CN108036918B - The FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations - Google Patents
The FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations Download PDFInfo
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- CN108036918B CN108036918B CN201810002322.8A CN201810002322A CN108036918B CN 108036918 B CN108036918 B CN 108036918B CN 201810002322 A CN201810002322 A CN 201810002322A CN 108036918 B CN108036918 B CN 108036918B
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Abstract
The invention discloses the FREE-PISTON SHOCK TUNNELs of one kind of multiple mode operations, including wind tunnel noumenon, distributed vacuum system, air supply system, track support system, wind tunnel noumenon includes driving mechanism, shock wave pipeline section, monofilm sandwiched film mechanism, jet pipe and test section, and distributed vacuum system vacuumizes driving mechanism, shock wave pipeline section and test section；Air supply system supplies driving mechanism and shock wave pipeline section；Wind tunnel noumenon is sequentially coaxially tightly connected with shock wave pipeline section, monofilm sandwiched film mechanism, jet pipe and test section.The present invention is based on the equipment of free-piston high enthalpy shock tunnel, by quickly replacing, connecting various parts and with three with the cooperation of main sandwiched film mechanism, wind-tunnel is set to have the test capability of enthalpy shock tunnel two states in conventional low enthalpy shock tunnel and long-time, the scope of application and test capability for improving performance of wind tunnel, reduce operating cost.
Description
Technical field
The present invention relates to the FREE-PISTON SHOCK TUNNELs of one kind of multiple mode operations, applied to the hypersonic of various states
Test.
Background technique
Deficiency when existing hypersonic field is studied on testing equipment includes inhaling for hypersonic and ultrahigh speed
Gas formula aircraft test with assessment propulsion trial equipment, need longer test period, high dynamic pressure, close to pure air,
Reproduction enthalpy, bigger size completely；For interceptor sensor and the long-time of mobility research, high dynamic pressure, the examination of high enthalpy
Test equipment.Test period is extremely important for the ability of new equipment.Currently for hypersonic technology and its all need of application
Asking mainly reduces cost while improving safety and reliability.
The diversification of equipment is attributable to large-scale flying condition in hypersonic test and the uniqueness for needing to study is existing
As.The research for carrying out aerodynamic characteristic under different simulated conditions to aircraft may be implemented in different types of wind-tunnel.Final is flight
The development of device provides wider test data, and the testing equipment that can more make full use of construction cost high.In Ma5
~12 hypersonic region, PERFECT GAS FLOW simulation is applicable.Under very high speed (ultrahigh speed region), heat,
Chemistry, radiation, ablation benefit are more important, it is therefore necessary to simulative gas effect.Utilize the hypersonic test of different type
The respective advantage of equipment integrates the test result of a variety of testing equipments and these results is extrapolated to in-flight for a project
For it is most important.Shock tunnel is very suitable to the aerodynamic force of 8 or more Mach number and the hypervelocity flight with chemical reaction flow
Test.
The prior art, including free-piston high enthalpy shock tunnel mode and conventional two kinds of mode, usual one of shock tunnel
Wind-tunnel only realizes one mode, and when same test needs the trystate of different mode, model needs between different wind-tunnel
It installs repeatedly, needs that resulting error will necessarily be introduced using different jet pipes, influence the accuracy and examination of test result
Test efficiency；It is all very high in construction and operating cost meanwhile since it is desired that build a plurality of wind-tunnel.
The runing time of existing FREE-PISTON SHOCK TUNNEL is shorter, is unable to satisfy the hypersonic dynamometry in part and special test
Demand.
Summary of the invention
Technology of the invention solves the problems, such as: in order to overcome the deficiencies of the prior art, providing oneself of one kind of multiple mode operations
By piston shock tunnel, big enthalpy range, long-time and inexpensive multi-mode operation mode are had both.
