CN113138061A - Improved wind tunnel air inlet channel test model supporting system - Google Patents
Improved wind tunnel air inlet channel test model supporting system Download PDFInfo
- Publication number
- CN113138061A CN113138061A CN202110684143.9A CN202110684143A CN113138061A CN 113138061 A CN113138061 A CN 113138061A CN 202110684143 A CN202110684143 A CN 202110684143A CN 113138061 A CN113138061 A CN 113138061A
- Authority
- CN
- China
- Prior art keywords
- wind tunnel
- ventilation
- arm
- angle
- cavity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- 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
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the field of wind tunnel tests and discloses an improved wind tunnel air inlet channel test model supporting system which comprises an air ventilation arm and an attack angle pre-deflection rod, wherein the air ventilation arm is connected with a rolling angle rotating shaft mechanism on a wind tunnel attack angle mechanism; the ventilation arm is sequentially provided with a gas passage, a wiring passage and a ventilation cavity from inside to outside; the gas passage is coaxially arranged with the ventilation cavity; the ventilating arm is connected with the attack angle pre-deflection rod; a gas passage extension section communicated with the gas passage and a wiring passage extension section communicated with the wiring passage are arranged in the attack angle pre-deflection rod; the ventilation cavity is communicated with a ventilation pipeline, and the gas passage extension section is communicated with a gas outlet pipeline; and a wire passing hole is formed in the wall of the attack angle pre-deflection rod. The invention solves the problems that the traditional model supporting system in the prior art cannot realize the integrated arrangement of ventilation and wiring, and the operation is inconvenient due to more instruments and more pipeline circuits in the wind tunnel test process.
Description
Technical Field
The invention belongs to the field of wind tunnel tests, and particularly relates to an improved wind tunnel air inlet channel test model supporting system.
Background
Air intake ducts are one of the important components of an air-breathing aircraft power plant. In order to research and evaluate the aerodynamic performance of an aircraft inlet duct in a wind tunnel test, the flow condition of a pipeline of the aircraft inlet duct is usually simulated in the wind tunnel, and the aerodynamic performance of the attack angle and the sideslip angle of the inlet duct under different incoming flow mach numbers is measured.
Typically, the air intake model is mounted in the wind tunnel by a support system. The low-speed wind tunnel is relatively low in air flow velocity, small in pneumatic load and large in wind tunnel size, the requirement for the supporting system is generally low in the test, the space for the cable and the air pipeline to be wired along the supporting system is sufficient in measurement and control, the cable and the air pipeline are easy to fix and protect, the requirement can be met even if the cable and the air pipeline are exposed in the air flow and are simply fixed and protected, and therefore the supporting system for the low-speed wind tunnel test is easy to design and low in complexity. However, in a high-speed wind tunnel and a hypersonic wind tunnel, because the airflow velocity is greatly increased, the wind tunnel pressure and temperature environment are complex, the model aerodynamic load is larger than that of a low-speed wind tunnel, and the size of the wind tunnel is smaller than that of the low-speed wind tunnel, the use environment of the model and the support system is complex than that of the low-speed wind tunnel, and the structural design requirements and the consideration factors for the model support are more.
In the prior art, cables led out from an air pipeline for measuring total pressure and static pressure on an air inlet model, a dynamic sensor, a flowmeter, a flow regulating system and the like are bundled into a bundle, are led to a wind tunnel attack angle mechanism from front to back along the outer surfaces of a model and a supporting rod of a supporting system, and then pass through a wind tunnel wall to be led out of a wind tunnel. The gas lines and cables need to be secured and protected during the extraction process, for example by ties or wires fastened at a distance, and by metal or plastic covers to protect them from high velocity gas streams. However, practical test experience shows that the cable routing mode on the outer surface of the supporting system can still cause the phenomena that a cable or an air pipeline is blown off and blown away, and a protective cover is blown to be damaged and blown away even if a protective cover is added under the continuous impact of supersonic velocity and even hypersonic velocity airflow, so that the data quality of wind tunnel tests is directly influenced, the test cost is increased, and the test efficiency is reduced.
In some test states, the stamping effect of the wind tunnel airflow is not enough to realize the simulation of the large-flow working condition of the air inlet, and at the moment, the ejector is additionally arranged at the rear part of the air inlet pipeline to help to suck the air in the air inlet in an ejection mode. In the prior art, high-pressure injection airflow required by an injector is provided by a high-pressure air source and an air supply pipeline. Rigid connection and inflexible installation of the air supply pipeline restrict the angle range of the wind tunnel for realizing the continuously variable model incidence angle and sideslip angle through the combination of the incidence angle and the sideslip angle or the roll angle mechanism. In order to realize the required angle, the wind tunnel test blowing must be suspended, and a section of air supply pipeline with different lengths and angles is replaced for switching according to the specific spatial position, so that the continuous angle changing capability of the wind tunnel mechanism cannot be fully utilized, and the working efficiency is obviously influenced. The problem is more prominent under the test requirement that a plurality of air inlets and a plurality of pipelines simultaneously need ejector air supply.
