CN112539909B - Gantry crane device for boundary layer measurement in pulse wind tunnel - Google Patents
Gantry crane device for boundary layer measurement in pulse wind tunnel Download PDFInfo
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- CN112539909B CN112539909B CN202011371355.3A CN202011371355A CN112539909B CN 112539909 B CN112539909 B CN 112539909B CN 202011371355 A CN202011371355 A CN 202011371355A CN 112539909 B CN112539909 B CN 112539909B
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention belongs to the technical field of experimental hydrodynamics, and discloses a gantry crane device for boundary layer measurement in a pulse wind tunnel, which comprises an air inlet channel model, a pressure bent frame and a portal frame in a door frame shape, wherein the portal frame is connected above the air inlet channel model, a cross beam of the portal frame is provided with mortise holes, the upper side of the pressure bent frame is provided with a tenon, the tenon of the pressure bent frame penetrates through the mortise holes of the portal frame to be connected with an upper cover plate, the windward side of the pressure bent frame is provided with probe holes, the leeward side of the pressure bent frame is provided with sensor mounting holes, pressure sensors are connected in the sensor mounting holes, the lower part of the leeward side of the cross beam of the portal frame is connected with a sensor protective cover, and the leeward sides of the portal frame and the cross beam are connected with cable protective covers; the invention solves the problems that pressure sensors interfere with each other in geometric positions when boundary layer pressure measuring points are densely arranged and the pipeline effect is obvious when a longer pitot tube is adopted for connection in the prior art, and is suitable for the research of the parameter measurement test of the boundary layer of the pulse wind tunnel.
Description
Technical Field
The invention relates to the technical field of experimental hydrodynamics, in particular to a gantry crane device for measuring a boundary layer in a pulse wind tunnel.
Background
When the hypersonic aircraft flies, the viscosity of fluid can cause that a boundary layer with the speed gradually changed from zero to the local main flow speed is formed on the surface of a fixed wall when airflow flows through the fixed wall, the existence of the boundary layer can cause the total pressure distortion, the total pressure recovery coefficient reduction, the turbulence degree increase of the airflow of an air inlet channel, even strong boundary layer interference and directly influence the starting performance and the pressure resistance of the air inlet channel, thereby influencing the flight safety of the aircraft. Therefore, how to accurately measure the boundary layer flow field of the air inlet channel so as to determine the flow distribution in the air inlet channel, calculate the air flow loss caused by the boundary layer, and further accurately judge the performance of the air inlet channel becomes an important subject of the wind tunnel test research of the hypersonic air inlet channel and is also an important link of the flow mechanism research of the air inlet channel.
In the research test of the boundary layer measurement of the hypersonic air inlet channel in the pulse wind tunnel, on one hand, due to the limitation of the millisecond-level effective test time of the pulse wind tunnel, a pulse pressure sensor is required to be adopted to ensure that the response time of a pressure measuring point is matched with the millisecond-level effective test time of the wind tunnel; on the other hand, in order to obtain complete boundary layer information, the measuring points on the boundary layer measuring pressure bent frame are arranged as densely as possible. When the boundary layer measuring device is designed, on one hand, due to the requirement of short response time of the pulsating pressure sensor, the distance from the airflow inlet to the pressure sensing surface of the pulsating pressure sensor must be as short as possible so as to reduce the deviation of the pipeline effect on the measuring result; on the other hand, in order to reduce mutual interference of sensors densely arranged in geometry and blockage caused by a local flow field, the sensors need to be connected with the model measuring part through connecting pipes as much as possible, so that the pipeline effect of the pressure measuring points is increased and the response time is delayed. Therefore, the design research of the boundary layer measuring device is developed, the rapid response of the pulsating pressure sensor and the coordination and unification of the dense arrangement of the pressure measuring points on the boundary layer measuring bent are achieved, and the method has important significance for acquiring reliable boundary layer data when an air inlet hypersonic test is developed in a pulse wind tunnel.