The technical solution of the invention is as follows:
The FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations, including wind tunnel noumenon, distributed vacuum system, gas supply system
System, track support system,
Wind tunnel noumenon includes driving mechanism, shock wave pipeline section, monofilm sandwiched film mechanism, jet pipe and test section,
Distributed vacuum system vacuumizes driving mechanism, shock wave pipeline section and test section；
Air supply system supplies driving mechanism and shock wave pipeline section；
Track support system provides support to driving mechanism, shock wave pipeline section, monofilm sandwiched film mechanism；
Wind tunnel noumenon is sequentially coaxially tightly connected with shock wave pipeline section, monofilm sandwiched film mechanism, jet pipe and test section, in monofilm
1 diaphragm is set in sandwiched film mechanism；
Under high enthalpy shock tunnel mode, driving mechanism includes piston emitter, piston, compression pipeline section and main folder film machine
Structure, wherein 1 diaphragm is arranged in main sandwiched film mechanism；
Piston is placed in piston emitter, by high pressure air drives, along compression pipeline section high-speed motion, and to compressed pipe
Gas-powered in section generates heating, pressurization；
Under low enthalpy shock tunnel mode, driving mechanism includes compression pipeline section and main sandwiched film mechanism, wherein in main folder film machine
2 diaphragms are set in structure, form middle gas chamber among 2 diaphragms；
In long-time under enthalpy shock tunnel mode, driving mechanism includes piston emitter, piston, compression pipeline section, master
Sandwiched film mechanism, the second compression pipeline section and the second monofilm sandwiched film mechanism, wherein check valve assembly is arranged in main sandwiched film mechanism；It is pressing
Buffer piston mechanism is arranged in draw section end makes piston slow down and stop when piston runs to compression pipeline section end with certain speed
Only.
Under high enthalpy shock tunnel mode, before wind tunnel operation main sandwiched film mechanism interior diaphragm to compression pipeline section, shock wave pipeline section into
Row gas barrier, monofilm sandwiched film mechanism interior diaphragm carry out gas barrier to shock wave pipeline section and test section.
After wind tunnel operation, compresses the diaphragm in the main sandwiched film mechanism of high temperature and high pressure gas bursting of pipeline section end and generate strong sharp
Wave, intense shock wave enter shock wave pipeline section and along its high-speed cruisings, form the test gas of high temperature and pressure, bursting in shock wave pipeline section end
Diaphragm in monofilm sandwiched film mechanism, high temperature and pressure test gas enter jet pipe, and the gas velocity of test setting is accelerated to by jet pipe
Degree enters high vacuum test section.
When buffer piston mechanism is arranged in compression pipeline section end, and piston runs to compression pipeline section end with certain speed, make
Piston slows down and stops.
Under low enthalpy shock tunnel mode, before wind tunnel operation main sandwiched film mechanism interior diaphragm to compression pipeline section, shock wave pipeline section into
Row gas barrier, monofilm sandwiched film mechanism interior diaphragm carry out gas barrier to shock wave pipeline section and test section.
After wind tunnel operation, the high pressure gas successively bursting main folder film machine in pipeline section is compressed in diaphragm middle gas chamber deflation pressure release
Diaphragm in structure simultaneously generates intense shock wave, and intense shock wave enters shock wave pipeline section and along its high-speed cruising, forms height in shock wave pipeline section end
The test gas of warm high pressure, the diaphragm in bursting monofilm sandwiched film mechanism, high temperature and pressure test gas enters jet pipe, and is added by jet pipe
The air velocity of speed to test setting enters high vacuum test section.
In long-time under enthalpy shock tunnel mode, piston is placed in piston emitter, passes through high pressure air drives, edge
Pipeline section high-speed motion is compressed, and heating, pressurization are generated to the gas-powered in compression pipeline section.
The second monofilm sandwiched film mechanism interior diaphragm carries out gas barrier to the second compression pipeline section, shock wave pipeline section before wind tunnel operation,
Monofilm sandwiched film mechanism interior diaphragm carries out gas barrier to shock wave pipeline section and test section.
After wind tunnel operation, the high temperature and high pressure gas of compression pipeline section end opens the entrance of the check valve assembly in main sandwiched film mechanism
Second compression pipeline section, opens the second monofilm sandwiched film mechanism interior diaphragm and generates intense shock wave, intense shock wave enters shock wave pipeline section and along it
High-speed cruising forms the test gas of high temperature and pressure in shock wave pipeline section end, the diaphragm in bursting monofilm sandwiched film mechanism, and high temperature is high
Pressure test gas enters jet pipe, and enters high vacuum test section by the air velocity that jet pipe accelerates to test setting.