In the existing wind tunnel, the attack angle of the model is easily realized by a wind tunnel attack angle mechanism, and the sideslip angle realization mode is greatly influenced by the overall structural design of the wind tunnel. In low speed wind tunnels, the sideslip angle is typically achieved by a turntable mechanism. The turntable mechanism rotates around a shaft to drive the supporting system and the model to rotate simultaneously, a mechanism coordinate system of the turntable mechanism is consistent with a coordinate system defined by the sideslip angle, and the rotating angle is equal to the sideslip angle. However, in high-speed wind tunnels and hypersonic wind tunnels, due to the restriction of complex structure, narrow space and large structural load of a wind tunnel body, a turntable structure cannot be used, and the high-speed wind tunnels and the hypersonic wind tunnels can only be indirectly realized by adopting similar structures such as sideslip angle pre-deviation joints and angle changing blocks on model supports or by combining an attack angle mechanism and a roll angle mechanism. For the combined condition of the attack angle and the sideslip angle, the angle indirectly realized by adopting similar structures such as a sideslip angle pre-deviation joint, an angle changing block and the like on the model support is not the true attack angle and the sideslip angle but a nominal attack angle and a nominal sideslip angle. The true angle and the nominal angle differ more and more as the angle increases. For example, when the nominal attack angle realized by the attack angle mechanism is 11 degrees, and the nominal sideslip angle realized by the model support is 10 degrees, the actual real attack angle is 11.165 degrees, and the actual real sideslip angle is 9.814 degrees; and when the nominal incidence angle is 60 degrees and the nominal sideslip angle is 30 degrees, the actual real incidence angle is 63.435 degrees and the actual real sideslip angle is 14.478 degrees. Therefore, the design of the model support system needs to consider the problem of how to realize the true attack angle and the sideslip angle.
In summary, for the existing low-speed wind tunnel, high-speed wind tunnel and hypersonic wind tunnel, the existing air inlet channel test technology has the problems of improper fixation and protection of air pipelines and cables, limitation and influence on the range of the attack angle and sideslip angle of the model by the air supply pipeline of the ejector, and the problem of how to realize the real attack angle and sideslip angle of the model supporting system. These problems affect the safety of the testing equipment, increase the testing cost and reduce the testing efficiency.
Disclosure of Invention
The problems that in the prior art, a traditional model supporting system cannot realize ventilation and wiring integration, and in the wind tunnel test process, instruments are multiple, pipeline lines are multiple, operation is inconvenient and the protection effect is poor are solved. The invention provides an improved wind tunnel air inlet channel test model supporting system.
The invention adopts the specific scheme that: an improved wind tunnel air inlet channel test model supporting system comprises an air ventilation arm and an attack angle pre-deflection rod, wherein the air ventilation arm is connected with a rolling angle rotating shaft mechanism on a wind tunnel attack angle mechanism; the ventilation arm is sequentially provided with a gas passage, a wiring passage and a ventilation cavity from inside to outside; the gas passage is coaxially arranged with the ventilation cavity; the ventilating arm is connected with the attack angle pre-deflection rod; a gas passage extension section communicated with the gas passage and a wiring passage extension section communicated with the wiring passage are arranged in the attack angle pre-deflection rod; the ventilation cavity is communicated with a ventilation pipeline, and the gas passage extension section is communicated with a gas outlet pipeline; high-pressure gas sequentially passes through a vent pipeline, a vent cavity, a gas passage extension section and a gas outlet pipeline and then flows out of the model supporting system; the wall of the angle-of-attack pre-deflection rod is provided with a wiring hole, and a line and a cable pass through the wiring hole, the wiring passage extension section and the wiring passage in sequence and then penetrate into a cavity in the wind tunnel angle-of-attack mechanism.
The tail end of the model supporting system is provided with a connecting section, the front end of the connecting section is connected with the ventilating arm, and the rear end of the connecting section is connected with the roll angle rotating shaft mechanism on the wind tunnel angle-of-attack mechanism.
The gas passage extension section is connected with the gas outlet pipeline through the special-shaped tee joint, and the gas flow is divided into two parts after passing through the special-shaped tee joint and then enters the gas outlet pipeline respectively.
The ventilation cavity is a cavity surrounded by the outer wall of the ventilation arm, the cover plate of the ventilation cavity and the side wall of the ventilation cavity of the outer wall of the ventilation arm.
The ventilation cavity is communicated with the gas passage through a first through hole; the first through hole is a hole formed in the outer wall of the ventilation arm.
And a bearing is arranged between the ventilation cavity cover plate and the ventilation arm, and the bearing is sleeved on the ventilation arm.
The number of the bearings is two, and one of the bearings is mounted in a manner of being clung to the check ring of the cover plate of the ventilation cavity; the other bearing is mounted against the end wall of the connecting section.
The model braced system front end sets up toper branch, the front end of toper branch is connected the sideslip angle and is equipped with multirow pinhole and multirow second through-hole on the board that leans towards in advance at the sideslip angle, the combination of pinhole on multirow pinhole and the test model tail end plane forms the sideslip angle range of preinclining at 1 interval, and the screw passes the second through-hole and is connected with model tail end plane screw hole.
