CN117664501A - Buffer structure and method for pipe wind tunnel - Google Patents
Buffer structure and method for pipe wind tunnel Download PDFInfo
- Publication number
- CN117664501A CN117664501A CN202410140109.9A CN202410140109A CN117664501A CN 117664501 A CN117664501 A CN 117664501A CN 202410140109 A CN202410140109 A CN 202410140109A CN 117664501 A CN117664501 A CN 117664501A
- Authority
- CN
- China
- Prior art keywords
- wind tunnel
- pipe
- corrugated pipe
- tube
- tunnel body
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 15
- 239000007921 spray Substances 0.000 claims abstract description 37
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 13
- 238000007906 compression Methods 0.000 claims description 24
- 230000001052 transient effect Effects 0.000 claims description 22
- 230000006835 compression Effects 0.000 claims description 18
- 238000007789 sealing Methods 0.000 claims description 17
- 230000003139 buffering effect Effects 0.000 claims description 12
- 230000001133 acceleration Effects 0.000 claims description 7
- 238000006243 chemical reaction Methods 0.000 claims description 6
- 238000013016 damping Methods 0.000 claims description 6
- 238000004458 analytical method Methods 0.000 claims description 5
- 238000007667 floating Methods 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 238000004364 calculation method Methods 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 4
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 229910002804 graphite Inorganic materials 0.000 claims description 4
- 239000010439 graphite Substances 0.000 claims description 4
- 230000010354 integration Effects 0.000 claims description 4
- 230000009471 action Effects 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 239000012528 membrane Substances 0.000 claims description 2
- 230000035939 shock Effects 0.000 abstract description 3
- 239000003566 sealing material Substances 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000000284 resting effect Effects 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Classifications
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A buffer structure and a buffer method for a pipe wind tunnel belong to the technical field of high Mach number tests. The invention comprises a pipe wind tunnel body, a corrugated pipe, an inflatable seal, a sliding seal, a diaphragm and a spray pipe, wherein the upstream of the corrugated pipe is fixedly connected with the pipe wind tunnel body, the downstream of the corrugated pipe is fixedly connected with the spray pipe, the inflatable seal and the sliding seal are arranged between the pipe wind tunnel body and the outer wall surface of the spray pipe, and the diaphragm is arranged in the spray pipe. The invention provides a tube wind tunnel buffer structure, which aims to solve the problem of reducing the influence of tube vibration on free flow disturbance, has simple form, strong binding property, no complex mechanical actuation system and operability in engineering practical application compared with the traditional pulse wind tunnels, namely shock tube wind tunnels and tube wind tunnels, and the provided tube wind tunnel buffer structure is not only suitable for tube wind tunnels, but also can be used for other pulse devices, namely has wide application range, flexible form and strong practicability.
Description
Technical Field
The invention relates to a buffer structure and a buffer method of a pipe wind tunnel, and belongs to the technical field of high Mach number tests.
Background
The pipe wind tunnel is used as a special pulse device, the pipe wind tunnel body is a long equal-diameter pipe, the upstream end is sealed, the downstream is connected with a spray pipe through a diaphragm or a quick valve, and the downstream of the spray pipe is sequentially connected with a test section and a vacuum tank. Due to the advantages of simple structure, convenient parameter adjustment, high flow field quality and the like, the ultrasonic flow field has been developed and applied in the sub/cross/supersonic speed field, and has been developed in the supersonic speed and hypersonic speed fields in recent years.
Because of the unique running mode of the pulse type wind tunnel, the rapid opening measures such as diaphragm rupture are generally adopted, so that strong impact force exists at the moment of starting the wind tunnel, and because of the unsteady shock wave and expansion wave system exist in the pipe wind tunnel, the impact force has oscillation characteristics, and larger impact can be brought to the pipe wind tunnel body, the model and the supporting system of the wind tunnel. In order to inhibit the impact of impact load, a floating type operation mode is generally adopted in a tube wind tunnel, namely, the whole tube wind tunnel body (comprising a test cabin) is arranged on a support through a sliding support frame, a model is fixed on a foundation through an independent support system separated from the test cabin, and the vibration isolation method of the model mechanism in the hypersonic wind tunnel test section disclosed by the publication No. CN112697382A is disclosed above, so that impact energy in the operation process is consumed through sliding friction with the ground, meanwhile, the static state of the model is ensured, and the principle requirement of the relative operation of a conventional temporary impact wind tunnel is met.