When springing back after piston stopping, the check valve assembly in main sandwiched film mechanism is closed, and prevents Piston rebound from generating swollen
Swollen wave enters the second compression pipeline section.
The advantages of the present invention over the prior art are that:
(1) present invention is based on the equipment of free-piston high enthalpy shock tunnel, by quickly replacing, connecting various portions
Part and with three with the cooperation of main sandwiched film mechanism, so that wind-tunnel is had enthalpy shock tunnel two in conventional low enthalpy shock tunnel and long-time
The test capability of kind state, improves the scope of application and test capability of performance of wind tunnel, reduces operating cost；
(2) with can only single mode operation wind-tunnel compared with, the FREE-PISTON SHOCK TUNNEL of multi-mode operation of the present invention has
Only mode can be realized by increasing or replacing a small amount of component in the more fully higher test mechanism of test capability and cost performance
Between convert, it is high-efficient.
Detailed description of the invention
Fig. 1 is high enthalpy shock tunnel structural schematic diagram of the present invention；
Fig. 2 is low enthalpy shock tunnel structural schematic diagram of the present invention；
Fig. 3 is enthalpy shock tunnel structural schematic diagram in long-time of the present invention；
Fig. 4 is high enthalpy shock tunnel main folder film structural scheme of mechanism of the present invention；
Fig. 5 is low enthalpy shock tunnel main folder film structural scheme of mechanism of the present invention；
Fig. 6 is enthalpy shock tunnel main folder film structural scheme of mechanism in long-time of the present invention.
Specific embodiment
Present invention will now be described in detail with reference to the accompanying drawings..
The FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations, including wind tunnel noumenon, distributed vacuum system 10, gas supply
System 11, track support system 12,
Wind tunnel noumenon includes driving mechanism, shock wave pipeline section 5, monofilm sandwiched film mechanism 6, jet pipe 7 and test section 8,
Distributed vacuum system vacuumizes driving mechanism, shock wave pipeline section 5 and test section 8；
Air supply system supplies driving mechanism and shock wave pipeline section 5；
Track support system provides support to driving mechanism, shock wave pipeline section 5, monofilm sandwiched film mechanism 6；
Wind tunnel noumenon is sequentially coaxially tightly connected with shock wave pipeline section 5, monofilm sandwiched film mechanism 6, jet pipe 7 and test section 8,
1 diaphragm is set in monofilm sandwiched film mechanism 6.
Under high enthalpy shock tunnel mode, as shown in Figure 1, driving mechanism includes piston emitter 1, piston 2, compressed pipe
Section 3 and main sandwiched film mechanism 4, wherein 1 diaphragm is arranged in main sandwiched film mechanism 4；
Piston 2 is placed in piston emitter 1, by high pressure air drives, along compression 3 high-speed motion of pipeline section, and to pressure
Gas-powered in draw section 3 generates heating, pressurization；
As shown in figure 4, main 4 interior diaphragm of sandwiched film mechanism is to compression pipeline section before wind tunnel operation under high enthalpy shock tunnel mode
3, shock wave pipeline section 5 carries out gas barrier, 6 interior diaphragm of monofilm sandwiched film mechanism to shock wave pipeline section 5 and test section 8 carry out gas every
From in compression 3 end of pipeline section, setting buffer piston mechanism makes to live when piston 2 runs to compression 3 end of pipeline section with certain speed
Plug 2 slows down and stops.
After wind tunnel operation, compresses the diaphragm in the main sandwiched film mechanism 4 of high temperature and high pressure gas bursting of 3 end of pipeline section and generate strong
Shock wave, intense shock wave enter shock wave pipeline section 5 and along its high-speed cruisings, form the test gas of high temperature and pressure in 5 end of shock wave pipeline section,
Diaphragm in bursting monofilm sandwiched film mechanism 6, high temperature and pressure test gas enters jet pipe 7, and accelerates to test setting by jet pipe 7
Air velocity enters high vacuum test section 8.