The existing air inlet outlet boundary layer measurement test system for a certain airplane scientific research test flight test is characterized in that 3 measurement rakes with 5 isotorus pitot tube measurement heads, 3 measurement rakes with 4 isotorus pitot tube measurement heads and 10 boundary layer total pressure measurement points, and 3 boundary layer total temperature measurement heads with 3 measurement points respectively are arranged on the same circumferential surface of an engine inlet, so that the measurement of the boundary layer air flow pressure of the engine working under various states is realized.
Disclosure of Invention
The invention aims to provide a gantry crane device for boundary layer measurement in a pulse wind tunnel, and aims to solve the problems that pressure sensors interfere with each other in geometric positions when boundary layer pressure measurement points are densely arranged and the pipeline effect is obvious when long pitot tubes are adopted for connection in the prior art.
In order to achieve the above purpose, the invention provides the following technical scheme:
the basic technical scheme provided by the invention is as follows: be used for boundary layer measuring portal crane device in pulse wind-tunnel, including intake duct model, pressure framed bent and portal frame, the portal frame is the door frame form, the portal frame is connected the top of intake duct model, the intake duct model is located the inboard of portal frame coexistence post, pressure framed bent lee face is connected with pressure sensor, the pressure framed bent is connected the inboard of portal frame coexistence post, portal frame lee face still is connected with sensor safety cover and cable safety cover, the sensor safety cover is located pressure sensor's rear side.
The principle of the basic technical scheme is as follows: the pressure bent is installed on the upper right of the air inlet channel model in a hanging mode through the portal frame, the pressure bent is connected with the pressure sensor, the sensor protection cover and the cable protection cover are respectively used for protecting cables of the pressure sensor and the sensor, and the pressure sensor can be guaranteed to normally work. Dense pressure measuring points required by boundary layer measurement are dispersedly distributed on a plurality of pressure bent frames, the adjustment of the positions of the pressure measuring points is realized by freely changing the sequence of the pressure bent frames on a portal frame in the test, the connection between a pressure sensor and a measuring part by using a pitot tube is avoided, the problems of mutual interference of the pressure sensor on the geometric position and obvious pipeline effect caused by the dense distribution requirement of the pressure measuring points are solved, and the boundary layer measurement test is effectively carried out in a pulse wind tunnel.
The beneficial effects of the basic technical scheme are as follows: dense pressure measuring points required by a boundary layer measuring test are dispersedly distributed on a plurality of pressure discharge frames, the pressure discharge frames are independently suspended on a portal frame for free interchange, the spatial positions of the pressure sensors are changed according to the actual need of exchanging the pressure discharge frames for measuring the pressure measuring points of the boundary layer, and the mutual interference of the pressure sensors on the geometric positions is solved; in addition, the pressure sensor is directly connected to the pressure bent, a long connecting pipeline is not arranged between the pressure sensor and the measuring part, obvious pipeline delay is avoided, the pipeline effect is effectively reduced, the compression surface of the air inlet channel model cannot be damaged due to the fact that the pressure bent freely hung on the upper right of the air inlet channel model is fixedly installed, the dense pressure measuring points are distributed on the pressure bent in a scattered mode, geometric interference between sensors of adjacent measuring points on the same bent can be avoided, the bent can be installed in a scattered mode as far as possible due to the fact that the number of the bent is controlled, airflow field blockage formed between the adjacent bent can be effectively prevented, and reliability of measured data is guaranteed.
Preferably, the mortise hole has been seted up to the crossbeam of portal frame, the upside of mortise hole is connected with the upper cover plate, the pressure bent frame is equipped with the tenon, the size of mortise hole equals the size of tenon, the pressure bent frame with the portal frame passes through the connection can be dismantled to the upper cover plate, the pressure bent frame with the local compression face of intake duct model is perpendicular.
Through the arrangement, the pressure bent frame can be conveniently disassembled and assembled to install or disassemble the pressure sensor, the geometric space position of the pressure sensor is guaranteed through position control of the pressure bent frame on the compression surface of the air inlet passage model, and pressure measurement data of all positions are guaranteed to be accurate and reliable.