However, as the pipe wind tunnel plays an increasingly important role in various tests, especially the requirement of a high-speed transition test, the disturbance requirement on free flow is extremely strict, and the disturbance level of the free flow in the actual flight environment is reduced as much as possible, so that the pipe wind tunnel is mainly used as the design core of the transition test.
Because the tube wind tunnel has no pressure regulating valve, stabilizing section and other structures, the free flow disturbance is lower than the traditional temporary flushing wind tunnel by the simple structure. In recent years, laminar flow jet pipe design technology has been developed, such as a low-disturbance wide Mach number wind tunnel laminar flow double-jet pipe design method for a pipe wind tunnel disclosed in the publication No. CN207923408U, so that free flow disturbance of a test section is further controlled. At the same time, the ratio of the influence of the vibration of the pipe body on the free flow disturbance is gradually increased.
As described above, in order to meet the special requirements of the transition test, the method is not limited to the suppression of the impact load on the model, and the structural vibration of the tube wind tunnel body needs to be reduced from the source, so that a novel buffering structure and method of the tube wind tunnel need to be provided to solve the above technical problems.
Disclosure of Invention
The present invention has been developed to address the problem of reducing the effects of pipe vibration on free flow disturbances by providing a pipe wind tunnel buffer structure, and a brief overview of the invention is provided below to provide a basic understanding of some aspects of the 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 first scheme is that the buffer structure of the pipe wind tunnel comprises a pipe wind tunnel body, a corrugated pipe, an inflatable seal, a sliding seal, a diaphragm and a spray pipe, wherein the upstream of the corrugated pipe is fixedly connected with the pipe wind tunnel body, the downstream of the corrugated pipe is fixedly connected with the spray pipe, the inflatable seal and the sliding seal are arranged between the pipe wind tunnel body and the outer wall surface of the spray pipe, and the diaphragm is arranged in the spray pipe.
Preferably: the downstream end of the pipe wind tunnel body is fixedly provided with a sealing end cover, the inner side wall of the sealing end cover is attached to the outer wall surface of the spray pipe, and the sealing end cover is provided with an inflatable seal and a sliding seal.
Preferably: the sealing end cover of the corrugated pipe is fixedly arranged at the downstream end part of the pipe wind tunnel body through an end cover flange.
Preferably: the upstream end of the corrugated pipe is fixedly connected with the pipe wind tunnel body through a flange and bolts.
Preferably: the downstream end of the corrugated pipe is fixedly connected with the spray pipe through a flange and bolts.
Preferably: the inflatable sealing material is rubber, and an inflatable cavity is formed in the inflatable sealing material.
Preferably: and graphite is adopted as the sliding sealing material.
The second scheme and the buffer method of the pipe wind tunnel are realized by the buffer structure of the pipe wind tunnel according to the first scheme, and the buffer method comprises the following steps:
step 1, in the preparation stage before the test, the inflatable seal is inflated by external air pressure, so as to isolate high pressure in a pipe wind tunnel from the external environment;
step 2, high-pressure inflation is carried out on the pipe wind tunnel body;
step 3, when the test starts, after the upstream driving pressure and the downstream vacuum environment reach the set requirements, carrying out deflation treatment on the inflatable seal, and simultaneously realizing transient operation of the wind tunnel through diaphragm rupture;
step 4, under the action of transient impact load caused by the rupture of the diaphragm in step 3, the corrugated pipe deforms, the pipe wind tunnel axially moves relative to the spray pipe, at the moment, the sealing is realized through sliding sealing, and impact energy generated by the transient impact load is consumed through the corrugated pipe and an air damping system in the corrugated pipe;
step 4.1, wherein the corrugated pipe in the step 4 is deformed, namely the corrugated pipe is pressed, and the compression amount isAt this time, the transient impact load of wind tunnel operation is +.>The deformation force of the bellows is +.>The gas damping force of the inner cavity of the corrugated pipe is +.>Neglecting the friction resistance of the pipe wind tunnel body during floating operation, the following relation is given:
formula (4.1)
Wherein,for the total mass of the tube wind tunnel body +.>The instantaneous acceleration of the tunnel body is the tube wind tunnel;