Under high enthalpy shock tunnel mode, universal piston emitter connection length 75m, internal diameter is 668mm compressed pipe；It is main
Sandwiched film mechanism is that buffer piston monofilm presss from both sides film mode；Shock wave length of tube 32m, internal diameter 290mm.Using in universal piston emitter
Pressure-air hundreds of kilograms of taskwork plug in compressed pipe is accelerated into high speed, and front was originally distributed in compressed pipe
Helium/argon driving gas is compressed.Compression pipe end is pressurized to helium/argon driving gas of high temperature and pressure in bursting main folder film machine
After diaphragm in structure, intense shock wave is generated in shock tube.Intense shock wave is run along shock tube, and is generated instead at monofilm sandwiched film mechanism
It penetrates, intense shock wave generates pressurized, heated effect, the rupture of diaphragm in monofilm sandwiched film mechanism to the test gas of in shock tube distribution
Afterwards, high temperature and pressure test gas enters jet pipe, and accelerates to the air velocity that test needs by jet pipe, to being mounted in test section
Test model generation effect, completes test.
Under low enthalpy shock tunnel mode, as shown in Fig. 2, driving mechanism includes compressing pipeline section 3 and main sandwiched film mechanism 4,
In in main sandwiched film mechanism 4 be arranged 2 diaphragms, form middle gas chamber among 2 diaphragms；
Under low enthalpy shock tunnel mode, as shown in figure 5, main 4 interior diaphragm of sandwiched film mechanism is to compression pipeline section before wind tunnel operation
3, shock wave pipeline section 5 carries out gas barrier, 6 interior diaphragm of monofilm sandwiched film mechanism to shock wave pipeline section 5 and test section 8 carry out gas every
From.
After wind tunnel operation, the high pressure gas successively bursting main folder film machine in pipeline section 3 is compressed in diaphragm middle gas chamber deflation pressure release
Diaphragm in structure 4 simultaneously generates intense shock wave, and intense shock wave enters shock wave pipeline section 5 and along its high-speed cruising, is formed in 5 end of shock wave pipeline section
The test gas of high temperature and pressure, the diaphragm in bursting monofilm sandwiched film mechanism 6, high temperature and pressure test gas enters jet pipe 7, and is sprayed
The air velocity that pipe 7 accelerates to test setting enters high vacuum test section 8.
Under low enthalpy shock tunnel mode, using the compression pipeline section of 10m long as high drive section, the shock tube of 32m long
Duan Zuowei is by drive section.Realize the controllable ruptures of membranes of high pressure using double diaphragms in main sandwiched film mechanism, generate intense shock wave, using shock wave plus
The test air crossed in heat shock wave duct generates the test air-flow of Pass Test requirement in test section after accelerating by jet pipe.
In long-time under enthalpy shock tunnel mode, as shown in figure 3, driving mechanism include piston emitter 1, piston 2,
Pipeline section 3, the compression pipeline section 14 of main sandwiched film mechanism 4, second and the second monofilm sandwiched film mechanism 15 are compressed, as shown in fig. 6, wherein in main folder
Check valve assembly is set in film mechanism 4；Buffer piston mechanism 13 is set in compression 3 end of pipeline section, piston 2 is run with certain speed
To when compressing 3 end of pipeline section, so that piston 2 is slowed down and stop.
In long-time under enthalpy shock tunnel mode, piston 2 is placed in piston emitter, by high pressure air drives,
Heating, pressurization are generated along compression 3 high-speed motion of pipeline section, and to the gas-powered in compression pipeline section 3.
15 interior diaphragm of the second monofilm sandwiched film mechanism carries out gas to the second compression pipeline section 14, shock wave pipeline section 5 before wind tunnel operation
Isolation, 6 interior diaphragm of monofilm sandwiched film mechanism carry out gas barrier to shock wave pipeline section 5 and test section 8.
