CN109883646A - A kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel - Google Patents
A kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel Download PDFInfo
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Abstract
A kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel, comprises the following steps that and 1) establishes air suction type propulsion trial system；2) carry out A group cold test, measure no propellant spray, air to flow down through-flow test data；3) carry out the hot test of B group, the hot test data for measuring propellant spray, air to flow down；4) carry out C group cold conditions jet test, the cold conditions jet test data for measuring propellant spray, nitrogen to flow down；5) difference for comparing A, B, C group test data, completes spray influence, combustion characteristics and cold and hot performance evaluation, realizes the simulation promoted to air suction type.The present invention passes through the spray control of fuel and the replacement of test gas, form tri- groups of check experiment analogy methods of A, B, C, both the combustion characteristics of air suction type propulsion trial can have been judged, the performance increment test data of available cold and hot again, additionally it is possible to which the propellant spray interference characteristic for air suction type propulsion trial is analyzed.
Description
Technical field
The present invention relates to a kind of air suction type propulsion trial analogy methods, belong to high temperature fuel supplying in hypersonic pulsed wind tunnel experimental technique
Field.
Background technique
Scramjet engine merged with other power such as rocket or turbogenerator to be formed combine circulation power, it can be achieved that
Aircraft is the important research hot spot in current hypersonic field both at home and abroad across airspace, wide fast domain, high maneuvering flight.As working as
The preceding air suction type propulsion device that uniquely can be realized hypersonic flight, scramjet engine work Mach number is very wide, theoretical
Show Mach number across 5 to 25, needs matched ground-testing plant and test simulation method to carry out correlation test research.So
And it is limited by heating efficiency, only high enthalpy shock tunnel, expansion tunnel (such as Australian T4, X3) high temperature pulse wind at present
Hole can satisfy High Mach number (8 or more Mach number) air suction type propulsion trial total temperature demand.However, the runing time of this kind of wind-tunnel
Very short, generally only several milliseconds, even less than one millisecond need to establish matched test simulation method, inhale for High Mach number
Gas formula propulsion trial provides technological approaches.
When Mach number lower (being no more than 8), the test period of air suction type propulsion trial equipment is all general long, and fuel is all
Can the spray after model flow field is established, time can be obtained water heater chiller unit data in bicycle in this way.Wherein cold conditions is no fuel
The open position of spray, hot is the possibility combustion state for having propellant spray.There was only several milliseconds of high-temperature pulse for test period
Wind-tunnel is rushed, this test simulation method is just completely not applicable.
Summary of the invention
It is an object of the invention to overcome the deficiencies in the prior art, the present invention provides a kind of based on high temperature pulse wind-tunnel
Air suction type propulsion trial analogy method solves high temperature pulse wind tunnel test time short caused High Mach number air suction type propulsion trial
Technical problem forms tri- groups of check experiment analogy methods of A, B, C, both by the spray control of fuel and the replacement of test gas
The combustion characteristics of air suction type propulsion trial, and the performance increment test data of available cold and hot can be judged, additionally it is possible to use
It is analyzed in the propellant spray interference characteristic of air suction type propulsion trial, carries out air suction type propulsion trial for high temperature pulse wind-tunnel and provide
Technological approaches also provides a kind of test method for High Mach number scramjet engine technical research.
The present invention is achieved by following technical solution: a kind of air suction type propulsion trial mould based on high temperature pulse wind-tunnel
Quasi- method, comprises the following steps that
1) according to wind tunnel operation characteristic, air suction type propulsion trial system is established；
2) make test gas air, and close trigger signal, carry out A group cold test, measure no propellant spray, air
To flow down through-flow test data；
3) make test gas air, and open trigger signal, carry out the hot test of B group, measure propellant spray, air comes
The hot test data flowed down；
4) make test gas nitrogen, and open trigger signal, carry out C group cold conditions jet test, measure propellant spray, nitrogen
Gas is come the cold conditions jet test data that flow down；
5) A, B, C group test data are compared, pressure, hot-fluid or axial force test data difference table or figure, realization pair are obtained
Cold and hot performance increment, combustion characteristics and spray interference assessment.
