CN109184952A - A kind of hypersonic inlet not self-holding ability quantitative analysis method in starting state Disengagement zone - Google Patents
A kind of hypersonic inlet not self-holding ability quantitative analysis method in starting state Disengagement zone Download PDFInfo
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- CN109184952A CN109184952A CN201810956232.2A CN201810956232A CN109184952A CN 109184952 A CN109184952 A CN 109184952A CN 201810956232 A CN201810956232 A CN 201810956232A CN 109184952 A CN109184952 A CN 109184952A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A kind of hypersonic inlet disclosed by the invention not self-holding ability quantitative analysis method in starting state Disengagement zone, the specific steps are as follows: step 1, according to air force theoretical model analysis as a result, proposing the self-holding index S in Disengagement zonei；Step 2, using formula 1.1 to the self-holding index S of the Disengagement zone self-sustaining condition in air intake duct start-up courseiIt is calculated；Step 3, using obtaining SiValue is in start-up course, under different not starting states, carries out quantitative analysis to the self-holding ability of hypersonic inlet not starting state Disengagement zone.The present invention solves the problems, such as to identify and judge Disengagement zone unstability critical state under the conditions of really viscosity by proposing self-holding this dynamic quantitative assessment parameter of index in Disengagement zone.
Description
Technical field
The invention belongs to hypersonic inlet start-up course flow mechanism analysis technical fields, and in particular to a kind of superb
The air intake duct not self-holding ability quantitative analysis method in starting state Disengagement zone.
Background technique
Hypersonic inlet is the critical component of scramjet engine, its main function is exactly to provide for combustion chamber
Lasting, stable, high quality pressurized air guarantees that the indoor igniting of burning and burning are gone on smoothly, and entire engine generates just
Thrust.Only when hypersonic inlet is in starting state, scramjet engine could be according to the normal work of design requirement
Make.Configuration regardless of air intake duct, the common trait in not starting state are that contract section entrance will appear flowing
Disengagement zone.Large-scale separation area is in the entire start-up course of air intake duct, and movement changing rule is phenomenon, and mechanical balance is point
Mechanism from area's steady stability, and its self-holding stabiliser is only Disengagement zone and can adapt to incoming flow dynamic change, carries out self and adjusts
Section maintains air intake duct not starting state, to form the bilingual area on starting characteristic figure, the key for causing flow field change sluggish is former
Cause.
The analysis of starting state to air intake duct start-up course and not at present, primarily directed to free stream Mach number, contract ratio,
In terms of one-dimensional affecting parameters；For the research of Disengagement zone, also primarily directed to its size, shape, flow field structure, mobile variation
In terms of phenomena such as regular.Systematically summarize static balancing reason, dynamic stability mechanism and the quantitative assessment Disengagement zone of Disengagement zone
Self-holding stabilizing power under the conditions of a certain incoming flow and configuration, for deepening the understanding to hypersonic inlet start-up course,
It has great theoretical and practical significance.
Summary of the invention
The object of the present invention is to provide a kind of hypersonic inlet not starting state Disengagement zone control oneself ability quantitative analysis method,
Give a parameter and its calculation formula for the self-holding ability in Disengagement zone in quantitative assessment air intake duct start-up course --- point
Control oneself index from area, solves existing analysis method under the conditions of true VISCOUS FLOW and be difficult to and judge Disengagement zone unstability and face
The problem of boundary's state.
The technical scheme adopted by the invention is that: starting state Disengagement zone ability of controlling oneself is not divided quantitatively for a kind of hypersonic inlet
Analysis method, the specific steps are as follows:
Step 1, according to Aerodynamics modal analysis results, the self-holding index S in Disengagement zone is proposedi, SiCalculation formula
It is as follows:
Wherein, PRIndicate separation shock wave pressure, P after the wave of the reflected shock wave of upper wall surfaceTIndicate that Disengagement zone leeward is high anti-
Pressure area starting point pressure, PSIndicate Disengagement zone leeward high back-pressure area vertex pressure；
Step 2, using formula (1.1) to the self-holding index S of the Disengagement zone self-sustaining condition in air intake duct start-up courseiIt carries out
It calculates；
Step 3, using obtaining SiValue under different not starting states, does not start shape to hypersonic inlet in start-up course
The self-holding ability of state Disengagement zone carries out quantitative analysis.
