CN116448373B - Wind tunnel test device using sub-cross supersonic flow field optimal region simultaneously - Google Patents
Wind tunnel test device using sub-cross supersonic flow field optimal region simultaneously Download PDFInfo
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- CN116448373B CN116448373B CN202310705581.8A CN202310705581A CN116448373B CN 116448373 B CN116448373 B CN 116448373B CN 202310705581 A CN202310705581 A CN 202310705581A CN 116448373 B CN116448373 B CN 116448373B
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- G—PHYSICS
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- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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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
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Abstract
A wind tunnel test device using a sub-cross supersonic flow field optimal region simultaneously belongs to the technical field of aviation aerodynamic wind tunnel test. The ultrasonic testing device comprises a wind tunnel test section and a model support section, wherein the downstream end of the wind tunnel test section is a super-expansion section, the model support section is arranged on the super-expansion section, and the wind tunnel test section can be respectively applied to a sub-transonic speed test and a supersonic speed test. The invention aims to solve the problem of position movement in the model rotation process when a model protection mechanism is needed because of larger impact load applied to the model during driving in a supersonic test of a temporary impact wind tunnel and the problem of position movement during model rotation when a connecting rod mechanism is adopted.
Description
Technical Field
The invention relates to a wind tunnel test device for simultaneously using a sub-cross supersonic flow field optimal region, and belongs to the technical field of aviation aerodynamic wind tunnel tests.
Background
Aerodynamics is a basic science for developing aerospace technology and other industrial technologies, and wind tunnel experiments are one of basic methods for aerodynamics research. The test section and the model support section are one of important parts of the wind tunnel, the test section is a place where the model performs wind tunnel test, the model support section is an important mechanism for installing the model and guaranteeing the test posture of the model, and the abortion quality of the test section and the functions of the model support section are important guarantees for obtaining reliable results of wind tunnel experiments.
In the supersonic test of the temporary impact wind tunnel, the impact load applied to the model is large during driving, and a model protection mechanism is needed. However, when the model protection mechanism is a model support and adopts a connecting rod mechanism, the problem of position movement in the model rotation process also needs to be solved.
Therefore, it is needed to design a wind tunnel test device that uses the optimal region of the sub-cross supersonic flow field at the same time to meet the use requirement of wind tunnel test, so as to solve the above technical problems.
Disclosure of Invention
The present invention has been developed to address the problem of movement of the position during rotation of the model in the supersonic test of a temporary impact wind tunnel, where the model is subjected to a large impact load during driving, a model protection mechanism is required, and a link mechanism is employed, and a brief overview of the present invention is given below to provide a basic understanding of some aspects of the present invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or critical elements of the invention or to delineate the scope of the invention.
The technical scheme of the invention is as follows:
the utility model provides a wind tunnel test device that uses sub-supersonic flow field optimum district simultaneously, includes wind tunnel test section and model support section, and the low reaches of wind tunnel test section is super section that expands, and super section that expands installs model support section, model support section includes balanced cylinder, lever, layer board, joint, linear guide, rocking arm, transfer line, first connecting rod, first pivot, the second connecting rod, second pivot and servo motor cylinder, first connecting rod, second connecting rod, joint and rocking arm constitute four bar mechanism, and install on the layer board through first pivot and second pivot, the layer board passes through linear guide and super section that expands establish sliding connection, servo motor cylinder and balanced cylinder side by side fixed mounting are on super section that expands, and the output of both is all established with the layer board top and is connected, the lever is rotated and is installed on the layer board, lever one end is rotated and is installed on super section that expands, the other end is articulated with transfer line one end, the transfer line other end is articulated with rocking arm, connect the end and go into inside the wind tunnel test section after passing super section entry.
Preferably: the wind tunnel test section comprises a resident chamber, an insert and a positioning mechanism, wherein the insert is arranged in the resident chamber, and the front end and the rear end of the resident chamber are respectively connected with external components positioned at the upstream and the downstream of the wind tunnel test section through the positioning mechanism.
Preferably: the parking room comprises a shell, a spring support, a middle beam, a trolley, a hydraulic cylinder, a guide rail and a rail, wherein the guide rail is arranged on the trolley, the middle beam is in sliding connection with the guide rail, two ends of the hydraulic cylinder are respectively connected with the middle beam and the trolley, the shell is mounted on the top of the middle beam through the spring support, and the plug-in unit is arranged inside the shell through the rail.