step 4.2, obtaining the change relation of the axial displacement of the tube wind tunnel body along with time by time integration of the instantaneous acceleration, thereby further obtaining the transient impact load of wind tunnel operationThe maximum value is estimated by the following calculation: step 4.2, obtaining the change relation of the axial displacement of the tube wind tunnel body along with time by time integration of the instantaneous acceleration, so as to further obtain the transient impact load of wind tunnel operation>The maximum value is estimated by the following calculation:
formula (4.2)
Wherein,the maximum inflation pressure of the tube wind tunnel body is set, and S is the area of the diaphragm;
and 4.3, taking the spray pipe as a stressed analysis object, wherein the spray pipe mainly receives the following forces: deformation reaction force of corrugated pipe，/>And->Equal and opposite, the reaction force of the gas compression in the inner cavity of the corrugated pipe +.>，/>And->Equal in size and opposite in direction, the following relationship holds:
formula (4.3)
Wherein,the impact force of the spray pipe is also the load which is needed to be born by the equipment foundation;
step 4.4, assuming that the compression amount of the corrugated pipe in the normal state is 0, after the corrugated pipe is impacted, the corrugated pipe is pressed, and the compression amount isThe direction of the force is positive in the downstream direction, and the following relation is given:
formula (4.4)
Wherein,is the elastic coefficient of the corrugated pipe;
step 4.5, regarding the instantaneous compression process of the gas in the inner cavity of the corrugated pipe as an adiabatic compression process, the following relation is given:
formula (4.5)
Wherein,for the bellows lumen gas density at initial rest, +.>For the bellows lumen volume at initial rest +.>For the bellows inner chamber gas pressure at the initial rest moment, +.>Is the gas density of the inner cavity of the corrugated pipe,>is the inner cavity volume of the corrugated pipe, < >>Is the cross-sectional area of the inner cavity of the corrugated pipe, < >>Is the pressure of the gas in the inner cavity of the corrugated pipe,/or>Is the specific heat ratio of the gas medium;
the following relationship is derived according to equation (4.5):
formula (4.6)
The instantaneous temperature to which the bellows is subjected is related to:
formula (4.7)
Wherein,is a gaseous medium constant;
the following relationship is derived according to equation (4.7):
formula (4.8)
By combining the above relations, the following relations are obtained:
formula (4.9)
Thereby, the transient impact load of wind tunnel operation is obtainedThe compression amount with the corrugated pipe is +.>The relation between the compression amount by the bellows +.>Obtaining transient impact load of wind tunnel operation>。
The invention has the following beneficial effects:
1. compared with the traditional pulse wind tunnel, namely shock tube wind tunnel and tube wind tunnel, the tube wind tunnel buffer structure provided by the invention has strong combination, no complex mechanical actuating system and operability in engineering practical application;
2. the tube wind tunnel buffering method provided by the invention is not only suitable for tube wind tunnels, but also can be used for other pulse equipment, namely, the application range is wide, the form is flexible, and the practicability is strong;
3. the invention can calculate the transient impact load of the exit wind tunnel, and can clearly know the stress of each section by the stress analysis of the whole system so as to analyze the test data.
Drawings
Fig. 1 is a schematic structural view of a buffering structure of a tube wind tunnel according to the present invention.
In the figure: the device comprises a 1-pipe wind tunnel body, a 2-corrugated pipe, a 3-gas-filled seal, a 4-sliding seal, a 5-diaphragm, a 6-spray pipe, a 7-sealing end cover and an 8-end cover flange.
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 present invention is divided into a fixed connection and a detachable connection, wherein the fixed connection (i.e. the non-detachable connection) includes, but is not limited to, a conventional fixed connection manner such as a hemmed connection, a rivet connection, an adhesive connection, a welded connection, etc., and the detachable connection includes, but is not limited to, a conventional detachable manner such as a threaded connection, a snap connection, a pin connection, a hinge connection, etc., and when the specific connection manner is not specifically limited, at least one connection manner can be found in the existing connection manner by default, so that the function can be realized, and a person skilled in the art can select the connection according to needs. For example: the fixed connection is welded connection, and the detachable connection is hinged connection.