The features of the present invention also characterized in that:
Step 2 is specifically implemented according to the following steps:
Step 2.1, to a certain air intake duct configuration and its contract ratio, one is chosen according to kantrowitz limit relation formula
Do not start free stream Mach number stream field and carry out unsteady numerical simulations, obtain an initialization does not start flow field；
Step 2.2, using unsteady numerical simulations, the flow field that do not start being calculated is primary condition, steps up and
Mach number is flowed, entirely accelerates the flow field of start-up course to calculate the air intake duct, Bottom Pressure curve is extracted, from pressure curve
In can directly obtain PTAnd PS, in Flow Field Calculation result, can extract pressure P after the wave of shock waveR, by PR、PTAnd PSSubstitution formula
(1.1) it calculates and obtains each the self-holding index of Disengagement zone does not determine reality until air intake duct start successfully under starting state
The free stream Mach number of existing air intake duct self-starting.
The formula of kantrowitz limit relation described in step 2.1 are as follows:
Wherein AiIndicate inlet mouth area, A*Indicate throat opening area, Ma∞Indicate free stream Mach number, γ is gas level pressure
Specific heat CpWith constant volume specific heat CvThe ratio between, the γ value of air is usually taken to be 1.40.
Mach number described in step 2.2 is with 0.005 to 0.010 for minimum unit increment.
The specific quantitative analysis method of step 3 are as follows:
Firstly, subtracting the previous air intake duct of a Mach number minimum unit increment in air intake duct self-starting free stream Mach number
The Instability state of not starting state, as air intake duct response critical state and Disengagement zone is calculated according to formula (1.1) and is obtained
Take the S of the Instability state of Disengagement zoneiValue Sic；
Then, according to the self-holding index S of this Disengagement zonei, judge the power of the self-holding ability in Disengagement zone at this time；SicIt is one
Value between 0 to 1, and SiValue range be in SicTo between 1, SiBe worth it is bigger, indicate Disengagement zone capacity of self-regulation and
Adaptation incoming flow changing capability is stronger, and air intake duct is more difficult to start；SiIt is worth the capacity of self-regulation of the Disengagement zone of smaller expression at this time
The ability that incoming flow changes is weaker with adapting to, the easier starting of air intake duct.
The beneficial effects of the present invention are:
(1) it by proposing self-holding this dynamic quantitative assessment parameter of index in Disengagement zone, solves and identifies and judges really
Under the conditions of viscosity the problem of Disengagement zone unstability critical state；
(2) mechanism that analysis and summary Disengagement zone static mechanical equilibrium reasons and the high back-pressure of Disengagement zone leeward generate；
(3) analysis and summary is under conditions of inlet flow conditions variation, Disengagement zone can self-control, realize dynamic stability
Basic reason；
(4) analysis method through the invention is current air intake duct assistant starting control means, and specifying should control
Central factor controls the self-holding index of Disengagement zone aiming at property, it is made to drop to Instability value, so that unstability disappears,
To realize that air intake duct starts.
Detailed description of the invention
Fig. 1 is that Disengagement zone static strength balances schematic diagram in the present invention；
Fig. 2 is leeward high back-pressure formation mechenism schematic diagram in Disengagement zone in the present invention；
Fig. 3 is that hypersonic inlet does not start Disengagement zone self-sustaining condition bottom plate typically along stroke pressure distribution curve in the present invention.
In figure, 1. Disengagement zone surface pressure windward, the leeward surface pressure in 2. Disengagement zone, shear stress suffered by 3. Disengagement zone, 4. points
From shock wave, 5. reflected shock waves, 6. pseudoshock mixing section pressurizing areas, 7. pressure liters, 8. stagnation pressure liters.
Specific embodiment
With reference to the accompanying drawing and specific embodiment the present invention is described in detail.
It is specific to walk the present invention provides a kind of not self-holding ability quantitative analysis method in starting state Disengagement zone of hypersonic inlet
It is rapid as follows:
Step 1, according to Aerodynamics modal analysis results, the self-holding index S in Disengagement zone is proposedi, SiCalculation formula
It is as follows:
Fig. 3 gives air intake duct not under starting state, and Disengagement zone is in the air intake duct Bottom Pressure edge for stable state of controlling oneself
The common trait and pattern of journey distribution curve: Bottom Pressure curve keeps horizontal first, uprushes near the burble point of Disengagement zone
To a certain height, windward side (burble point is between vertex) pressure curve in Disengagement zone highly keeps horizontal herein, is separating
The vertex in area starts, and pressure curve starts to be increased monotonically, and just begins to decline after attachment pressure curve again reaches maximum value.
In Fig. 3, ordinate is p/p0It is that bottom plate wall surface edge flows to the ratio between pressure and the incoming flow static pressure in somewhere, PRIt indicates to divide
From shock wave after the wave of the reflected shock wave 5 of upper wall surface pressure, PTIndicate the high back-pressure area starting point pressure of Disengagement zone leeward, PSIt indicates
Disengagement zone leeward high back-pressure area vertex pressure.
