CN108036918A - 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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- CN108036918A CN108036918A CN201810002322.8A CN201810002322A CN108036918A CN 108036918 A CN108036918 A CN 108036918A CN 201810002322 A CN201810002322 A CN 201810002322A CN 108036918 A CN108036918 A CN 108036918A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses the FREE-PISTON SHOCK TUNNEL 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 possess 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 of performance of wind tunnel are improved, reduces operating cost.
Description
Technical field
The present invention relates to the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations, applied to the hypersonic of various states
Experiment.
Background technology
Deficiency when existing hypersonic field is studied on testing equipment includes being used for the suction of hypersonic and ultrahigh speed
Gas formula aircraft is tested with the propulsion trial equipment of assessment, it is necessary to longer test period, high dynamic pressure, close to pure air,
Reproduction enthalpy, the size of bigger 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
Ask mainly reduces cost while safety and reliability is improved.
The uniqueness that the variation of equipment is attributable to large-scale flying condition and needs to study in hypersonic experiment shows
As.Different types of wind-tunnel can realize the research for carrying out aerodynamic characteristic under different simulated conditions to aircraft.Final is flight
The development of device provides wider test data, and can more make full use of the high testing equipment of construction cost.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 experiment of different type
The respective advantage of equipment, integrates the result of the test 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 for Mach number more than 8 and the aerodynamic force of the hypervelocity flight with chemical reaction flow
Test.
The prior art, including free-piston high enthalpy shock tunnel pattern and conventional two kinds, usual one of shock tunnel pattern
Wind-tunnel only realizes one mode, and when same experiment needs the trystate of different mode, model is needed between different wind-tunnel
Installation will necessarily introduce resulting error, influence accuracy and the examination of result of the test, it is necessary to using different jet pipes repeatedly
Test efficiency；Meanwhile since it is desired that build a plurality of wind-tunnel, it is all very high in construction and operating cost.
The run time of existing FREE-PISTON SHOCK TUNNEL is shorter, can not meet the hypersonic dynamometry in part and special test
Demand.
The content of the invention
The technology of the present invention solves the problems, such as：For overcome the deficiencies of the prior art and provide one kind of multiple mode operations from
By piston shock tunnel, big enthalpy scope, long-time and inexpensive multi-mode operation mode are had concurrently.
The present invention technical solution be：
The FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations, including wind tunnel noumenon, distributed vacuum system, 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 pattern, driving mechanism includes piston emitter, piston, compression pipeline section and main folder film machine
Structure, wherein setting 1 diaphragm 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 produces heating, pressurization；
Under low enthalpy shock tunnel pattern, driving mechanism includes compression pipeline section and main sandwiched film mechanism, wherein in main folder film machine
2 diaphragms are set in structure, middle gas chamber is formed among 2 diaphragms；
In long-time under enthalpy shock tunnel pattern, 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 setting check valve assembly in main sandwiched film mechanism；Pressing
Draw section end sets buffer piston mechanism, when piston runs to compression pipeline section end with certain speed, piston is slowed down and is stopped
Only.
Under high enthalpy shock tunnel pattern, 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 diaphragm and generation in the main sandwiched film mechanism of high temperature and high pressure gas bursting of compression pipeline section end are strong sharp
Ripple, intense shock wave enter shock wave pipeline section and along its high-speed cruisings, and the test gas of high temperature and pressure, bursting are formed 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 experiment setting is accelerated to by jet pipe
Degree enters high vacuum test section.
Buffer piston mechanism is set in compression pipeline section end, when piston runs to compression pipeline section end with certain speed, is made
Piston slows down and stops.
Under low enthalpy shock tunnel pattern, 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, diaphragm middle gas chamber deflation pressure release, compresses the gases at high pressure bursting main folder film machine successively in pipeline section
Diaphragm in structure simultaneously produces intense shock wave, and intense shock wave enters shock wave pipeline section and along its high-speed cruising, and height is formed 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 experiment setting enters high vacuum test section.
In long-time under enthalpy shock tunnel pattern, piston is placed in piston emitter, passes through high pressure air drives, edge
Pipeline section high-speed motion is compressed, and heating, pressurization are produced 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 check valve assembly in the open-top main sandwiched film mechanism of high temperature and high pressure gas of compression pipeline section end enters
Second compression pipeline section, open-top second monofilm sandwiched film mechanism interior diaphragm simultaneously produces intense shock wave, intense shock wave enter shock wave pipeline section and along its
High-speed cruising, the diaphragm in the test gas of shock wave pipeline section end formation high temperature and pressure, bursting monofilm sandwiched film mechanism, high temperature are high
Pressure test gas enters jet pipe, and the air velocity tested and set is accelerated to by jet pipe and enters high vacuum test section.
