CN110686850A - Test device and test method for continuously adjusting opening-closing ratio of transonic test section - Google Patents
Test device and test method for continuously adjusting opening-closing ratio of transonic test section Download PDFInfo
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- CN110686850A CN110686850A CN201910940370.6A CN201910940370A CN110686850A CN 110686850 A CN110686850 A CN 110686850A CN 201910940370 A CN201910940370 A CN 201910940370A CN 110686850 A CN110686850 A CN 110686850A
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Abstract
The invention discloses a test device and a test method for continuously adjusting the opening-closing ratio of a transonic speed test section, which relate to the technical field of wind tunnel tests. According to the invention, the air permeable area of the wall plate is controlled by adjusting the contraction mechanism, so that the flow field of the wind tunnel is optimized, the data measured in the simulation process of the aircraft is closer to the actual data of the aircraft in the flight process, and the experimental data measured in the experimental process of the aircraft is accurate.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests, in particular to a test device and a test method for continuously adjusting the opening-closing ratio of a transonic speed test section.
Background
The wind tunnel is a ground pipeline-shaped device for simulating the flight environment of the aircraft, a wind tunnel test section generates certain airflow required by the test, and the aircraft model is installed in the wind tunnel test section for testing. During the test, the model is generally static, the airflow in the test section blows to the aircraft model in an opposite direction, the aircraft flight in the air is simulated through the same movement of the airflow and the model (relative movement principle), and the flight attitude of the aircraft in the air is simulated through changing the attitude of the model.
The flow field quality in a wind tunnel test is required to be the same as the real sky as much as possible, such as uniform airflow, low turbulence and the like, and the flow field quality condition depends on the type of the opening or the grooving of the wall plate, such as the size of the hole, the angle of the hole, the distribution of the hole, the size of the groove, the distribution of the groove and the like. Generally, the hole wall has good wave-absorbing characteristics (namely, shock waves generated by flowing around an aircraft can be eliminated or weakened when hitting a test section wall plate, cannot be reflected to a test model or can be reflected back very weakly, and because the sky is borderless during real flight and the shock waves cannot be reflected back, the shock waves hit the wall plate during the test and can cause the distortion of flow simulation), the noise is large, and the wall is just opposite to the wall.
No matter the open pore wall and the open pore wall are adopted, the wind tunnel flow field reaches the optimal flow field quality to the opening-closing ratio (the ratio of the total area of the holes or the grooves opened on the wall plate to the total area of the wall plate) and the ventilation area distribution requirement under different simulation speeds, namely the optimal flow field under the different speeds of the wind tunnel is corresponding to different opening-closing ratios and ventilation area distribution laws. The opening-closing ratio and the ventilation area distribution of the wind tunnel are fixed at present, and the flow field quality of the whole transonic speed range needs to be considered, so that the flow field under each simulation speed is not optimal, and the deviation of test data and theoretical data is caused.
Disclosure of Invention
The invention aims to provide a test device with continuously adjustable opening-closing ratio of a transonic test section and a test method thereof, and aims to solve the problems.
In order to realize the purpose of the invention, the technical scheme is as follows: the utility model provides a test device that transonic speed test section switching ratio is adjustable in succession, includes the test section, the test section includes upper and lower wallboard and two lateral wall boards, and all seted up the bleeder vent on the upper and lower wallboard, and all install the shrink mechanism that changes the bleeder vent internal diameter in every bleeder vent.
Further, the upper wall plate and the lower wall plate respectively comprise a plurality of unit plates, a plurality of air holes are uniformly distributed on the plurality of unit plates, and the plurality of unit plates are spliced and fixed one by one.
Furthermore, two all install transparent observation window on the lateral wall board, and still install a plurality of pivoted wheels below the experimental section.
Furthermore, both ends of the upper wall plate and the lower wall plate are provided with fin structures.
Furthermore, the mounting groove has been seted up to the venthole inner wall, and shrink mechanism installs in the mounting groove.
Furthermore, the unit plate comprises a substrate, and the air holes are formed in the substrate; the contraction mechanism comprises a rubber sleeve arranged in the mounting groove, and the inner wall of the rubber sleeve extends along the inner wall of the air hole; and the base plate is also provided with a plurality of driving structures which drive the rubber sleeves to protrude inwards one by one.
Further, a radial gap is reserved between the outer wall of the rubber sleeve and the inner wall of the mounting groove; the driving structure is an inflation channel arranged on the substrate, and the exhaust end of the inflation channel is communicated with the mounting groove.
Furthermore, the unit plate also comprises a cover plate covered on the lower surface of the base plate, and the lower end of the mounting groove penetrates through the lower surface of the base plate; the cover plate is further provided with an air exhaust hole and an inflation inlet, the inner wall of the air exhaust hole extends along the inner wall of the air vent, and the inflation inlet extends along the inflation channel.
Furthermore, the base plate is also provided with inflation connectors which are respectively in one-to-one correspondence with the inflation ports.
Further, the lower end of the rubber sleeve is also provided with an everted lower edge platform; the lower end of the mounting groove penetrates through the surface of the base plate, and the lower edge table is tightly pressed between the cover plate and the base plate.
Furthermore, the upper end of the rubber sleeve is also provided with an outward-turned upper edge table, and the upper edge table is fixed with the inner wall of the mounting groove.