Preferably: the plug-in components include wallboard angle adjustment mechanism, upper and lower wallboard, side wall board, front end plate, wheel, optical window, little optical window and half mould mechanism, and upper and lower wallboard and side wall board constitute rectangular frame structure jointly to set up in the room inside, all be equipped with optical window and little optical window on upper and lower wallboard and the side wall board, the side wall board bottom has the wheel, is provided with half mould mechanism on the side wall board, and upper and lower wallboard front side passes through front end plate and is connected with the room front side establishment, and upper and lower wallboard rear side passes through wallboard angle adjustment mechanism and is connected with the room rear side establishment.
Preferably: the positioning mechanism comprises a positioning pin, lugs, pin seats and a positioning hydraulic cylinder, wherein the positioning hydraulic cylinder is arranged at the top of the positioning pin, the lugs are inserted into the pin seats, and the bottoms of the positioning pin penetrate through the lugs positioned in the pin seats after penetrating into the pin seats.
Preferably: the residence chamber is provided with an escalator and a working platform.
Preferably: the wind tunnel test section comprises a second front end plate, a second rear end plate, a second side wall plate, a second trolley, a positioning mechanism, a second upper wall plate, a second lower wall plate, a second upper cavity wall plate, a second lower cavity wall plate, a second adjusting mechanism, a second upper resident chamber, a second lower resident chamber and a model protection mechanism, wherein the second upper wall plate, the second lower wall plate and the second side wall plate jointly form a test area of the model, the second side wall plate, the second upper wall plate and the second upper cavity wall plate form a second upper resident chamber of the test area, the second side wall plate, the second lower wall plate and the second lower cavity wall plate form a second lower resident chamber of the test area, the front end plate and the rear end plate of the test area are respectively fixedly provided with the second front end plate and the second rear end plate, the second front end plate and the second rear end plate are respectively connected with external components positioned at the upper and lower stream of the wind tunnel test section through the positioning mechanism, the rear sides of the second upper wall plate and the second lower wall plate respectively form a connection with the second rear end plate through the second adjusting mechanism, the second upper end plate and the second upper wall plate and the second lower wall plate are respectively arranged symmetrically in the test area and the second upper resident chamber and the model protection mechanism are respectively arranged at the two sides of the model.
The invention has the following beneficial effects:
1. the wind tunnel test section can be respectively applied to a sub-transonic test and a supersonic test, and the two tests share one model support section, so that the whole wind tunnel test device has stronger comprehensiveness, more flexible structure and higher practical value;
2. the invention sets up the model protection mechanism when carrying on the supersonic test, after the wind tunnel starts, the real-time protection model, avoid in supersonic test of the temporary impact wind tunnel, the impact load that the test model receives is great while driving, cause the damage, influence the test result data;
3. the model support disclosed by the invention comprehensively adopts the lifting supporting plate, the lever mechanism principle and the four-bar mechanism principle, so that the test model can move up and down in the rotating process, the rotating center of the test model is kept on the axis of the wind tunnel, and meanwhile, the movement of the rotating center of the test model in the axis direction is controlled within a certain range, so that the test model is always positioned in an optimal flow field area, and the aim that the test can be carried out by utilizing the optimal flow field area when the test model is in subspan supersonic speed is realized.
Drawings
FIG. 1 is a mating installation view of a first embodiment of the present invention;
FIG. 2 is a perspective view of a wind tunnel test section according to a first embodiment of the present invention;
FIG. 3 is a side view of a wind tunnel test section according to a first embodiment of the present invention;
FIG. 4 is a front view of a wind tunnel test section according to a first embodiment of the present invention;
FIG. 5 is a rear view of a wind tunnel test section according to a first embodiment of the present invention;
FIG. 6 is a perspective view of an insert according to a first embodiment of the invention;
FIG. 7 is a mating installation view of a positioning mechanism according to a first embodiment of the present invention;
FIG. 8 is a mating installation view of a second embodiment of the present invention;
FIG. 9 is a perspective view of a wind tunnel test section according to a second embodiment of the present invention;
FIG. 10 is a mating installation view of a wind tunnel test section according to a second embodiment of the present invention;
FIG. 11 is a schematic structural view of a mold carrier section of the present invention;
fig. 12 is a view of the use of the model scaffold segment of the present invention.