When being sprung back after piston stopping, the check valve assembly in main sandwiched film mechanism is closed, and prevents Piston rebound from producing swollen
Swollen ripple enters the second compression pipeline section.
The present invention compared with prior art the advantages of be：
(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, wind-tunnel is possessed 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 monotype operation wind-tunnel compared with, the FREE-PISTON SHOCK TUNNEL of multi-mode operation of the present invention has
More fully test capability and the test system of cost performance higher, only can implementation pattern by increasing or replacing a small amount of component
Between change, it is efficient.
Brief description of the drawings
Fig. 1 is high enthalpy shock tunnel structure diagram of the present invention；
Fig. 2 is low enthalpy shock tunnel structure diagram of the present invention；
Fig. 3 is enthalpy shock tunnel structure 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.
Embodiment
The present invention will be described in detail below in conjunction with the accompanying drawings.
The FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations, including wind tunnel noumenon, distributed vacuum system 10, 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 pattern, as shown in Figure 1, driving mechanism includes piston emitter 1, piston 2, compressed pipe
Section 3 and main sandwiched film mechanism 4, wherein setting 1 diaphragm 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 produces heating, pressurization；
As shown in figure 4, under high enthalpy shock tunnel pattern, main 4 interior diaphragm of sandwiched film mechanism is to compressing pipeline section before wind tunnel operation
3rd, shock wave pipeline section 5 carries out gas barrier, 6 interior diaphragm of monofilm sandwiched film mechanism shock wave pipeline section 5 and test section 8 are carried out gas every
From setting buffer piston mechanism in compression pipeline section 3 end, when piston 2 runs to compression 3 end of pipeline section with certain speed, make work
Plug 2 slows down and stops.
After wind tunnel operation, the diaphragm and generation in the main sandwiched film mechanism 4 of high temperature and high pressure gas bursting of 3 end of compression pipeline section are strong
Shock wave, intense shock wave enter shock wave pipeline section 5 and along its high-speed cruisings, and the test gas of high temperature and pressure is formed 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 experiment setting by jet pipe 7
Air velocity enters high vacuum test section 8.
Under high enthalpy shock tunnel pattern, universal piston emitter connection length 75m, internal diameter is 668mm compressed pipes；It is main
Sandwiched film mechanism presss from both sides film pattern for buffer piston monofilm；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 at a high speed, and front was originally distributed in compressed pipe
Helium/argon driving gas is compressed.Helium/argon that compression pipe end is pressurized to high temperature and pressure drives gas in bursting main folder film machine
After diaphragm in structure, intense shock wave is produced in shock tube.Intense shock wave is run along shock tube, and is produced instead at monofilm sandwiched film mechanism
Penetrate, intense shock wave produces 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 the air velocity of experiment needs is accelerated to by jet pipe, in test section
Test model acts, and completes experiment.
Under low enthalpy shock tunnel pattern, as shown in Fig. 2, driving mechanism includes compression pipeline section 3 and main sandwiched film mechanism 4, its
In 2 diaphragms are set in the main sandwiched film mechanism 4, form middle gas chamber among 2 diaphragms；
Under low enthalpy shock tunnel pattern, as shown in figure 5, main 4 interior diaphragm of sandwiched film mechanism is to compressing pipeline section before wind tunnel operation
3rd, shock wave pipeline section 5 carries out gas barrier, 6 interior diaphragm of monofilm sandwiched film mechanism shock wave pipeline section 5 and test section 8 are carried out gas every
From.
After wind tunnel operation, diaphragm middle gas chamber deflation pressure release, compresses the gases at high pressure bursting main folder film machine successively in pipeline section 3
Diaphragm in structure 4 simultaneously produces 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 experiment setting enters high vacuum test section 8.
Under low enthalpy shock tunnel pattern, high drive section, the shock tube of 32m long are used as by the use of the compression pipeline section of 10m long
Duan Zuowei is by drive section.Realize the controllable rupture of membranes of high pressure using double diaphragms in main sandwiched film mechanism, produce intense shock wave, using shock wave plus
The experiment air crossed in heat shock wave duct, produces the test air-flow of Pass Test requirement in test section after accelerating by jet pipe.