Step 2, using formula (1.1) to the self-holding index S of the Disengagement zone self-sustaining condition in air intake duct start-up courseiIt carries out
It calculates；
Firstly, choosing one according to kantrowitz limit relation formula 1.2 to a certain air intake duct configuration and its contract ratio
Do not start free stream Mach number stream field and carry out numerical simulation, obtain an initialization does not start flow field, as shown in Figure 2.Wherein
AiIndicate inlet mouth area, A*Indicate throat opening area, Ma∞Indicate free stream Mach number, γ is gas specific heat at constant pressure CpHold with equal
Specific heat CvThe ratio between, the γ value of air is usually taken to be 1.40.
Then, using unsteady numerical simulations, the flow field that do not start being calculated is primary condition, with Mach number 0.005
It is minimum unit increment to 0.010, steps up free stream Mach number, entirely accelerate the flow field of start-up course to carry out the air intake duct
It calculates, extracts Bottom Pressure curve as shown in Figure 3 by calculating fluid software, P can be directly obtained from pressure curveTWith
PS, in Flow Field Calculation result, can extract pressure P after the wave of reflected shock wave 5R, by PR、PTAnd PSSubstitution formula 1.1, which calculates, to be obtained often
One the self-holding index of Disengagement zone does not determine until air intake duct starts successfully and realizes air intake duct self-starting under starting state
Free stream Mach number.
Step 3, using obtaining SiValue under different not starting states, does not start shape to hypersonic inlet in start-up course
The self-holding ability of state Disengagement zone carries out quantitative analysis.
For example, according to plane of symmetry flow field structure, observing point at this time as shown in Figure 2 in a certain Flow Field Calculation result
From macroscopic forms such as area's shape, size, length, height.
It is not opened in the previous air intake duct that air intake duct self-starting free stream Mach number subtracts a Mach number minimum unit increment
Dynamic state, as the Instability state of air intake duct response critical state and Disengagement zone.It is calculated according to formula 1.1 and obtains separation
The S of the Instability state in areaiValue Sic。
Then, according to the self-holding index S of this Disengagement zonei, judge the power of the self-holding ability in Disengagement zone at this time；SicIt is one
Value between 0 to 1, SiValue range be in SicTo between 1, SiValue is bigger, indicates the capacity of self-regulation of Disengagement zone and fits
Answer incoming flow changing capability stronger, air intake duct is more difficult to start；SiBe worth smaller expression Disengagement zone at this time capacity of self-regulation and
The ability for adapting to incoming flow variation is weaker, the easier starting of air intake duct.
The unstability critical value S of Disengagement zoneicIt is the mark for judging air intake duct response critical state.Starting air intake duct seeks to needle
The S of Disengagement zone is controlled propertyiValue, is allowed to drop to unstability critical value Sic, Disengagement zone is to the slight perturbations of incoming flow at this time
It all realizes to control oneself without capacity of self-regulation and stablize, Disengagement zone unstability disappears, and air intake duct realizes starting.
According to Aerodynamics modal analysis results, the self-holding index S in Disengagement zone is proposediAnalytic process it is as follows:
Using the Disengagement zone closed area of not starting state as control volume, force analysis is carried out for its static balancing.Such as Fig. 1
Shown, by surface pressure 1 windward, the suffered shearing in Disengagement zone on the leeward surface pressure 2 in Disengagement zone and entire outer profile is answered for Disengagement zone
Power 3.Because the flow direction of Disengagement zone is that clockwise, mainstream is along flowing to direction, and according to anti-to the viscous force of Disengagement zone
Force principal, wall surface are equally that edge flows to direction to the direction of Disengagement zone, therefore, shear stress 3 suffered by Disengagement zone
It is all that edge flows to direction.The static strength of Disengagement zone balances, and actually Disengagement zone is windward suffered by surface pressure 1 and Disengagement zone
Component of the sum of the shear stress 3 in flow direction, equal to component of the leeward surface pressure in flow direction.Because the suffered shearing in Disengagement zone is answered
Power 3 windward than Disengagement zone more than surface pressure 1 and Disengagement zone 2 low three orders of magnitude of leeward surface pressure, do not open in air intake duct by Disengagement zone
Static strength balance under dynamic state, actually the resultant force of surface pressure and leeward surface pressure in flow direction is zero windward.