In the figure: the test section comprises a 1-0 wind tunnel test section, a 2-0 model support section, a 1-parking chamber, a 2-plug, a 3-positioning mechanism, a 4-shell, a 5-spring support, a 6-middle beam, a 7-trolley, an 8-hydraulic cylinder, a 9-escalator and a working platform, a 10-guide rail, a 11-track, a 12-wallboard angle adjusting mechanism, a 13-upper and lower wallboard, a 14-side wallboard, a 15-front end plate, a 16-wheel, a 17-optical window, a 18-small optical window, a 19-half mold mechanism, a 20-positioning pin, a 21-lug, a 22-pin seat, a 23-positioning hydraulic cylinder, a 24-second front end plate, a 25-second rear end plate, a 26-second side wallboard, a 27-second trolley, a 28-servo electric cylinder, a 29-second upper wallboard, a 30-second lower wallboard, a 31-second upper cavity wallboard, a 32-second lower cavity wallboard, a 33-second adjusting mechanism, a 34-second upper parking chamber, a 35-second lower parking chamber, a 36-protection mechanism, a 37-38, a 39-super-lever, a 40-expansion joint, a 45-second rotary shaft, a 45-rotary shaft, a 46-guide rail, a 48-second guide rail, a 45-upper rotating shaft, a 45-rotating shaft, a 48-second guide rail, a 45-rotating shaft, a 46-and a guide rail.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The connection mentioned in the invention is divided into a fixed connection and a detachable connection, wherein the fixed connection is a conventional fixed connection mode such as a non-detachable connection including but not limited to a hemmed connection, a rivet connection, an adhesive connection, a welded connection and the like, the detachable connection is a conventional detachable mode such as a threaded connection, a snap connection, a pin connection, a hinge connection and the like, and when a specific connection mode is not limited explicitly, at least one connection mode can be found in the conventional connection mode by default, so that the function can be realized, and a person skilled in the art can select the device according to needs. For example: the fixed connection is welded connection, and the detachable connection is hinged connection.
Embodiment one: 1-7 and 11-12, a wind tunnel test device using a sub-span supersonic flow field optimal region simultaneously in the embodiment comprises a wind tunnel test section 1-0 and a model support section 2-0, wherein the downstream end of the wind tunnel test section 1-0 is a super-expansion section 39, and the super-expansion section 39 is provided with the model support section 2-0;
when a sub-transonic test is carried out, the wind tunnel test section 1-0 is a transonic test section, the sub-transonic test section comprises a resident chamber 1, an insert 2 and a positioning mechanism 3, the insert 2 is arranged in the resident chamber 1, the front end and the rear end of the resident chamber 1 are respectively connected with external components positioned at the upstream and the downstream of the wind tunnel test section 1-0 through the positioning mechanism 3, and the transonic test section can be replaced by the insert 2 with different design according to test requirements.
The parking room 1 comprises a shell 4, spring supports 5, a middle beam 6, a trolley 7, a hydraulic cylinder 8, a guide rail 10 and a rail 11, wherein the guide rail 10 is arranged on the trolley 7, the middle beam 6 is in sliding connection with the guide rail 10, two ends of the hydraulic cylinder 8 are respectively connected with the middle beam 6 and the trolley 7, the shell 4 is arranged at the top of the middle beam 6 through the four spring supports 5, a test section is accurately positioned under the action of a front-rear positioning mechanism, and an escalator and a working platform 9 are arranged on the parking room 1 and used for equipment maintenance above. The plug-in components 2 pass through track 11 to be set up in casing 4 inside, and casing 4 and intermediate beam 6 can follow axial displacement under the effect of pneumatic cylinder 8, and the overhead traveling crane 7 can make casing 4 and intermediate beam 6 follow perpendicular to axis direction to carry out the test section and change.