The first embodiment is as follows: referring to fig. 1, a buffer structure of a pipe wind tunnel of the present embodiment is described, including a pipe wind tunnel body 1, a bellows 2, an inflatable seal 3, a sliding seal 4, a diaphragm 5 and a nozzle 6, instead of a flange and a bolt direct connection form adopted by a conventional pipe wind tunnel body 1 and a nozzle 6, a pipe wind tunnel body 1 located at an upstream of the pipe wind tunnel is still fixedly connected in a conventional flange or other form, the pipe wind tunnel body 1 of the present embodiment is connected with the nozzle 6 through the bellows 2, and the pipe wind tunnel body 1 is integrally fixed on a foundation through a sliding track and operates in a floating form; the spray pipe 6 is fixedly connected with the downstream test section by adopting the traditional flange and other fixed connection, no relative movement exists, the upstream of the corrugated pipe 2 is fixedly connected with the pipe wind tunnel body 1, the downstream of the corrugated pipe 2 is fixedly connected with the spray pipe 6, the inflatable seal 3 and the sliding seal 4 are arranged between the pipe wind tunnel body 1 and the outer wall surface of the spray pipe 6, and the membrane 5 is arranged in the spray pipe 6.
The downstream end of the pipe wind tunnel body 1 is fixedly provided with a sealing end cover 7, the inner side wall of the sealing end cover 7 is attached to the outer wall surface of the spray pipe 6, and an inflatable seal 3 and a sliding seal 4 are arranged.
The sealing end cover 7 of the corrugated pipe 2 is fixedly arranged at the downstream end part of the pipe wind tunnel body 1 through an end cover flange 8.
The upstream end of the corrugated pipe 2 is fixedly connected with the pipe wind tunnel body 1 through a flange and bolts. The downstream end of the bellows 2 is fixedly connected with the spray pipe 6 through a flange and bolts.
The material of the inflatable seal 3 adopts rubber, and an inflatable cavity is formed in the inflatable seal 3, and the inflatable seal 3 is inflated through external air pressure, so that the effect of reinforcing the seal is achieved, and further, the isolation between the high-pressure environment in the pipe and the outside is realized.
The sliding seal 4 is made of graphite.
The second embodiment is as follows: the present embodiment is described with reference to fig. 1, and is implemented by a buffering structure of a tube wind tunnel according to the first embodiment, where the buffering method of the tube wind tunnel of the present embodiment includes the following steps:
step 1, in the preparation stage before the test, the inflatable seal 3 is inflated by external air pressure, so that the inflatable seal 3 is of a main sealing structure and is used for isolating high pressure and external environment in the pipe wind tunnel body 1;
step 2, high-pressure inflation is carried out on the pipe wind tunnel body 1; in general, it is recommended that the inflation pressure be controlled between 4 and 8 atm, with 1 atm being 1 atmosphere.
Step 3, when the test starts, after the upstream driving pressure and the downstream vacuum environment meet the set requirements, carrying out deflation treatment on the inflatable seal 3, wherein the sliding seal 5 is of a main sealing structure, and because the process time is shorter, the strong sliding characteristic of the sliding seal 5 is mainly utilized, graphite and other forms are suggested, and meanwhile, the transient operation of the wind tunnel is realized through the rupture of the diaphragm 5;
step 4, under the action of transient impact load caused by the rupture of the diaphragm 5 in step 3, the corrugated pipe 2 deforms, the pipe wind tunnel body 1 axially moves relative to the spray pipe 6, at the moment, the sealing is realized through the sliding seal 4, and impact energy generated by the transient impact load is consumed through the corrugated pipe 2 and an air damping system in the corrugated pipe;
step 4.1, wherein the corrugated pipe 2 in the step 4 is deformed, namely the corrugated pipe 2 is pressed, and the compression amount isAt this time, the upstream pipe wind tunnel body is taken as a stress analysis object and mainly receives the following forces: transient impact load of wind tunnel operation is +.>The deformation force of the bellows 2 is +.>The gas damping force of the inner cavity of the corrugated pipe 2 is +.>Neglecting the frictional resistance of the tube wind tunnel body 1 during floating operation, the following relation is given:
formula (4.1)
Wherein,for the total mass of the tube wind tunnel body 1, +.>The instantaneous acceleration of the tube wind tunnel body 1;