In long-time under enthalpy shock tunnel pattern, as shown in figure 3, driving mechanism include piston emitter 1, piston 2,
Pipeline section 3, the compression 14 and second monofilm sandwiched film mechanism 15 of pipeline section of main sandwiched film mechanism 4, second 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 3 end of compression pipeline section, piston 2 is run with certain speed
During to compression 3 end of pipeline section, piston 2 is slowed down and stop.
In long-time under enthalpy shock tunnel pattern, piston 2 is placed in piston emitter, by high pressure air drives,
Heating, pressurization are produced 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, check valve assembly in the open-top main sandwiched film mechanism 4 of high temperature and high pressure gas of compression pipeline section 3 end into
Enter the second compression pipeline section 14, open-top second monofilm sandwiched film mechanism, 15 interior diaphragm simultaneously produces intense shock wave, and intense shock wave enters shock wave pipeline section 5
And along its high-speed cruising, the film in the test gas of 5 end of shock wave pipeline section formation high temperature and pressure, bursting monofilm sandwiched film mechanism 6
Piece, high temperature and pressure test gas enter jet pipe 7, and the air velocity tested and set is accelerated to by jet pipe 7 and is tested into high vacuum
Pipeline section 8.
When being sprung back after the stopping of piston 2, the check valve assembly in main sandwiched film mechanism 4 is closed, and prevents piston 2 from springing back what is produced
Dilatational wave enters the second compression pipeline section 14.
In long-time under enthalpy shock tunnel pattern, relative to high enthalpy shock tunnel pattern, long 24m, internal diameter are added
The second compression section of 290mm, and three with main sandwiched film mechanism set piston holdback.By the compression of taskwork plug in compressed pipe
Helium/argon driving gas enters the second compression section by holdback check valve, is produced in the second monofilm sandwiched film mechanism implosion strong sharp
While ripple, helium/argon driving gas is prevented by holdback check valve, be cannot be introduced into compressed pipe, is avoided energy loss.Together
When, the second longer compression section so that the reflection of dilatational wave needs the longer time.Therefore when adding 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 loading tank body
Injection device, transmitting tube composition.Taskwork plug is fitted into emitter, in emission 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 experiment, taskwork plug is in compressed pipe
High speed is moved, and compresses the driving gas being filled with 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 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 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, is 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, and outer surface sets 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；It is 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 outer surface is set
Every screw thread.Left folder membrane body and right folder membrane body are connected by being spaced screw thread pair with middle folder membrane body respectively.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 parts, for suitable for the high enthalpy shock wave of free-piston
The buffer piston monofilm sandwiched film mechanism of wind-tunnel；Three with sandwiched film mechanism it is left and right folder membrane body clamp a piece of diaphragm respectively when, for adapt to it is low
Double film sandwiched film mechanisms of enthalpy shock tunnel；Three is fast with the left folder membrane body clamp piston buffer unit of sandwiched film mechanism, right folder membrane body clamping
During fast check valve, to adapt to the buffer piston holdback of 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 tube chamber to press from both sides membrane body internal diameter, one end outer surface sets interval screw thread；Middle folder membrane cavity is through-hole pipe structure, inner surface two
Setting one is intersegmental every screw thread respectively at end；Right folder membrane body links together with jet pipe, and inner cavity includes venturi contraction section.It is left folder membrane body and
Right folder membrane body is connected by being spaced screw thread pair with middle folder membrane body respectively.
Replaceable jet pipe is inner mold face rotary structure, and entirety is connected into by each segmentation is axial.Often the jet pipe of having has
One specific outlet air flow velocity, corresponding to different trystates.Lance system can vertically 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 housing shell, vacuum tank critical piece groups
Into.In test, under the action of vacuum system, the high vacuum state of below 10Pa can be reached, meet various experimental conditions
Needs.Inside sets the attack angle mechanism system of 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 hole axially is distributed with, for connecting inflation, vacuum system or mounting test system sensor.Every section of second compressed pipe is matched somebody with somebody
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 are connected by being spaced screw thread pair with middle folder membrane body respectively.
Elongated high accuracy 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 stent and ground, stent and interorbital are second layer accurate adjustment, are protected
Demonstrate,prove the parallel surface group that orbital plane is high flatness.Fine adjustment type stent is used to support compressed pipe, shock tube and the second compressed pipe, lower part
For hard wheel group, it can be moved along track is smooth, middle part is rigid support body, and top is pipeline hoop.Pipeline hoop and rigidity are propped up
There is the adjustment structure of height and horizontal cross both direction between frame body, it is ensured that be supported pipeline in each position and wind-tunnel
Axis it is consistent.