Preferably, the pressure bent frame is provided with a plurality of mortise holes, the number of the mortise holes corresponds to the number of the pressure bent frame, and the plurality of pressure bent frames are independently suspended and freely exchanged.
Through the arrangement, the pressure bent frames are connected at the same time and freely exchanged, so that the problem of mutual interference of the sensors in the geometric position is further solved; in addition, a plurality of pressure sensors are arranged and connected on the pressure bent frame, so that the number of boundary layer pressure measuring points is effectively increased, the dense arrangement of the measuring points is realized, the measurement of parameters of the boundary layer is realized, and the further research on the flow mechanism of the air passage is facilitated.
Preferably, the front end of the portal frame-shaped windward side is in a sharp wedge shape, and the contact surface profile of the inner side of the portal frame two vertical columns and the air inlet channel model is consistent with the local profile of the two side walls of the air inlet channel model.
Through the arrangement, the sharp wedge-shaped portal frame windward side avoids strong detached shock waves formed when air flow passes through the portal frame from interfering a local flow field, so that the air flow can smoothly flow, and the authenticity of measured data is further improved; the contact surface contour of the inner sides of the two vertical columns of the portal frame and the air inlet model is consistent with the local contour of the two side walls of the air inlet model, so that the portal crane device is reliably fixed at the upper right side of the air inlet model, the phenomenon that the air flow flows through the gap between the contact surfaces between the two vertical columns of the portal frame and the two side walls of the air inlet model to interfere the local flow field is avoided, and the influence on the flowing air flow can be effectively avoided.
Preferably, the angle of the wedge is 30 °.
With the arrangement, interference to the local flow field is minimized.
Preferably, the windward side of pressure framed bent is the sharp wedge of axial symmetry, the probe hole has been seted up to the sharp arris of the sharp wedge of axial symmetry, the axis of probe hole is parallel with the local incoming flow of probe opening point department, the bullet head has been arranged on the stand that pressure framed bent and axial symmetry sharp wedge meet, the stand width between the bullet head equals the width of the bottom stand of axial symmetry sharp wedge, the leeward side of pressure framed bent is the plane, the leeward side has seted up the sensor mounting hole, pressure sensor with the sensor mounting hole is connected, the bullet head, probe hole and the coincidence of the axis of the sensor mounting hole three of pressure.
Through the arrangement, only the probe of the sensor is arranged on the windward side to serve as the inlet of the boundary layer pressure measurement detection airflow, and the body of the pressure sensor is arranged on the leeward side, so that the strong interference of bow shock waves generated when the head of the pressure sensor is directly exposed in the detection airflow to the measurement airflow and the strong impact of the detection airflow to the head of the pressure sensor to damage the pressure sensing element of the sensor are avoided; the pressure bent frame windward side is in an axisymmetric sharp wedge shape, so that strong interference of strong detached shock waves generated on the pressure bent frame windward side to flowing air flow is avoided, and the truth and reliability of detection data are further ensured; the bullet heads distributed on the upright post connected with the pressure bent frame and the axisymmetric wedge ensure that a sensor and a sensor protective cover are conveniently installed at the position of the bullet heads and avoid the phenomenon that a reverse step is formed in the bullet head area to interfere with a local flow field; the width of the upright post between the bullet heads is equal to that of the bottom upright post of the axisymmetric sharp wedge, so that the space between the pressure bent frames and the space between the pressure sensors are ensured to be as wide as possible, the blockage of the flow fields of the pressure bent frames and the pressure sensors is reduced, and the real reliability of the detection data is ensured again.
Preferably, the angle of the axisymmetric wedge is 60 °.
Through the arrangement, the obvious pipeline effect caused by the fact that the length between the probe inlet and the pressure sensing element of the pressure sensor is lengthened due to the fact that the angle of the pointed wedge is too small is avoided, meanwhile, the phenomenon that shock waves are too strong due to the fact that the angle of the pointed wedge is too large is also avoided, and strong interference on local airflow is weakened.