Furthermore, a reinforcing sleeve is sleeved outside the rubber sleeve, and an inflation cavity is formed between the reinforcing sleeve and the rubber sleeve; the upper end of the reinforcing sleeve is tightly abutted to the upper edge platform, and the lower end of the reinforcing sleeve is tightly abutted to the lower edge platform; the reinforcing sleeve is also provided with a vent hole for communicating the inflation cavity with the inflation channel.
Further, the inner wall of the reinforcing sleeve is in sealing fit with the outer wall of the rubber sleeve; the outer wall of the rubber sleeve is also provided with an annular groove, and two ends of the vent hole are respectively butted with the inflation channel and the annular groove.
Furthermore, a sealing groove is formed in the lower surface of the substrate and surrounds the air inlet end of the inflation channel; and a sealing ring is also arranged in the sealing groove.
Furthermore, the cover plate is made of one of 6MnR steel or red copper.
Furthermore, a plurality of the air holes are arranged in a multi-row mode at even intervals, and the multi-row air holes are obliquely arranged along the central axis of the substrate.
A test method for a transonic velocity test section comprises the following specific steps:
(1) mounting a simulated aircraft on a model support section in a main tunnel body loop of the wind tunnel;
(2) installing the test section on a main tunnel body loop of the wind tunnel;
(3) starting a power section of a compressor in a main tunnel body loop of the wind tunnel to enable airflow to flow in a test section;
(4) when the airflow flows in the test section, the inflation channels are inflated one by one through the air inlets, and the inflation quantity of each inflation channel is designed according to the simulation condition;
(5) the air flow entering the inflation channel enters the annular groove through the vent hole;
(6) the airflow entering the annular groove acts on the rubber sleeves, so that each rubber sleeve bulges towards the inside of the rubber sleeve to different degrees, and the ventilation area of each air hole is changed;
(7) recording the opening-closing ratio and the ventilation area of each air hole;
(8) and recording the wind speed passing through each air vent, and performing the next calculation according to the wind speed recorded in the step 8 and the ventilation area recorded in the step 6.
The beneficial effect of the invention is that,
according to the invention, the opening degree of the air holes is changed by adjusting the contraction mechanism, so that the ventilation area of the air holes can be controlled, the flow field of the air flow in the test section is closer to the flow field of the air flow of the airplane in the flying process, the data measured in the simulation process of the airplane is closer to the actual data of the airplane in the flying process, and the experimental data measured in the experimental process of the airplane is accurate.
Drawings
FIG. 1 is a schematic structural diagram of a test device with continuously adjustable opening-closing ratio of a transonic speed test section provided by the invention;
FIG. 2 is a schematic diagram of the structure of the test section of FIG. 1;
FIG. 3 is a bottom view of the unit plate of FIG. 2;
FIG. 4 is a partial cross-sectional view of the cell plate of FIG. 2;
fig. 5 is a structural view of the rubber bushing of fig. 4.
Reference numbers and corresponding part names in the drawings:
1. the device comprises a base plate, 2, air holes, 3, an installation groove, 4, a rubber sleeve, 5, an inflation channel, 6, a cover plate, 7, an exhaust hole, 8, an inflation inlet, 9, an inflation joint, 10, a lower edge platform, 11, a reinforcing sleeve, 12, a lower edge platform, 13, an air hole, 14, a ring groove, 15, a sealing groove, 16, a sealing ring, 17, a test section, 18, a transparent observation window, 19 and wheels;
17a, upper and lower wall plates, 17c, side wall plates, 17d, fin structures.
Detailed Description
The present invention will be described in further detail below with reference to specific embodiments and with reference to the attached drawings.
Fig. 1 to 5 show a test device with a continuously adjustable opening/closing ratio of a transonic speed test section provided by the invention, which comprises a test section 17, wherein the test section 17 comprises an upper wall plate 17a, a lower wall plate 17a and two side wall plates 17c, air holes 2 are respectively formed in the upper wall plate 17a and the lower wall plate 17a, and a contraction mechanism for changing the inner diameter of each air hole 2 is installed in each air hole 2.
The test section 17 is a rectangular test section 17, and two ends of the test section 17 are both open, so that a rectangular flow field is formed in the test section 17; the upper and lower wall plates 17a and the two side plates 17c are detachably mounted, so that the upper and lower wall plates 17a and the two side wall plates 17c can be replaced according to experimental requirements. Two side wall plates 17c are vertically installed between the upper wall plate and the lower wall plate, thereby collectively forming a test section 17; the upper wall plate 17a and the lower wall plate 17a are provided with a plurality of air holes 2, and the plurality of air holes 2 are uniformly distributed on the upper wall plate 17a and the lower wall plate 17 a; the pore diameter of the air hole 2 can be set according to the measurement requirements, such as: the aperture can be 12-18 mm, and the central axis of the air hole 2 and the height direction of the test section 17 form an included angle of 60 degrees; under the condition that the contraction mechanism does not act, the ventilation area of the air holes 2 is fixed, the inner walls of the air holes 2 are smooth inner walls at the moment, and the ventilation area of the air holes 2 is the maximum ventilation area at the moment; when the contraction mechanism works, the contraction mechanism changes the ventilation area of the air holes 2, so that the ventilation area of the air holes 2 is reduced or enlarged, and the contraction mechanism is arranged in each air hole 2, so that the ventilation area of each air hole 2 is controlled by the independent contraction mechanism, the opening degree and the ventilation area of each air hole 2 can be adjusted according to requirements at different simulation speeds, the flow field in the test section 17 is closer to the flow field of the airplane in the flying process at different simulation speeds, the optimal flow field quality in the test section 17 is achieved as far as possible, the flow field of the airplane in the flying process is accurately simulated, and finally, the data measured by experiments are more accurate.