The ventilation arm, the ventilation cavity cover plate and the solid embedded bearing are sealed and sealed by a tooth-shaped combination through a rotating shaft. The ventilation cavity and the ventilation pipe are sealed by an O-shaped rubber sealing ring.
The routing path is a kidney-shaped routing path.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the invention, the model supporting system is internally provided with the ventilation arm and the attack angle pre-deflection rod, the ventilation arm is internally provided with different gas passages and wiring passages, and the attack angle pre-deflection rod is internally provided with corresponding gas passages and wiring passages, so that high-pressure gas sequentially passes through the ventilation pipeline, the ventilation cavity, the gas passages, the gas passage extension section and the gas outlet pipeline and then flows out of the model supporting system; on the other hand, the line and the cable pass through the wiring hole and penetrate into the cavity in the wind tunnel angle-of-attack mechanism after sequentially passing through the wiring path extension section and the wiring path, so that the integrated design of the air path and the line is realized, the device of the model supporting system is more compact, and the model supporting system has the advantages of convenience and quickness in operation.
(2) The ventilation arm is connected with the rolling angle rotating shaft mechanism on the wind tunnel angle-of-attack mechanism, and the circuit is integrally designed in the wiring passage in the ventilation arm and the angle-of-attack pre-deflection rod, so that the rolling angle rotating shaft mechanism drives the ventilation arm to rotate, and the cable rotates along with the ventilation arm in the process of driving the angle-of-attack pre-deflection rod to rotate by the ventilation arm, and is not interfered, so that the normal operation of the circuit is not influenced, the rotation of each component is not influenced, and the wind tunnel angle-of-attack mechanism has the advantage of good testing effect.
(3) The front end of the model supporting system is provided with the conical supporting rod; the angle-of-attack pre-deflection rod is connected with a roll angle rotating shaft mechanism on the wind tunnel angle-of-attack mechanism, so that the conical support rod and the angle-of-attack pre-deflection rod at the front end can be ensured to rotate along with the roll angle rotating shaft, and the measurement of the roll angle of the model is realized. The tapered supporting rod and the attack angle pre-deflection rod at the front end of the model supporting system respectively realize the pre-deflection of the sideslip angle and the pre-deflection of the attack angle. The method is characterized in that a sideslip angle pre-deflection and an attack angle pre-deflection are realized by an attack angle mechanism, a roll angle rotating shaft mechanism and a model supporting system of the wind tunnel, a model roll angle and a pitch angle are formed in a wind tunnel space, and a real attack angle and a sideslip angle of the model are realized through coordinate system conversion, so that the problems that some wind tunnel air passages and lines cannot be effectively protected and are limited by a movement mechanism and the realized attack angle and sideslip angle are actually nominal angles are solved; meanwhile, the model supporting system is simple in structure and convenient to install, and the angle of attack range required by different models is met by replacing the angle of attack pre-deflection rod. In addition, a plurality of inner and outer grooves can be expanded by the ventilation arm in the model supporting system, and the air supply requirements of more than 2 air inlet pipeline models are met.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a cross-sectional view of the present invention;
FIG. 3 is a view taken along line A of FIG. 1;
FIG. 4 is a schematic view of the structure of the ventilation arm of the present invention;
FIG. 5 is a schematic view of a cover plate structure of a vent chamber according to the present invention;
FIG. 6 is a schematic view of a tooth-shaped combined seal between the bearing and the rotating shaft at the position I in FIG. 2;
FIG. 7 is a top view of the present invention;
FIG. 8 is a cross-sectional view taken along line B-B of FIG. 7;
FIG. 9 is a cross-sectional view taken along line C-C of FIG. 1;
FIG. 10 is a cross-sectional view taken along line D-D of FIG. 7;
FIG. 11 is an installation schematic of the present invention;
wherein the reference numerals are respectively:
50. the device comprises a wind tunnel angle-of-attack mechanism, 51. a vent pipeline, 52. a roll angle rotating shaft mechanism, 53. a model supporting system, 53-1. a connecting section, 53-1-1. a connecting section end wall, 53-2. a vent arm, 53-2-1. a vent cavity cover plate check ring, 53-2-2. a vent arm check ring, 53-2-3. a vent arm outer wall, 53-2-4. a vent cavity side wall, 53-2-5. a gas passage inlet, 53-3. a vent cavity cover plate, 53-3-1. a cover plate end face, 53-3-2. a cover plate bearing check ring, 53-4. a bearing, 53-5. a vent cavity, 53-6. a gas passage, 53-7. a special-shaped tee joint, 53-8. a gas outlet pipeline, 53-9. a wiring hole, 53-10 parts of a wiring passage, 53-11 parts of a rotating shaft, 53-12 parts of a fairing, 54 parts of a conical support rod, 54-1 parts of a sideslip angle pre-deviation plate, 54-2 parts of an angle of attack pre-deviation rod, 54-3 parts of a wiring passage cover plate, 55 parts of a flow regulating and injecting system, 56 parts of an air inlet channel model, 59 parts of an embedded pipeline, 60 parts of an air supply hose and 61 parts of a room-parking pipeline interface.