The air suction type propulsion trial system includes propellant spray valve, fuel storage tank, sequential control system, triggering pressure
Sensor；Propulsion trial model and fuel storage tank pass through connection by metal hose, install propellant spray valve, fuel on metal hose
Spray valve is mounted in propulsion trial model or close to propulsion trial model；Triggering pressure sensor is mounted on wind-tunnel by drive section
Interior or its upstream, the output signal for triggering pressure sensor are connected to sequential control system by shielded cable, as timing control
The external trigger signal of system processed；Sequential control system exports time delayed signal all the way, is connected to propellant spray valve by shielded cable,
Open signal as propellant spray valve；
Triggering pressure sensor experiences the air pressure change of installed position, generates corresponding voltage triggering signal, sends
To sequential control system；
The external trigger signal threshold value and output delay waiting time, sequential control system that sequential control system is arranged receive
After external trigger signal, judge whether it reaches the external trigger signal threshold value being previously set, is set in advance when trigger signal amplitude reaches
When fixed threshold value, sequential control system starts to clock, and after waiting by the output delay time being previously set, output enabling signal is extremely
Propellant spray valve；Propellant spray valve is opened according to enabling signal, and the fuel in fuel storage tank is transported to propulsion trial model
It is internal.
The method for selecting of the triggering pressure sensor installation site are as follows:
Firstly, the response time of response time and sequential control system to propellant spray valve carry out test determination；
Secondly, being carried out to during wind tunnel operation by the gas pressure change sequential relationship in drive section and its upstream components
Detection, filters out the triggering pressure sensor installation position for meeting the response time requirement of propellant spray valve and sequential control system
Set, at this pressure change and wind-tunnel by drive section end stagnation pressure change between time interval be greater than propellant spray valve and timing
The sum of response time of control system, it is ensured that propellant spray flow field shifts to an earlier date than wind tunnel test flow field or synchronous foundation, it is ensured that several millis
Incoming flow test gas and fuel compatible are inside propulsion trial model in efficiency test time second.
The step 2), step 3) wind-tunnel incoming flow test gas parameter corresponding with step 4) are consistent.
The step 3) propellant spray flow corresponding with step 4) is consistent.
The specific method is as follows for the step 5):
By hot test data obtained in through-flow test data obtained in comparison step 2) and step 3), carry out cold
Hot performance analysis, provides pressure, hot-fluid or axial force data difference table or figure, difference is cold and hot performance increment size；
By comparing cold conditions jet test data obtained in hot test data obtained in step 3) and step 4), into
Row combustion characteristic analysis, provides pressure, hot-fluid or axial force data difference table or figure, and difference is burning contribution amount；
By comparing cold conditions jet test data obtained in through-flow test data obtained in step 2) and step 4), into
Row spray interference analysis, provides pressure, hot-fluid or axial force data difference table or figure, and difference is spray interference volume.
The advantages of the present invention over the prior art are that:
(1) present invention makes to fire using the triggering propellant spray control valve starting of high temperature pulse wind-tunnel upstream somewhere pressure signal
Material spray is established in advance than Flow Field in Wind Tunnel or even test model flow field, it is ensured that incoming air in several milliseconds of efficiency test times
It is air involved in air suction type propulsion trial and fuel blending, igniting and combustion with fuel compatible in the combustion chamber of test model
Burning provides technological approaches.
(2) present invention uses three groups of check experiment analogy methods, solves high temperature pulse wind-tunnel time short caused air-breathing
Formula propulsion trial data acquisition problem.
(3) present invention is not only that the high temperature impulse wind tunnels such as high enthalpy shock tunnel, expansion tunnel provide a kind of experimental technique,
A kind of practicable analogy method also is provided for High Mach number air suction type propulsion trial, High Mach number ultra-combustion ramjet is started
The development of machine technology has important support effect.
Detailed description of the invention
Fig. 1 is the schematic diagram of air suction type propulsion trial analogy method of the invention；
Fig. 2 is air suction type propulsion trial system schematic；
Fig. 3 is the typical coupled relation figure between propellant spray of the invention and the foundation of test model flow field；
Fig. 4 is the resulting Typical experimental results curve graph of the present invention；
Fig. 5 is difference curve figure between the resulting different group test datas of the present invention
Specific embodiment
Structure Figure and examples illustrate the present invention below.