On the basis of in Disengagement zone, static strength balances conclusion, the original of the high back-pressure generation of further Analyze & separate area leeward
Cause.Since Disengagement zone windward side is easier to understand by the impact of incoming flow in face of direction of flow by biggish normal pressure,
And self-sustaining condition is entered in air intake duct in Disengagement zone, free stream Mach number and contract ratio at this moment is to be sufficiently great to initiate air intake duct
, why air intake duct maintains not starting state, it is primarily due to the self―sustaining of Disengagement zone, in other words, the institute of Disengagement zone
It is that incoming flow has been withstood to Disengagement zone by high back-pressure due to its leeward so that downstream cannot be blowed to by the high-speed flow of direction of flow
Motive force caused by.As shown in Fig. 2, the practical interior stream that the leeward facial contour in Disengagement zone and upper wall surface are not formed under starting state
The pseudoshock mixing section pressurizing area 6 in road, pseudoshock mixing section pressurization originate in Disengagement zone top, terminate at Disengagement zone tail
Portion, there are supersonic speed, subsonic speed mixing section in runner, main flow area air-flow rises rapidly in pseudoshock section pressure, carries on the back to Disengagement zone
Wind face forms high back-pressure, and Disengagement zone is made to form stress balance in the horizontal direction, to be stabilized presence.In conclusion
The present invention proposes an important conclusion, and the high back-pressure of Disengagement zone leeward of support Disengagement zone horizontal direction statics balance is by dividing
The pseudoshock mixing section pressurizing area 6 newly compressed in wall surface in the practical runner collectively constituted from area's contour line and upper wall surface causes
's.
In Disengagement zone on the basis of leeward high back-pressure mechanism of production, further Analyze & separate area adapts to incoming flow variation,
The reason of carrying out self-control, realizing dynamic stability.Its key is negative feedback mechanism, i.e., when incoming flow parameter changes,
Disengagement zone has enough capacitys of self-regulation, in other words self-control remaining, by itself be moved and changed in realize from
One mechanical balance state is transformed into another new mechanical balance state.In other words, when free stream Mach number increases, because
It must increase for the pressure potential of windward side, the mechanical balance of Disengagement zone has the tendency that being destroyed, and Disengagement zone needs while increasing leeward
The pressure in face maintains its own to be stabilized, and forms new mechanical balance, it to be a dynamic mistake that here it is self-holding stabilizations
Journey.Start-up course, the process stablized and be destroyed of actually controlling oneself.
Control oneself index S the invention proposes Disengagement zonei(Self-sustaining Index) is for quantitatively evaluation starting
Self-holding ability of the Disengagement zone in the process under a certain Mach number, with self-holding index, by Disengagement zone windward side and leeward surface pressure
The various influence factors such as balance, compression-type face, incoming flow parameter, spillway discharge and the feedback mechanism between them unite,
It is predicted for the future trend of Disengagement zone under a certain state.
As shown in Fig. 2, the high back-pressure of Disengagement zone leeward is mainly supported by two parts, first part is that separation swashs
For wave in the reflected shock wave 5 of upper wall surface, the second part is that the pseudoshock mixing section that Disengagement zone leeward and upper wall surface are constituted is pressurized
Region 6.If incoming flow parameter is changed, it is exactly to need through the two portions of de-regulation that Disengagement zone, which maintains the high back-pressure of leeward,
Divide to realize.
Large-scale separation area is to maintain existing for itself by separation shock wave in the reflected shock wave 5 of upper wall surface, in fact, pseudo- swash
The boosting capability of wave mixing section pressurizing area 6 be it is certain, controllability is poor, and separates shock wave in the reflected shock wave 5 of upper wall surface
Boosting capability can change with Mach number and change, controllability is strong, so Disengagement zone is to the adaptive main of incoming flow
It is to be realized by separation shock wave in the reflected shock wave 5 of upper wall surface.It therefore, can be in the high back-pressure area of Disengagement zone leeward
The ratio that the high back-pressure area stagnation pressure of leeward rises that accounts for is risen by Analyze & separate shock wave pressure caused by the reflected shock wave 5 of upper wall surface,
Carry out the power of the self-holding ability of Disengagement zone under the quantitative a certain inlet flow conditions of evaluation.The present invention proposes that the self-holding index in Disengagement zone calculates
Formula is as follows:
Wherein, SiIt is the self-holding index in Disengagement zone, PRIndicate separation shock wave pressure, P after the wave of the reflected shock wave 5 of upper wall surfaceT
Indicate the high back-pressure area starting point pressure of Disengagement zone leeward, PSIndicate Disengagement zone leeward high back-pressure area vertex pressure.