The upper and lower wall plates 17a respectively comprise a plurality of unit plates, a plurality of air holes 2 are uniformly distributed on the plurality of unit plates, the plurality of unit plates are spliced and fixed one by one, the specific number of the unit plates can be determined according to the specific width of the test section 17, the plurality of unit plates can be fixedly connected through screws, in order to ensure that two adjacent unit plates can be in sealed butt joint, one side edge of each unit plate can be provided with a raised line extending along the length direction of the unit plate, the other side surface of each unit plate is provided with a groove matched with the raised line, and the two adjacent unit plates can be more conveniently butted through the clamping of the raised line and the groove; meanwhile, through the clamping of the convex strips and the grooves, the sealing performance between the two adjacent unit plates is better, the flow field in the test section 17 is prevented from being influenced due to the gap between the two adjacent unit plates, the quality of the flow field in the test section 17 is ensured, and the data of a wind tunnel experiment are more accurate. The flatness of the upper and lower wall plates 17a is ensured by splicing the plurality of unit plates together into the upper and lower wall plates 17a, so that the flow field quality in the test section 17 is higher.
The two ends of the upper wall plate 17a and the lower wall plate 17a are respectively provided with a fin structure 17d, so that when the test section 17 is installed in a main tunnel body loop of the wind tunnel, the fin structures 17d can play a role in positioning, the test section 17 is more accurately installed, and the influence on a flow field in the wind tunnel is prevented. When the upper and lower wall plates 17a are composed of a plurality of unit plates, the fin structures 17d on the upper and lower wall plates 17a are located at both ends of the unit plates, respectively.
An installation groove 3 is formed in the inner wall of the air hole 2, and the contraction mechanism is installed in the installation groove 3; mounting groove 3 is the annular, and mounting groove 3 mainly used installs shrink mechanism, makes shrink mechanism after the installation, and shrink mechanism's inner wall and bleeder vent 2's inner wall parallel and level make bleeder vent 2 level more, make the air current flow more smoothly after getting into bleeder vent 2 to the simulation flow field precision that makes in the test section 17 is higher, makes final measuring precision higher, has guaranteed the accuracy of flow field quality.
The unit plate comprises a substrate 1, and air holes 2 are arranged on the substrate 1; the contraction mechanism comprises a rubber sleeve 4 arranged in the mounting groove 3, and the inner wall of the rubber sleeve 4 extends along the inner wall of the air hole 2; and a plurality of driving structures which drive the rubber sleeves 4 to protrude inwards are further arranged on the base plate 1. The central axis of the rubber sleeve 4 and the central axis of the central hole are on the same straight line, namely the included angle between the central axis of the rubber sleeve 4 and the thickness direction of the substrate 1 is also 60 degrees, and as the substrate 1 is horizontally arranged, namely in the wind tunnel experiment process, the air holes 2, the rubber sleeve 4 and the horizontal plane are 60 degrees, the airflow state of the airplane in the flying process is simulated; the inner diameter of the rubber sleeve 4 is the same as that of the air holes 2, so that the inner wall of the air holes 2 can still be kept level after the rubber sleeve 4 is installed, and the inner wall of the air holes 2 is kept flat.
The rubber sleeve 4 is made of natural rubber, the hardness of the rubber sleeve 4 is preferably 55HRC \65HRC \75HRC, the shrinkage rate of the rubber sleeve 4 is about 2.1%, the specific hardness and the shrinkage rate of the rubber sleeve 4 can be adjusted according to technical requirements in the actual use process, and the thickness of the rubber sleeve 4 can be adjusted according to the measurement requirement and the shrinkage rate of the rubber sleeve 4 in order to ensure the shrinkage of the rubber sleeve 4. In the installation, the both ends of rubber sleeve 4 are fixed respectively at the both ends of mounting groove 3, make the both ends of rubber sleeve end fixed, prevent that drive structure from making 4 deformation process of rubber sleeve, and rubber sleeve 4 takes place dislocation displacement in inflation channel 5, makes the deformation of rubber sleeve 4 can only warp to the center of bleeder vent 2, guarantees that the shape of rubber sleeve 4 in the shrink process is fixed repeatedly.
The driving structure is used for driving the rubber sleeve 4 to restore or enabling the rubber sleeve 4 to swell, and the contraction degree of the rubber sleeve 4 is different according to the driving condition of the driving structure, so that the opening degree of each air hole 2 can be controlled according to the experiment requirement; when the driving structure drives the rubber sleeve 4 to reset, the air holes 2 are in a fully opened state, and the air holes 2 are in the maximum ventilation area. The invention can effectively control the opening degree and the ventilation area of the air holes 2, thereby accurately simulating the flow field generated by the airplane in the flying process and ensuring the accuracy of experimental measurement; meanwhile, as the contraction mechanism is arranged in each air hole 2, the ventilation area of each air hole 2 is controlled by the independent contraction mechanism, so that the opening degree and the ventilation area of each air hole 2 can be adjusted according to requirements at different simulation speeds.