As shown in Figure 1, a kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel, comprises the following steps that
1) according to wind tunnel operation characteristic, air suction type propulsion trial system is established；
As shown in Fig. 2, air suction type propulsion trial system, including propellant spray valve, fuel storage tank, sequential control system,
Trigger pressure sensor；Propulsion trial model and fuel storage tank pass through connection by metal hose, installation fuel spray on metal hose
Valve is infused, propellant spray valve is mounted in propulsion trial model or close to propulsion trial model；Triggering pressure sensor is mounted on wind
Hole drive section upstream, triggering pressure sensor are connect with sequential control system by shielded cable, sequential control system and fuel
Spray valve is connected by shielded cable；Trigger sensor generates corresponding voltage triggered according to the air pressure change of installed position
Signal is sent to sequential control system, the external trigger signal as sequential control system；Trigger pressure sensor installation site
Method for selecting are as follows: firstly, response time of propellant spray valve (is received open signal and fully opened to propellant spray valve and passed through
The time gone through) and the response time of sequential control system carry out test determination；Secondly, to during wind tunnel operation by drive section and
Gas pressure change sequential relationship in its upstream components is detected, and is filtered out and is met propellant spray valve and sequential control system
Response time requirement triggering pressure sensor installation site, pressure change and wind-tunnel are changed by drive section end stagnation pressure at this
Between time interval be greater than the sum of response time of propellant spray valve and sequential control system, make to ensure propellant spray flow field
Shift to an earlier date than wind tunnel test flow field or synchronize and establish, so that it is guaranteed that incoming flow test gas and fuel are total in several milliseconds of efficiency test times
It is stored in inside propulsion trial model.
The activation threshold value and propellant spray valve that sequential control system is arranged were opened with the output delay waiting time；Timing control
After system receives external trigger signal, judge whether it reaches the threshold value being previously set, once reaching, sequential control system is just opened
Beginning clocks, after being waited by the delay time being previously set, output open signal to propellant spray valve；Propellant spray valve is according to unlatching
Signal is opened, and the fuel in fuel storage tank is transported to inside propulsion trial model.
Wind-tunnel can be switched between air and nitrogen by test gas in drive section according to test demand；Propulsion trial model
There are propellant spray structures, are mounted in test chamber.
2) make test gas air, and close trigger signal, carry out A group cold test, measure no propellant spray, air
To flow down the data such as the corresponding pressure of through-flow test, hot-fluid or axial force；
3) make test gas air, and open trigger signal, carry out the hot test of B group, measure propellant spray, air comes
The data such as the corresponding pressure of the hot test flowed down, hot-fluid or axial force；
4) make test gas nitrogen, and open trigger signal, carry out C group cold conditions jet test, measure propellant spray, nitrogen
Gas is come data such as the corresponding pressure of cold conditions jet test, hot-fluid or the axial forces that flow down；
Wherein, step 2), step 3) wind-tunnel incoming flow test gas parameter corresponding with step 4) are consistent.Step 3) and step
4) corresponding propellant spray flow is consistent.
5) difference for comparing A, B, C group test data completes spray influence, combustion characteristics and cold and hot performance evaluation, real
The simulation that now air suction type is promoted；The specific method is as follows:
By hot test data obtained in through-flow test data obtained in comparison step 2) and step 3), carry out cold
Hot performance analysis, obtains the data differences such as pressure, hot-fluid or axial force；Difference is bigger, and performance increment is more excellent.
By comparing cold conditions jet test data obtained in hot test data obtained in step 3) and step 4), into
Row combustion characteristic analysis obtains the data differences such as pressure, hot-fluid or axial force；；If difference very close zero, does not fire
It burns, it is nitrogen that this, which is based on C group test incoming flow, burning can not occur with fuel obtain；If difference is much larger than zero, fire
It burns, and difference is bigger, burns more abundant, the heat of release is more.
By comparing cold conditions jet test data obtained in through-flow test data obtained in step 2) and step 4), into
Row spray impact analysis, obtains the data differences such as pressure, hot-fluid or axial force；Difference is bigger, and spray interference is bigger.