The plug-in unit 2 comprises a wallboard angle adjusting mechanism 12, an upper wallboard 13, a lower wallboard 13, a side wallboard 14, a front end plate 15, wheels 16, an optical window 17, a small optical window 18 and a half mould mechanism 19, wherein the upper wallboard 13, the lower wallboard 13 and the side wallboard 14 jointly form a rectangular frame structure and are arranged in the residence chamber 1, the upper wallboard 13, the lower wallboard 13 and the side wallboard 14 are respectively provided with the optical window 17 and the small optical window 18 for various optical tests, the wheels 16 are arranged at the bottom of the side wallboard 14 and are used for replacing the plug-in unit 2, the half mould mechanism 19 is arranged on the side wallboard 14 and used for half mould and wing type tests, the front sides of the upper wallboard 13 and the lower wallboard 13 are connected with the front side of the residence chamber 1 through the front end plate 15, the rear sides of the upper wallboard 13 and the residence chamber 1 are connected through the wallboard angle adjusting mechanism 12, and the wallboard angle adjusting mechanism 12 comprises a motor and a spiral lifter, and the motor drives the spiral lifter to realize telescopic movement, so that the relative positions of the upper wallboard 13 and the lower wallboard are driven.
Different external parts are further connected to the two sides of the upstream and downstream of the wind tunnel test section 1-0, a spray pipe is arranged on the upstream of the wind tunnel test section 1-0, the upstream of the wind tunnel test section 1-0 is connected with the outlet end face of the spray pipe through a positioning mechanism 3, and the downstream of the wind tunnel test section 1-0 is connected with other external parts through the positioning mechanism 3.
The positioning mechanism 3 adopts a plug pin mechanism, and comprises a positioning pin 20, lugs 21, pin seats 22 and a positioning hydraulic cylinder 23, wherein the positioning hydraulic cylinder 23 is arranged at the top of the positioning pin 20, the lugs 21 are inserted into the pin seats 22, and the bottoms of the positioning pin 20 penetrate through the lugs 21 positioned in the pin seats 22 after penetrating into the pin seats 22.
During positioning, the lug 21 is arranged on the front side of the wind tunnel test section 1-0, the tail of the external part positioned on the upstream of the wind tunnel test section 1-0 is sequentially provided with the positioning hydraulic cylinder 23 and the pin seat 22 from top to bottom, when the wind tunnel test section 1-0 is driven by the hydraulic cylinder 8 to lean against the tail of the upstream external part, the lug 21 on the front side of the wind tunnel test section 1-0 is inserted into the pin seat 22 on the tail of the external part, the positioning hydraulic cylinder 23 drives the positioning pin 20 to penetrate through the lug 21, positioning and installation of the front side of the wind tunnel test section 1-0 on the upstream external part are realized, and the external part positioned on the downstream of the wind tunnel test section 1-0 is arranged in the same way as the upstream of the wind tunnel test section.
The model support section 2-0 comprises a balance cylinder 37, a lever 38, a support plate 40, a test model 41, a joint 42, a linear guide rail 43, a rotating arm 44, a transmission rod 45, a first connection rod 46, a first rotating shaft 47, a second connection rod 48, a second rotating shaft 49 and a servo motor cylinder 28, wherein the first connection rod 46, the second connection rod 48, the joint 42 and the rotating arm 44 form a four-bar mechanism, the four-bar mechanism is arranged on the support plate 40 through the first rotating shaft 47 and the second rotating shaft 49, the support plate 40 is in sliding connection with the super-expansion section 39 through the linear guide rail 43, namely the linear guide rail 43 is fixedly arranged on the shell 4, the support plate 40 is in sliding fit with the linear guide rail 43, the servo motor cylinder 28 and the balance cylinder 37 are fixedly arranged on the super-expansion section 39 side by side, the output ends of the servo motor cylinder and the super-expansion section are respectively connected with the top of the support plate 40, the lever 38 is rotatably arranged on the support plate 40, one end of the lever 38 is rotatably arranged on the super-expansion section 39, the other end of the transmission rod 45 is hinged with the rotating arm 44, the end of the joint 42 is hinged, and the end of the super-expansion section 39 penetrates through the inlet of the super-expansion section 39, and then is connected with the test model 41. During operation, the servo electric cylinder 28 is adopted to drive, the motion is transmitted to the supporting plate 40 and the transmission rod 45 through the lever 38, the supporting plate 40 moves up and down along the linear sliding rail 43, the transmission rod 45 drives the rotating arm 44 to rotate around the second rotating shaft 49, and the connecting rod mechanism drives the joint 42 to rotate, so that the continuous change of the attack angle of the test model 41 is realized. Meanwhile, the balance cylinder 37 is added beside the servo motor cylinder 28, so that the weight of the mechanism and the supporting plate can be balanced, the load of the servo motor cylinder 28 is reduced, and the mechanism is prevented from suddenly falling down when the servo motor cylinder 28 is out of control.
