CN103940604A - Computer programmed type aircraft static force loading test device and method - Google Patents
Computer programmed type aircraft static force loading test device and method Download PDFInfo
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- CN103940604A CN103940604A CN201410191096.4A CN201410191096A CN103940604A CN 103940604 A CN103940604 A CN 103940604A CN 201410191096 A CN201410191096 A CN 201410191096A CN 103940604 A CN103940604 A CN 103940604A
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Abstract
The invention provides a computer programmed type aircraft static force loading test device and a method, belongs to the field of aircraft testing and aims at solving the problem that an existing aircraft static force test is not suitable for a small high-precision bearing sample piece. The scheme is that the upper-end clamping portion of a movable clamping device clamps the fixed end of the sample piece, x-axis and y-axis motor plane guide rails are arranged on the upper surface of a base of the movable clamping device, and laser displacement sensors are arranged at the ends of the x-axis and y-axis motor plane guide rails and located under the suspended end of the sample piece. A strain gauge adheres to the surface of the sample piece. An upper computer issues a static force loading instruction through a single chip microcomputer. A loading portion can performs static force loading on the sample piece. The strain gauge acquires strain information of the sample piece. The laser displacement sensors acquire displacement information of the suspended end of the sample piece. A digital speckle scanner acquires stress information of the sample piece and returns the stress information to the upper computer through the 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 to arrange experimental facilities, and the huge heaviness of charger and long in experimental period need to spend a large amount of manpowers and debug in detail, repeatedly checks, thereby with high costs.Simultaneously the error of large-scale load test is larger, is unfavorable for the test of the high-precision small-sized force-bearing exemplar of requirement, and device is can recycling rate of waterused low, has caused greatly waste.It is very necessary that a set of new-type test examining system is provided.
Summary of the invention
The present invention seeks to not to be suitable in order to solve existing aircraft slow test the problem of the test of high-precision small-sized force-bearing exemplar, a kind of computer program controlled formula aircraft static loading test device and method is provided.
Computer program controlled formula aircraft static loading test device of the present invention, it comprises packaged type clamping apparatus, xy spindle motor flat guide, a plurality of loading portion, 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, in the end of xy spindle motor flat guide and below being positioned at the free end of test specimen, is provided with laser displacement sensor; Foil gauge is pasted on test specimen surface;
The static loading instruction output end of host computer is connected with the static loading instruction input end of single-chip microcomputer;
The static loading instruction output end of single-chip microcomputer is connected with the input end of each loading portion;
Loading portion 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 displacement information of the strain information of described test specimen, 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 portion comprises x spindle motor, y spindle motor, x axle dial sensor, y axle 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 spindle motor and y spindle motor, is provided with x axle dial sensor on x spindle motor; On y spindle motor, be provided with y axle dial sensor;
Loading frame top is provided with cylinder, is provided with solenoid valve and automatically controlled pressure regulator valve on cylinder outlet pipe, and 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 shaft position instruction output end of motor drive module is connected with the Enable Pin of x spindle motor; The rotating cycle of x axle dial sensor metering x spindle motor;
The y shaft position instruction output end of motor drive module is connected with the Enable Pin of y spindle motor; The rotating cycle of y axle dial sensor metering y spindle 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 1, according to the aerodynamic loading of test specimen, determine the quantity of loading portion, size and the position of the loaded load of each loading portion;
Step 2, each loading portion of PC control move to assigned address;
Step 3, host computer arrange the aperture of automatically controlled pressure regulator valve of the loading portion of all participation work, and then, the solenoid valve of the loading portion of all participation work of PC control is opened simultaneously, makes the cylinder induced effect bar of loading portion 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; The surface that digital speckle scanner scanning test specimen is impacted, the stress information of collection test specimen; The displacement information of the strain information of described test specimen, 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, and the foundation as the judgement of test specimen intensity, completes static loading test.
Advantage of the present invention:
1, dirigibility, native system is comprised 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 can, according to the Test Information of input, complete the work such as experiment loading, data acquisition according to setting program full automation;
3, economy, a complete set of system can, by single complete operation, can complete experimental duties when 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 test installed additional detects sensing equipment can Real-time Feedback test situation, while exceeding warning value, can give the alarm.
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 portion;
Fig. 5 is the control principle block diagram of loading portion.