step 4.2, obtaining the change relation of the axial displacement of the tube wind tunnel body 1 along with time by time integration of the instantaneous acceleration, and further carrying out wind tunnel operation on the instantaneous impact loadThe maximum value is estimated by the following calculation:
formula (4.2)
Wherein,the maximum inflation pressure of the tube wind tunnel body 1 is set, S is the area of the diaphragm 5;
and 4.3, taking the spray pipe 6 as a stressed analysis object, wherein the spray pipe 6 mainly receives the following forces: deformation reaction force of the bellows 2，/>And->Equal and opposite, the reaction force of the gas compression in the inner cavity of the corrugated pipe 2>，/>And->Equal in size and opposite in direction, the following relationship holds:
formula (4.3)
Wherein,the impact force of the spray pipe 6 is also the load which is needed to be born by the equipment foundation;
step 4.4, assuming that the compression amount of the corrugated tube 2 in the normal state is 0, after the impact is applied, the corrugated tube 2 is pressed, the compression amount isThe direction of the force is positive in the downstream direction, and the following relation is given:
formula (4.4)
Wherein,is the elastic coefficient of the corrugated pipe 2;
step 4.5, the instantaneous compression process of the gas in the inner cavity of the corrugated pipe 2 can be regarded as an adiabatic compression process, and the following relation is given:
formula (4.5)
Wherein,for the initial resting moment of the gas density in the inner chamber of the bellows 2,/->For the volume of the inner chamber of the bellows 2 at the initial standstill, < >>For the initial resting moment bellows 2 lumen gas pressure, +.>For the gas density of the inner cavity of the corrugated pipe 2 +.>Is the inner cavity volume of the corrugated pipe 2->Is the cross-sectional area of the inner cavity of the corrugated pipe 2 +.>For the gas pressure in the inner cavity of the bellows 2 +.>Is the specific heat ratio of the gas medium;
the following relationship is derived according to equation (4.5):
formula (4.6)
The instantaneous temperature to which the bellows 2 is subjected has the following relationship:
formula (4.7)
Wherein,is a gaseous medium constant;
the following relationship is derived according to equation (4.7):
formula (4.8)
By combining the above relations, the following relations are obtained:
formula (4.9)
Thereby, the transient impact load of wind tunnel operation is obtainedThe compression with the bellows 2 is +.>The relation between the compression amount by the bellows 2 +.>Obtaining transient impact load of wind tunnel operation>。
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 (8)
1. The utility model provides a buffer structure of pipe wind tunnel which characterized in that: comprises a pipe wind tunnel body (1), a corrugated pipe (2), an inflatable seal (3), a sliding seal (4), a membrane (5) and a spray pipe (6), wherein the upstream of the corrugated pipe (2) is fixedly connected with the pipe wind tunnel body (1), the downstream of the corrugated pipe (2) is fixedly connected with the spray pipe (6), an inflatable seal (3) and a sliding seal (4) are arranged between the outer wall surfaces of the pipe wind tunnel body (1) and the spray pipe (6), and a diaphragm (5) is arranged in the spray pipe (6).
2. The buffering structure of a tube wind tunnel according to claim 1, wherein: the downstream end of the pipe wind tunnel body (1) is fixedly provided with a sealing end cover (7), the inner side wall of the sealing end cover (7) is attached to the outer wall surface of the spray pipe (6), and an inflatable seal (3) and a sliding seal (4) are arranged.
3. A buffering structure for a tube wind tunnel according to claim 2, wherein: the sealing end cover (7) of the corrugated pipe (2) is fixedly arranged at the downstream end part of the pipe wind tunnel body (1) through an end cover flange (8).
4. The buffering structure of a tube wind tunnel according to claim 1, wherein: the upstream end of the corrugated pipe (2) is fixedly connected with the pipe wind tunnel body (1) through a flange and bolts.
5. The buffering structure of a tube wind tunnel according to claim 1, wherein: the downstream end of the corrugated pipe (2) is fixedly connected with the spray pipe (6) through a flange and bolts.
6. The buffering structure of a tube wind tunnel according to claim 1, wherein: the material of the inflatable seal (3) is rubber, and an inflatable cavity is formed in the inflatable seal.
7. The buffering structure of a tube wind tunnel according to claim 1, wherein: and the sliding seal (4) is made of graphite.