The invention provides a method for arranging pressure measuring points of a gantry crane device for measuring a boundary layer in a pulse wind tunnel, which comprises the following steps:
p1, distributing the boundary layer pressure measuring points which are densely distributed on a plurality of pressure bent frames (5) in a scattered manner;
p2, firstly, sequencing the pressure bent frames (5), and then sequencing all boundary layer pressure measuring points according to the sequence that the distance between the boundary layer pressure measuring points and the local surface of the air inlet channel model (1) is from small to large;
p3, carrying out first round of measurement point arrangement: matching the serial numbers of the measuring points with the serial numbers of the pressure bent frames, only arranging one measuring point on each pressure bent frame (5), and finishing the first round of measuring point arrangement;
and P4, carrying out next round of measurement point arrangement: matching the serial numbers of the measuring points with the next serial number of the corresponding pressure bent, only arranging one measuring point on each pressure bent (5), and finishing the arrangement of the measuring points in the round;
p5, repeating the arrangement mode of the P4, and arranging all the measuring points on the bent frame (5);
p6, and the channels formed by any two adjacent pressure bent frames (5) do not cause local flow field blockage.
The invention also provides an installation method of the gantry crane device for measuring the boundary layer in the pulse wind tunnel, which comprises the following steps:
z1, connecting the upper end of each pressure bent frame with a beam of a portal frame, and suspending the lower ends of the pressure bent frames;
z2, installing a pressure sensor and a sensor protection cover on the pressure bent frame, and protecting cables of the sensor by using the cable protection cover;
and Z3, fixing the gantry crane device at the downstream of the outlet section of the air inlet model to perform a boundary layer parameter measurement test.
Drawings
FIG. 1 is a schematic structural diagram of a gantry crane device for boundary layer measurement in a pulse wind tunnel according to the present invention;
FIG. 2 is an explosion diagram of a gantry crane device for boundary layer measurement in a pulsed wind tunnel according to the present invention;
the names of corresponding labels in the drawings are:
the device comprises an air inlet channel model 1, a first screw 2, a positioning pin 3, a pressure sensor 4, a pressure bent frame 5, a portal frame 6, an upper cover plate 7, a second screw 8, a sensor protection cover 9, a third screw 10, a fourth screw 11, a first cable protection cover 12, a second cable protection cover 13 and a third cable protection cover 14.
Detailed Description
The invention is described in further detail below with reference to the following figures and embodiments:
as shown in fig. 1 and fig. 2, the gantry crane device for boundary layer measurement in a pulse wind tunnel comprises an air inlet model 1, four pressure bent frames 5, a gantry frame 6, a first screw 2, a positioning pin 3, a second screw 8, a third screw 10 and a fourth screw 11, wherein the gantry frame 6 is in a door frame shape, the contact surface profile between the inner sides of two vertical columns of the gantry frame 6 and the air inlet model 1 is consistent with the local profile of two side walls of the air inlet model 1, the gantry frame 6 is connected above the air inlet model 1 through the first screw 2 and the positioning pin 3, the air inlet model 1 is arranged at the inner sides of two vertical columns of the gantry frame 6, the front end of the windward side of the gantry frame 6 is in a 30-degree pointed wedge shape, four mortise holes are arranged on a cross beam of the gantry frame 6, tenons are arranged on the upper sides of the four pressure bent frames 5, the size of the mortise holes is equal to that of the tenons, the tenons of the pressure bent frames 5 pass through the mortise holes and are connected with an upper cover plate 7, the upper cover plate 7 is connected with a cross beam of a portal frame 6 through a second screw 8, the lower sides of the pressure bent frames 5 are suspended and are vertical to a local compression surface of the air inlet channel model 1, four pressure bent frames 5 are freely exchanged, the windward side of each pressure bent frame 5 is in an axisymmetric sharp wedge shape with an angle of 60 degrees, probe holes are formed in sharp edges of the axisymmetric sharp wedge shape, the axes of the probe holes are parallel to the axes of spray pipes of the pulse wind tunnel, the leeward side of each pressure bent frame 5 is a plane, sensor mounting holes are formed in the leeward side of each pressure bent frame 5, pressure sensors 4 are connected in the sensor mounting holes, pressure probes penetrate through the probe holes of each pressure bent frame 5, bullet heads are fixedly connected to the bottoms of the axisymmetric sharp wedge-shaped sharp edges, the widths of the upright columns among the bullet heads are equal to the widths of the upright columns at the bottoms of the sharp wedges, the axes of the bullet heads, the probe holes and the sensor mounting holes coincide, and the tail ends of the bullet heads are used for mounting the pressure sensors 4, the back of portal frame 6 is connected with sensor safety cover 9 through third screw 10, and pressure sensor 4's rear side is located to sensor safety cover 9, and the left side, the right side and the upside of the leeward side of portal frame 6 all are connected with first cable safety cover 12, second cable safety cover 13 and third cable safety cover 14 respectively through fourth screw 11.