After wind tunnel operation, compression 3 end of pipeline section high temperature and high pressure gas open the check valve assembly in main sandwiched film mechanism 4 into
Enter the second compression pipeline section 14, open 15 interior diaphragm of the second monofilm sandwiched film mechanism and generate intense shock wave, intense shock wave enters shock wave pipeline section 5
And along its high-speed cruising, the test gas of high temperature and pressure is formed in 5 end of shock wave pipeline section, the film in bursting monofilm sandwiched film mechanism 6
Piece, high temperature and pressure test gas enters jet pipe 7, and enters high vacuum test by the air velocity that jet pipe 7 accelerates to test setting
Pipeline section 8.
When springing back after the stopping of piston 2, the check valve assembly in main sandwiched film mechanism 4 is closed, and piston 2 is prevented to spring back generation
Dilatational wave enters the second compression pipeline section 14.
In long-time under enthalpy shock tunnel mode, relative to high enthalpy shock tunnel mode, long 24m, internal diameter are increased
The second compression section of 290mm, and three in main sandwiched film mechanism be arranged piston holdback.By the compression of taskwork plug in compressed pipe
Helium/argon driving gas enters the second compression section by holdback check valve, generates in the second monofilm sandwiched film mechanism implosion and swashs by force
While wave, helium/argon driving gas is prevented by holdback check valve, be cannot be introduced into compressed pipe, is avoided energy loss.Together
When, longer second compression section, so that the reflection of dilatational wave needs the longer time.Therefore when increasing the efficiency test of wind-tunnel
Between.
Universal piston emitter is self-driving type piston trigger mechanism, by air storage chamber tank body and the axial hair for being packed into tank body
Injection device, transmitting tube composition.Taskwork plug is fitted into emitter, during the launch process, by by the high pressure in air storage chamber tank body
Air is rapidly introduced into taskwork plug back cavity, taskwork plug is pushed into transmitting tube and compressed pipe, high-speed cruising.Universal transmitter structure counterweight
The structure of piston does not require, and can meet the piston transmitting needs at various pressures of different weight, structure and size.
Taskwork plug is rotary structure, and overall diameter is equal with compression bore.During the test, taskwork plug is in compressed pipe
Medium-high speed sports compress the driving gas being filled in compressed pipe.
Compression pipeline section is the elongated pipeline configuration of uniform internal diameter, and inner surface is smooth, axially distributed on tube wall to have radial through-hole, is used
In connection inflation, vacuum system or mounting test system sensor.Every section of compressed pipe has wheel support with one, is supported in elongated
In track groups.
Shock wave pipeline section is the elongated pipeline configuration of uniform internal diameter, and inner surface is smooth, axially distributed on tube wall to have radial through-hole, is used
In connection inflation, vacuum system or mounting test system sensor.Every section of shock tube has wheel support with one, is supported in elongated
In track groups.
Three with main sandwiched film mechanism be hollow composite unit structure, be mainly made of left folder membrane body, middle folder membrane body and right folder membrane body.
Left folder membrane body is connected with compression pipeline section, and internal diameter is consistent with compression pipeline section, outer surface setting interval screw thread；Middle folder membrane body is three sections of platforms
Rank cavity configuration, both ends are interval thread cavity, and centre is central diameter chamber, and internal diameter is between compressed pipe and shock tube；Right folder membrane body and
Shock tube is connected, and inside includes an insert installation cavity and a latus rectum chamber equal with shock wave bore, between the setting of outer surface
Every screw thread.Left folder membrane body and right folder membrane body pass through interval screw thread pair respectively and are connected with middle folder membrane body.Three use the left folder film of sandwiched film mechanism
Body clamp piston buffer unit and monolithic diaphragm, when right folder membrane body does not clamp components, for suitable for the high enthalpy shock wave of free-piston
The buffer piston monofilm sandwiched film mechanism of wind-tunnel；Three when clamping a piece of diaphragm with the left and right folder membrane body of sandwiched film mechanism respectively, low to adapt to
Double film sandwiched film mechanisms of enthalpy shock tunnel；Three use the left folder membrane body clamp piston buffer unit of sandwiched film mechanism, and right folder membrane body clamping is fast
When fast check valve, for the buffer piston holdback for adapting to enthalpy shock tunnel in long-time.