8. A method for buffering a tube wind tunnel, which is realized by the buffer structure of any one of claims 1-7, and is characterized by comprising the following steps:
step 1, in the preparation stage before the test, the inflatable seal (3) is inflated by external air pressure to isolate high pressure in the pipe wind tunnel body (1) from the external environment;
step 2, high-pressure inflation is carried out on the pipe wind tunnel body (1);
step 3, when the test starts, after the upstream driving pressure and the downstream vacuum environment meet the set requirements, carrying out deflation treatment on the inflatable seal (3), and simultaneously realizing transient operation of the wind tunnel through rupture of the diaphragm (5);
step 4, under the action of transient impact load caused by rupture of the diaphragm (5) in step 3, the corrugated pipe (2) deforms, the pipe wind tunnel body (1) axially moves relative to the spray pipe (6), at the moment, sealing is realized through the sliding seal (4), and impact energy generated by the transient impact load is consumed through the corrugated pipe (2) and an air damping system in the corrugated pipe;
step 4.1, wherein the corrugated pipe (2) in the step 4 is deformed, namely the corrugated pipe (2) is pressed, and the compression amount isAt this time, the transient impact load of wind tunnel operation is +.>The deformation force of the corrugated pipe (2) is +.>The inner cavity gas damping force of the corrugated pipe (2) is +.>Neglecting the friction resistance of the pipe wind tunnel body (1) during floating operation, the following relation is given:
formula (4.1)
Wherein,for the total mass of the tube wind tunnel body (1), +.>The instantaneous acceleration of the tube wind tunnel body (1);
step 4.2, obtaining the change relation of the axial displacement of the tube wind tunnel body (1) along with time by time integration of the instantaneous acceleration, and further operating the transient impact load of the wind tunnelThe maximum value is estimated by the following calculation:
formula (4.2)
Wherein,the maximum inflation pressure of the tube wind tunnel body (1) is set, and S is the area of the diaphragm (5);
and 4.3, taking the spray pipe (6) as a stressed analysis object, wherein the spray pipe (6) mainly receives the following forces: deformation reaction force of corrugated pipe (2)，/>And->Equal and opposite, the reaction force of the inner cavity gas compression of the corrugated pipe (2)>，/>And->Equal in size and opposite in direction, the following relationship holds:
formula (4.3)
Wherein,the impact force of the spray pipe (6) is also the load which is needed to be born by the equipment foundation;
step 4.4, assuming that the compression amount of the corrugated pipe (2) in the normal state is 0, after the corrugated pipe (2) is impacted, the corrugated pipe (2) is compressed, and the compression amount isThe direction of the force is positive in the downstream direction, and the following relation is given:
formula (4.4)
Wherein,is a corrugated pipe2) Is a coefficient of elasticity of (a);
step 4.5, regarding the instantaneous compression process of the inner cavity gas of the corrugated pipe (2) as an adiabatic compression process, the following relation is given:
formula (4.5)
Wherein,for the gas density of the inner cavity of the bellows (2) at the initial standstill,/-, for the time of the initial standstill>For the inner chamber volume of the bellows (2) at the initial standstill time,/-, for>For the gas pressure in the inner space of the bellows (2) at the initial standstill,/>Is the gas density of the inner cavity of the corrugated pipe (2)>Is the inner cavity volume of the corrugated pipe (2), +.>Is the cross-sectional area of the inner cavity of the corrugated pipe (2)>Is the gas pressure of the inner cavity of the corrugated pipe (2)>Is the specific heat ratio of the gas medium;
the following relationship is derived according to equation (4.5):
formula (4.6)
The instantaneous temperature to which the bellows (2) is subjected has the following relationship:
formula (4.7)
Wherein,is a gaseous medium constant;
the following relationship is derived according to equation (4.7):
formula (4.8)
By combining the above relations, the following relations are obtained:
formula (4.9)
Thereby, the transient impact load of wind tunnel operation is obtainedThe compression amount with the corrugated pipe (2) is +.>The relation between the compression amount by the bellows (2)>Obtaining transient impact load of wind tunnel operation>。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410140109.9A CN117664501A (en) | 2024-02-01 | 2024-02-01 | Buffer structure and method for pipe wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410140109.9A CN117664501A (en) | 2024-02-01 | 2024-02-01 | Buffer structure and method for pipe wind tunnel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117664501A true CN117664501A (en) | 2024-03-08 |