The model support section 2-0 adopts a four-bar mechanism for transmission, so that the efficiency of a transmission mechanism is improved, and a lifting supporting plate 40, a lever mechanism principle and a four-bar mechanism principle are adopted, so that the test model 41 can be ensured to move up and down in the rotating process, the rotating center of the test model 41 is kept on the axis of the wind tunnel, and meanwhile, the movement of the rotating center of the test model 41 in the axis direction is controlled within a certain range, so that the test model 41 is always positioned in an optimal flow field area; the servo electric cylinder 28 is adopted for driving, the high-precision linear guide rail 43 is used for limiting, the corner precision of the model support section 2-0 is guaranteed, the balance cylinder 37 is adopted for balancing the weight of the transmission mechanism and the supporting plate 40, the load of the servo electric cylinder 28 is reduced, and the safety of the system is protected.
Embodiment two: 7-12, a wind tunnel test device using a sub-span supersonic flow field optimal region simultaneously in the embodiment comprises a wind tunnel test section 1-0 and a model support section 2-0, wherein the downstream end of the wind tunnel test section 1-0 is a super-expansion section 39, and the super-expansion section 39 is provided with the model support section 2-0;
in the case of a supersonic test, the wind tunnel test section 1-0 is a supersonic test section, which comprises a second front end plate 24, a second rear end plate 25, a second side wall plate 26, a second trolley 27, a positioning mechanism 3, a second upper wall plate 29, a second lower wall plate 30, a second upper chamber wall plate 31, a second lower chamber wall plate 32, a second adjusting mechanism 33, a second upper residence chamber 34, a second lower residence chamber 35 and a model protecting mechanism 36, wherein the second upper wall plate 29, the second lower wall plate 30 and the second side wall plate 26 together form a test area of the model, wherein the second upper wall plate 29 and the second lower wall plate 30 have adjustable wall angles, the second side wall plate 26, the second upper wall plate 29 and the second upper chamber wall plate 31 form a second upper residence chamber 34 of the test area, the second side wall plate 26, the second lower wall plate 30 and the second lower chamber wall plate 32 form a second lower residence chamber 35 of the test area, the front end and the rear end of the test area are respectively and fixedly provided with a second front end plate 24 and a second rear end plate 25, the second front end plate 24 and the second rear end plate 25 are respectively and fixedly connected with external parts positioned at the upstream and the downstream of the wind tunnel test section 1-0 through a positioning mechanism 3, the bottom of the test area is provided with a second trolley 27, the rear sides of a second upper wall plate 29 and a second lower wall plate 30 are respectively and fixedly connected with the second rear end plate 25 through a second adjusting mechanism 33, the wall plate angles of the second upper wall plate 29 and the second lower wall plate 30 are adjusted through the second adjusting mechanism 33, the model protection mechanisms 36 are 2 groups in total, the upper and lower sides are symmetrical, the main body structures of the model protection mechanisms 36 are symmetrically arranged in the second upper resident chamber 34 and the second lower resident chamber 35 respectively, the end parts of the model protection mechanisms 36 respectively extend out of the second upper resident chamber 34 and the second lower resident chamber 35 to be arranged at the upper side and the lower side of the test model 41, the model protection mechanisms 36 comprise electric cylinders and supporting arms, the electric cylinder is arranged inside the second upper resident chamber 34 and the second lower resident chamber 35, the supporting arm penetrates through the second upper resident chamber 34 and the second lower resident chamber 35 to clamp and hold the test model 41, the electric cylinder is used for protecting the model when a supersonic test with a large partial load is started, and after the flow field is stable, the supporting arm is quickly retracted into the second upper resident chamber 34 and the second lower resident chamber 35.
The positioning mechanism 3 is the same as the positioning mechanism 3 in the first embodiment, as shown in fig. 7, different external parts are connected to the two sides of the upstream and downstream of the wind tunnel test section 1-0, a spray pipe is generally arranged at the upstream of the wind tunnel test section 1-0, the upstream of the wind tunnel test section 1-0 is connected with the outlet end face of the spray pipe through the positioning mechanism 3, and the downstream of the wind tunnel test section 1-0 is also connected with other external parts through the positioning mechanism 3.
