CN111044381A - Variable-profile wing universal testing mechanism - Google Patents
Variable-profile wing universal testing mechanism Download PDFInfo
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- CN111044381A CN111044381A CN201911381334.7A CN201911381334A CN111044381A CN 111044381 A CN111044381 A CN 111044381A CN 201911381334 A CN201911381334 A CN 201911381334A CN 111044381 A CN111044381 A CN 111044381A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
Abstract
The invention provides a variable profile wing universal testing mechanism, which comprises a model fixing and supporting module, a measuring module, a sensor measuring module, a guiding and positioning module and a fixing platform, wherein the model fixing and supporting module and the guiding and positioning module are arranged on the fixing platform, the sensor measuring module is arranged on the guiding and positioning module through the measuring module, the model is arranged on the model fixing and supporting module, and the sensor measuring module can move on the guiding and positioning module along the axial direction of the model through the measuring module. The structure is simple, the universality is strong, the robustness is good, and the cost is low.
Description
Technical Field
The invention relates to the technical field of aviation equipment tests, in particular to a variable-profile wing universal testing mechanism.
Background
In flight, the external loads acting on the airfoil of the model are: distributed power acting along the entire airfoil, distributed mass forces of the airfoil itself, and concentrated mass forces of equipment mounted on the airfoil. Under these loads, the airfoils experience internal forces, including bending, shearing, and twisting, which cause deformation. It is important to check the deformation amount of the airfoil under variable load.
The model adopts the folding wing mechanism, which has important significance for improving the transportation and storage of the model, the adaptability to the carrier, the reduction of the size of the packing box and the like, the unfolding performance of the folding wing mechanism is related to the condition whether the model can fly normally after being launched and the completion of the set task, and the unfolding performance comprises the unfolding time, the unfolding impact force, the unfolding synchronism and the like, so the method has important significance for the research on the unfolding performance of the folding wing mechanism.
The method for measuring the unfolding time adopted in the literature, namely the technology for testing the rapid unfolding performance of the folding wings of the tactical model, is to use the on-off-on of a circuit, namely to measure the unfolding time of four folding wings, and to obtain the unfolding time by using a circuit at a rotating shaft to get an electric shock, when the folding wings are folded, the circuit is designed to be in a conducting state, and low voltage is output; when the wing surface is unfolded completely, the circuit is switched on to output low voltage. The deployment time of the airfoil can be obtained based on the on-off-on of the electrical circuit. Although the method can effectively measure the unfolding time of the airfoil, the method needs to arrange a circuit contact at the folding rotating shaft to realize the unfolding through the circuit, is not practical in actual measurement, and cannot be applied to measurement when the airfoils of various types are unfolded.
Patent document CN102506734A discloses a device for non-contact measurement of wing deformation, which includes a digital camera, a scale plate and a level gauge. The main optical axis of the camera lens is adjusted and recorded through the scales on the scale plate, namely the angle of the included angle between the axis which passes through the circle center of the lens and is vertical to the plane of the lens and the connecting line of the two cameras is adjusted, so that the resolution of the effective range can be accurate to 0.1 degrees, but the device has higher measurement precision on the deformation angle, but the specific deformation quantity of the airfoil surface when the airfoil surface is loaded cannot be measured visually.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a variable-profile wing universal testing mechanism.
The invention provides a variable-profile wing universal testing mechanism which comprises a model fixing and supporting module 1, a measuring module 3, a sensor measuring module 4, a guiding and positioning module 5 and a fixing platform 6, wherein the model fixing and supporting module is arranged on the model fixing and supporting module;
the model fixing and supporting module 1 and the guiding and positioning module 5 are both arranged on a fixing platform 6;
the sensor measuring module 4 is arranged on the guiding and positioning module 5 through the measuring module 3;
the model 2 is arranged on the model fixing and supporting module 1;
the sensor measuring module 4 can be moved by the measuring module 3 in the axial direction of the model 2 on the guide positioning module 5.
Preferably, the sensor measuring module 4 comprises a sensor connecting plate 13, an optical fiber module, a pneumatic module, a proximity sensor 14, a displacement sensor 17 and a grating scale 20;
the optical fiber module, the pneumatic module, the proximity sensor 14, the displacement sensor 17 and the grating ruler 20 are all installed on the sensor connecting plate 13.