The method for arranging the pressure measuring points of the gantry crane device for measuring the boundary layer in the pulse wind tunnel comprises the following specific steps:
p1, distributing the boundary layer pressure measuring points which are densely distributed on a plurality of pressure bent frames 5 in a dispersed manner;
p2, numbering the pressure bent frames 5 in sequence to obtain a first pressure bent frame, a second pressure bent frame, a third pressure bent frame and a fourth pressure bent frame; numbering all boundary layer pressure measuring points in sequence according to the sequence of the distances from the boundary layer pressure measuring points to the local surface of the air inlet channel model 1 from small to large to obtain a first pressure measuring point, a second pressure measuring point, a third pressure measuring point and a fourth pressure measuring point;
p3, carrying out first round of measurement point arrangement: arranging the first measuring points on a first pressure bent frame; arranging the second measuring points on a second pressure bent frame; arranging the third measuring points on a third pressure bent frame, and arranging the fourth measuring points on a fourth pressure bent frame; each pressure bent 5 is arranged and only has one measuring point, and the first round of measuring point arrangement is finished;
and P4, carrying out next round of measurement point arrangement: arranging the second measuring points on the first pressure bent frame 5, arranging the third measuring points on the second pressure bent frame, continuing the arrangement until all the pressure bent frames 5 are arranged, and finishing the measuring point arrangement;
p5, repeating the arrangement mode until all the measuring points are arranged on the pressure bent frame 5; the arrangement mode can ensure the maximization of the distance between the adjacent pressure measuring points on any pressure bent frame 5, thereby effectively avoiding the interference of the pressure sensors 4 on the same pressure bent frame 5 on the geometric position.
P6, the channel formed by any two adjacent pressure bent frames 5 does not cause the blockage of the local flow field, the advantage of a plurality of pressure bent frames 5 is beneficial to avoiding the interference of the pressure sensors 4 on the same pressure bent frame 5, but the more the number of the pressure bent frames 5 is, the better, because the excessive pressure bent frames 5 easily cause the blockage of the flow channel between the adjacent pressure bent frames 5.
The installation method of the gantry crane device for measuring the boundary layer in the pulse wind tunnel comprises the following specific steps:
z1, connecting the upper end of each pressure bent frame 5 with a beam of a portal frame 6, and suspending the lower ends of the pressure bent frames 5;
z2, installing a pressure sensor 4 and a sensor protection cover 9 on the pressure bent frame 5, and protecting cables of the sensor 4 by cable protection covers 12-14;
and Z3, fixing the gantry crane device 6 at the downstream of the outlet section of the air inlet channel model 1 to perform a boundary layer parameter measurement test.