Detailed Description
The invention is further described with reference to the following figures and detailed description.
An improved wind tunnel air inlet channel test model supporting system comprises an air ventilation arm 53-2 and an attack angle pre-deflection rod 54-2, wherein the air ventilation arm 53-2 is connected with a roll angle rotating shaft mechanism 52 on a wind tunnel attack angle mechanism 50; the ventilation arm 53-2 is provided with a gas passage 53-6, a routing passage 53-10 and a ventilation cavity 53-5 in sequence from inside to outside in the radial direction; the gas passage 53-6 is coaxially arranged with the ventilation cavity 53-5; the ventilation arm 53-2 is connected with the attack angle pre-deflection rod 54-2; a gas passage extension section communicated with the gas passage 53-6 and a routing passage extension section communicated with the routing passage 53-10 are arranged in the attack angle pre-deflection rod 54-2; the vent cavity 53-5 is communicated with a vent pipeline 51, and the gas passage extension is communicated with a gas outlet pipeline 53-8; high-pressure gas sequentially passes through a vent pipeline 51, a vent cavity 53-5, a gas passage 53-6, a gas passage extension section and a gas outlet pipeline 53-8 and then flows out of the model supporting system; the wall of the attack angle pre-deflection rod 54-2 is provided with a wiring hole 53-9, and a line and a cable pass through the wiring hole 53-9, the extended section of the wiring passage and the wiring passage 53-10 in sequence and then penetrate into a cavity in the wind tunnel attack angle mechanism 50.
Referring to fig. 4 and 8, in one embodiment, the vent arm is cylindrical in shape; the ventilation cavity is an annular ventilation cavity, and the gas passage 53-6 is a cylindrical cavity body with the axis of the ventilation arm as the axis.
The gas passage extension section is an extension part of the gas passage 53-6 on the attack angle pre-deflection rod 54-2, the function and the structure of the gas passage 53-6 arranged in the ventilation arm are the same or similar, and the inner wall of the gas passage is smooth; the extended section of the routing path is the extended part of the routing path 53-10 on the attack angle pre-deflection rod 54-2, and has the same or similar function and structure with the routing path 53-10 arranged in the ventilation arm; the structure is the cell type, and the smooth cable of inner wall or electric wire accomodate the passageway of placing. After the gas passage extension section is communicated with the gas passage, introducing gas into a flow regulating and injecting system; and after the routing path extension section is communicated with the routing path, the cable is introduced into the wind tunnel attack angle.
The attack angle pre-deflection rod is a round rod in shape, and a gas passage extension section and a routing passage extension section are sequentially arranged in the interior of the attack angle pre-deflection rod from inside to outside in the radial direction.
The tail end of the model supporting system is provided with a connecting section 53-1, the front end of the connecting section 53-1 is connected with the ventilating arm 53-2, the rear end of the connecting section is connected with the rolling angle rotating shaft mechanism 52 on the wind tunnel attack angle mechanism 50, and the connecting section is convenient to disassemble the model supporting system.
Referring to the attached figure 8, the extended section of the gas passage is connected with a gas outlet pipeline 53-8 through a special-shaped tee joint 53-7, and the gas flow is divided into two parts after passing through the special-shaped tee joint and enters the gas outlet pipeline 53-8 respectively, so that the high-pressure gas supply of the double-engine gas inlet passage flow regulating and ejecting system 55 is realized.
The vent cavity 53-5 is a cavity surrounded by the vent arm outer wall 53-2-3 of the vent arm 53-2, the vent cavity cover plate 53-3 and the vent cavity side wall 53-2-4 of the vent arm outer wall 53-2-3.
The ventilation cavity 53-5 is communicated with the gas channel through a first through hole; the first through hole is a hole formed in the outer wall 53-2-3 of the ventilation arm 53-2, so that high-pressure gas can smoothly enter the gas passage.
And a bearing is arranged between the vent cavity cover plate 53-3 and the vent arm 53-2, and the bearing is sleeved on the vent arm 53-2. The bearing is a solid mosaic bearing, and the rotation of the ventilation arm is smoother due to the installation of the bearing.
The number of the bearings is two, and one of the bearings is tightly attached to the vent cavity cover plate retainer ring 53-2-1; the other bearing is mounted against the connecting segment end wall 53-1-1.
The front end of the model supporting system is provided with a conical supporting rod 54, the front end of the conical supporting rod is connected with a sideslip angle pre-biasing plate 54-1, the sideslip angle pre-biasing plate is a flat plate, the sideslip angle pre-biasing plate 54-1 is provided with a plurality of rows of pin holes and a plurality of rows of second through holes, the plurality of rows of pin holes are combined with pin holes on a test model tail end plane to form a sideslip angle pre-biasing range with intervals of 1 degree, and a screw penetrates through the second through holes to be connected with a threaded hole of the model tail end plane. Specifically, one pin hole in the multiple rows of pin holes and one pin hole on the plane of the tail end of the test model are combined to form a pin hole combination, and one pin hole combination can form a sideslip angle; the pin holes in the multiple rows can form a sideslip angle pre-deviation range with 1 degree interval after combination.
