CN113044244A - Strength test loading device and loading method - Google Patents
Strength test loading device and loading method Download PDFInfo
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- CN113044244A CN113044244A CN202110273618.5A CN202110273618A CN113044244A CN 113044244 A CN113044244 A CN 113044244A CN 202110273618 A CN202110273618 A CN 202110273618A CN 113044244 A CN113044244 A CN 113044244A
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- loading
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- power supply
- test piece
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- 238000011068 loading method Methods 0.000 title claims abstract description 129
- 238000012360 testing method Methods 0.000 title claims abstract description 73
- 239000011248 coating agent Substances 0.000 claims abstract description 7
- 238000000576 coating method Methods 0.000 claims abstract description 7
- 230000007246 mechanism Effects 0.000 claims description 16
- 210000003298 dental enamel Anatomy 0.000 claims 1
- 239000002966 varnish Substances 0.000 claims 1
- 230000006698 induction Effects 0.000 abstract description 9
- 239000004922 lacquer Substances 0.000 abstract 1
- 239000002390 adhesive tape Substances 0.000 description 10
- 239000003973 paint Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 239000002320 enamel (paints) Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model provides an intensity test loading device and loading method, loading device contain device body and power loading structure, its characterized in that, power loading structure contain a plurality of loading coils and a plurality of fixed joint, every loading coil passes through a fixed joint and connects on the device body, loading coil and programmable power supply, switch and computer control system signal of telecommunication be connected, when the loading is experimental, at the surface coating of testpiece one deck magnetic induction lacquer, through the electric current size and the direction of computer control system control power loading structure loading coil to control loading coil to the size and the direction of testpiece surface magnetic attraction, realize the non-contact atress loading on intensity testpiece surface.
Description
Technical Field
The invention belongs to the field of airplane strength tests, and particularly relates to a strength test loading device and a loading method.
Background
The force to be loaded in the airplane strength test is complex, and mainly comprises aerodynamic force, inertia force, thrust force and the like. The method commonly used at present is to stick an adhesive tape on an airplane, connect the adhesive tape with a hydraulic actuator cylinder through a pull rod, and pull the adhesive tape through a hydraulic system so as to stress an airplane test piece. The problems with this approach are: the surface area of the aircraft test piece is large, and each adhesive tape is used as an independent stress point to enable the simulation to be closer to the actual force, and the adhesive tape is divided into small parts to be adhered. The pasting workload is huge, and the requirement on the pasting reliability is high. Secondly, the adhesive tape is drawn by a hydraulic system. The aircraft surface area is big, and the rubberized tape quantity of pasting is huge, and hydraulic system starts the tractive, and there is certain time difference from the first rubberized tape atress to the last rubberized tape atress, and there is the deviation with the stress state in the aircraft true flight. The adhesive tape can only transmit positive tension, when negative pressure is needed, the adhesive tape needs to be pasted on the inner surface of the airplane, and the pressure on the surface of the airplane is achieved by stretching the adhesive tape on the inner surface of the airplane through a hydraulic system. The test equipment is complicated. Fourthly, the adhesive tape can only be used once, which causes resource waste and high test cost. Aiming at the defects, the non-contact force loading device which is simple in implementation process, high in control precision, sensitive in response, capable of being flexibly switched in the forward and reverse force loading directions and suitable for test pieces of different shapes is designed, and the engineering test value is remarkable.
Disclosure of Invention
The application aims to provide a strength test loading device and a loading method for an airplane structure strength test, and aims to establish a universal non-contact force loading device and a loading method for realizing loading stress of an airplane test piece through electromagnetic control.
The utility model provides an intensity test loading device, contains device body and power loading structure, its characterized in that, power loading structure contain a plurality of loading coils and a plurality of fixed joint, every loading coil passes through a fixed joint and connects on the device body, loading coil and programmable power supply, switch and computer control system signal of telecommunication be connected, loading coil can produce magnetic attraction under the circular telegram condition.
The program-controlled power supply is divided into a plurality of power supply units, each power supply unit corresponds to a specified loading coil, the loading coils, the corresponding power supply units and the power switches form a closed circuit, the circuit relationship among the loading coils is in parallel connection, and the computer control system controls the current magnitude and direction of each power supply unit so as to control the magnitude and direction of the magnetic attraction force of the loading coils.
The coil fixing joint is provided with a telescopic mechanism and a rotating mechanism, and the spatial position of the loaded coil can be controlled through the telescopic mechanism and the rotating mechanism respectively.
The application also provides a loading method using the strength test loading device, which is characterized by comprising the following steps of 1) coating a layer of magnetic induction paint on the surface of a test piece, wherein the magnetic induction paint can be subjected to non-contact loading by the magnetic attraction of a coil, and 2) fixing the test piece at a proper position of the strength test loading device to ensure that the loading coil of the test loading device keeps a preset distance from the surface of the test piece; 3) the magnitude and the direction of the current of the force loading structure loading coil are controlled by the computer control system, so that the magnitude and the direction of the magnetic attraction force of the loading coil on the surface of the test piece are controlled, and the non-contact stress loading of the surface of the strength test piece is realized.