The above description is only an example of the present invention, and the common general knowledge of the technical solutions or characteristics known in the solutions is not described herein too much. It should be noted that, for those skilled in the art, without departing from the technical solution of the present invention, several variations and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (3)
1. Be used for boundary layer measuring gantry crane device in the pulse wind tunnel, its characterized in that: the device comprises an air inlet channel model (1), a pressure bent frame (5) and a portal frame (6), wherein the portal frame (6) is in a door frame shape, the portal frame (6) is connected above the air inlet channel model (1), the air inlet channel model (1) is arranged on the inner sides of two columns of the portal frame (6), the leeward side of the pressure bent frame (5) is connected with a pressure sensor (4), the pressure bent frame (5) is connected on the inner sides of the two columns of the portal frame (6), the leeward side of the portal frame (6) is also connected with a sensor protection cover (9) and a cable protection cover, and the sensor protection cover (9) is arranged on the rear side of the pressure sensor (4);
the device comprises a portal frame (6), a pressure bent frame (5), a portal frame (1) and a portal frame, wherein a mortise is formed in a cross beam of the portal frame (6), an upper cover plate (7) is connected to the upper side of the mortise, a tenon is arranged on the pressure bent frame (5), the size of the mortise is equal to that of the tenon, the pressure bent frame (5) is detachably connected with the portal frame (6) through the upper cover plate (7), and the pressure bent frame (5) is perpendicular to a local compression surface of the air inlet channel model (1);
the number of the pressure bent frames (5) is multiple, the number of the mortise holes corresponds to that of the pressure bent frames (5), and the pressure bent frames (5) are independently suspended and freely exchanged;
the front end of a doorframe-shaped windward surface of the portal frame (6) is in a sharp wedge shape of 30 degrees, and the contour of the contact surface between the inner sides of two vertical columns of the portal frame (6) and the air inlet channel model (1) is consistent with the local contour of two side walls of the air inlet channel model (1);
the windward side of pressure framed bent (5) is 60 axisymmetric point wedge forms, the probe hole has been seted up to the sharp arris of axisymmetric point wedge form, the axis of probe hole is parallel with the local incoming flow of probe opening point department, pressure framed bent (5) with bullet heads have been arranged on the stand that the axisymmetric point wedge meets, the stand width between the bullet head equals the width of the bottom stand of axisymmetric point wedge, the leeward side of pressure framed bent (5) is the plane, the sensor mounting hole has been seted up to the leeward side, pressure sensor (4) with the sensor mounting hole is connected, wear to be equipped with pressure probe in the probe hole of pressure framed bent (5), bullet head probe hole with sensor mounting hole three's axis coincidence.
2. The arrangement method of the pressure measuring points of the gantry crane device for measuring the boundary layer in the pulse wind tunnel according to claim 1, which is characterized by comprising the following steps:
p1, distributing the boundary layer pressure measuring points which are densely distributed on a plurality of pressure bent frames (5) in a scattered manner;
p2, firstly, sequencing the pressure bent frames (5), and then sequencing all boundary layer pressure measuring points according to the sequence that the distance between the boundary layer pressure measuring points and the local surface of the air inlet channel model (1) is from small to large;
p3, carrying out first round of measurement point arrangement: matching the serial numbers of the measuring points with the serial numbers of the pressure bent frames, only arranging one measuring point on each pressure bent frame (5), and finishing the first round of measuring point arrangement;
and P4, carrying out next round of point arrangement: matching the serial numbers of the measuring points with the next serial number of the corresponding pressure bent, only arranging one measuring point on each pressure bent (5), and finishing the arrangement of the measuring points in the round;
p5, repeating the arrangement mode of the P4, and arranging all the measuring points on the pressure bent frame (5);
p6, and the channel formed by any two adjacent pressure bent frames (5) does not cause the blockage of the local flow field.