The positioning mechanism 3 adopts a plug pin mechanism, and comprises a positioning pin 20, lugs 21, pin seats 22 and a positioning hydraulic cylinder 23, wherein the positioning hydraulic cylinder 23 is arranged at the top of the positioning pin 20, the lugs 21 are inserted into the pin seats 22, and the bottoms of the positioning pin 20 penetrate through the lugs 21 positioned in the pin seats 22 after penetrating into the pin seats 22.
During positioning, the front side of the wind tunnel test section 1-0 is provided with the lug 21, the tail of an external part positioned at the upstream of the wind tunnel test section 1-0 is sequentially provided with the positioning hydraulic cylinder 23 and the pin seat 22 from top to bottom, the lug 21 at the front side of the wind tunnel test section 1-0 is inserted into the pin seat 22 at the tail of the external part, the positioning hydraulic cylinder 23 drives the positioning pin 20 to penetrate through the lug 21, positioning and installation of the front side of the wind tunnel test section 1-0 on the upstream external part are realized, and the external part positioned at the downstream of the wind tunnel test section 1-0 is arranged in the same way as the upstream of the external part.
The model support section 2-0 comprises a balancing cylinder 37, a lever 38, a support plate 40, a test model 41, a joint 42, a linear guide rail 43, a rotating arm 44, a transmission rod 45, a first connecting rod 46, a first rotating shaft 47, a second connecting rod 48, a second rotating shaft 49 and a servo motor cylinder 28, wherein the first connecting rod 46, the second connecting rod 48, the joint 42 and the rotating arm 44 form a four-bar mechanism and are arranged on the support plate 40 through the first rotating shaft 47 and the second rotating shaft 49, the support plate 40 is in sliding connection with the super-expansion section 39 through the linear guide rail 43, namely the linear guide rail 43 is fixedly arranged on the second rear end plate 25, the support plate 40 is in sliding fit with the linear guide rail 43, the servo motor cylinder 28 and the balancing cylinder 37 are fixedly arranged on the super-expansion section 39 side by side, the output ends of the servo motor cylinder are connected with the top of the support plate 40, the lever 38 is rotatably arranged on the support plate 40, one end of the lever 38 is rotatably arranged on the super-expansion section 39, the other end of the transmission rod 45 is hinged with the rotating arm 44, the end of the joint 42 penetrates through the super-expansion section 39 to enter the test section 1-0, and is connected with the test model 41. During operation, the servo electric cylinder 28 is adopted to drive, the motion is transmitted to the supporting plate 40 and the transmission rod 45 through the lever 38, the supporting plate 40 moves up and down along the linear sliding rail 43, the transmission rod 45 drives the rotating arm 44 to rotate around the second rotating shaft 49, and the connecting rod mechanism drives the joint 42 to rotate, so that the continuous change of the attack angle of the test model 41 is realized. Meanwhile, the balance cylinder 37 is added beside the servo motor cylinder 28, so that the weight of the mechanism and the supporting plate can be balanced, the load of the servo motor cylinder 28 is reduced, and the mechanism is prevented from suddenly falling down when the servo motor cylinder 28 is out of control.
It should be noted that, in the above embodiments, as long as the technical solutions that are not contradictory can be arranged and combined, those skilled in the art can exhaust all the possibilities according to the mathematical knowledge of the arrangement and combination, so the present invention does not describe the technical solutions after the arrangement and combination one by one, but should be understood that the technical solutions after the arrangement and combination have been disclosed by the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A wind tunnel test device using a sub-cross supersonic flow field optimal region simultaneously is characterized in that: the device comprises a wind tunnel test section (1-0) and a model support section (2-0), wherein the downstream end of the wind tunnel test section (1-0) is a super-expansion section (39), the model support section (2-0) is installed on the super-expansion section (39), the model support section (2-0) comprises a balance cylinder (37), a lever (38), a support plate (40), a joint (42), a linear guide rail (43), a rotating arm (44), a transmission rod (45), a first connecting rod (46), a first rotating shaft (47), a second connecting rod (48), a second rotating shaft (49) and a servo electric cylinder (28), the first connecting rod (46), the second connecting rod (48), the joint (42) and the rotating arm (44) form a four-bar mechanism, the super-expansion section (39) is installed on the support plate (40) through the first rotating shaft (47) and the second rotating shaft (49), the support plate (40) is in sliding connection with the super-expansion section (39) through the linear guide rail (43), the servo electric cylinder (28) and the balance cylinder (37) are fixedly installed on the super-expansion section (39) side by side, the output ends of the two super-expansion section (39) are connected with the top of the lever (40) side by side, one end of the output end of the super-expansion section is in rotation connection with the lever (40), one end of the super-expansion section (38) is rotatably installed on the support plate (38), the other end of the transmission rod (45) is hinged with the rotating arm (44), and the end part of the joint (42) penetrates through the inlet of the super-expansion section (39) and then stretches into the wind tunnel test section (1-0).