Embodiment:
Step 1 drives high enthalpy shock tunnel as objective for implementation using certain free-piston, establishes air suction type propulsion trial system,
As shown in Figure 2；
The wind-tunnel that the air suction type propulsion trial system includes is shock tube by drive section, can replace shock wave according to demand
Test gas in pipe；The propulsion trial model is the vertical spray structure of fuel；The propellant spray response valve time is
35ms；The sequential control system response time is 0.5ms, and delay time can be arbitrarily arranged between 0~500ms；Wind-tunnel
The pressure monitoring sign mutation moment shifts to an earlier date than the wind-tunnel shock wave pipe end stagnation pressure sign mutation moment at Range compress pipe end 2.5m
50ms is selected as trigger signal for signal is detected at this；Wind tunnel test time 10ms；The trigger signal threshold of sequential control system is set
Value be 0.6V and the delay time of delay output signal be 10ms, retention time 60ms；When can ensure that several milliseconds of efficiency tests
Interior incoming air and fuel compatible are inside propulsion trial model, as shown in Figure 3.Double dot dash line is trigger signal in Fig. 3, empty
Line is fuel valve downstream spray chamber pressure signal (foundation of propellant spray field), and solid line is by drive section end stagnation pressure signal (characterization wind
Hole flow field is established), dotted line is test model wall pressure signal (characterization test model flow field is established)；
Step 2 will be filled with air in shock tube, A is carried out in the connection of cutting triggering pressure sensor and sequential control system
Group cold conditions through-flow test, measures cold conditions through-flow test pressure data.
Step 3 will be filled with air and pressure is identical as A group in shock tube, will triggering pressure sensor output signal access
Extremely and sequential control system, fuel storage tank 4 are filled with fuel, carry out the hot test of B group, measure hot test pressure data.
Step 4 will be filled with nitrogen and pressure is identical as A group air pressure in shock tube, will triggering pressure sensor output
Signal accesses to and sequential control system, and the fuel pressure in fuel storage tank is identical as B group, carries out C group cold conditions jet test,
Measure the cold conditions jet test pressure data under the conditions of propellant spray does not burn.
Fig. 4 is resulting Typical experimental results, and solid line is that A group cold conditions pressure is distributed (air incoming flow, fuel not spray), point
It is marked as the hot pressure distribution (air incoming flow, propellant spray) of B group, dotted line is that (nitrogen comes C group cold conditions spray distribution of pressure interference
Stream, propellant spray and spray amount are identical as B group)；
Step 5, comparison A group and B group test data difference, obtain cold and hot performance increment.Fig. 4 in solid line and click and sweep
Difference between line, difference is cold and hot performance increment between the two, as shown in solid lines in fig. 5.
Step 6, comparison B group and C group test data difference illustrate between fuel and incoming air not if undifferentiated
It burns, it is nitrogen that this, which is based on C group test incoming flow, can not generate burning with fuel obtain；Notable difference if it exists is then sent out
Raw burning, and difference is bigger, and combustion efficiency is better.Fig. 4 in chain-dotted line and dotted line between difference, between the two difference be
For burn contribution margin, as shown in the chain-dotted line in Fig. 5.
Step 7, comparison A group and C group test data difference judge Jet enterference influence degree by difference size.Fig. 4
In solid line and dotted line between difference, difference is Jet enterference amount between the two, as shown in broken line in fig. 5.
The above elaborates a specific embodiment of the invention with manometric test data instance, but test data is unlimited
It is pressed in surveying, is also possible to the data such as calorimetric or dynamometry.
The content that description in the present invention is not described in detail belongs to technology well known to those skilled in the art.
Claims (6)
1. a kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel, which is characterized in that comprise the following steps that
1) according to wind tunnel operation characteristic, air suction type propulsion trial system is established；
2) make test gas air, and close trigger signal, carry out A group cold test, measure no propellant spray, air incoming flow
Lower through-flow test data；
3) make test gas air, and open trigger signal, carry out the hot test of B group, measure propellant spray, air to flow down
Hot test data；
4) make test gas nitrogen, and open trigger signal, carry out C group cold conditions jet test, measure propellant spray, nitrogen comes
The cold conditions jet test data flowed down；
5) A, B, C group test data are compared, pressure, hot-fluid or axial force test data difference table or figure are obtained, is realized to cold and hot
State property energy increment, combustion characteristics and spray interference assessment.
2. a kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel according to claim 1, feature
Be: the air suction type propulsion trial system includes propellant spray valve, fuel storage tank, sequential control system, triggering pressure biography
Sensor；Propulsion trial model and fuel storage tank pass through connection by metal hose, and propellant spray valve, fuel spray are installed on metal hose
Note valve is mounted in propulsion trial model or close to propulsion trial model；Triggering pressure sensor is mounted on wind-tunnel by drive section
Or its upstream, the output signal for triggering pressure sensor is connected to sequential control system by shielded cable, as timing control
The external trigger signal of system；Sequential control system exports time delayed signal all the way, is connected to propellant spray valve by shielded cable, makees
For the open signal of propellant spray valve；Triggering pressure sensor experiences the air pressure change of installed position, generates corresponding electricity
Trigger signal is pressed, sequential control system is sent to；The external trigger signal threshold value and output delay that sequential control system is arranged wait
Time after sequential control system receives external trigger signal, judges whether it reaches the external trigger signal threshold value being previously set, when
When trigger signal amplitude reaches the threshold value being previously set, sequential control system starts to clock, when being delayed by the output being previously set
Between wait after, output enabling signal is to propellant spray valve；Propellant spray valve is opened according to enabling signal, will be in fuel storage tank
Fuel is transported to inside propulsion trial model.
3. a kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel according to claim 2, feature
It is: the method for selecting of the triggering pressure sensor installation site are as follows:
Firstly, the response time of response time and sequential control system to propellant spray valve carry out test determination；
Secondly, being examined to during wind tunnel operation by the gas pressure change sequential relationship in drive section and its upstream components
It surveys, filters out the triggering pressure sensor installation site for meeting the response time requirement of propellant spray valve and sequential control system,
At this pressure change and wind-tunnel by drive section end stagnation pressure change between time interval be greater than propellant spray valve and timing control
The sum of the response time of system processed, it is ensured that propellant spray flow field shifts to an earlier date than wind tunnel test flow field or synchronous foundation, it is ensured that several milliseconds
Incoming flow test gas and fuel compatible are inside propulsion trial model in the efficiency test time.
4. a kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel according to claim 1 or 2, special
Sign is: the step 2), step 3) wind-tunnel incoming flow test gas parameter corresponding with step 4) are consistent.
5. a kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel according to claim 4, feature
Be: the step 3) propellant spray flow corresponding with step 4) is consistent.
6. a kind of air suction type propulsion trial analogy method based on high temperature pulse wind-tunnel according to claim 1, feature
Be: the specific method is as follows for the step 5):
By hot test data obtained in through-flow test data obtained in comparison step 2) and step 3), cold and hot is carried out
Performance evaluation, provides pressure, hot-fluid or axial force data difference table or figure, and difference is cold and hot performance increment size；
By cold conditions jet test data obtained in hot test data obtained in comparison step 3) and step 4), fired
Specificity analysis is burnt, pressure, hot-fluid or axial force data difference table or figure are provided, difference is burning contribution amount；
By cold conditions jet test data obtained in through-flow test data obtained in comparison step 2) and step 4), sprayed
Note interference analysis, provides pressure, hot-fluid or axial force data difference table or figure, and difference is spray interference volume.
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| CN114166455A (en) * | 2021-12-07 | 2022-03-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test method for pulse wind tunnel |
| CN113884267B (en) * | 2021-12-07 | 2022-02-25 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test device for pulse wind tunnel |
| CN114166455B (en) * | 2021-12-07 | 2023-03-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test method for pulse wind tunnel |
| CN114184349A (en) * | 2022-02-15 | 2022-03-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining supersonic jet static operation pressure matching point of jet wind tunnel |
| CN114184349B (en) * | 2022-02-15 | 2022-04-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining supersonic jet static operation pressure matching point of jet wind tunnel |
| CN114354124A (en) * | 2022-03-11 | 2022-04-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-precision synchronous control method for impulse wind tunnel jet flow interference test |
| CN114354124B (en) * | 2022-03-11 | 2022-07-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-precision synchronous control method for jet flow interference test of pulse wind tunnel |
| CN117470721A (en) * | 2023-12-28 | 2024-01-30 | 山西建龙实业有限公司 | Method for measuring and evaluating high-temperature degradation strength and granularity degradation behavior of metallurgical coke |
| CN117470721B (en) * | 2023-12-28 | 2024-03-26 | 山西建龙实业有限公司 | Method for measuring and evaluating high-temperature degradation strength and granularity degradation behavior of metallurgical coke |
| CN118150107A (en) * | 2024-05-09 | 2024-06-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel and wide-parameter operation method thereof |
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