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, a plurality of loading portion 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, in the end of xy spindle motor flat guide 2 and below being positioned at the free end of test specimen 4, is provided with laser displacement sensor 6; Foil gauge 5 is pasted on test specimen 4 surfaces;
The static loading instruction output end of host computer 10 is connected with the static loading instruction input end 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 portion 3;
3 pairs of test specimens of loading portion 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 ends; Digital speckle scanner 7 gathers the stress information of test specimen 4; The displacement information of the strain information of described test specimen 4, test specimen 4 free ends 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 consists of an x axis rail 201 and n bar y axis rail, every y axis rail by+y axis rail 202 and-203 two sections of y axis rails form, n is positive integer.
Y axis rail is demountable structure.
Position and the quantity of y axis rail are adjustable, after dismounting, reinstall again, can change the position of intersecting point of y axle and x axle.Motor is first advanced on x axis rail 201, and arrive and specify after x coordinate, then go to y axis rail, as specified y coordinate for just, go to+y axis rail 202, as specified y coordinate for bearing, go to-y axis 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 portion 3 comprises x spindle motor 301, y spindle motor 302, x axle dial sensor 303, y axle 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 spindle motor 301 and y spindle motor 302, is provided with x axle dial sensor 303 on x spindle motor 301; On y spindle motor 302, be provided with y axle dial sensor 304;
Loading frame 305 tops are provided with cylinder 306, are provided with solenoid valve 308 and automatically controlled pressure regulator valve 309 on cylinder 306 outlet pipes, and cylinder 306 induced effect bars 3061 load 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 shaft position instruction output end of motor drive module 307 is connected with the Enable Pin of x spindle motor 301; The rotating cycle of x axle dial sensor 303 metering x spindle motors 301;
The y shaft position instruction output end of motor drive module 307 is connected with the Enable Pin of y spindle motor 302; The rotating cycle of y axle dial sensor 304 metering y spindle motors 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: below in conjunction with Fig. 1 to Fig. 5, present embodiment is described, the method based on computer program controlled formula aircraft static loading test device described in embodiment three, the method comprises the following steps:
Step 1, according to the aerodynamic loading of test specimen 4, determine the quantity of loading portion 3, size and the position of the loaded load of each loading portion 3;
Step 2, host computer 10 are controlled each loading portion 3 and are moved to assigned address;
Step 3, host computer 10 arrange the aperture of automatically controlled pressure regulator valve 309 of the loading portion 3 of all participation work, then, the solenoid valve 308 that host computer 10 is controlled the loading portion 3 of all participation work is opened simultaneously, makes the cylinder 306 induced effect bars 3061 of loading portion 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 informations; The surface that digital speckle scanner 7 scanning test specimens 4 are impacted, the stress information of collection test specimen 4; The displacement information of the strain information of described test specimen 4, test specimen 4 free ends 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, and the foundation as the judgement of test specimen semi-finals degree, completes static loading test.
In step 1, the quantity of the aerodynamic loading of test specimen 4 is very huge, and do static loading test, the load quantity loading is limited, be generally 8-20, therefore, the aerodynamic loading of test specimen 4 need to be carried out to equivalent-simplification processing, those skilled in the art adopt node translation method and equivalent point converter technique to complete conventionally.Known, the quantity of the participation work of loading portion 3 is 8～20, completes after processing, has determined position and the loaded load size of each loading portion 3 of the work that participates in.
Embodiment five: present embodiment is described further embodiment four, in step 2, host computer 10 is controlled the process that each loading portion 3 moves to assigned address and is:
Host computer 10 is assigned position command to single-chip microcomputer 9, and described position command comprises x coordinate and y coordinate, and single-chip microcomputer 9 drives 301 work of x spindle motors by motor drive module 307, drives the cylinder 306 of this loading portion 3 on x axis rail 201, to move to the x coordinate of appointment; The displacement that x spindle motor 301 is advanced is by 303 meterings of x axle dial sensor;
Stop driving x spindle motor 301, drive 302 work of y spindle motor simultaneously, make y spindle motor 302 drive the cylinder 306 of this loading portion 3 on y axis rail, to move to the y coordinate of appointment, the displacement that y spindle motor 302 is advanced is by 304 meterings of y axle dial sensor.
