CN103940604B - Computer program controlled formula aircraft static loading test device and method - Google Patents
Computer program controlled formula aircraft static loading test device and method Download PDFInfo
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- CN103940604B CN103940604B CN201410191096.4A CN201410191096A CN103940604B CN 103940604 B CN103940604 B CN 103940604B CN 201410191096 A CN201410191096 A CN 201410191096A CN 103940604 B CN103940604 B CN 103940604B
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Abstract
Computer program controlled formula aircraft static loading test device and method, belongs to aircraft test field, and the present invention solves the problem that existing aircraft slow test is not suitable for the test of high-precision small-sized force-bearing exemplar.The present invention program: the stiff end of the upper end clamping part clamping test pieces of packaged type clamping apparatus, the base upper surface of packaged type clamping apparatus is provided with xy spindle motor flat guide, is provided with laser displacement sensor in the end of xy spindle motor flat guide below the free end being positioned at test specimen; Foil gauge is pasted in surface of test piece; Host computer issues static loading instruction by single-chip microcomputer; Loading unit carries out static loading to test specimen; Foil gauge gathers the strain information of test specimen; Laser displacement sensor gathers the displacement information of test specimen free end; Digital speckle scanner gathers the stress information of test specimen; And return host computer by single-chip microcomputer.
Description
Technical field
The present invention relates to a kind of static loading test, belong to aircraft test field.
Background technology
The slow test test of aircraft is requisite part in Flight Vehicle Design process.At the test phase of aircraft, need to carry out strength and stiffness check to aircraft parts.The present stage static trial of aircraft is all manually arrange experimental facilities, charger both bulk and long in experimental period, needs to spend a large amount of manpower to debug in detail, repeatedly check, thus with high costs.Simultaneously the error of large-scale load test is comparatively large, is unfavorable for the test of the high-precision small-sized force-bearing exemplar of requirement, and device can recycling rate of waterused low, cause and greatly waste.A set of new-type test examining system is provided to be very necessary.
Summary of the invention
The present invention seeks to the problem not being suitable for the test of high-precision small-sized force-bearing exemplar in order to solve existing aircraft slow test, providing a kind of computer program controlled formula aircraft static loading test device and method.
Computer program controlled formula aircraft static loading test device of the present invention, it comprises packaged type clamping apparatus, xy spindle motor flat guide, multiple loading unit, foil gauge, laser displacement sensor, digital speckle scanner, data acquisition circuit, single-chip microcomputer and host computer;
The stiff end of the upper end clamping part clamping test pieces of packaged type clamping apparatus, the base upper surface of packaged type clamping apparatus is provided with xy spindle motor flat guide, is provided with laser displacement sensor in the end of xy spindle motor flat guide below the free end being positioned at test specimen; Foil gauge is pasted in surface of test piece;
The static loading instruction output end of host computer is connected with the static loading command input of single-chip microcomputer;
The static loading instruction output end of single-chip microcomputer is connected with the input end of each loading unit;
Loading unit carries out static loading to test specimen;
Foil gauge gathers the strain information of test specimen; Laser displacement sensor gathers the displacement information of test specimen free end; Digital speckle scanner gathers the stress information of test specimen; The strain information of described test specimen, the displacement information of test specimen free end and the stress information of test specimen return to single-chip microcomputer by data acquisition circuit, and the image data output terminal of single-chip microcomputer is connected with the image data input end of host computer.