The body of the conical support rod 54 is a cone, the front end of the cone is provided with an arc smooth surface in a smooth manner, and the cone is connected with the attack angle pre-deflection rod 54-2 through a bolt; a sideslip angle pre-deviation plate 54-1 is arranged below the front part of the conical support rod 54; the sliding angle pre-biased plate 54-1 is integrally formed with the tapered strut 54.
The ventilation arm 53-2, the ventilation cavity cover plate 53-3 and the solid mosaic bearing 53-4 are sealed by a tooth-shaped combined seal 53-11 for a rotating shaft. The vent cavity and the vent pipeline 51 are sealed by an O-shaped rubber sealing ring.
The routing paths 53-10 are waist-shaped routing paths, and the waist-shaped routing paths are convenient for arranging cable lines and convenient for operation.
The model supporting system 53, the conical supporting rod 54 and the attack angle pre-deflecting rod 54-2 at the front end of the model supporting system can be designed into a plurality of different conical supporting rods and attack angle pre-deflecting rods according to the requirements of attack angles and sideslip angles of different models, each attack angle pre-deflecting rod has different pre-deflecting angles, the attack angle of the wind tunnel attack angle mechanism can be expanded, and the attack angle range of different models can be met by replacing the attack angle pre-deflecting rod during use. The attack angle pre-deflection rod 54-2 is movably connected with the ventilation arm, and further connected with the ventilation arm through a bolt.
The high-pressure gas enters the gas passage in the model supporting system 53 through the vent pipe 51, is transmitted to the flow regulating and injecting system 55, and is used for high-pressure injection gas supply for the injector of the flow regulating and injecting system 55.
The model support system 53, at the rear end, is a vent arm 53-2 and a vent chamber cover plate 53-3. The straight port at the front end of the connecting section 53-1 is sleeved on the straight port at the rear end of the ventilation arm 53-2 and is fixed by a screw; the vent cavity cover plate 53-3 is pressed by the baffle plate on the front end surface of the connecting section 53-1, and the rear end of the connecting section 53-1 is connected with the roll angle rotating shaft mechanism 52 on the wind tunnel attack angle mechanism 50 through a screw.
When the roll angle rotating shaft mechanism 52 rotates, the connecting section 53-1 and the ventilation arm 53-2 connected with the roll angle rotating shaft mechanism are driven to rotate together, the ventilation arm 53-2 is fixedly connected with the conical support rod 54 and the attack angle pre-deflection rod 54-2 at the front end of the model supporting system 53 through screws and rotates together with the roll angle rotating shaft mechanism 52, and therefore the model rolls in the range of 0-90 degrees.
The wind tunnel angle-of-attack mechanism 50, the roll angle rotating shaft mechanism 52, the sideslip angle pre-deflection plate 54-1 and the angle-of-attack pre-deflection rod 54-2 on the model supporting system 53 are used together, and the model roll angle and the pitch angle are combined in the wind tunnel. Knowing the roll angle, the pitch angle, the pre-deflection angle of the attack angle and the pre-deflection angle of the sideslip angle of the model, for the model, the coordinate matrix conversion obtained by converting the model from a ground coordinate system to a body axis coordinate system is consistent with the coordinate matrix conversion obtained by converting the model from an airflow coordinate system to the body axis coordinate system, and after the matrix is converted, the real attack angle and the sideslip angle of the model are obtained.
The vent arm 53-2 is used as a rotating piece, and a solid mosaic bearing 53-4 is arranged between the vent arm 53-2 and the vent cavity cover plate 53-3, so that the surface rotation friction is reduced, and the smooth rotation of the vent arm 53-2 is ensured.
In one embodiment, the interior of the vent arm 53-2 is in the form of an internal and external passageway in the axial direction, the internal passageway comprising a gas passageway 53-6, a vent lumen 53-5; the gas passage is communicated with the ventilation cavity through a gas passage inlet 53-2-5 and a first through hole formed in the outer wall 53-2-3 of the ventilation arm 53-2; the high-pressure gas supplied from the ventilation line 51 may flow into the gas passage 53-6. The outer side passages are 2 waist-shaped routing passages 53-10, penetrate through the whole ventilation arm 53-2, are communicated with the inner routing passages 53-10 of the attack angle pre-deflection rod 54-2 forwards, and are communicated with the inner routing passages of the three sections of the connecting section 53-1, the roll angle rotating shaft mechanism 52 and the wind tunnel attack angle mechanism 50 backwards. The cables, air pipes and the like on the model pass through the wiring hole 53-9 and pass through the hollow cavity in the roll angle rotating shaft mechanism 52 and the wind tunnel incidence angle mechanism 50 along the wiring path 53-10.