The beneficial effect of this application lies in: 1) the loading device realizes non-contact loading on the surface of the test piece through magnetic attraction force generated by electromagnetic induction, and the loading device can realize automatic accurate control; 2) the computer control system can control the magnitude and direction of current transmitted to the loading coil by the program-controlled power supply unit in real time, so that the magnetic attraction force borne by the aircraft test piece is changed in real time, and the control accuracy, the error and the time delay are small; 3) a space envelope area can be formed by adjusting the telescopic and rotary mechanisms on the coil fixed joint, and different test piece shapes can be adapted in the envelope area, so that the loading device has strong universality; 4) the non-contact loading on the surface of the test piece can be realized only by coating a layer of magnetic induction paint coating on the surface of the test piece, and the spraying work of the magnetic induction paint coating is simple and easy to realize; 4) the whole test loading system is controlled by a circuit, and compared with the traditional hydraulic loading system, the test loading system is high in reliability, sensitive in response, wide in adaptability and high in engineering practical value.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of the relationship between the loading device and the test piece.
FIG. 2 is a schematic diagram showing the axial relationship between the loading device for strength test and the test piece.
Fig. 3 is a schematic view of the fixed joint connection telescopic and rotary mechanism of the loading coil.
Fig. 4 is a schematic diagram of the circuit control principle of the loading coil.
The numbering in the figures illustrates: the device comprises a supporting upright post 1, an upper arch frame 2, a lower arch frame 3, a fixed joint 4, a loading coil 5, a test piece 6, enamel paint 7, a telescopic mechanism 8 and a rotating mechanism.
Detailed Description
The embodiment takes the strength loading test of straight section test pieces such as an airplane fuselage as an example, and further describes the strength test loading device and the loading method.
Referring to the attached drawings, the strength test loading device comprises a device body and force loading structures, wherein the device body is suitable for straight section test pieces such as an airplane body, the device body comprises two supporting upright posts 1 and a pair of arch frames in opposite directions, an upper arch frame 2 and a lower arch frame 3, the two arch frames are connected between the two supporting upright posts to form an annular support, a plurality of force loading structures are uniformly arranged on the inner side of each arch frame, and a conductive coil 5 of each force loading structure is connected to the inner side of each arch frame through a coil fixing joint 4.
The force loading structure comprises a plurality of loading coils 5 and a plurality of fixed joints 4, each loading coil 5 is connected to the device body through one fixed joint 4, the loading coils 5 are in electrical signal connection with a programmable power supply, a power switch and a computer control system, and the loading coils 5 can generate magnetic attraction under the condition of electrification, as shown in fig. 4.
In implementation, in order to control the relative position relationship between the loading coil and the test piece and the spatial position of the loading coil, a telescopic and rotary mechanism 8 is provided on the coil fixing joint, as shown in fig. 3, the fixing joint 4 of the loading coil 5 is connected with the upper arch 2 of the device body through a telescopic and rotary mechanism, so that the spatial position of the loading coil 5 and the relative position between the loading coil 5 and the test piece 6 can be respectively controlled through the telescopic and rotary mechanism 8.
According to the loading method for carrying out the strength loading test on the straight section test piece such as the airplane body and the like by using the strength test loading device, referring to fig. 1 and fig. 2, firstly, a layer of magnetic induction paint 7 is coated on the surface of the test piece 6, the magnetic induction paint 7 can be subjected to non-contact loading of the magnetic attraction force of a coil, the magnetic induction paint coating generates an ampere force under the action of a magnetic field generated by a loading coil, and the ampere force changes along with the size and the direction of the magnetic field generated by the loading coil, namely, the ampere force is used as the loading force of the test device on the test piece; during testing, fixing a test piece 6 at a proper position of a strength test loading device, and keeping a preset distance between a loading coil 5 of the test loading device and the surface of the test piece 6; the magnitude and the direction of the current of the force loading structure loading coil 5 are controlled by the computer control system, so that the magnitude and the direction of the magnetic attraction force of the loading coil on the surface of the test piece are controlled, and the non-contact stress loading of the surface of the test piece is realized.
In the implementation, the program-controlled power supply is divided into a plurality of power supply units, each power supply unit corresponds to a designated loading coil one by one, the loading coils, the corresponding program-controlled power supply units and the power switches form a closed circuit, and the circuit relationships among the loading coils are in parallel connection and do not interfere with each other. The computer control system controls the magnitude and direction of the current in each programmable power supply unit so that a magnetic field of a particular direction and magnitude is generated by the loading coil. The loading coils 5 are conductive coils with a certain number of turns, all the loading coils 5 are fixed on the arch frame through coil fixing joints 4, the distance between the loading coils 5 and the surface of the test piece 6 is adjusted through the telescopic and rotary mechanism 8, the axial direction of the loading coils 5 is ensured to be vertical to the surface of the test piece 6, each loading coil 5 can independently generate a magnetic field under the action of current, and the magnetic induction direction is normal to the surface of the aircraft test piece; the arch-shaped frame is provided with enough mounting reserved positions of the coil fixing joints 4, and the mounting number of the fixing joints 4 can be adjusted according to the test requirement, so that the number of the loading coils 5 is set in a targeted manner, and the number requirement and the position requirement of loading points required by the test are met. The material stiffness of the support columns 1 and the arch of the device body should be sufficient to ensure that no significant deformation occurs during test loading.