A radial gap is reserved between the outer wall of the rubber sleeve 4 and the inner wall of the mounting groove 3; the driving structure is an inflation channel 5 arranged on the substrate 1, and the exhaust end of the inflation channel 5 is communicated with the mounting groove 3. A certain radial distance is reserved between the outer wall of the rubber sleeve 4 and the inner wall of the mounting groove 3, so that an annular chamber is formed between the outer wall of the rubber sleeve 4 and the inner wall of the mounting groove 3, and a circle of the rubber sleeve 4 can be coated by the chamber; at least one inflation channel 5 is arranged, when one inflation channel 5 is arranged, the inflation channel 5 is vertically arranged on the substrate 1, and the air outlet end of the inflation channel 5 is positioned in the middle or the lower part of the chamber; the air inlet end of the inflation channel 5 penetrates through the lower surface of the base plate 1, the air outlet end of the inflation channel 5 penetrates through the inner wall of the mounting groove 3, the air outlet end of the inflation channel 5 is communicated with the cavity, when air flow enters the inflation channel 5, the air flow in the inflation channel 5 smoothly enters the cavity, at the moment, air in the cavity is uniformly coated on the outer wall of the rubber sleeve 4, when the air pressure in the cavity reaches a certain degree, the air pressure in the cavity can extrude the rubber sleeve 4 to deform the rubber sleeve 4, at the moment, the rubber sleeve 4 expands towards the inside of the air vent 2, the opening degree of the air vent 2 is changed, the ventilation area of the air vent 2 is changed, the adjustment of the opening degree and the ventilation area of the air vent 2 is realized, the flow field of the wind tunnel can achieve the optimal flow field quality at different simulation speeds, and the flow field of an airplane in the flying process can be accurately simulated, the data measured by the experiment are more accurate finally.
The unit plate also comprises a cover plate 6 covered on the lower surface of the base plate 1, and the lower end of the mounting groove 3 penetrates through the lower surface of the base plate 1; air exhaust hole 7 and inflation inlet 8 have still been seted up on apron 6, and the inner wall of air exhaust hole 7 extends along 2 inner walls of bleeder vent, and inflation inlet 8 extends along inflation channel 5.
The cover plate 6 is fixedly arranged on the lower surface of the base plate 1 through screws, specifically, the cover plate 6 and the base plate 1 are fixedly arranged together through a plurality of screws, the screws are uniformly distributed on the cover plate 6, when the cover plate 6 is arranged, the cover plate 6 is sequentially pre-tightened from the middle of the cover plate 6 along the periphery, the cover plate 6 is prevented from being deformed or not tightly sealed due to the fact that the screws on the cover plate 6 are not uniformly fastened, after all the screws are pre-tightened, the cover plate 6 is sequentially fastened along the periphery from the middle of the cover plate 6, and therefore the cover plate 6 is fixedly arranged.
The distribution rule of the air exhaust holes 7 on the cover plate 6 is the same as that of the air vents 2 on the base plate 1, the aperture of the air exhaust holes 7 is the same as that of the air vents 2, the central axis of the air exhaust holes 7 is on the same straight line with that of the air vents 2, namely, in the wind tunnel experiment process, the central axis of the air exhaust holes 7 is 60 degrees with the ground surface, the transition of the butt joint of the air exhaust holes 7 and the air vents 2 is avoided, and the flowing air flow entering the air vents 2 can be smoothly discharged through the air exhaust holes 7; the thickness of the cover plate 6 is designed according to the thickness of the substrate 1 and the actual situation in the wind tunnel experiment process.
The aperture of inflation inlet 8 is the same with inflation channel 5's diameter, and inflation inlet 8 is seted up perpendicularly on apron 6, and inflation inlet 8 and the sealed butt joint of inflation channel 5, the air current of avoiding getting into through inflation inlet 8 leaks from inflation inlet 8 and inflation channel 5's butt joint department, the volume of the air current of guaranteeing to enter into in the cavity is more accurate, thereby the extrusion force that makes rubber sleeve 4 receive is more accurate, make the switching of bleeder vent 2 more accurate, make the draught area of bleeder vent 2 more accurate, finally make the flow field of simulating out the aircraft at the flight in-process more accurate, make finally make the experimental measurement data more accurate.
And the base plate 1 is also provided with inflation connectors 9 which are respectively in one-to-one correspondence with the inflation ports 8. The quick-screwing connector PC-M5 of the inflation connector 9 is characterized in that the inflation connector 9 is mounted in one of a threaded fixing mode and a welding mode, one end of the inflation connector 9 is mounted in the inflation inlet 8 when the inflation connector is used, the other end of the inflation connector 9 is connected with a pipeline for conveying airflow, in order to avoid the influence of the pipeline for conveying airflow on experimental data in the wind tunnel experiment process, an air path wiring groove for mounting the pipeline can be formed in the surface of the cover plate 6, the pipeline can be mounted in the air path wiring groove, and the flatness of the lower surface of the cover plate 6 is guaranteed. In the actual experiment process, the air holes 2 on the base plate 1 can be divided into a plurality of groups, the opening and closing degrees of each group of air holes 2 are the same, namely, the swelling degrees of the rubber sleeves 4 in each group of air holes 2 are the same, the amount of air flow for driving the rubber sleeves 4 to swell is the same, at the moment, the air charging connectors 9 corresponding to the group of air holes 2 can be connected in parallel, the air flow entering the group of air charging connectors 9 is ensured to be consistent, and the structure of the invention is simpler. After the inflation connectors 9 in the same group are connected in parallel, the diameter of the main air inlet end of the pipeline is larger than the diameter of the air outlet end for respectively sending airflow to the inflation connectors 9, meanwhile, the pipeline for conveying the airflow adopts a pressure-resistant copper tube, the pressure-resistant parameter of the pipeline is 20OC and 40MPa/cm2, the hardness of the pipeline is HB35-40, and the melting point of the pipeline is 1083 OC.