Family
ID=90086602
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410140109.9A Pending CN117664501A (en) | 2024-02-01 | 2024-02-01 | Buffer structure and method for pipe wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117664501A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU152348U1 (en) * | 2014-12-15 | 2015-05-20 | Федеральное государственное бюджетное учреждение науки Институт проблем механики им. А.Ю. Ишлинского Российской академии наук (ИПМех РАН) | HYPERSONIC SHOCK AERODYNAMIC TUBE |
| CN112595482A (en) * | 2020-12-08 | 2021-04-02 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Deformation chamber for supersonic wind tunnel test |
| CN112697382A (en) * | 2020-12-22 | 2021-04-23 | 中国空气动力研究与发展中心超高速空气动力研究所 | Vibration isolation method for model mechanism in hypersonic wind tunnel test section |
| CN112857733A (en) * | 2021-03-10 | 2021-05-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device for quickly closing shock tunnel throat |
| CN115575077A (en) * | 2022-11-21 | 2023-01-06 | 中国航空工业集团公司沈阳空气动力研究所 | Vibration isolation system for tunnel body of pipe wind tunnel |
-
2024
- 2024-02-01 CN CN202410140109.9A patent/CN117664501A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU152348U1 (en) * | 2014-12-15 | 2015-05-20 | Федеральное государственное бюджетное учреждение науки Институт проблем механики им. А.Ю. Ишлинского Российской академии наук (ИПМех РАН) | HYPERSONIC SHOCK AERODYNAMIC TUBE |
| CN112595482A (en) * | 2020-12-08 | 2021-04-02 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Deformation chamber for supersonic wind tunnel test |
| CN112697382A (en) * | 2020-12-22 | 2021-04-23 | 中国空气动力研究与发展中心超高速空气动力研究所 | Vibration isolation method for model mechanism in hypersonic wind tunnel test section |
| CN112857733A (en) * | 2021-03-10 | 2021-05-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device for quickly closing shock tunnel throat |
| CN115575077A (en) * | 2022-11-21 | 2023-01-06 | 中国航空工业集团公司沈阳空气动力研究所 | Vibration isolation system for tunnel body of pipe wind tunnel |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107976295B (en) | 2 m-magnitude free piston driven high-enthalpy shock wave wind tunnel | |
| CN107806977B (en) | Combined wide Mach number high enthalpy pulse wind tunnel tube structure | |
| KR101180986B1 (en) | Moving Model Rig for Ultra-Speed Tube Train | |
| Kyriakides et al. | On the inflation of a long elastic tube in the presence of axial load | |
| CN110031181B (en) | TPS reverse thrust nacelle thrust calibration test method | |
| CN115541169B (en) | Superposed driving pipe wind tunnel compact quick-opening system and method | |
| CN207703439U (en) | A kind of high enthalpy shock tunnel of 2m magnitudes free-piston driving | |
| CN117147093B (en) | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft | |
| CN112444368A (en) | Ground simulation test device for ultrahigh-speed reentry test airflow | |
| CN117664501A (en) | Buffer structure and method for pipe wind tunnel | |
| CN115575077A (en) | Vibration isolation system for tunnel body of pipe wind tunnel | |
| Verma et al. | Relation between shock unsteadiness and the origin of side-loads inside a thrust optimized parabolic rocket nozzle | |
| CN112857733B (en) | Device for quickly closing shock tunnel throat | |
| CN115931283B (en) | Accurate measurement device for thrust characteristics of double culvert spray pipe | |
| Lafferty et al. | Measurements of Fluctuating Pitot Pressure," Tunnel Noise," in the AEDC Hypervelocity Wind Tunnel No. 9 | |
| CN115387908A (en) | Air inlet passage isolation section flow control device based on wall plate aeroelastic effect and design method | |
| CN118008917B (en) | Control device and method for pipe wind tunnel driving piston | |
| JPH07218381A (en) | Apparatus and method for controlling waveform in shock wind-tunnel | |
| Berrier et al. | Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft | |
| CN215720469U (en) | Aeroengine electronic equipment damping damper adopting air compression chamber for damping | |
| Verma et al. | Cold gas dual-bell tests in high-altitude simulation chamber | |
| Chen et al. | The Design and Testing of an Electromechanically Actuated Pitot Probe to Characterize Flow in a Mach 7 Wind Tunnel | |
| CN103303492B (en) | A kind of steel rope pretension force design method of airplane flexible control system | |
| Juhany et al. | AT0 Ludwieg tube wind tunnel at KAU | |
| SU857765A1 (en) | Pressure ratio pickup |
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 |