2. The wind tunnel test device for simultaneously using a sub-cross supersonic flow field optimal area according to claim 1, wherein the wind tunnel test device is characterized in that: the wind tunnel test section (1-0) comprises a resident chamber (1), an insert (2) and a positioning mechanism (3), wherein the insert (2) is arranged inside the resident chamber (1), and the front end and the rear end of the resident chamber (1) are respectively connected with external components positioned at the upstream and the downstream of the wind tunnel test section (1-0) through the positioning mechanism (3).
3. The wind tunnel test device for simultaneously using a sub-cross supersonic flow field optimal area according to claim 2, wherein the wind tunnel test device is characterized in that: the parking room (1) comprises a shell (4), a spring support (5), a middle beam (6), a trolley (7), a hydraulic cylinder (8), a guide rail (10) and a rail (11), wherein the guide rail (10) is arranged on the trolley (7), the middle beam (6) is in sliding connection with the guide rail (10), two ends of the hydraulic cylinder (8) are respectively connected with the middle beam (6) and the trolley (7), the shell (4) is arranged at the top of the middle beam (6) through the spring support (5), and the plug-in unit (2) is arranged inside the shell (4) through the rail (11).
4. A wind tunnel test device using a sub-cross supersonic flow field optimum region simultaneously according to claim 3, wherein: the plug-in components (2) include wallboard angle adjustment mechanism (12), upper and lower wallboard (13), side wall board (14), front end board (15), wheel (16), optical window (17), little optical window (18) and half mould mechanism (19), upper and lower wallboard (13) and side wall board (14) constitute rectangular frame structure jointly, and set up in the inside of resident room (1), all be equipped with optical window (17) and little optical window (18) on upper and lower wallboard (13) and side wall board (14), side wall board (14) bottom has wheel (16), be provided with half mould mechanism (19) on side wall board (14), upper and lower wallboard (13) front side is established with resident room (1) front side through front end board (15) and is connected, upper and lower wallboard (13) rear side is established with resident room (1) rear side through wallboard angle adjustment mechanism (12).
5. The wind tunnel test device for simultaneously using a sub-cross supersonic flow field optimal area according to claim 4, wherein the wind tunnel test device is characterized in that: the positioning mechanism (3) comprises a positioning pin (20), lugs (21), pin seats (22) and positioning hydraulic cylinders (23), wherein the positioning hydraulic cylinders (23) are arranged at the tops of the positioning pin (20), the lugs (21) are inserted into the pin seats (22), and the bottoms of the positioning pin (20) penetrate through the lugs (21) positioned in the pin seats (22) after penetrating into the pin seats (22).
6. The wind tunnel test device for simultaneously using a sub-cross supersonic flow field optimal area according to claim 5, wherein the wind tunnel test device is characterized in that: the residence chamber (1) is provided with an escalator and a working platform (9).
7. The wind tunnel test device for simultaneously using a sub-cross supersonic flow field optimal area according to claim 1, wherein the wind tunnel test device is characterized in that: the wind tunnel test section (1-0) comprises a second front end plate (24), a second rear end plate (25), a second side wall plate (26), a second trolley (27), a positioning mechanism (3), a second upper wall plate (29), a second lower wall plate (30), a second upper cavity wall plate (31), a second lower cavity wall plate (32), a second regulating mechanism (33), a second upper resident chamber (34), a second lower resident chamber (35) and a model protection mechanism (36), wherein the second upper wall plate (29), the second lower wall plate (30) and the second side wall plate (26) jointly form a test area of the model, the second side wall plate (26), the second upper wall plate (29) and the second upper cavity wall plate (31) form a second upper resident chamber (34) of the test area, the second side wall plate (26), the second lower wall plate (30) and the second lower cavity wall plate (32) form a second lower resident chamber (35) of the test area, the front end and the rear end of the test area are fixedly provided with a second front end plate (24) and a second rear end plate (25) respectively, the second front end plate (24) and the second rear end plate (25) are respectively connected with the second upper end plate (25) through the positioning mechanism (31) and the second upper end plate (27) respectively, the wind tunnel test section is arranged at the bottom of the test section (1), the rear sides of the second upper wall plate (29) and the second lower wall plate (30) are respectively connected with the second rear end plate (25) through a second adjusting mechanism (33), a second upper resident chamber (34) and a second lower resident chamber (35) are respectively symmetrically provided with a model protection mechanism (36), and the end parts of the model protection mechanism (36) respectively extend out of the second upper resident chamber (34) and the second lower resident chamber (35) to be arranged on the upper side and the lower side of the test model (41).