Flexible air supply system is by high-pressure air source, compressor set, remote control valve group, fixed -piping system, flexible duct
System, helium/argon gas supply group composition.By remote control valve group, the path in fixed -piping system is controlled, and utilize 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 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, diverse location, different vacuums during to different modalities.It is connected by flexible duct with equipment, ensures wind
Hole body is smooth when axially running.
With can only be compared with the wind-tunnel of monotype operation, the FREE-PISTON SHOCK TUNNEL of this multi-mode operation has more fully
The test system of test capability and cost performance higher.Based on structure using free-piston high enthalpy shock tunnel, only pass through increasing
Adding or replacing a small amount of component can change between implementation pattern, and efficient and cost is low.
Free-piston high enthalpy shock tunnel pattern, 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 run time.Low enthalpy shock tunnel, jet pipe parameter in room are total temperature
1240K, stagnation pressure 2.1MPa, run time 20ms；Enthalpy shock tunnel in long-time, jet pipe parameter in room are total temperature 2000K, stagnation pressure
1.86MPa, run time 100ms.
The foregoing is merely the preferred embodiment of the present invention, is not used for limiting the scope of the invention.For ability
For the technical staff in domain, without creative efforts, some 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 not being described in detail in description of the invention belongs to the known technology 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
Unite (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)；
Wind tunnel noumenon and shock wave pipeline section (5), monofilm sandwiched film mechanism (6), jet pipe (7) and test section (8) the sequentially coaxially company of sealing
Connect, 1 diaphragm is set in monofilm sandwiched film mechanism (6)；
Under high enthalpy shock tunnel pattern, driving mechanism includes piston emitter (1), piston (2), compression pipeline section (3) and master
Sandwiched film mechanism (4), wherein setting 1 diaphragm 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
Compress the gas-powered in pipeline section (3) and produce heating, pressurization；
Under low enthalpy shock tunnel pattern, 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), middle gas chamber is formed among 2 diaphragms；
In long-time under enthalpy shock tunnel pattern, 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；Buffer piston mechanism (13) is set in compression pipeline section (3) end, piston (2) is run with certain speed
During to compression pipeline section (3) end, piston (2) is slowed down and stop.
2. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 1, it is characterised in that：Swash in high enthalpy
Under ripple wind-tunnel pattern, 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, compress the diaphragm in the main sandwiched film mechanism of high temperature and high pressure gas bursting (4) of pipeline section (3) end and produce 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 enters jet pipe (7), and accelerates to experiment 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 claimed in claim 1, it is characterised in that：In compressed pipe
Section (3) end sets buffer piston mechanism, when piston (2) runs to compression pipeline section (3) end with certain speed, makes piston (2)
Slow down and stop.
5. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 1, it is characterised in that：Swash in low enthalpy
Under ripple wind-tunnel pattern, 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, gases at high pressure in compression pipeline section (3) diaphragm in the main sandwiched film mechanism of bursting (4) successively
And intense shock wave is produced, 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 experiment setting enters high vacuum test section (8).
7. the FREE-PISTON SHOCK TUNNEL of one kind of multiple mode operations as claimed in claim 1, it is characterised in that：For a long time
Under middle enthalpy shock tunnel pattern, piston (2) is placed in piston emitter, high along compression pipeline section (3) by high pressure air drives
Speed movement, and heating, pressurization are produced 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 the second compression pipeline section (14), shock wave pipeline section (5) on gas barrier, monofilm folder
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 check valve assembly compressed in the open-top main sandwiched film mechanism (4) of high temperature and high pressure gas of pipeline section (3) end enters the second compressed pipe
Section (14), open-top second monofilm sandwiched film mechanism (15) interior diaphragm simultaneously produces intense shock wave, intense shock wave enter shock wave pipeline section (5) and along its
High-speed cruising, the diaphragm in the test gas of shock wave pipeline section (5) end formation high temperature and pressure, bursting monofilm sandwiched film mechanism (6),
High temperature and pressure test gas enters jet pipe (7), and the air velocity tested and set is accelerated to by jet pipe (7) and is tested into high vacuum
Pipeline section (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 the dilatational wave that piston (2) rebound produces 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 |
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| CN111024357A (en) * | 2019-12-11 | 2020-04-17 | 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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