The arrangement of the routing channels 53-10 ensures that the cable and the air pipeline can follow up when the model continuously walks at the attack angle and the roll angle, is not limited by the length caused by the change of the attack angle and the sideslip angle, and effectively protects the cable and the air pipeline. Before the cables and the air pipelines are routed, the routing path cover plate 54-3 is opened, and after the cables and the air pipelines are routed and carded, the routing path cover plate 54-3 is screwed and fixed well.
The arrows in the figure indicate the gas flow direction.
High-pressure air from a high-pressure air source enters the wind tunnel parking chamber through the parking chamber pipeline interface 61, and enters the ventilation pipeline 51 in the wind tunnel parking chamber through the air supply pipeline 60 and the embedded pipeline 59 installed in the wind tunnel attack angle mechanism 50. The pre-buried pipeline 59 and the ventilation pipeline 51 are connected by a section of adapting steel pipe or hose.
The relative positions of the vent arm 53-2, the vent cavity cover plate 53-3 and the bearing 53-4 are as follows:
two solid mosaic bearings 53-4 are respectively positioned at two sides of the ventilation cavity in the axial direction and sleeved on the ventilation arm 53-2. The front end solid mosaic bearing 53-4 is tightly attached to the vent cavity cover plate retainer ring 53-2-1, and the rear end solid mosaic bearing 53-4 is tightly attached to the connecting section end wall 53-1-1. The vent chamber cover plate 53-3 is mounted over the solid insert bearing 53-4.
The inner surface of the vent cavity cover plate 53-3 is provided with a cover plate bearing retainer ring 53-3-2 and a rear end bearing baffle according to the positions of the two bearings, and the cover plate bearing retainer ring is used for assisting the fixing of the installation positions of the two solid mosaic bearings 53-4.
The vent arm 53-2, the vent cavity cover plate 53-3, the bearing 53-4 and the connecting section 53-1 are installed in the following sequence:
firstly, the front end of the ventilation arm 53-2 is sleeved with the ventilation cavity cover plate retainer ring 53-2-1 and is tightly attached to the side face of the fairing 53-12, then the front end solid embedded bearing 53-4 is tightly attached to the ventilation cavity cover plate retainer ring 53-2-1 and is sleeved on the ventilation arm 53-2, and the solid embedded bearing 53-4 is fixed on the ventilation arm 53-2 by a jackscrew. And then one of the vent arm check rings 53-2-2 is installed on the cover plate bearing check ring 53-3-2 by a screw, then the vent cavity cover plate 53-3 is integrally installed in close contact with the vent cavity cover plate check ring 53-2-1, the end surface 53-3-1 of the vent cavity cover plate and the vent cavity cover plate check ring 53-2-1 are connected by the screw, and the installation of the vent cavity cover plate 53-3 is completed. At the moment, the rear bearing baffle on the vent cavity cover plate 53-3 is in place, then the other vent arm check ring 53-2-2 and the solid mosaic bearing 53-4 at the rear end are tightly attached to the rear bearing baffle on the vent cavity cover plate 53-3 for installation, and finally the straight opening at the front end of the connecting section 53-1 is sleeved on the straight opening at the rear end of the vent arm 53-2 and fixed by screws, so that the end wall 53-1-1 of the connecting section at the front end of the connecting section 53-1 can be ensured to be capable of pressing each check ring and baffle.
The invention integrally arranges the ventilation and the wiring in the improved model supporting system, thereby solving the problems that the traditional model supporting system in the prior art cannot realize the integral arrangement of the ventilation and the wiring, the operation is inconvenient and the instrument is limited by a movement mechanism due to more instruments and more pipeline circuits in the wind tunnel test process, and the realized attack angle and sideslip angle are actually the engineering problems of nominal angles. The invention not only improves the working efficiency, but also saves a large amount of cost.
Claims (10)
1. An improved wind tunnel air inlet channel test model supporting system is characterized in that the model supporting system (53) comprises an air ventilation arm (53-2) and an attack angle pre-deflection rod (54-2), and the air ventilation arm (53-2) is connected with a roll angle rotating shaft mechanism (52) on a wind tunnel attack angle mechanism (50); the ventilation arm (53-2) is sequentially provided with a gas passage (53-6), a routing passage (53-10) and a ventilation cavity (53-5) from inside to outside; the gas channel (53-6) is coaxially arranged with the ventilation cavity (53-5); the ventilation arm (53-2) is connected with the attack angle pre-deflection rod (54-2); a gas passage extension section communicated with the gas passage (53-6) and a routing passage extension section communicated with the routing passage (53-10) are arranged in the attack angle pre-deflection rod (54-2); the ventilation cavity (53-5) is communicated with a ventilation pipeline (51), and the extended section of the gas passage is communicated with a gas outlet pipeline (53-8); high-pressure gas sequentially passes through a ventilation pipeline (51), a ventilation cavity (53-5), a gas passage (53-6), a gas passage extension section and a gas outlet pipeline (53-8) and then flows out of the model supporting system (53); the wall of the angle-of-attack pre-deflection rod (54-2) is provided with a wiring hole (54-9), and a line and a cable enter from the wiring hole (54-9), sequentially pass through the wiring passage extension section and the wiring passage (53-10) and then penetrate into a cavity in the wind tunnel angle-of-attack mechanism (50).