Loading unit comprises x-axis motor, y-axis motor, x-axis dial sensor, y-axis dial sensor, loading frame, cylinder, motor drive module, solenoid valve and automatically controlled pressure regulator valve;
The below of loading frame is fixedly installed x-axis motor and y-axis motor, x-axis motor is provided with x-axis dial sensor; Y-axis motor is provided with y-axis dial sensor;
Be provided with cylinder above loading frame, cylinder outlet pipe be provided with solenoid valve and automatically controlled pressure regulator valve, cylinder induced effect bar loads acting force to test specimen;
The position load instructions output terminal of single-chip microcomputer is connected with the input end of motor drive module;
The x-axis position command output terminal of motor drive module is connected with the Enable Pin of x-axis motor; The rotating cycle of x-axis dial sensor metering x-axis motor;
The y-axis position command output terminal of motor drive module is connected with the Enable Pin of y-axis motor; The rotating cycle of y-axis dial sensor metering y-axis motor;
The switching cylinder instruction output end of single-chip microcomputer is connected with the Enable Pin of solenoid valve;
The cylinder pressure instruction output end of single-chip microcomputer is connected with the Enable Pin of automatically controlled pressure regulator valve.
Method based on described computer program controlled formula aircraft static loading test device comprises the following steps:
Step one, according to the quantity of aerodynamic loading determination loading unit of test specimen, the size of the loaded load of each loading unit and position;
The each loading unit of step 2, PC control moves to assigned address;
Step 3, host computer arrange the aperture of the automatically controlled pressure regulator valve of the loading unit of all participation work, and then, the solenoid valve of the loading unit of all participation work of PC control is opened simultaneously, make the cylinder induced effect bar of loading unit load acting force to test specimen;
Step 4, foil gauge gather the strain information of test specimen; Laser displacement sensor gathers test specimen free end displacement information; Digital speckle scanner scanning test specimen, by the surface impacted, gathers the stress information of test specimen; The strain information of described test specimen, the displacement information of test specimen free end and the stress information of test specimen return to single-chip microcomputer by data acquisition circuit;
The strain information of step 5, test specimen, stress information and free end displacement information return to host computer, as the foundation that test piece intensity judges, complete static loading test.
Advantage of the present invention:
1, dirigibility, native system is made up of modular test framework and dismountable charger, can assemble according to the size requirement of test exemplar temporarily;
2, automaticity is high, and this cover system according to the Test Information of input, can complete the work such as experiment loading, data acquisition according to setting program full automation;
3, economy, a complete set of system by single complete operation, can complete experimental duties while saving human cost efficiently;
4, accuracy, a complete set of automated experiment equipment, can get rid of the error that human factor is brought, and the testing inspection sensing equipment installed additional can Real-time Feedback test situation, can give the alarm when exceeding warning value.
Accompanying drawing explanation
Fig. 1 is the structural representation of computer program controlled formula aircraft static loading test device of the present invention;
Fig. 2 is the control principle block diagram of computer program controlled formula aircraft static loading test device of the present invention;
Fig. 3 is the structural representation of xy spindle motor flat guide 2;
Fig. 4 is the structural representation of loading unit;
Fig. 5 is the control principle block diagram of loading unit.
Embodiment
Embodiment one: present embodiment is described below in conjunction with Fig. 1 and Fig. 2, computer program controlled formula aircraft static loading test device described in present embodiment, it comprises packaged type clamping apparatus 1, xy spindle motor flat guide 2, multiple loading unit 3, foil gauge 5, laser displacement sensor 6, digital speckle scanner 7, data acquisition circuit 8, single-chip microcomputer 9 and host computer 10;
The stiff end of the upper end clamping part clamping test pieces 4 of packaged type clamping apparatus 1, the base upper surface of packaged type clamping apparatus 1 is provided with xy spindle motor flat guide 2, is provided with laser displacement sensor 6 in the end of xy spindle motor flat guide 2 below the free end being positioned at test specimen 4; Foil gauge 5 is pasted on test specimen 4 surface;
The static loading instruction output end of host computer 10 is connected with the static loading command input of single-chip microcomputer 9;
The static loading instruction output end of single-chip microcomputer 9 is connected with the input end of each loading unit 3;
Loading unit 3 pairs of test specimens 4 carry out static loading;
Foil gauge 5 gathers the strain information of test specimen 4; Laser displacement sensor 6 gathers the displacement information of test specimen 4 free end; Digital speckle scanner 7 gathers the stress information of test specimen 4; The strain information of described test specimen 4, the displacement information of test specimen 4 free end and the stress information of test specimen 4 return to single-chip microcomputer 9 by data acquisition circuit 8, and the image data output terminal of single-chip microcomputer 9 is connected with the image data input end of host computer 10.
Embodiment two: present embodiment is described below in conjunction with Fig. 3, present embodiment is described further embodiment one, xy spindle motor flat guide 2 is made up of an x-axis guide rail 201 and n bar y-axis guide rail, every bar y-axis guide rail is made up of+y-axis guide rail 202 and-203 two sections, y-axis guide rail, and n is positive integer.
Y-axis guide rail is demountable structure.
Position and the quantity of y-axis guide rail are adjustable, reinstall after dismounting again, can change the position of intersecting point of y-axis and x-axis.Motor is first advanced on x-axis guide rail 201, arrives after specifying x coordinate, then goes to y-axis guide rail, as specified y coordinate to be just, then goes to+y-axis guide rail 202, as specified y coordinate to be negative, then goes to-y-axis guide rail 203.This experimental provision is flexible.
Embodiment three: present embodiment is described below in conjunction with Fig. 4 and Fig. 5, present embodiment is described further embodiment one, and loading unit 3 comprises x-axis motor 301, y-axis motor 302, x-axis dial sensor 303, y-axis dial sensor 304, loading frame 305, cylinder 306, motor drive module 307, solenoid valve 308 and automatically controlled pressure regulator valve 309;
The below of loading frame 305 is fixedly installed x-axis motor 301 and y-axis motor 302, x-axis motor 301 is provided with x-axis dial sensor 303; Y-axis motor 302 is provided with y-axis dial sensor 304;
Be provided with cylinder 306 above loading frame 305, cylinder 306 outlet pipe be provided with solenoid valve 308 and automatically controlled pressure regulator valve 309, cylinder 306 induced effect bar 3061 loads acting force to test specimen 4;
The position load instructions output terminal of single-chip microcomputer 9 is connected with the input end of motor drive module 307;
The x-axis position command output terminal of motor drive module 307 is connected with the Enable Pin of x-axis motor 301; X-axis dial sensor 303 measures the rotating cycle of x-axis motor 301;
The y-axis position command output terminal of motor drive module 307 is connected with the Enable Pin of y-axis motor 302; Y-axis dial sensor 304 measures the rotating cycle of y-axis motor 302;
The switching cylinder instruction output end of single-chip microcomputer 9 is connected with the Enable Pin of solenoid valve 308;
The cylinder pressure instruction output end of single-chip microcomputer 9 is connected with the Enable Pin of automatically controlled pressure regulator valve 309.
Embodiment four: present embodiment is described below in conjunction with Fig. 1 to Fig. 5, based on the method for formula aircraft static loading test device computer program controlled described in embodiment three, the method comprises the following steps:
Step one, according to the quantity of aerodynamic loading determination loading unit 3 of test specimen 4, the size of the loaded load of each loading unit 3 and position;
Step 2, host computer 10 control each loading unit 3 and move to assigned address;
Step 3, host computer 10 arrange the aperture of the automatically controlled pressure regulator valve 309 of the loading unit 3 of all participation work, then, the solenoid valve 308 that host computer 10 controls the loading unit 3 of all participation work is opened simultaneously, makes the cylinder 306 induced effect bar 3061 of loading unit 3 load acting force to test specimen 4;
Step 4, foil gauge 5 gather the strain information of test specimen 4; Laser displacement sensor 6 gathers test specimen 4 free end displacement information; Digital speckle scanner 7 scans test specimen 4 by the surface impacted, and gathers the stress information of test specimen 4; The strain information of described test specimen 4, the displacement information of test specimen 4 free end and the stress information of test specimen 4 return to single-chip microcomputer 9 by data acquisition circuit 8;
The strain information of step 5, test specimen 4, stress information and free end displacement information return to host computer 10, as the foundation that test specimen semi-finals degree judges, complete static loading test.
In step one, the quantity of the aerodynamic loading of test specimen 4 is very huge, and do static loading test, the load quantity loaded is limited, be generally 8-20, therefore, need the aerodynamic loading of test specimen 4 to carry out equivalent-simplification process, those skilled in the art adopt node shifting method and equivalent point converter technique usually.Known, the quantity of the participation work of loading unit 3 is 8 ~ 20, after completing process, namely determines position and the loaded load size of each loading unit 3 of participation work.
Embodiment five: present embodiment is described further embodiment four, in step 2, host computer 10 controls the process that each loading unit 3 moves to assigned address and is:
Host computer 10 assigns position command to single-chip microcomputer 9, and described position command comprises x coordinate and y coordinate, and single-chip microcomputer 9 drives x-axis motor 301 to work by motor drive module 307, drives the cylinder 306 of this loading unit 3 on x-axis guide rail 201, move to the x coordinate of specifying; The displacement that x-axis motor 301 is advanced is measured by x-axis dial sensor 303;
Stop driving x-axis motor 301, drive y-axis motor 302 to work, make y-axis motor 302 drive the cylinder 306 of this loading unit 3 on y-axis guide rail, move to the y coordinate of specifying, the displacement that y-axis motor 302 is advanced is measured by y-axis dial sensor 304 simultaneously.
Claims (5)
1. computer program controlled formula aircraft static loading test device, it is characterized in that, it comprises packaged type clamping apparatus (1), xy spindle motor flat guide (2), multiple loading unit (3), foil gauge (5), laser displacement sensor (6), digital speckle scanner (7), data acquisition circuit (8), single-chip microcomputer (9) and host computer (10);
The stiff end of upper end clamping part clamping test pieces (4) of packaged type clamping apparatus (1), the base upper surface of packaged type clamping apparatus (1) is provided with xy spindle motor flat guide (2), is provided with laser displacement sensor (6) in the end of xy spindle motor flat guide (2) below the free end being positioned at test specimen (4); Foil gauge (5) is pasted on test specimen (4) surface;
The static loading instruction output end of host computer (10) is connected with the static loading command input of single-chip microcomputer (9);
The static loading instruction output end of single-chip microcomputer (9) is connected with the input end of each loading unit (3);
Loading unit (3) carries out static loading to test specimen (4);
Foil gauge (5) gathers the strain information of test specimen (4); Laser displacement sensor (6) gathers the displacement information of test specimen (4) free end; Digital speckle scanner (7) gathers the stress information of test specimen (4); The stress information of the strain information of described test specimen (4), the displacement information of test specimen (4) free end and test specimen (4) returns to single-chip microcomputer (9) by data acquisition circuit (8), the image data output terminal of single-chip microcomputer (9) is connected with the image data input end of host computer (10)
Loading unit (3) comprises x-axis motor (301), y-axis motor (302), x-axis dial sensor (303), y-axis dial sensor (304), loading frame (305), cylinder (306), motor drive module (307), solenoid valve (308) and automatically controlled pressure regulator valve (309);
The below of loading frame (305) is fixedly installed x-axis motor (301) and y-axis motor (302), x-axis motor (301) is provided with x-axis dial sensor (303); Y-axis motor (302) is provided with y-axis dial sensor (304);
Loading frame (305) top is provided with cylinder (306), cylinder (306) outlet pipe is provided with solenoid valve (308) and automatically controlled pressure regulator valve (309), and cylinder (306) induced effect bar (3061) loads acting force to test specimen (4);
The position load instructions output terminal of single-chip microcomputer (9) is connected with the input end of motor drive module (307);
The x-axis position command output terminal of motor drive module (307) is connected with the Enable Pin of x-axis motor (301); The rotating cycle of x-axis dial sensor (303) metering x-axis motor (301);
The y-axis position command output terminal of motor drive module (307) is connected with the Enable Pin of y-axis motor (302); The rotating cycle of y-axis dial sensor (304) metering y-axis motor (302);
The switching cylinder instruction output end of single-chip microcomputer (9) is connected with the Enable Pin of solenoid valve (308);
The cylinder pressure instruction output end of single-chip microcomputer (9) is connected with the Enable Pin of automatically controlled pressure regulator valve (309).