3. The method for installing the gantry crane device for measuring the boundary layer in the pulse wind tunnel according to claim 1, characterized by comprising the following steps:
z1, connecting the upper end of each pressure bent frame (5) with a beam of a portal frame (6), and suspending the lower end of each pressure bent frame (5);
z2, installing a pressure sensor (4) and a sensor protection cover (9) on the pressure bent frame (5), and protecting a cable of the pressure sensor (4) by using the cable protection cover;
and Z3, fixing the portal frame (6) at the downstream of the outlet section of the air inlet channel model (1) to perform a boundary layer parameter measurement test.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103063399A (en) * | 2013-01-09 | 2013-04-24 | 浙江大学 | Framed bent device for wind tunnel flow field |
| CN203024954U (en) * | 2013-01-09 | 2013-06-26 | 浙江大学 | Frame bent device for flow field test of wind tunnel |
| CN107014582A (en) * | 2017-05-18 | 2017-08-04 | 西北工业大学 | A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system |
| CN108844706A (en) * | 2018-08-21 | 2018-11-20 | 北京化工大学 | A kind of array multi-function windtunnel drive system |
| CN109765029A (en) * | 2018-12-30 | 2019-05-17 | 北京信息科技大学 | It is a kind of that device is surveyed based on the flow field school of fiber grating and F-P microcavity |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001201414A (en) * | 2000-01-20 | 2001-07-27 | Smc Corp | Combined sensor and flow controller provided with the combined sensor |
| GB2452026B (en) * | 2007-07-27 | 2010-05-05 | Assystem | Instrumentation rake and aerofoil having instrumentation elements and method of manufacture therefor |
| CN103033335B (en) * | 2012-12-12 | 2015-01-07 | 中国航空工业空气动力研究院 | Slide rail type airplane model rear body release wind tunnel test device |
| CN205581136U (en) * | 2016-01-06 | 2016-09-14 | 中国建筑科学研究院 | Framed bent is measured to transient state multiple spot wind speed |
| FR3050823B1 (en) * | 2016-04-28 | 2018-04-20 | Safran Aircraft Engines | DEVICE FOR MEASURING AERODYNAMIC SIZES FOR PLACING IN A FLOWING VEHIC OF A TURBOMACHINE |
| CN107576471A (en) * | 2017-08-22 | 2018-01-12 | 甘肃省治沙研究所 | It is a kind of to be used for collection wind speed and the horizontal wind speed instrument support of vertically adjustable multipoint observation in wind-tunnel |
| CN207423489U (en) * | 2017-11-13 | 2018-05-29 | 中国航天空气动力技术研究院 | A kind of new pressure measurement rake for Boundary Layer on Flat Plate measurement |
| CN208171557U (en) * | 2018-05-21 | 2018-11-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of electron number densitiy measurement probe bent device |
| CN209241360U (en) * | 2018-11-20 | 2019-08-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of Multi probe water-cooled test framed bent |
| CN110441023B (en) * | 2019-07-30 | 2022-07-29 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Miniature measurement rake for wind tunnel test and 3D printing method thereof |
| CN111855135B (en) * | 2020-07-30 | 2022-07-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel airflow average speed measuring bent frame and measuring method |
-
2020
- 2020-11-30 CN CN202011371355.3A patent/CN112539909B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103063399A (en) * | 2013-01-09 | 2013-04-24 | 浙江大学 | Framed bent device for wind tunnel flow field |
| CN203024954U (en) * | 2013-01-09 | 2013-06-26 | 浙江大学 | Frame bent device for flow field test of wind tunnel |
| CN107014582A (en) * | 2017-05-18 | 2017-08-04 | 西北工业大学 | A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system |
| CN108844706A (en) * | 2018-08-21 | 2018-11-20 | 北京化工大学 | A kind of array multi-function windtunnel drive system |
| CN109765029A (en) * | 2018-12-30 | 2019-05-17 | 北京信息科技大学 | It is a kind of that device is surveyed based on the flow field school of fiber grating and F-P microcavity |
Non-Patent Citations (1)
| Title |
|---|
| 高超声速通气模型喷管出口气流参数测量试验技术研究;舒海峰等;《实验流体力学》(第06期);全文 * |
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