Claims (5)
1. The utility model provides an intensity test loading device, contains device body and power loading structure, its characterized in that, power loading structure contain a plurality of loading coils and a plurality of fixed joint, every loading coil passes through a fixed joint and connects on the device body, loading coil and programmable power supply, switch and computer control system signal of telecommunication be connected, loading coil can produce magnetic attraction under the circular telegram condition.
2. The strength test loading device according to claim 1, wherein the programmable power supply is divided into a plurality of power supply units, each power supply unit corresponds to a designated loading coil, the loading coils, the corresponding power supply units and the power switches form a closed circuit, the loading coils are connected in parallel, and the computer control system controls the magnitude and direction of the current of each power supply unit, thereby controlling the magnitude and direction of the magnetic attraction force of the loading coils.
3. The strength test loading device of claim 1 or 2, wherein the coil fixing joint is provided with a telescopic mechanism and a rotary mechanism, and the spatial position of the loaded coil can be controlled by the telescopic mechanism and the rotary mechanism respectively.
4. The strength test loading device of claim 3, wherein the device body comprises two support columns and a pair of oppositely directed arches, the arches are connected between the two support columns to form a ring-shaped support, a plurality of force loading structures are uniformly arranged on the inner side of the arch, and the conductive coil of each force loading structure is connected to the inner side of the arch through a coil fixing joint.
5. A loading method using the strength test loading device of claims 1 to 4, characterized by comprising 1) coating the surface of the test piece with a layer of enamel varnish which can be loaded contactlessly by the magnetic attraction of the coil, 2) fixing the test piece in a proper position of the strength test loading device so that the loading coil of the test loading device is kept at a predetermined distance from the surface of the test piece; 3) the magnitude and the direction of the current of the force loading structure loading coil are controlled by the computer control system, so that the magnitude and the direction of the magnetic attraction force of the loading coil on the surface of the test piece are controlled, and the non-contact stress loading of the surface of the strength test piece is realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110273618.5A CN113044244A (en) | 2021-03-12 | 2021-03-12 | Strength test loading device and loading method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110273618.5A CN113044244A (en) | 2021-03-12 | 2021-03-12 | Strength test loading device and loading method |
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| CN113044244A true CN113044244A (en) | 2021-06-29 |
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| CN202110273618.5A Pending CN113044244A (en) | 2021-03-12 | 2021-03-12 | Strength test loading device and loading method |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010164494A (en) * | 2009-01-17 | 2010-07-29 | Saitama Univ | Wind tunnel testing device of rotating spherical body |
| CN102109416A (en) * | 2010-12-15 | 2011-06-29 | 西安理工大学 | Non-contact electromagnetic loading device for high speed electric spindle |
| CN102662089A (en) * | 2012-02-13 | 2012-09-12 | 清华大学 | Non-contact loader |
| CN104648691A (en) * | 2014-12-11 | 2015-05-27 | 中国航天空气动力技术研究院 | Aerodynamic electromagnetic simulation test device |
| CN104807629A (en) * | 2015-05-08 | 2015-07-29 | 武汉理工大学 | Electromagnetic hydraulic comprehensive simulation test loading device for shafting |
| CN109946182A (en) * | 2019-03-18 | 2019-06-28 | 三峡大学 | A kind of pulse force loading device and its method suitable for sheet metal biaxial tensile test |
-
2021
- 2021-03-12 CN CN202110273618.5A patent/CN113044244A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010164494A (en) * | 2009-01-17 | 2010-07-29 | Saitama Univ | Wind tunnel testing device of rotating spherical body |
| CN102109416A (en) * | 2010-12-15 | 2011-06-29 | 西安理工大学 | Non-contact electromagnetic loading device for high speed electric spindle |
| CN102662089A (en) * | 2012-02-13 | 2012-09-12 | 清华大学 | Non-contact loader |
| CN104648691A (en) * | 2014-12-11 | 2015-05-27 | 中国航天空气动力技术研究院 | Aerodynamic electromagnetic simulation test device |
| CN104807629A (en) * | 2015-05-08 | 2015-07-29 | 武汉理工大学 | Electromagnetic hydraulic comprehensive simulation test loading device for shafting |
| CN109946182A (en) * | 2019-03-18 | 2019-06-28 | 三峡大学 | A kind of pulse force loading device and its method suitable for sheet metal biaxial tensile test |
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