2. computer program controlled formula aircraft static loading test device according to claim 1, it is characterized in that, xy spindle motor flat guide (2) is made up of an x-axis guide rail (201) and n bar y-axis guide rail, every bar y-axis guide rail is made up of+y-axis guide rail (202) and-(203) two sections, y-axis guide rail, and n is positive integer.
3. computer program controlled formula aircraft static loading test device according to claim 2, it is characterized in that, y-axis guide rail is demountable structure.
4., based on the method for formula aircraft static loading test device computer program controlled described in claim 1, it is characterized in that, the method comprises the following steps:
Step one, according to the size of the quantity of the aerodynamic loading determination loading unit (3) of test specimen (4), the loaded load of each loading unit (3) and position;
Step 2, host computer (10) control each loading unit (3) and move to assigned address;
Step 3, host computer (10) arrange the aperture of the automatically controlled pressure regulator valve (309) of the loading unit (3) of all participation work, then, the solenoid valve (308) that host computer (10) controls the loading unit (3) of all participation work is opened simultaneously, makes cylinder (306) the induced effect bar (3061) of loading unit (3) load acting force to test specimen (4);
Step 4, foil gauge (5) gather the strain information of test specimen (4); Laser displacement sensor (6) gathers test specimen (4) free end displacement information; Digital speckle scanner (7) scanning test specimen (4), by the surface impacted, gathers the stress information of test specimen (4); The stress information of the strain information of described test specimen (4), the displacement information of test specimen (4) free end and test specimen (4) returns to single-chip microcomputer (9) by data acquisition circuit (8);
The strain information of step 5, test specimen (4), stress information and free end displacement information return to host computer (10), as the foundation that test specimen (4) intensity judges, complete static loading test.
5. the method for computer program controlled formula aircraft static loading test device according to claim 4, is characterized in that, in step 2, host computer (10) controls the process that each loading unit (3) moves to assigned address and is:
Host computer (10) assigns position command to single-chip microcomputer (9), described position command comprises x coordinate and y coordinate, single-chip microcomputer (9) drives x-axis motor (301) work by motor drive module (307), drives the cylinder of this loading unit (3) (306) on x-axis guide rail (201), move to the x coordinate of specifying; The displacement that x-axis motor (301) is advanced is measured by x-axis dial sensor (303);
Stop driving x-axis motor (301), drive y-axis motor (302) work simultaneously, make y-axis motor (302) drive the cylinder of this loading unit (3) (306) on y-axis guide rail, move to the y coordinate of specifying, the displacement that y-axis motor (302) is advanced is measured by y-axis dial sensor (304).
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106500952A (en) * | 2016-11-28 | 2017-03-15 | 中国空气动力研究与发展中心高速空气动力研究所 | The measurement apparatus of wing flexibility matrix |
| CN107167329B (en) * | 2017-06-07 | 2020-03-03 | 北京航空航天大学 | Aerodynamic loading test device for control surface of asymmetric aircraft |
| CN107264836B (en) * | 2017-07-28 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Cabin door large-range follow-up loading test device and test method |
| CN109372826B (en) * | 2018-12-13 | 2020-03-24 | 中国工程物理研究院化工材料研究所 | Linear continuous static force loading control method |
| CN110228603B (en) * | 2019-05-29 | 2022-11-18 | 陕西飞机工业（集团）有限公司 | Static test end frame for simulating aircraft air state |
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