Claims (6)
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), a plurality of loading portions (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), in the end of xy spindle motor flat guide (2) and the free end below that is positioned at test specimen (4) be provided with laser displacement sensor (6); 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 instruction input end 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 portion (3);
Loading portion (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 displacement information of the strain information of described test specimen (4), 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).
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) consists of an x axis rail (201) and n bar y axis rail, every y axis rail by+y axis rail (202) and-(203) two sections of formations of y axis rail, n is positive integer.
3. computer program controlled formula aircraft static loading test device according to claim 2, is characterized in that, y axis rail is demountable structure.
4. computer program controlled formula aircraft static loading test device according to claim 1, it is characterized in that, loading portion (3) comprises x spindle motor (301), y spindle motor (302), x axle dial sensor (303), y axle 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 spindle motor (301) and y spindle motor (302), is provided with x axle dial sensor (303) on x spindle motor (301); On y spindle motor (302), be provided with y axle dial sensor (304);
Loading frame (305) top is provided with cylinder (306), on 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 shaft position instruction output end of motor drive module (307) is connected with the Enable Pin of x spindle motor (301); The rotating cycle of x axle dial sensor (303) metering x spindle motor (301);
The y shaft position instruction output end of motor drive module (307) is connected with the Enable Pin of y spindle motor (302); The rotating cycle of y axle dial sensor (304) metering y spindle 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).
5. the method based on computer program controlled formula aircraft static loading test device described in claim 4, is characterized in that, the method comprises the following steps:
Step 1, according to the aerodynamic loading of test specimen (4), determine the quantity of loading portion (3), size and the position of the loaded load of each loading portion (3);
Step 2, host computer (10) are controlled each loading portion (3) and are moved to assigned address;
Step 3, host computer (10) arrange the aperture of automatically controlled pressure regulator valve (309) of the loading portion (3) of all participation work, then, host computer (10) is controlled the solenoid valve (308) of the loading portion (3) of all participation work and is opened simultaneously, makes cylinder (306) the induced effect bar (3061) of loading portion (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; The surface that digital speckle scanner (7) scanning test specimen (4) is impacted, the stress information of collection test specimen (4); The displacement information of the strain information of described test specimen (4), 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), and the foundation as the judgement of test specimen (4) intensity, completes static loading test.
6. computer program controlled formula aircraft static loading test method according to claim 5, is characterized in that, host computer in step 2 (10) is controlled the process that each loading portion (3) moves to assigned address and is:
Host computer (10) is assigned position command to single-chip microcomputer (9), described position command comprises x coordinate and y coordinate, single-chip microcomputer (9) drives x spindle motor (301) work by motor drive module (307), drives the cylinder (306) of this loading portion (3) on x axis rail (201), to move to the x coordinate of appointment; The displacement that x spindle motor (301) is advanced is measured by x axle dial sensor (303);
Stop driving x spindle motor (301), drive y spindle motor (302) work simultaneously, make y spindle motor (302) drive the cylinder (306) of this loading portion (3) on y axis rail, to move to the y coordinate of appointment, the displacement that y spindle motor (302) is advanced is measured by y axle dial sensor (304).
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| CN201410191096.4A CN103940604B (en) | 2014-05-07 | 2014-05-07 | Computer program controlled formula aircraft static loading test device and method |
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| CN201410191096.4A CN103940604B (en) | 2014-05-07 | 2014-05-07 | Computer program controlled formula aircraft static loading test device and method |
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Cited By (5)
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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 |
| CN107167329A (en) * | 2017-06-07 | 2017-09-15 | 北京航空航天大学 | A kind of air force load testing machine of unsymmetrical flight device rudder face |
| CN107264836A (en) * | 2017-07-28 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | The a wide range of following loading experimental rig of hatch door and test method |
| CN109372826A (en) * | 2018-12-13 | 2019-02-22 | 中国工程物理研究院化工材料研究所 | A kind of linear continuous static loading control method |
| CN110228603A (en) * | 2019-05-29 | 2019-09-13 | 陕西飞机工业（集团）有限公司 | It is a kind of for simulating the slow test end frame of Aircraft Air state |
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| 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 |
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| CN110228603A (en) * | 2019-05-29 | 2019-09-13 | 陕西飞机工业（集团）有限公司 | It is a kind of for simulating the slow test end frame of Aircraft Air state |
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| CN103940604B (en) | 2016-03-16 |
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