Monofilm sandwiched film mechanism is hollow composite unit structure, is mainly made of left folder membrane body, middle folder membrane body and right folder membrane body.It is left
It is consistent with shock wave lumen to press from both sides membrane body internal diameter, one end outer surface setting interval screw thread；Middle folder membrane cavity is through-hole pipe structure, inner surface two
One section of interval screw thread is respectively set in end；Right folder membrane body links together with jet pipe, and inner cavity includes venturi contraction section.Left folder membrane body and
Right folder membrane body passes through interval screw thread pair respectively and is connected with middle folder membrane body.
Replaceable jet pipe is inner mold face rotary structure, is axially connected into entirety by each segmentation.Every tool jet pipe has
One specific outlet air flow velocity, corresponding to different trystates.Lance system can along axial direction and horizontal transverse movement,
To replace different jet pipes, meet the needs of different tests.
High vacuum universal test section is internal cavity structure, by three main casing, lower case, vacuum tank main component groups
At.In test, under the action of vacuum system, it can achieve 10Pa high vacuum state below, meet various experimental conditions
Needs.The attack angle mechanism system of inside setting vibration isolation, is used to support model, meets different tests for model support and posture
Needs.
Second compression section is the elongated pipeline configuration of uniform internal diameter, and internal diameter is equal with shock wave pipeline section, and inner surface is smooth.Edge on tube wall
Radial through-hole axially is distributed with, for connecting inflation, vacuum system or mounting test system sensor.Every section of second compressed pipe is matched
One has wheel support, is supported in elongated inner orbit group.
Second monofilm sandwiched film mechanism structure is similar with monofilm sandwiched film mechanism, and internal cavity internal diameter is consistent with shock tube.Right folder
Membrane body and left folder membrane body are symmetrical structure, and left folder membrane body and right folder membrane body pass through interval screw thread pair respectively and be connected with middle folder membrane body.
Elongated high-precision support system is made of high-precision orbital group and fine adjustment type support of pipelines.High-precision orbital group is two
The adjustable segmented tracks assembly of layer.It is first layer accurate adjustment between bracket and ground, bracket and interorbital are second layer accurate adjustment, are protected
Demonstrate,prove the parallel surface group that orbital plane is high flatness.Fine adjustment type bracket is used to support compressed pipe, shock tube and the second compressed pipe, lower part
For hard wheel group, can move along track is smooth, middle part is rigid support body, and top is pipeline hoop.Pipeline hoop and rigidity branch
There is the adjustment structure of height and horizontal cross both direction between frame body, it is ensured that be supported pipeline at various locations and wind-tunnel
Axis it is consistent.
Flexible air supply system is by high-pressure air source, compressor set, Remote control valve door group, fixed -piping system, flexible duct
System, helium/argon gas gas supply group composition.By Remote control valve door group, the access in fixed -piping system is controlled, and utilizes flexibility
Pipe-line system will need the equipment that supplies and corresponding coupling for fixed pipe installations to connect, and realize under wind-tunnel multiple modalities, no
With the flexibility gas supply of supply position.
Composite vacuum system is made of multiple compressor sets and single-stage compressor, by combining and replacing position, is met
The requirement of difference component, different location, different vacuum degrees when to different modalities.It is connected by flexible duct with equipment, guarantees wind
Hole ontology is smooth in axially operation.
With can only be compared with the wind-tunnel of single mode operation, the FREE-PISTON SHOCK TUNNEL of this multi-mode operation has more fully
Test capability and the higher test mechanism of cost performance.Based on structure using free-piston high enthalpy shock tunnel, only pass through increasing
Add or replace between mode can be realized in a small amount of component and converts, it is high-efficient and at low cost.
Free-piston high enthalpy shock tunnel mode, jet pipe parameter in room are 4000~8000K of total temperature, total enthalpy is about 6~
15MJ/Kg, stagnation pressure are 5~25MPa or so, 2~5ms of runing time.Low enthalpy shock tunnel, jet pipe parameter in room are total temperature
1240K, stagnation pressure 2.1MPa, runing time 20ms；Enthalpy shock tunnel in long-time, jet pipe parameter in room are total temperature 2000K, stagnation pressure
1.86MPa, runing time 100ms.