2. The improved wind tunnel air inlet channel test model supporting system as claimed in claim 1, wherein the model supporting system (53) is provided with a connecting section (53-1) at the tail end, the front end of the connecting section (53-1) is connected with the ventilating arm (53-2), and the rear end is connected with the roll angle rotating shaft mechanism (52) on the wind tunnel attack angle mechanism (50).
3. The improved wind tunnel inlet channel test model support system according to claim 1, wherein the gas passage extension section is connected with the gas outlet pipeline (53-8) through a special-shaped tee joint (53-7), and the gas flow is divided into two parts after passing through the special-shaped tee joint (53-7) and then enters the gas outlet pipeline (53-8).
4. The improved wind tunnel inlet channel test model support system according to claim 1, wherein the vent cavity (53-5) is communicated with the gas passage (53-6) through a first through hole; the first through hole is a hole formed in the outer wall (53-2-3) of the ventilation arm (53-2).
5. The improved wind tunnel air inlet channel test model supporting system according to claim 1, wherein the air vent cavity (53-5) is a cavity surrounded by an air vent arm outer wall (53-2-3) of the air vent arm (53-2), an air vent cavity cover plate (53-3) and an air vent cavity side wall (53-2-4) of the air vent arm outer wall (53-2-3).
6. The improved wind tunnel inlet channel test model supporting system according to claim 5, wherein a bearing (53-4) is installed between the vent cavity cover plate (53-3) and the vent arm (53-2), and the bearing (53-4) is sleeved on the vent arm (53-2).
7. The improved wind tunnel inlet channel test model supporting system according to claim 6, wherein the number of the bearings (53-4) is two, and one of the bearings (53-4) is closely attached to the vent cavity cover plate retainer ring (53-2-1); the other bearing is mounted against the end wall (53-1-1) of the connecting section.
8. The improved wind tunnel inlet channel test model supporting system according to claim 7, wherein the ventilating arm (53-2), the ventilating cavity cover plate (53-3) and the bearing (53-4) are sealed by a tooth-shaped combined seal (53-11) through a rotating shaft, and the ventilating cavity (53-5) and the ventilating pipeline (51) are sealed by an O-shaped rubber sealing ring.
9. The improved wind tunnel air inlet channel test model supporting system according to any one of claims 1 to 8, wherein a tapered supporting rod (54) is arranged at the front end of the model supporting system (53), the front end of the tapered supporting rod (54) is connected with a sideslip angle pre-deviation plate (54-1), a plurality of rows of pin holes and a plurality of rows of second through holes are arranged on the sideslip angle pre-deviation plate (54-1), the plurality of rows of pin holes are combined with pin holes on a plane of the tail end of the test model to form a sideslip angle pre-deviation range with 1 degree interval, and screws penetrate through the plurality of rows of second through holes to be connected with threaded holes on the plane of the tail end of the model.
10. The improved wind tunnel inlet test model support system according to any one of claims 1 to 8, wherein said routing paths (53-10) are kidney-shaped routing paths.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110684143.9A CN113138061B (en) | 2021-06-21 | 2021-06-21 | Improved wind tunnel air inlet channel test model supporting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110684143.9A CN113138061B (en) | 2021-06-21 | 2021-06-21 | Improved wind tunnel air inlet channel test model supporting system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113138061A true CN113138061A (en) | 2021-07-20 |
| CN113138061B CN113138061B (en) | 2021-08-13 |
Family
ID=76815877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110684143.9A Active CN113138061B (en) | 2021-06-21 | 2021-06-21 | Improved wind tunnel air inlet channel test model supporting system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113138061B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113607374A (en) * | 2021-08-08 | 2021-11-05 | 中国航空工业集团公司沈阳飞机设计研究所 | Guiding line concentration device applied to low-speed flutter wind tunnel test protection system |
| CN116448374A (en) * | 2023-06-15 | 2023-07-18 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet duct wind tunnel test method for simulating multiple interference |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106507936B (en) * | 2012-12-31 | 2014-04-09 | 中国人民解放军国防科学技术大学 | A kind of free jet test cable takes off pulling device |
| CN105738070A (en) * | 2016-04-28 | 2016-07-06 | 贵州航空发动机研究所 | Airplane admission passage outlet flow field measuring device |
| CN106441785A (en) * | 2016-09-07 | 2017-02-22 | 中国航空工业集团公司沈阳空气动力研究所 | Support mechanism for small propulsion device inlet engine compatibility test in intermittent wind tunnel |
| CN208579903U (en) * | 2018-08-14 | 2019-03-05 | 中国航天空气动力技术研究院 | A kind of high intensity air intake duct wind tunnel test supporting mechanism |
| CN111537183A (en) * | 2020-05-19 | 2020-08-14 | 刘祥 | Ventilation model internal resistance supporting and measuring system |