The lower end of the rubber sleeve 4 is also provided with an everted lower edge platform 10; the lower end of the mounting groove 3 penetrates through the surface of the substrate 1, and the lower edge table 10 is tightly pressed between the cover plate 6 and the substrate 1. The lower end of the mounting groove 3 penetrates through the surface of the base plate 1, so that the lower end of the mounting groove 3 is a chamfered surface, and the lower end of the mounting groove 3 is elliptical, namely the lower end of the rubber sleeve 4 is elliptical; the thickness of the lower edge table 10 is preferably 1-1.5 mm, and the specific thickness of the lower edge table 10 can be adjusted according to actual conditions. Lower along platform 10 and rubber sleeve 4 integrated into one piece setting, and the material along platform 10 is the same with rubber sleeve 4's material down, lower surface along platform 10 and rubber sleeve 4's lower surface parallel and level, and the lower surface along platform 10 is less than base plate 1's lower surface down, when making apron 6 compress tightly on base plate 1's lower surface, the packing force that apron 6 was applyed can be used earlier down along platform 10, make down along platform 10 compressed tightly fix between base plate 1 and apron 6, make the lower extreme of rubber sleeve 4 by fixed mounting, can not only guarantee the fixing to rubber sleeve 4, prevent that rubber sleeve 4 from taking place the dislocation displacement when bloating through the air current, and make the installation of rubber sleeve 4 and change more convenient.
The upper end of the rubber sleeve 4 is also provided with an eversion upper edge platform 12, and the upper edge platform 12 is fixed with the inner wall of the mounting groove 3. The upper edge table 12 and the rubber sleeve 4 are integrally formed, the lower end of the rubber sleeve 4 is circular, namely the upper edge table 12 is also circular, the thickness of the upper edge table 12 is preferably 1.2-1.3 mm, and the specific thickness of the upper edge table 12 can be adjusted according to actual conditions; go up along the upper end of platform 12 and the upper end parallel and level of rubber sleeve 4, increase the area of contact of 4 upper ends of rubber sleeve and mounting groove 3, make the fixed effect of 4 upper ends of rubber sleeve better to it is more firm to make the fixed of 4 lower extremes of rubber sleeve.
A reinforcing sleeve 11 is further sleeved outside the rubber sleeve 4, and an inflation cavity is formed between the reinforcing sleeve 11 and the rubber sleeve 4; the upper end of the reinforcing sleeve 11 is tightly abutted to the upper edge platform 12, and the lower end of the reinforcing sleeve 11 is tightly abutted to the lower edge platform 10; the reinforcing sleeve 11 is further provided with a vent hole 13 for communicating the inflation cavity with the inflation channel 5.
The reinforcing sleeve 11 is a copper pipe, the upper end of the reinforcing sleeve 11 is tightly abutted to the upper edge platform 12, the lower end of the reinforcing sleeve 11 is tightly abutted to the lower edge platform 10, in order to enable the reinforcing sleeve 11 to have better abutting effect on the upper edge platform 12 and the lower edge platform 10, a groove matched with the end part of the reinforcing sleeve 11 can be formed in the upper edge platform 12 and the lower edge platform 10, the two ends of the reinforcing sleeve 11 can be respectively clamped in the two grooves, and the clamping position of the reinforcing sleeve 11 is more accurate; the central axis of the reinforcing sleeve 11 and the central axis of the rubber sleeve 4 are on the same straight line, at the moment, the inflation cavity between the rubber sleeve 4 and the reinforcing sleeve 11 is the cavity, and the inflation cavity is still annular, so that the inflation cavity is still coated outside the rubber sleeve 4, the airflow in the inflation cavity can still uniformly act on the rubber outer sleeve, and the extrusion force applied to the rubber sleeve 4 is more uniform. The vent holes 13 are in butt joint with the inflation channel 5, so that airflow entering the inflation channel 5 directly enters the inflation cavity through the vent holes 13, and the airflow can smoothly enter the inflation cavity.
By arranging the reinforcing sleeve 11 outside the rubber sleeve 4, when the cover plate 6 compresses the lower edge platform 10, the pressing force applied to the lower edge platform 10 acts on the reinforcing sleeve 11, so that the lower edge platform 10 is compressed between the reinforcing sleeve 11 and the cover plate 6, and the upper end of the reinforcing sleeve 11 is abutted against the upper edge platform 12, so that the upper edge platform 12 is clamped between the inner wall of the mounting groove 3 and the upper edge platform 12, the upper edge platform 12 and the lower edge platform 10 are fixed, and finally, the two ends of the rubber sleeve 4 are fixed, and the rubber sleeve 4 is more conveniently fixed; meanwhile, the cross section of the reinforcing sleeve 11 is annular, so that when the reinforcing sleeve 11 abuts against the upper edge platform 12 and the lower edge platform 10, the pressing force applied to the upper edge platform 12 and the lower edge platform 10 is annular, the lower edge platform 10 and the cover plate 6, the upper edge platform 12 and the inner wall of the mounting groove 3 form a sealing ring structure, and after the rubber sleeve 4 is fixedly mounted, the two ends of the rubber sleeve 4 are hermetically mounted, so that the air flow entering the air holes 2 can flow more smoothly.
The inner wall of the reinforcing sleeve 11 is in sealing fit with the outer wall of the rubber sleeve 4; the outer wall of the rubber sleeve 4 is also provided with a ring groove 14, and two ends of the vent hole 13 are respectively butted with the inflation channel 5 and the ring groove 14. The outer wall of the reinforcing sleeve 11 is in sealing fit with the inner wall of the mounting groove 3, the inner diameter of the reinforcing sleeve 11 is matched with the outer diameter of the rubber sleeve 4, and specifically, two ends of the rubber sleeve 4 are mounted in the reinforcing sleeve 11 in an embedded manner, so that the reinforcing sleeve 11 can effectively support two ends of the rubber sleeve 4, and the two ends of the rubber sleeve 4 are more stably mounted; through seting up annular 14 on rubber sleeve 4 outer wall, at this moment, the inflation chamber is annular 14 promptly, not only is used for storing the air current, and makes rubber sleeve 4 set up the thickness of annular 14 department thinner, makes the partial compliance that rubber sleeve 4 is located annular 14 better, makes the air current that enters into in annular 14 make rubber sleeve 4 bulge to inside more easily, and it is more convenient to the extrusion of rubber sleeve 4 to make things convenient for. By butting the two ends of the vent hole 13 with the cavity and the inflation channel 5 respectively, the airflow entering the inflation channel 5 can directly enter the annular groove 14 through the vent hole 13, and then directly acts on the rubber sleeve 4.
A sealing groove 15 is further formed in the lower surface of the substrate 1, and the sealing groove 15 surrounds the air inlet end of the air inflation channel 5; a sealing ring 16 is further arranged in the sealing groove 15; the sealing groove 15 is a circular groove, the center of the sealing groove 15 and the central axis of the inflation channel 5 are on the same straight line, and the groove bottom of the sealing groove 15 can be a plane or an arc surface; sealing washer 16 is O type sealing washer 16, and sealing washer 16's extreme lower position is not higher than the extreme lower position along platform 10 down, when apron 6 compresses tightly on base plate 1, sealing washer 16 is compressed tightly fixedly, make inflation inlet 8 be sealed butt joint with inflation channel 5, prevent effectively that the air current from producing when getting into inflation channel 5 and leaking, the volume of the air current of guaranteeing to enter into annular 14 is more accurate, guarantee that the degree that the rubber sleeve bloated is more accurate, finally make the switching degree and the draught area of bleeder vent 2 more accurate, thereby accurate simulation has out the flow field that the aircraft produced at the flight in-process, guarantee the accuracy of experimental survey.
The cover plate 6 is made of one of 6MnR steel or red copper. When the cover plate 6 is made of red copper, the tensile strength of the cover plate 6 is not less than 315, the elongation of the cover plate 6 is not less than 30, the processing specifications of the cover plate 6 are that the hot working temperature is 650-850 ℃, the annealing temperature is 600-700 ℃, and the low-temperature annealing temperature for eliminating the internal stress is 270-300 ℃, so that the cover plate 6 can be conveniently compressed on the substrate 1, and the quality of the cover plate 6 is ensured.
It is a plurality of bleeder vent 2 is the even interval of multirow and arranges, and the concrete mode of arranging of bleeder vent 2 can set up according to the in service behavior.
The embodiment also provides a transonic velocity test section test method, which comprises the following specific steps:
(1) the method comprises the steps of installing a simulation aircraft on a model support section in a wind tunnel main body loop, specifically, when the simulation aircraft is installed, firstly taking the model support section off a wind tunnel main body, then installing the simulation aircraft on the model support section, and finally installing the model support section with the installed aircraft in the wind tunnel main body loop, thereby realizing the installation of the simulation aircraft.
(2) The test section 17 is installed on the main tunnel body loop of the wind tunnel, specifically, the test section 17 is pushed to the main tunnel body loop of the wind tunnel through a machine tool, and two ends of the test section are respectively fixed with the main tunnel body loop of the tunnel, so that the test section 17 is installed.
(3) And starting a power section of a compressor in the main tunnel body loop of the wind tunnel to enable airflow to flow in the test section and form a flow field in the test section.
(4) When the airflow flows in the test section, the inflation channels 5 are inflated one by one through the air inlets, and the inflation quantity of each inflation channel 5 is designed according to the simulation condition.
Specifically, the pipelines for conveying the air flow are connected to the air charging connectors 9, the air holes 2 in the base plate 1 are divided into a plurality of groups, the opening and closing degrees and the ventilation areas of the air holes 2 in each group meet, namely the air charging channels 5 in the same group can adopt the same air charging pipeline for charging air, and the air flow in the same air charging pipeline firstly enters the air charging connectors 9 in the same group respectively.
(5) The air flow entering the inflation channel 5 enters the ring groove 14 through the vent hole 13.
Specifically, after the air flow enters the inflation connector 9, the air flow enters the inflation channel 5 through the inflation port 8, the air flow entering the inflation channel 5 enters the annular groove 14 through the vent hole 13, the air flow is filled in the annular groove 14, and the air flow entering the annular groove 14 can directly act on the rubber sleeve 4.
(6) The airflow entering the annular groove 14 acts on the rubber sleeve 4, so that each rubber sleeve 4 bulges towards the inside of the rubber sleeve 4 in different degrees, and the ventilation area of each ventilation hole 2 changes.
Specifically, when the air current enters the annular groove 14, the air pressure of the air current in the annular groove 14 is larger, the air current in the annular groove 14 enables the rubber sleeve 4 to be gradually bulged, when the air current entering the annular groove 14 reaches a fixed amount, the rubber sleeve 4 stops continuously bulging, the air current in the annular groove 14 is kept fixed at the moment, the bulging degree of the rubber sleeve 4 is guaranteed, the opening and closing degree and the ventilation area of the air holes 2 are fixed, and the opening and closing degree and the ventilation area of the air holes 2 are prevented from being changed due to gradual shrinkage of the rubber sleeve 4 under a long-time experiment.
(7) Recording the opening-closing ratio and the ventilation area of each air hole 2; specifically, the opening-closing ratio and the ventilation area of the air holes 2 are recorded, the recorded mode can be measured through a sensor arranged on the inner wall of the air holes 2, measured data are transmitted to a controller for recording, data can be recorded on a computer through manual work, and reading of the data in the later-stage calculation process is facilitated.
(8) When the airflow flows in the test section 17, recording the wind speed passing through each air vent 2, and performing the next calculation according to the wind speed recorded in the step 8 and the ventilation area recorded in the step 6; the wind speed of the air holes 2 can be directly recorded by a sensor, so that recorded data are more accurate.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (13)
1. The utility model provides a test device that transonic speed test section switching ratio is adjustable in succession, its characterized in that includes test section (17), test section (17) include upper and lower wall plate (17a) and two lateral wall boards (17c), and all seted up bleeder vent 2 on upper and lower wall plate (17a), and all install the shrink mechanism that changes 2 internal diameters of bleeder vent in every bleeder vent 2.
2. The transonic speed test section opening-closing ratio continuously adjustable test device according to claim 1, characterized in that the upper and lower wall plates (17a) each comprise a plurality of unit plates, a plurality of air holes (2) are uniformly distributed on the plurality of unit plates, and the plurality of unit plates are spliced and fixed one by one.
3. The transonic test section opening-closing ratio continuously adjustable test device according to claim 1 or 2, characterized in that a transparent observation window is installed on each of the two side wall plates (17c), and a plurality of rotating wheels are installed on the bottom surface of the test section (17); both ends of the upper and lower wall plates (17a) have fin structures (17 d).
4. The transonic speed test section opening-closing ratio continuously adjustable test device according to claim 2, characterized in that an installation groove (3) is formed in the inner wall of the vent hole (2), and the contraction mechanism is installed in the installation groove (3).
5. The transonic speed test section opening-closing ratio continuously adjustable test device according to claim 4, characterized in that the unit plate comprises a base plate (1), and the air holes (2) are installed on the base plate (1); the contraction mechanism comprises a rubber sleeve (4) arranged in the mounting groove (3), and the inner wall of the rubber sleeve (4) extends along the inner wall of the air hole (2); and the base plate (17a) is also provided with a plurality of driving structures which drive the rubber sleeves (4) to protrude inwards one by one.
6. The transonic speed test section opening-closing ratio continuously adjustable test device according to claim 5, characterized in that a radial gap is left between the outer wall of the rubber sleeve (4) and the inner wall of the mounting groove (3); the driving structure is an inflation channel (5) arranged on the substrate (1), and the exhaust end of the inflation channel (5) is communicated with the mounting groove (3).
7. The transonic test section opening-closing ratio continuously adjustable test device of claim 6, characterized in that the unit plate further comprises a cover plate (6) covering the lower surface of the base plate (1), and the lower end of the mounting groove (3) penetrates through the lower surface of the base plate (1); air exhaust hole (7) and inflation inlet (8) have still been seted up on apron (6), and air exhaust hole (7) inner wall extends along bleeder vent (2) inner wall, and inflation inlet (8) extend along inflation channel (5).
8. The transonic test section opening-closing ratio continuously adjustable test device of claim 7, characterized in that the cover plate (6) is further provided with inflation connectors (9) corresponding to the inflation ports (8) one by one.
9. The transonic test section open-close ratio continuously adjustable test device of any one of claims 4 to 8, characterized in that the lower end of said rubber sleeve (4) further has an everted lower edge platform (10); the lower end of the mounting groove (3) penetrates through the surface of the base plate (1), and the lower edge platform (10) is tightly pressed between the cover plate (6) and the base plate (1).
10. The transonic speed test section opening-closing ratio continuously adjustable test device according to claim 9, characterized in that the upper end of the rubber sleeve (4) is further provided with an everted upper edge table (12), and the upper edge table (12) is fixed with the inner wall of the mounting groove (3).
11. The transonic speed test section opening-closing ratio continuously adjustable test device according to claim 10, characterized in that a reinforcing sleeve (11) is further sleeved outside the rubber sleeve (4), and an inflation cavity is formed between the reinforcing sleeve (11) and the rubber sleeve (4); the upper end of the reinforcing sleeve (11) is tightly abutted against the upper edge platform (12), and the lower end of the reinforcing sleeve (11) is tightly abutted against the lower edge platforms (12) (10); the reinforcing sleeve (11) is also provided with a vent hole (13) for communicating the inflation cavity with the inflation channel (5).
12. The transonic test section opening-closing ratio continuously adjustable test device according to claim 11, characterized in that the inner wall of the reinforcing sleeve (11) is in sealing fit with the outer wall of the rubber sleeve (4); the outer wall of the rubber sleeve (4) is further provided with a ring groove (14), and two ends of the vent hole (13) are respectively butted with the inflation channel (5) and the ring groove (14).
13. A test method for a transonic velocity test section comprises the following specific steps:
(1) mounting a simulated aircraft on a model support section in a main tunnel body loop of the wind tunnel;
(2) mounting the test section (17) on a main tunnel body loop of the wind tunnel;
(3) starting a power section of a compressor in a main tunnel body loop of the wind tunnel to enable airflow to flow in a test section;
(4) when the airflow flows in the test section, the inflation channels (5) are inflated one by one through the air inlets, and the inflation quantity of each inflation channel (5) is designed according to the simulation condition;
(5) the airflow entering the inflation channel (5) enters the annular groove (14) through the vent hole (13);
(6) the airflow entering the annular groove (14) acts on the rubber sleeves (4), so that each rubber sleeve (4) bulges towards the inside of the rubber sleeve (4) to different degrees, and the ventilation area of each air hole (2) is changed;
(7) recording the opening-closing ratio and the ventilation area of each air hole (2);
(8) when wind flows in the test section (17), the wind speed passing through each vent (2) is recorded, and the next calculation is performed based on the wind speed recorded in step 8 and the vent area recorded in step 6.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113092052A (en) * | 2021-04-09 | 2021-07-09 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Hole wall opening-closing ratio continuous adjustable device applied to transonic wind tunnel test section |
| CN113188751A (en) * | 2021-05-17 | 2021-07-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Transonic wind tunnel optical test section |
| CN114509232A (en) * | 2022-01-20 | 2022-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Modular hole wall device for wind tunnel test |
| CN114993601A (en) * | 2022-08-01 | 2022-09-02 | 中国航空工业集团公司沈阳空气动力研究所 | 2 m 4 wind tunnel groove wall test section |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0027229A1 (en) * | 1979-10-12 | 1981-04-22 | DEUTSCHE FORSCHUNGSANSTALT FÜR LUFT- UND RAUMFAHRT e.V. | Wind tunnel test section |
| CN101050696A (en) * | 2007-05-10 | 2007-10-10 | 河南理工大学 | Bag type paste injection hole sealing device and its hole sealing method |
| CN101507955A (en) * | 2009-03-17 | 2009-08-19 | 江苏大学 | Elastic telescopic pressure-limit current-limit device |
| CN104826888A (en) * | 2015-04-17 | 2015-08-12 | 苏州铭德铝业有限公司 | Air amplifier capable of increasing air flow |
| CN205192693U (en) * | 2015-12-11 | 2016-04-27 | 成都万友滤机有限公司 | End cap is examined to expandable gas |
| CN206862600U (en) * | 2017-07-06 | 2018-01-09 | 沈阳金凯瑞科技有限公司 | A kind of test chamber control device of porosity continuously adjustabe |
| CN109794926A (en) * | 2019-01-24 | 2019-05-24 | 浙江工业大学 | A kind of flexible structure of stiffness variable |
| CN110124462A (en) * | 2019-05-31 | 2019-08-16 | 华侨大学 | A kind of variable cross section guiding device |
-
2019
- 2019-09-30 CN CN201910940370.6A patent/CN110686850B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0027229A1 (en) * | 1979-10-12 | 1981-04-22 | DEUTSCHE FORSCHUNGSANSTALT FÜR LUFT- UND RAUMFAHRT e.V. | Wind tunnel test section |
| CN101050696A (en) * | 2007-05-10 | 2007-10-10 | 河南理工大学 | Bag type paste injection hole sealing device and its hole sealing method |
| CN101507955A (en) * | 2009-03-17 | 2009-08-19 | 江苏大学 | Elastic telescopic pressure-limit current-limit device |
| CN104826888A (en) * | 2015-04-17 | 2015-08-12 | 苏州铭德铝业有限公司 | Air amplifier capable of increasing air flow |
| CN205192693U (en) * | 2015-12-11 | 2016-04-27 | 成都万友滤机有限公司 | End cap is examined to expandable gas |
| CN206862600U (en) * | 2017-07-06 | 2018-01-09 | 沈阳金凯瑞科技有限公司 | A kind of test chamber control device of porosity continuously adjustabe |
| CN109794926A (en) * | 2019-01-24 | 2019-05-24 | 浙江工业大学 | A kind of flexible structure of stiffness variable |
| CN110124462A (en) * | 2019-05-31 | 2019-08-16 | 华侨大学 | A kind of variable cross section guiding device |
Non-Patent Citations (4)
| Title |
|---|
| 冯帅: "矿用注浆封孔器的研制及应用", 《煤矿机械》 * |
| 刘政崇: "《风洞结构设计》", 31 May 2005 * |
| 芮伟: "共轴双驱型开闭比调节装置控制系统", 《兵工自动化》 * |
| 董谊信等: "2.4m* 2.4m引射式跨声速风洞", 《流体力学实验与测量》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113092052A (en) * | 2021-04-09 | 2021-07-09 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Hole wall opening-closing ratio continuous adjustable device applied to transonic wind tunnel test section |
| CN113188751A (en) * | 2021-05-17 | 2021-07-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Transonic wind tunnel optical test section |
| CN113188751B (en) * | 2021-05-17 | 2022-08-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Transonic wind tunnel optical test section |
| CN114509232A (en) * | 2022-01-20 | 2022-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Modular hole wall device for wind tunnel test |
| CN114509232B (en) * | 2022-01-20 | 2023-08-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Hole wall device for modularized wind tunnel test |
| CN114993601A (en) * | 2022-08-01 | 2022-09-02 | 中国航空工业集团公司沈阳空气动力研究所 | 2 m 4 wind tunnel groove wall test section |
| CN114993601B (en) * | 2022-08-01 | 2022-09-30 | 中国航空工业集团公司沈阳空气动力研究所 | 2 m 4 wind tunnel groove wall test section |
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