The above description is only a preferred embodiment of the present invention, the protection scope being not intended to limit the invention.For ability
For the technical staff in domain, without creative efforts, several modification and replacement can be made to the present invention,
All such modifications and replacement should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (10)
1. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations, it is characterised in that: including wind tunnel noumenon, distributed vacuum system
System (10), air supply system (11), track support system (12),
Wind tunnel noumenon includes driving mechanism, shock wave pipeline section (5), monofilm sandwiched film mechanism (6), jet pipe (7) and test section (8),
Distributed vacuum system vacuumizes driving mechanism, shock wave pipeline section (5) and test section (8)；
Air supply system supplies driving mechanism and shock wave pipeline section (5)；
Track support system provides support to driving mechanism, shock wave pipeline section (5), monofilm sandwiched film mechanism (6)；
Driving mechanism and shock wave pipeline section (5), monofilm sandwiched film mechanism (6), jet pipe (7) and test section (8) the sequentially coaxially company of sealing
It connects, 1 diaphragm is set in monofilm sandwiched film mechanism (6)；
Under high enthalpy shock tunnel mode, driving mechanism includes piston emitter (1), piston (2), compression pipeline section (3) and master
Sandwiched film mechanism (4), wherein 1 diaphragm is arranged in main sandwiched film mechanism (4)；
Piston (2) is placed in piston emitter (1), and by high pressure air drives, pipeline section (3) high-speed motion is compressed on edge, and right
It compresses the gas-powered in pipeline section (3) and generates heating, pressurization；
Under low enthalpy shock tunnel mode, driving mechanism includes compression pipeline section (3) and main sandwiched film mechanism (4), wherein in main folder film
2 diaphragms are set in mechanism (4), form middle gas chamber among 2 diaphragms；
In long-time under enthalpy shock tunnel mode, driving mechanism includes piston emitter (1), piston (2), compression pipeline section
(3), main sandwiched film mechanism (4), the second compression pipeline section (14) and the second monofilm sandwiched film mechanism (15), wherein in main sandwiched film mechanism (4)
Interior setting check valve assembly；In compression pipeline section (3) end setting buffer piston mechanism (13), piston (2) is run with certain speed
To when compressing pipeline section (3) end, so that piston (2) is slowed down and stop.
2. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as described in claim 1, it is characterised in that: swash in high enthalpy
Under wave wind-tunnel mode, before wind tunnel operation main sandwiched film mechanism (4) interior diaphragm to compression pipeline section (3), shock wave pipeline section (5) carry out gas every
From monofilm sandwiched film mechanism (6) interior diaphragm carries out gas barrier to shock wave pipeline section (5) and test section (8).
3. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 2, it is characterised in that: wind tunnel operation
Afterwards, it compresses the diaphragm in the main sandwiched film mechanism of high temperature and high pressure gas bursting (4) of pipeline section (3) end and generates intense shock wave, intense shock wave
Into shock wave pipeline section (5) and along its high-speed cruising, the test gas of high temperature and pressure, bursting list are formed in shock wave pipeline section (5) end
Diaphragm in film sandwiched film mechanism (6), high temperature and pressure test gas enter jet pipe (7), and accelerate to test setting by jet pipe (7)
Air velocity enters high vacuum test section (8).
4. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as described in claim 1, it is characterised in that: in compressed pipe
Buffer piston mechanism, which is arranged, in section (3) end makes piston (2) when piston (2) runs to compression pipeline section (3) end with certain speed
Slow down and stops.
5. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as described in claim 1, it is characterised in that: swash in low enthalpy
Under wave wind-tunnel mode, before wind tunnel operation main sandwiched film mechanism (4) interior diaphragm to compression pipeline section (3), shock wave pipeline section (5) carry out gas every
From monofilm sandwiched film mechanism (6) interior diaphragm carries out gas barrier to shock wave pipeline section (5) and test section (8).
6. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 5, it is characterised in that: wind tunnel operation
Afterwards, diaphragm middle gas chamber deflation pressure release, high pressure gas in compression pipeline section (3) the successively diaphragm in the main sandwiched film mechanism of bursting (4)
And intense shock wave is generated, intense shock wave enters shock wave pipeline section (5) and along its high-speed cruising, and it is high to form high temperature in shock wave pipeline section (5) end
The test gas of pressure, the diaphragm in bursting monofilm sandwiched film mechanism (6), high temperature and pressure test gas enter jet pipe (7), and by jet pipe
(7) air velocity for accelerating to test setting enters test section (8).
7. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as described in claim 1, it is characterised in that: for a long time
Under middle enthalpy shock tunnel mode, piston (2) is placed in piston emitter, high along compression pipeline section (3) by high pressure air drives
Speed movement, and heating, pressurization are generated to the gas-powered in compression pipeline section (3).
8. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 7, it is characterised in that: wind tunnel operation
Preceding second monofilm sandwiched film mechanism (15) interior diaphragm carries out gas barrier, monofilm folder to the second compression pipeline section (14), shock wave pipeline section (5)
Film mechanism (6) interior diaphragm carries out gas barrier to shock wave pipeline section (5) and test section (8).
9. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 7, it is characterised in that: wind tunnel operation
Afterwards, the high temperature and high pressure gas for compressing pipeline section (3) end opens the check valve assembly in main sandwiched film mechanism (4) into the second compressed pipe
Section (14), opens the second monofilm sandwiched film mechanism (15) interior diaphragm and generates intense shock wave, intense shock wave enters shock wave pipeline section (5) and along it
High-speed cruising forms the test gas of high temperature and pressure in shock wave pipeline section (5) end, the diaphragm in bursting monofilm sandwiched film mechanism (6),
High temperature and pressure test gas enters jet pipe (7), and enters test section by the air velocity that jet pipe (7) accelerates to test setting
(8)。
10. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 9, it is characterised in that: work as piston
(2) after stopping when springing back, the check valve assembly in main sandwiched film mechanism (4) is closed, prevent piston (2) spring back the dilatational wave that generates into
Enter the second compression pipeline section (14).
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| CN109632239A (en) * | 2018-12-11 | 2019-04-16 | 中国航天空气动力技术研究院 | A kind of variable cross-section weight piston compressor |
| CN110057531A (en) * | 2019-04-02 | 2019-07-26 | 合肥铭远航空科技有限公司 | Shock tube Test Data Collecting analysis system |
| CN110487505B (en) * | 2019-08-22 | 2020-11-06 | 温州春桦秋时科技有限公司 | Self-displacement buffer type shock tunnel |
| CN111024357B (en) * | 2019-12-11 | 2021-07-13 | 中国航天空气动力技术研究院 | Method for simulating flight environment by large-size free piston high-enthalpy shock tunnel |
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| CN111693247B (en) * | 2020-06-22 | 2021-04-20 | 中国科学院力学研究所 | Bidirectional detonation driving method for detonation-driven shock tunnel |
| CN112444368A (en) * | 2020-10-26 | 2021-03-05 | 中国航天空气动力技术研究院 | Ground simulation test device for ultrahigh-speed reentry test airflow |
| CN112629806B (en) * | 2021-01-11 | 2022-05-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device and method for stopping shock tunnel non-effective test airflow |
| CN113432823B (en) * | 2021-06-22 | 2022-07-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Polyester film clamping device |
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| CN116380367B (en) * | 2023-06-06 | 2023-08-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hydrogen leakage monitoring device and monitoring method for shock tube of high-pressure hydrogen driver |
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| CN203178060U (en) * | 2013-01-14 | 2013-09-04 | 中国人民解放军总参谋部工程兵科研三所 | Hypersonic aircraft ground simulation test dedicated shock wave tunnel |
| RU166717U1 (en) * | 2016-04-28 | 2016-12-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | COOLED DAMPER FOR SUPPRESSING PRESSURE OSCILLATIONS IN THE COMBUSTION CHAMBER OF A HIGH-ETHALPIAN AIR FLOWS OF A ALTITUDE STAND |
| CN106840579B (en) * | 2016-12-07 | 2019-01-25 | 中国航天空气动力技术研究院 | A kind of variable cross-section weight piston compressor |
| CN106763413B (en) * | 2016-12-21 | 2019-01-11 | 中国航天空气动力技术研究院 | A kind of free-piston two-stage buffering stop stop mechanism |
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