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| CN117387898B (en) * | 2023-12-12 | 2024-02-23 | 中国航空工业集团公司沈阳空气动力研究所 | Locking and sealing mechanism and locking and sealing method for wind tunnel residence chamber and super-expansion section |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH075066A (en) * | 1993-06-17 | 1995-01-10 | Mitsubishi Heavy Ind Ltd | Rolling regulation device for wind tunnel testing model |
| JP2001174363A (en) * | 1999-12-20 | 2001-06-29 | Kawada Kogyo Kk | Measuring probe orientating device |
| JP2002340733A (en) * | 2001-05-11 | 2002-11-27 | National Aerospace Laboratory Of Japan | Free jet hypersonic wind tunnel testing apparatus |
| CN104931222A (en) * | 2015-05-04 | 2015-09-23 | 中国航天空气动力技术研究院 | Projectile separation trajectory captive test system |
| CN106840584A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of multivariant sub- big attack angle mechanism of transonic and supersonic wind tunnel |
| CN107356401A (en) * | 2017-08-23 | 2017-11-17 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model guard system suitable for wind tunnel test |
| CN111024362A (en) * | 2019-12-19 | 2020-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Test device and test method for estimating interstage separation track in symmetric plane |
| CN112268676A (en) * | 2020-10-15 | 2021-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Supersonic wind tunnel model pitching motion protection device |
| 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 |
| CN115290286A (en) * | 2022-10-10 | 2022-11-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Integrated learning evaluation system for flow field stability of sub-span supersonic wind tunnel |
| CN115655637A (en) * | 2022-12-15 | 2023-01-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Lifting mechanism of large hypersonic high-temperature wind tunnel model feeding system |
-
2023
- 2023-06-15 CN CN202310705581.8A patent/CN116448373B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH075066A (en) * | 1993-06-17 | 1995-01-10 | Mitsubishi Heavy Ind Ltd | Rolling regulation device for wind tunnel testing model |
| JP2001174363A (en) * | 1999-12-20 | 2001-06-29 | Kawada Kogyo Kk | Measuring probe orientating device |
| JP2002340733A (en) * | 2001-05-11 | 2002-11-27 | National Aerospace Laboratory Of Japan | Free jet hypersonic wind tunnel testing apparatus |
| CN104931222A (en) * | 2015-05-04 | 2015-09-23 | 中国航天空气动力技术研究院 | Projectile separation trajectory captive test system |
| CN106840584A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of multivariant sub- big attack angle mechanism of transonic and supersonic wind tunnel |
| CN107356401A (en) * | 2017-08-23 | 2017-11-17 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model guard system suitable for wind tunnel test |
| CN111024362A (en) * | 2019-12-19 | 2020-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Test device and test method for estimating interstage separation track in symmetric plane |
| CN112268676A (en) * | 2020-10-15 | 2021-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Supersonic wind tunnel model pitching motion protection device |
| 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 |
| CN115290286A (en) * | 2022-10-10 | 2022-11-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Integrated learning evaluation system for flow field stability of sub-span supersonic wind tunnel |
| CN115655637A (en) * | 2022-12-15 | 2023-01-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Lifting mechanism of large hypersonic high-temperature wind tunnel model feeding system |
Non-Patent Citations (1)
| Title |
|---|
| A novel VAWT passive flow control numerical and experimental investigations: Guided Vane Airfoil Wind Turbine;Ahmed Aboelezz;Ocean Engineering;第257卷;111704 * |
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