| CN111947879A (en) * | 2020-08-31 | 2020-11-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet flow test device for wind tunnel model |
| CN112781827A (en) * | 2020-12-30 | 2021-05-11 | 中国航天空气动力技术研究院 | Ventilating support arm device applied to thrust measurement of vectoring nozzle and application |
| CN112903232A (en) * | 2021-01-22 | 2021-06-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Flow regulating device for wind tunnel test of aircraft atmospheric data system |
-
2021
- 2021-06-21 CN CN202110684143.9A patent/CN113138061B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106507936B (en) * | 2012-12-31 | 2014-04-09 | 中国人民解放军国防科学技术大学 | A kind of free jet test cable takes off pulling device |
| CN105738070A (en) * | 2016-04-28 | 2016-07-06 | 贵州航空发动机研究所 | Airplane admission passage outlet flow field measuring device |
| CN106441785A (en) * | 2016-09-07 | 2017-02-22 | 中国航空工业集团公司沈阳空气动力研究所 | Support mechanism for small propulsion device inlet engine compatibility test in intermittent wind tunnel |
| CN208579903U (en) * | 2018-08-14 | 2019-03-05 | 中国航天空气动力技术研究院 | A kind of high intensity air intake duct wind tunnel test supporting mechanism |
| CN111537183A (en) * | 2020-05-19 | 2020-08-14 | 刘祥 | Ventilation model internal resistance supporting and measuring system |
| CN111947879A (en) * | 2020-08-31 | 2020-11-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet flow test device for wind tunnel model |
| CN112781827A (en) * | 2020-12-30 | 2021-05-11 | 中国航天空气动力技术研究院 | Ventilating support arm device applied to thrust measurement of vectoring nozzle and application |
| CN112903232A (en) * | 2021-01-22 | 2021-06-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Flow regulating device for wind tunnel test of aircraft atmospheric data system |
Non-Patent Citations (2)
| Title |
|---|
| SIDLOF PETR,ETAL: "Turbulence intensity measurement in the wind tunnel used for airfoil flutter investigation", 《EXPERIMENTAL FLUID MECHANICS 2016》 * |
| 马晓光 等: "小型推进系统进发匹配高速风洞特种试验技术研究", 《空气动力学学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113607374A (en) * | 2021-08-08 | 2021-11-05 | 中国航空工业集团公司沈阳飞机设计研究所 | Guiding line concentration device applied to low-speed flutter wind tunnel test protection system |
| CN113607374B (en) * | 2021-08-08 | 2024-02-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Guide line concentration device applied to low-speed flutter wind tunnel test protection system |
| CN116448374A (en) * | 2023-06-15 | 2023-07-18 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet duct wind tunnel test method for simulating multiple interference |
| CN116448374B (en) * | 2023-06-15 | 2023-08-22 | 中国航空工业集团公司沈阳空气动力研究所 | Air inlet duct wind tunnel test method for simulating multiple interference |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113138061B (en) | 2021-08-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113138061B (en) | Improved wind tunnel air inlet channel test model supporting system | |
| CN108088649B (en) | Model device for fixedly connecting spray pipe with shape in wind tunnel test and test method | |
| CN106840591B (en) | A kind of experimental rig directly measuring jet flow thrust | |
| CN104848904A (en) | Air duct flow measuring system | |
| CN107860554B (en) | Tail jet flow test integrated model device in wind tunnel test and test method | |
| CN101776530B (en) | System and method for testing indoor natural ventilating model of building | |
| CN113588201A (en) | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment | |
| CN105527068A (en) | Wind tunnel dynamic force measurement test device for canard configuration rotating missile | |
| CN109100110B (en) | Be applied to two throat thrust vectoring nozzle support arm device of ventilating | |
| CN113588200B (en) | High-flow reverse jet test device and method for hypersonic aircraft | |
| CN106768798A (en) | One kind is used for big angle of attack rear lateral jet flow dynamometer check structure | |
| CN109470401B (en) | Straight-rod airspeed tube with attack angle resolving function | |
| CN102478451A (en) | Active flow control testing unit for air inlet duct of high-speed wind tunnel | |
| CN110793746A (en) | Wind tunnel test device for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN105424369A (en) | Pneumatic model tester for aircraft engine | |
| CN110793745A (en) | Supersonic wind tunnel flow calibration and measurement pressure hose protection device | |
| CN106441781B (en) | A kind of measurable air intake duct throttling set of flow | |
| CN115824572A (en) | Wind tunnel dynamic pressure measuring device and measuring method | |
| CN110274750B (en) | Supercavitation navigation body test model with elastic tail edge | |
| CN103115746A (en) | Shock tunnel module support device | |
| CN113049242B (en) | Testing device and testing method for blockage of cooling hole of middle shell of automobile turbocharger | |
| KR101533963B1 (en) | Thrust measuring device for measuring roll moment of side jet thruster for guided missile | |
| CN110567673B (en) | Wind tunnel test method for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN209606052U (en) | A kind of balance strut for wind-tunnel hot exhaust interference test | |
| CN109556865B (en) | Wing body combined model support for air inlet channel test |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |