703 can also be arranged on other positions, this
Embodiment is not limited to the particular location of pressure sensor 703, as long as ensureing that the pressure value of force termination 701 can be gathered,
And the pressure value is passed into numerical control positioning system.
Optionally, as shown in figure 1, the deformation measuring device 1 of the present embodiment can be three coordinate measuring machine, three coordinate is surveyed
Amount machine includes measurement probe 101；The three coordinate measuring machine, for the force application mechanism 7 to the wing 5 apply pressure when,
According to the X of default multiple measurement points, Y-coordinate, to measure the Z coordinate value of each measurement point.
Optionally, the present embodiment can use the arm-type three coordinate measuring machine of automatic suspension.Inputted on three coordinate measuring machine
The X of one group of measurement point, Y-coordinate value, the three coordinate measuring machine can successively be measured to the Z coordinate of the measurement point of input.
The present embodiment may include steps of to the measurement process of the flexibility matrix of wing 5：
Wing 5 is fixed on model supporting device 2, N number of point to be measured and N number of loading point to be added, N are set on wing 5
Individual point to be measured is identical with the coordinate of N number of loading point to be added；
Input X, the Y-coordinate value of N number of point to be measured in the host computer of numerical control positioning system, and N number of loading point to be added is each
Self-corresponding pressure value, wherein N >=1；
Deformation measuring device 1 measures the initial Z coordinate value of N number of point to be measured, and is designated as Zi 0(i=1,2 ..., N)；
Numerical control positioning system control mobile device 6 is moved so that mobile device 6 drives the force accurate movement of termination 701 extremely
The underface of 1st loading point to be added；
It is the 1st loading point to be added that the control of force application mechanism 7 force termination 701 applies pressure value F1, F1 to the 1st loading point to be added
Corresponding pressure value；
Deformation measuring device 1 is measured successively to the Z coordinate of N number of point to be measured, and is designated as Zi1 0(i=1,2 ..., N)；
The numerical control positioning system control drive force of mobile device 6 termination 701 is moved to the underface of the 2nd loading point to be added,
And repeat the above steps, obtain when applying F2 pressure values to the 2nd loading point to be added, the Z coordinate value of N number of point to be measured is designated as
Zi2 0(i=1,2 ..., N)；
Repeat the above steps, when applying its corresponding pressure value at each loading point to be added, measure the Z of N number of point to be measured
Coordinate value；
According to the flexibility matrix of below equation Wings 5,
Cij=(Zij 0-Zi 0)/Fj(i=1,2 ..., N, j=1,2 ..., N)
Wherein, CijFor flexibility matrix, i represents ith measurement point, and j is expressed as j-th of load(ing) point, FjFor j-th of load(ing) point
Pressure value.
The utility model provide wing flexibility matrix measurement apparatus, by force application mechanism set force termination,
Servo electric jar and pressure sensor, make servo electric jar and force application mechanism institute are controlled according to the control command of numerical control positioning system
The pressure value of pressure, pressure sensor is used to gathering the pressure value that is pressed to measurement point of force termination, and by the pressure value of collection
Numerical control positioning system is sent to, monitoring of the numerical control positioning system to the termination actual loaded process that exerts a force is realized, and then improve machine
The automation of wing measurement apparatus and reliability.
The structural representation of the measurement apparatus example IV for the wing flexibility matrix that Fig. 4 provides for the utility model.Upper
State on the basis of embodiment, the workbench 3 of the present embodiment, its surface is provided with X to line slideway 301, the mobile device 6
Including moved along the first moving carriage 601 from the X to line slideway 301, be arranged on first moving carriage 601
Y-direction line slideway 602, the second moving carriage 603, Y-direction servomotor and the X moved along the Y-direction line slideway 602 are to watching
Take motor (not shown)；The X to servomotor respectively with first moving carriage 601 and the numerical control positioning system
Electrical connection, the Y-direction servomotor is electrically connected with second moving carriage 603 and the numerical control positioning system respectively, described
Servo electric jar 702 is fixedly installed on second moving carriage 603.
Specifically, as shown in figure 4, being provided with X on the surface of the workbench 3 of the present embodiment to line slideway 301, movement
Device 6 includes the first moving carriage 601, the second moving carriage 603 and Y-direction line slideway 602.Wherein, the first moving carriage 601
X is arranged on on line slideway 301, and can be moved along X to line slideway 301, Y-direction line slideway 602 is fixedly installed
On the first moving carriage 601, the second moving carriage 603 is arranged on Y-direction line slideway 602, and can be along Y-direction straight line
Guide rail 602 is moved, and force application mechanism 7 is fixedly installed on the second moving carriage 603.
The mobile device 6 of the present embodiment also includes X to servomotor and Y-direction servomotor, and wherein X distinguishes to servomotor
Be connected with the first moving carriage 601 and numerical control alignment system, for receive numerical control positioning system transmission on X to mobile control
System order, and controlled according to the control command the first moving carriage 601 to be moved in X on line slideway 301.Y-direction servo
Motor is connected with the second moving carriage 603 and numerical control alignment system respectively, for receive numerical control positioning system transmission on Y-direction
Mobile control command, and control according to the control command shifting of second moving carriage 603 on Y-direction line slideway 602
It is dynamic.And then, the force application mechanism 7 being fixed on the second moving carriage 603 is moved to the underface of measurement point.
The X of the present embodiment is to line slideway 301, Y-direction line slideway 602, the first moving carriage 601 and the second moving carriage
603 one two-dimentional mobile working platform system of composition.Wherein, the motion of the first moving carriage 601 and the second moving carriage 603
Completed by servomotor drive deceleration mechanism, rack pinion.Specifically, the rotation of servomotor is changed into shifting
The common knowledge moved horizontally as those skilled in the art of dynamic planker, will not be repeated here.
Further, the present embodiment also in X to being provided with X to displacement transducer (not shown) on line slideway 301,
Y-direction displacement transducer (not shown) is provided with Y-direction line slideway 602；The X to displacement transducer, the Y-direction position
Displacement sensor is electrically connected with the numerical control positioning system respectively；The X is to displacement transducer and the Y-direction displacement transducer,
Current location for measuring the force application mechanism 7, and the current location is exported to the numerical control positioning system.
The present embodiment, in X to X is provided with to displacement transducer on line slideway 301, is set on Y-direction line slideway 602
There is Y-direction displacement transducer, X is electrically connected to displacement transducer and Y-direction displacement transducer with numerical control positioning system.
Illustrate, it is assumed that the coordinate for the target measurement point A that user inputs in numerical control positioning system is (10,20).
During beginning, the current X-coordinate of force application mechanism 7 that X is gathered to displacement transducer is 5mm, the force that Y-direction displacement transducer is collected
The current Y-coordinate of mechanism 7 is 3mm, and Y=3 is sent to numerical control positioning system by X=5, Y-direction displacement transducer by X to displacement transducer
System.Numerical control positioning system according to target location (10,20), calculate obtain force application mechanism 7 need the positional distance of movement for (5,
17).Force application mechanism 7 is needed mobile distance (5,17) to be converted into control lives of the X to servomotor respectively by numerical control positioning system
Order and the control command of Y-direction servomotor.Then, the control command that X is sent to servomotor according to numerical control positioning system, drives
The positive mobile 5mm of first moving carriage 601, the control command that Y-direction servomotor is sent according to numerical control positioning system drives second
The positive mobile 17mm of moving carriage 603 so that force application mechanism 7 is moved to the underface of A points.Optionally, the X of the present embodiment is to position
Displacement sensor and Y-direction displacement transducer can gather the position coordinates of force application mechanism 7 in real time, and the position coordinates is sent into number
Control alignment system so that numerical control positioning system grasps the position of force application mechanism 7 in real time, and then realizes to the accurate of force application mechanism 7
Positioning.
Optionally, the X of the present embodiment to displacement transducer and Y-direction displacement transducer can be grating scale, i.e. in X to straight
X is posted on line guide rail 301 to grating scale, as X to displacement transducer.Y-direction grating scale is posted on Y-direction line slideway 602, is made
For Y-direction displacement transducer.Optionally, the X of the present embodiment can also be other structures to displacement transducer and Y-direction displacement transducer
Displacement transducer.
The measurement apparatus for the wing flexibility matrix that the utility model is provided, by setting X to be led to straight line on workbench
Rail, in X to transportable first moving carriage is set on line slideway, sets Y-direction line slideway on the first moving carriage,
Moveable second moving carriage, one two-dimentional mobile working platform system of said structure formation are set on Y-direction line slideway
System, wherein, force application mechanism is fixedly installed on the second moving carriage.Numerical control positioning system can be by controlling above-mentioned two-dimentional shifting
Dynamic Work platform system controls the force application mechanism to be moved to the underface of measurement point.
The structural representation of the measurement apparatus embodiment five for the wing flexibility matrix that Fig. 5 provides for the utility model.Upper
On the basis of stating embodiment, as shown in figure 5, the numerical control positioning system 80 of the present embodiment can include receiving host computer 8 and bottom
Machine 9；The host computer 8 is electrically connected with the slave computer 9, and the slave computer 9 is respectively with the X to displacement transducer, the Y-direction
Displacement transducer, the X are to servomotor, the Y-direction servomotor, the servo electric jar 702 and the pressure sensor
703 electrically connect.
As shown in figure 5, the numerical control positioning system 80 of the present embodiment includes host computer 8 and slave computer 9, host computer 8 is used to connect
User's input is received, and control command is issued to slave computer 9.There is the host computer 8 of the present embodiment the XY with deformation measuring device 1 to sit
Mark system calibration function, the display function of XY coordinates and pressure value, setting function, the pressure value error correction of measurement point and pressure value
The function such as function and XY spatial error corrections.
As shown in figure 5, the slave computer 9 of the present embodiment can include：XY coordinates acquisition module 901, controller 902 and servo
Motor drive module 903, force acquisition module 904 and communication module 905.Wherein, XY coordinates acquisition module 901 respectively with X to
Displacement transducer, Y-direction displacement transducer and controller 902 are electrically connected, and servomotor drive module 903 is electric to servo with X respectively
Machine, Y-direction servomotor, servo electric jar 702 and controller 902 are electrically connected, controller 902 by communication module 905 with it is upper
Machine 8 is connected.
XY coordinates acquisition module 901 obtains working as the termination 701 that exerts a force by X to displacement transducer and Y-direction displacement transducer
Front position coordinate, and the current position coordinates for the termination 701 that exerts a force are sent to controller 902.Controller 902 is according to force termination
The target measurement point coordinates that 701 current position coordinates and host computer 8 are sent by communication module 905, obtains force termination
701 X is sent to servomotor driving to moving displacement and Y-direction moving displacement, and by X to moving displacement and Y-direction moving displacement
Module 903.Servomotor drive module 903 drives X to servomotor according to X to moving displacement, is driven according to Y-direction moving displacement
Y-direction servomotor, so that force termination 701 is moved at target measurement coordinate.
Force acquisition module 904 is electrically connected with pressure sensor 703 and controller 902 respectively, the force acquisition module 904
For being powered for pressure sensor 703, the measurement signal to pressure sensor 703 is amplified and digitized, and is digitized
Measured pressure value, and measured pressure value is sent to controller 902.Controller 902 is pressed the measurement by communication module 905
Force value is sent to host computer 8, so that the host computer 8 is shown.
The servomotor drive module 903 of the present embodiment completes the control of the electric current loop, speed ring of servomotor, makes to be driven
Dynamic object at a high speed, high-precision positioning.
The measurement apparatus for the wing flexibility matrix that the utility model is provided, by setting host computer in numerical control positioning system
And slave computer, the host computer is used to receiving the control command of user, and the control command is sent into slave computer, slave computer according to
The control command controls the action of mobile device and force application mechanism.The measurement apparatus of the present embodiment, control command is simple, upper
X, the Y-coordinate value of point to be measured are inputted on the machine of position, force termination can be accurate to up to above-mentioned X, Y-coordinate position, on host computer
The pressure value that each loading point to be added needs to load is inputted, force termination can treat load(ing) point and accurately exert a force.
Finally it should be noted that：Various embodiments above is only limited to illustrate the technical solution of the utility model, rather than to it
System；Although the utility model is described in detail with reference to foregoing embodiments, one of ordinary skill in the art should
Understand：It can still modify to the technical scheme described in foregoing embodiments, or to which part or whole
Technical characteristic carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from this practicality newly
The scope of each embodiment technical scheme of type.
Claims (9)
1. a kind of measurement apparatus of wing flexibility matrix, it is characterised in that including：Deformation measuring device, model supporting device, work
Make platform, mobile device, force application mechanism and numerical control alignment system, the mobile device is arranged on the workbench, described
Force application mechanism is arranged in the mobile device, the numerical control positioning system respectively with the mobile device and the force application mechanism
Electrical connection；
The model supporting device is fixed on the end of the workbench, for fixing the wing；
The numerical control positioning system, for controlling the mobile device to be moved on the workbench, so that the mobile dress
The drive force application mechanism movement is put, and, for controlling diverse location application pressure of the force application mechanism to the wing；
The deformation measuring device is fixedly installed at the position of the workbench, for measuring the wing described
Deflection under force application mechanism pressure applied.
2. measurement apparatus according to claim 1, it is characterised in that the model supporting device includes side plate and is arranged on
Groove on the surface of side plate；
The side plate is fixedly installed on the end of the workbench, and the wing is fixedly installed on the predeterminated position of the groove
Place.
3. measurement apparatus according to claim 2, it is characterised in that the force application mechanism includes force termination and servo electricity
Dynamic cylinder, the force termination is arranged on the top of the servo electric jar, the servo electric jar and the numerical control positioning system
Electrical connection.
4. measurement apparatus according to claim 3, it is characterised in that the force application mechanism also includes：Pressure sensor, institute
Pressure sensor is stated to electrically connect with the numerical control positioning system, the force termination respectively；
The pressure sensor, the number is given for gathering force termination pressure applied, and by the pressure output
Control alignment system.
5. measurement apparatus according to claim 4, it is characterised in that the surface of the workbench is provided with X to straight line
Guide rail, the first moving carriage that the mobile device includes moving along from the X to line slideway, is arranged on described first and moves
Y-direction line slideway, the second moving carriage moved along the Y-direction line slideway, X on planker are watched to servomotor and Y-direction
Take motor；
The X is connected with first moving carriage and the numerical control positioning system respectively to servomotor, the Y-direction servo electricity
Machine is connected with second moving carriage and the numerical control positioning system respectively, and the servo electric jar is fixedly installed on described
On two moving carriages.
6. measurement apparatus according to claim 5, the X is to being provided with X to displacement transducer on line slideway, the Y
Y-direction displacement transducer is provided with to line slideway；
The X is electrically connected with the numerical control positioning system respectively to displacement transducer, the Y-direction displacement transducer；
The X is used to measure the current location of the force application mechanism to displacement transducer and the Y-direction displacement transducer, and
The current location is exported to the numerical control positioning system.
7. measurement apparatus according to claim 6, it is characterised in that the numerical control positioning system includes host computer and bottom
Machine；
The host computer and the next mechatronics, the slave computer is respectively with the X to displacement transducer, Y-direction position
Displacement sensor, the X are to servomotor, the Y-direction servomotor, the servo electric jar and the pressure sensor Electricity Federation
Connect.
8. measurement apparatus according to claim 1, it is characterised in that the deformation measuring device is three coordinate measuring machine,
The three coordinate measuring machine includes measurement probe；
The three coordinate measuring machine, for when the force application mechanism applies pressure to the wing, according to default multiple surveys
X, the Y-coordinate of point are measured, the Z coordinate value of each measurement point is measured.
9. measurement apparatus according to claim 6, it is characterised in that the X is passed to displacement transducer and the Y-direction displacement
Sensor is grating scale.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621280671.9U CN206399626U (en) | 2016-11-28 | 2016-11-28 | The measurement apparatus of wing flexibility matrix |
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| CN201621280671.9U CN206399626U (en) | 2016-11-28 | 2016-11-28 | The measurement apparatus of wing flexibility matrix |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114701659A (en) * | 2022-04-02 | 2022-07-05 | 航天特种材料及工艺技术研究所 | Characterization testing device and method for small-load bending and torsion deformation of composite material airfoil |
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2016
- 2016-11-28 CN CN201621280671.9U patent/CN206399626U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114701659A (en) * | 2022-04-02 | 2022-07-05 | 航天特种材料及工艺技术研究所 | Characterization testing device and method for small-load bending and torsion deformation of composite material airfoil |
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