Preferably, the fiber optic module includes a fiber optic sensor 19, a fiber optic mount 24, and a fiber optic slide 25;
the optical fiber sensor 19 is arranged on an optical fiber sliding groove 25 through an optical fiber fixing piece 24;
the fiber securing member 24 is movable along the length of the fiber slide 25.
Preferably, the pneumatic module comprises a cylinder guide 15 and a cylinder 16;
a position calibration device 18 is arranged on the cylinder 16;
the air cylinder 16 is arranged on the air cylinder guide rail 15;
the proximity sensor 14 and the displacement sensor 17 are electrically connected with the air cylinder 16 respectively;
the cylinder 16 is movable in the radial direction of the mold 2 by a cylinder guide 15.
Preferably, the steel plate also comprises a right-angle rib plate 21 and a double-Y-shaped rib plate 22;
the number of the sensor measuring modules 4 is 4;
wherein, 4 sensor connecting plates 13 are respectively and uniformly arranged along the circumferential direction inside the measuring module 3 and are arranged on the measuring module 3 to form 4 measuring stations;
the 4 sensor connecting plates 13 are respectively a first connecting plate 131, a second connecting plate 132, a third connecting plate 133 and a fourth connecting plate 134;
the first connecting plate 131 and the second connecting plate 132, the second connecting plate 132 and the third connecting plate 133, and the third connecting plate 133 and the fourth connecting plate 134 are respectively connected through double-Y-shaped rib plates 22;
the first connecting plate 131 and the fourth connecting plate 134 are close to the fixed platform 6 and are respectively installed on the measuring module 3 through right-angle rib plates 21.
Preferably, the fixed support module 1 comprises a support rib plate 10, a lower bracket 11 and an upper bracket 12;
the upper part of the lower support 11 is detachably connected with the upper support 12 to form an annular structure, and the lower part of the lower support 11 is welded on the support rib plate 10.
Preferably, the lower bracket 11 is manufactured by a sheet metal process;
the lower support 11 and the upper support 12 are provided with buffer layers;
and reinforcing rib plates are also connected to the side surfaces of the supporting rib plates 10.
Preferably, the measuring module 3 comprises a frame 31, two support angle steels 9 and two guide rail sliders 8;
the frame 31 is perpendicular to the guide rail sliding block 8, and two ends of the bottom of the frame 31 are respectively arranged on the guide rail sliding block 8;
one end of the support angle steel 9 is connected with the upright column on one side of the square frame 31, and the other end of the support angle steel 9 is connected with the guide rail sliding block 8 at the bottom of the upright column;
wherein, two support angles 9 strengthen and support the frame 31.
Preferably, the guiding and positioning module 5 comprises a measuring rail 51 and a locking device 7;
the measuring guide rail 51 is arranged on the fixed platform 6;
the measuring module 3 can slide along the measuring guide rail 51 in a matching way;
when the measuring module 3 does not slide, the locking device 7 can be used for locking and positioning.
Preferably, the number of the fixed support modules 1 is two;
the two fixed supporting modules 1 are respectively arranged at two ends of the fixed platform 6;
the model 2 passes through the measuring module 3, and two ends of the model are respectively arranged on the two fixed supporting modules 1.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention is movable, saves space, has modular design, is convenient to disassemble and replace, and has the advantages of expansibility and the like; the device can be suitable for measuring the wing surface unfolding time of various models and the deformation displacement under the simulated load, and has the advantages of simple structure, strong universality, good robustness and low cost.
2. The four sensor connecting plates 13 are provided with the U-shaped reserved grooves, so that the airfoil of the model 2 can be smoothly unfolded, the structure is simple, and the practicability is high.
3. The sensor measuring module 4 and the measuring module 3 are completely closed, so that the strength and the stability of the whole device are improved.
4. The displacement sensor 17 adopted in the invention is calibrated through the grating ruler 20, the air cylinder 16 is calibrated through the pressure sensor, and the pressure sensor is calibrated through the standard mass block, so that the system measurement result is more accurate and reliable, and the measurement precision is high.
5. According to the invention, through the position adjustment of the sensor measuring module 4, the measurement of any point of the airfoil surface in the radial direction can be realized. Through sensor measurement module 4, measurement module 3 can link firmly through locking device 7 and measurement guide rail 51, realize the fixed of vertical direction and can realize along the axial removal of model 2, realize the detection of model 2 airfoil in the axial direction, realize the detection of different positions through model 2 immobility, saved the space of device greatly.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of the present invention after installing a mold 2;
FIG. 2 is a schematic structural view of the present invention without the mold 2 installed;
fig. 3 is a schematic structural diagram of the sensor measuring module 4;
fig. 4 is a schematic structural diagram of the sensor measuring module 4;
fig. 5 is a schematic structural view of the model fixing support module 1;
fig. 6 is a schematic structural diagram of the measurement module 3;
fig. 7 is a schematic structural view of the sensor connecting plate 13;
fig. 8 is a schematic structural view of the proximity sensor 14;
fig. 9 is a schematic structural view of the optical fiber sensor 19;
fig. 10 is a schematic structural view of the sensor connecting plate 13.
The figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
According to the general testing mechanism for the variable-profile wing, as shown in fig. 1, the general testing mechanism comprises a model fixing and supporting module 1, a measuring module 3, a sensor measuring module 4, a guiding and positioning module 5 and a fixing platform 6, wherein the model fixing and supporting module 1 and the guiding and positioning module 5 are both installed on the fixing platform 6, the fixing platform 6 is placed on the ground to play a role in shock insulation protection on the measuring module 3, and in a preferred embodiment, the fixing platform 6 is made of cast iron; the sensor measuring module 4 is installed on the guiding and positioning module 5 through the measuring module 3, the model 2 is installed on the model fixing and supporting module 1, the sensor measuring module 4 can move on the guiding and positioning module 5 along the axial direction of the model 2 through the measuring module 3, and preferably, the number of the fixing and supporting modules 1 is two; the two fixed supporting modules 1 are respectively arranged at two ends of the fixed platform 6; the model 2 passes through the measuring module 3, and two ends of the model are respectively arranged on the two fixed supporting modules 1. According to the invention, through the position adjustment of the sensor measuring module 4, the measurement of any point of the airfoil surface in the radial direction can be realized. The invention is movable, saves space and is suitable for various models; the displacement sensor 17 and the air cylinder 16 are calibrated by the system, so that the measurement precision is high; the modular design is convenient to disassemble and replace, and the system has the advantages of expansibility and the like; the device can be suitable for measuring the wing surface unfolding time of various models and the deformation displacement under the simulated load, and has the advantages of high measurement precision, simple structure, strong universality, good robustness and low cost.
Specifically, as shown in fig. 1, 4, 8 and 10, the sensor measurement module 4 includes a sensor connection board 13, a fiber module, a pneumatic module, a proximity sensor 14, a displacement sensor 17 and a grating scale 20; the optical fiber module, the pneumatic module, the proximity sensor 14, the displacement sensor 17 and the grating ruler 20 are all arranged on the sensor connecting plate 13, and in a preferred embodiment, the optical fiber module further comprises a right-angle rib plate 21 and a double-Y-shaped rib plate 22; the number of the sensor measuring modules 4 is 4; the measuring module 3 is provided with a measuring module, wherein 4 sensor connecting plates 13 are respectively and uniformly arranged along the circumferential direction inside the measuring module 3 and are arranged on the measuring module 3 to form 4 measuring stations, and the 4 sensor connecting plates 13 are arranged in a centrosymmetric manner; the 4 sensor connecting plates 13 are respectively a first connecting plate 131, a second connecting plate 132, a third connecting plate 133 and a fourth connecting plate 134; the first connecting plate 131 and the second connecting plate 132, the second connecting plate 132 and the third connecting plate 133, and the third connecting plate 133 and the fourth connecting plate 134 are respectively connected through double-Y-shaped rib plates 22; the first connecting plate 131 and the fourth connecting plate 134 are close to the fixed platform 6 and are respectively installed on the measuring module 3 through right-angle rib plates 21. Wherein each station comprises 2 cylinders 16 and 2 displacement sensors 17. The four sensor connecting plates 13 are outwards connected with the measuring module 3, wherein a right-angle rib plate 21 is used between the first connecting plate 131 and the fourth connecting plate 134 instead of a double-Y-shaped rib plate 22, so that the sensor measuring module 4 cannot interfere with the model fixing and supporting module 1 when moving; as shown in fig. 7, the four sensor connecting plates 13 are all provided with U-shaped preformed grooves, so that the airfoil of the model 2 can be smoothly unfolded, the structure is simple, and the practicability is high. The sensor measuring module 4 and the measuring module 3 are completely closed, so that the strength and the stability of the whole device are improved.
Further, a fixing piece 23 is arranged at the top of the center of the sensor connecting plate 13, as shown in fig. 8, a center sliding groove is arranged on the fixing piece 23, and the proximity sensor 14 is installed in the center sliding groove on the fixing piece 23 and used for sensing whether the wing surface of the model 2 is unfolded in place; as shown in fig. 9, the optical fiber module includes an optical fiber sensor 19, an optical fiber fixing member 24, and an optical fiber sliding groove 25; the optical fiber sensor 19 is arranged on an optical fiber sliding groove 25 through an optical fiber fixing piece 24; as shown in fig. 8, the proximity sensor 14 is fixed to the fiber mount 24 with a stud and nut, wherein the position of the stud can be slid in the fiber mount 24 to achieve fine adjustment of the distance of the proximity sensor 14. The fiber mount 24 is movable along the length of the fiber slide 25 to enable the fiber sensor 19 to be adapted for different sized airfoil deployment measurements. The optical fiber sensor 19 can move left and right on the optical fiber fixing piece 24 for fine adjustment; the optical fiber sensor 19 is used for sensing the unfolding of the airfoil of the model 2; the optical fiber sensor 19 and the proximity sensor 14 can be adjusted in installation position to adapt to different types of airfoils, are suitable for various types of models 2, and are good in universality.
Further, as shown in fig. 1 and 4, the pneumatic module includes a cylinder guide rail 15 and a cylinder 16, and a position calibration device 18 is mounted on the cylinder 16 to facilitate adjusting the position of the cylinder 16; the air cylinder 16 is arranged on the air cylinder guide rail 15; the proximity sensor 14 and the displacement sensor 17 are electrically connected with the air cylinder 16 respectively; the cylinder 16 is movable in the radial direction of the mold 2 by a cylinder guide 15. The pneumatic module controls the air cylinder 16 to drive air pressure to apply force load on the model 2, and the displacement sensor 17 detects the elastic deformation quantity of the airfoil. As shown in fig. 5 and 6, the cylinder 16 needs to be moved in the radial direction of the mold 2. A cylinder guide rail 15 is arranged on the sensor connecting plate 13, a cylinder 16 moves along the radial direction of the model 2 through the cylinder guide rail 15, and a displacement sensor 17 is connected with the cylinder 16 and used for measuring the deformation of the airfoil; there is a proximity sensor 14 for sensing that cylinder 16 has contacted the airfoil; the position calibration device 18 at the head of the air cylinder 16 can realize that the force is applied at a precise position, and the position of the air cylinder 16 is adjusted after the point of applying the force is determined, so that the detection accuracy is improved. According to the pressure relation between the input air pressure and the actual air cylinder 16, the forward and reverse displacement of the air cylinder 16 is controlled by inputting the air pressure required by the given pressure, and the effect of applying the corresponding pressure to the given point is achieved.
Specifically, as shown in fig. 1 and 5, the fixed support module 1 includes a support rib plate 10, a lower bracket 11 and an upper bracket 12; the upper part of the lower bracket 11 is detachably connected with the upper bracket 12 to form a ring structure, for example, the upper bracket is connected with a nut through a bolt; the upper bracket 12 can deform, the model 2 is fastened and fixed by the deformation of the upper bracket 12, and the lower part of the lower bracket 11 is welded on the support rib plate 10; the lower bracket 11 is manufactured by a sheet metal process; the lower support 11 and the upper support 12 are provided with a buffer layer, for example, a layer of organic polymer material is filled inside the upper support 12 and the lower support 11, so that the model 2 is not damaged in the process of clamping the model 2. In order to ensure the stability of the fixed support module 1, the side surface of the support rib plate 10 is also connected with a reinforcing rib plate to increase the strength; the fixed support module 1 ensures the positioning of the model 2 in the axial direction; the measuring module 3 can realize the fixation of the model 2 in the radial direction and can move the model 2 along the axial direction of the model.
Further, as shown in fig. 1 and 6, the measuring module 3 includes a frame 31, two support angle steels 9, and two rail sliders 8; the frame 31 is perpendicular to the guide rail sliding block 8, and two ends of the bottom of the frame 31 are respectively arranged on the guide rail sliding block 8; the two joints of the square frame 31 and the guide rail sliding block 8 are respectively supported as inclined struts through two supporting angle steels 9 so as to enhance the connection strength and ensure the strength and stability of the square frame 31.
Specifically, as shown in fig. 1, 2, and 3, the guiding and positioning module 5 includes a measuring rail 51 and a locking device 7; the measuring guide rail 51 is arranged on the fixed platform 6; the measuring module 3 can slide along the measuring guide rail 51 in a matching way; when the measuring module 3 does not slide, the locking device 7 can be used for locking and positioning. The measurement module 3 is moved and fixed in the axial direction of the model 2 through the measurement guide rail 51 and the locking device 7, and in addition, the radial direction of the model 2 is moved and fixed through the cylinder guide rail 15, the cylinder 16 and the calibration device 18; the two are combined to achieve the simulation force application and airfoil deformation displacement measurement on any point of the model 2, and the structure is reasonable.
The working principle of the invention is as follows:
in the actual measurement process, firstly, a displacement sensor 17 is calibrated through a grating ruler 20, an air cylinder 16 is calibrated through a pressure sensor, the pressure sensor is calibrated through a standard mass block, the wing surface expansion is sensed through an optical fiber sensor 19 for measuring the wing surface expansion time, a timer is started to time each channel when triggered, the proximity sensor 14 senses that the wing surface is expanded in place, and the timer is stopped, so that the expansion time of each channel is obtained; for the pneumatic simulation deformation measurement, firstly, according to a set pressure, the pressure in a pneumatic circuit is controlled through the air cylinder 16, four air cylinders are measured at one time to serve as single-side force application simulation of four wing surfaces, a smaller pressure is output to drive an air rod of the air cylinder 16 to extend, when the proximity sensor 14 detects triggering, the air rod of the air cylinder 16 is shown to be in contact with the wing surfaces, the displacement sensor 17 returns to zero, the pressure is increased to a set value at the moment, the air cylinder 16 is switched according to the output result of the displacement sensor 17, and finally deformation quantity of the four wing surfaces during single-side force application.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A variable-profile wing universal testing mechanism is characterized by comprising a model fixing and supporting module (1), a measuring module (3), a sensor measuring module (4), a guiding and positioning module (5) and a fixing platform (6);
the model fixing and supporting module (1) and the guiding and positioning module (5) are both arranged on a fixing platform (6);
the sensor measuring module (4) is arranged on the guiding and positioning module (5) through the measuring module (3);
the model (2) is arranged on the model fixing and supporting module (1);
the sensor measuring module (4) can be moved on the guide positioning module (5) along the axial direction of the model (2) by means of the measuring module (3).
2. The universal testing mechanism for profile wings according to claim 1, wherein the sensor measuring module (4) comprises a sensor connecting plate (13), a fiber optic module, a pneumatic module, a proximity sensor (14), a displacement sensor (17) and a grating scale (20);
the optical fiber module, the pneumatic module, the proximity sensor (14), the displacement sensor (17) and the grating ruler (20) are all installed on the sensor connecting plate (13).
3. The universal testing mechanism with variable profile wings of claim 2, wherein the fiber optic module comprises a fiber optic sensor (19), a fiber optic fixture (24) and a fiber optic chute (25);
the optical fiber sensor (19) is arranged on the optical fiber sliding groove (25) through an optical fiber fixing piece (24);
the optical fiber fixing member (24) can move along the length direction of the optical fiber sliding groove (25).
4. The universal testing mechanism for profile wings according to claim 2, wherein the pneumatic module comprises a cylinder rail (15) and a cylinder (16);
a position calibration device (18) is arranged on the cylinder (16);
the air cylinder (16) is arranged on the air cylinder guide rail (15);
the proximity sensor (14) and the displacement sensor (17) are respectively and electrically connected with the air cylinder (16);
the air cylinder (16) can move along the radial direction of the model (2) through an air cylinder guide rail (15).
5. The variable-profile wing universal testing mechanism is characterized by further comprising a right-angle rib plate (21) and a double-Y-shaped rib plate (22);
the number of the sensor measuring modules (4) is 4;
the measuring module (3) is provided with a measuring module (3), wherein 4 sensor connecting plates (13) are respectively and uniformly arranged along the circumferential direction inside the measuring module (3) and are arranged on the measuring module (3) to form 4 measuring stations;
the 4 sensor connecting plates (13) are respectively a first connecting plate (131), a second connecting plate (132), a third connecting plate (133) and a fourth connecting plate (134);
the first connecting plate (131) is connected with the second connecting plate (132), the second connecting plate (132) is connected with the third connecting plate (133), and the third connecting plate (133) is connected with the fourth connecting plate (134) through double-Y-shaped rib plates (22);
the first connecting plate (131) and the fourth connecting plate (134) are close to the fixed platform (6) and are respectively installed on the measuring module (3) through right-angle rib plates (21).
6. The universal testing mechanism for the variable profile wing according to claim 1, wherein the fixed support module (1) comprises a support rib plate (10), a lower bracket (11) and an upper bracket (12);
the upper part of the lower support (11) is detachably connected with the upper support (12) to form a ring-shaped structure, and the lower part of the lower support (11) is welded on the support rib plate (10).
7. The universal testing mechanism with variable profile wings of claim 6, wherein the lower bracket (11) is manufactured by a sheet metal process;
buffer layers are arranged on the lower support (11) and the upper support (12);
and the side surface of the supporting rib plate (10) is also connected with a reinforcing rib plate.
8. The universal testing mechanism for profile-variable wings according to claim 1, wherein the measuring module (3) comprises a frame (31), two support angles (9) and two guide rail sliders (8);
the square frame (31) is perpendicular to the guide rail sliding block (8), and two ends of the bottom of the square frame (31) are respectively installed on the guide rail sliding block (8);
one end of the support angle steel (9) is connected with the upright column on one side of the square frame (31), and the other end of the support angle steel (9) is connected with the guide rail sliding block (8) at the bottom of the upright column;
wherein the two supporting angle steels (9) are used for reinforcing and supporting the square frame (31).
9. The universal testing mechanism for wing with variable profile according to claim 1, characterized in that the guiding and positioning module (5) comprises a measuring guide rail (51) and a locking device (7);
the measuring guide rail (51) is arranged on the fixed platform (6);
the measuring module (3) can slide along the measuring guide rail (51) in a matching way;
when the measuring module (3) does not slide, the locking device (7) can be used for locking and positioning.
10. The variable profile wing universal test mechanism according to claim 1, wherein the number of fixed support modules (1) is two;
the two fixed supporting modules (1) are respectively arranged at two ends of the fixed platform (6);
the model (2) penetrates through the measuring module (3) and two ends of the model are respectively installed on the two fixed supporting modules (1).
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| CN201911381334.7A CN111044381B (en) | 2019-12-27 | 2019-12-27 | Variable-profile wing universal testing mechanism |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113848046A (en) * | 2021-09-08 | 2021-12-28 | 湖南航天机电设备与特种材料研究所 | Testing device for testing unfolding synchronism of wing surface of folding wing aircraft |
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| CN109000866A (en) * | 2018-06-07 | 2018-12-14 | 东北大学 | Unmanned plane answers material wing dynamic characteristic and damage check equipment under dust storm-thermal environment |
| CN208672447U (en) * | 2018-08-14 | 2019-03-29 | 深圳联合飞机科技有限公司 | A kind of rotor measuring device |
| CN109141905A (en) * | 2018-10-01 | 2019-01-04 | 北京航天三发高科技有限公司 | A kind of six square phase test bay and its method for measuring vectored thrust |
| CN109827723A (en) * | 2019-01-25 | 2019-05-31 | 苏州为鹿测试技术有限公司 | The full machine intensity of fixed wing aircraft and modal test flexible support system |
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| CN113848046A (en) * | 2021-09-08 | 2021-12-28 | 湖南航天机电设备与特种材料研究所 | Testing device for testing unfolding synchronism of wing surface of folding wing aircraft |
| CN113848046B (en) * | 2021-09-08 | 2023-11-24 | 湖南航天机电设备与特种材料研究所 | Testing device for testing wing surface unfolding synchronism of folding wing aircraft |
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