As shown in figure 3, being apparent from, PR-PT5 bring of reflected shock wave pressure for separation shock wave in upper wall surface rises 7, and PS-PTThen
It is to separate shock wave to mix with pseudoshock the stagnation pressure liter 8 that pressurizing area generates jointly in the reflected shock wave of upper wall surface.Control oneself Disengagement zone
Index SiActually proportion of the pressure rise across shock envelope in total pressurization is exactly that pressure liter 7 and stagnation pressure rise the ratio between 8, therefore, 0 < Si<
1, it is the parameter between one 0 to 1, and control oneself index S for Disengagement zoneiIt is bigger, indicate that the self-holding ability in the Disengagement zone under the state is got over
By force, a possibility that Disengagement zone is very strong to the variation adaptability of incoming flow parameter, and air intake duct lower a moment at this time enters starting state
It is smaller；Control oneself index S for Disengagement zoneiIt is smaller, although indicating that the Disengagement zone under the state is in mechanical balance state, to lower a moment
The adaptability of incoming flow variation is weaker, and Disengagement zone is controlled oneself, and ability is weaker, and Disengagement zone is easier closer to instability status, air intake duct
Starting.Control oneself index S for Disengagement zoneiIt is a variable, is characterized under certain contract type face, under certain inlet flow conditions,
The ability of change in future is deacclimatized with state at that time in large-scale separation area.During startup, SiBe it is continually changing, when point
From area close to unstability critical state, SiReach minimum value.SiMinimum value be one for the air intake duct of some fixed configuration
Fixed, therefore, the unstability critical state of air intake duct Disengagement zone during startup is exactly its SiReach the state of minimum value.Table
The adaptability of incoming flow Parameters variation has been weakened in bright Disengagement zone significantly, has gone to increase without enough adjusting remainings leeward
Face back-pressure matches the increase bring windward side pressure increase of Mach number, although Disengagement zone at this time is in statics balance shape
It state but is easily destroyed.Control oneself index S for the Disengagement zone for the Instability state being calculatediAs identifying and judgeing the air intake duct
The index of Disengagement zone Instability state.The macroscopic form of Disengagement zone and its index of controlling oneself do not have proportional relation, some Disengagement zone
Very big, index of controlling oneself is small instead, and the ability for adapting to incoming flow variation is low.This shows that index is controlled oneself as quantitative analysis point in Disengagement zone
Control oneself an important dynamic parameter of ability from area, than some macroscopical presentations of Disengagement zone, can more disclose Disengagement zone and start
The internal motivation and essential reason of Change and Development in journey.
Claims (5)
1. a kind of not self-holding ability quantitative analysis method in starting state Disengagement zone of hypersonic inlet, which is characterized in that specific steps
It is as follows:
Step 1, according to Aerodynamics modal analysis results, the self-holding index S in Disengagement zone is proposedi, SiCalculation formula such as
Under:
Wherein, PRIndicate separation shock wave pressure, P after the wave of the reflected shock wave of upper wall surfaceTIndicate the high back-pressure area of Disengagement zone leeward
Starting point pressure, PSIndicate Disengagement zone leeward high back-pressure area vertex pressure；
Step 2, using formula (1.1) to the self-holding index S of the Disengagement zone self-sustaining condition in air intake duct start-up courseiIt is calculated；
Step 3, using obtaining SiValue is in start-up course, and under different not starting states, to hypersonic inlet, starting state is not separated
The self-holding ability in area carries out quantitative analysis.
2. a kind of hypersonic inlet as described in claim 1 not self-holding ability quantitative analysis method in starting state Disengagement zone,
It is characterized in that, step 2 is specifically implemented according to the following steps:
Step 2.1, to a certain air intake duct configuration and its contract ratio, one is chosen according to kantrowitz limit relation formula and is not opened
Dynamic free stream Mach number stream field carries out unsteady numerical simulations, and obtain an initialization does not start flow field；
Step 2.2, using unsteady numerical simulations, the flow field that do not start being calculated is primary condition, steps up incoming flow horse
Conspicuous number entirely accelerates the flow field of start-up course to calculate the air intake duct, extracts Bottom Pressure curve, can from pressure curve
To directly obtain PTAnd PS, in Flow Field Calculation result, can extract pressure P after the wave of shock waveR, by PR、PTAnd PSSubstitution formula (1.1)
Calculate obtain each not under starting state Disengagement zone self-holding index, until air intake duct start successfully, determination realize into
The free stream Mach number of air flue self-starting.
3. a kind of hypersonic inlet as described in claim 1 not self-holding ability quantitative analysis method in starting state Disengagement zone,
It is characterized in that, the formula of kantrowitz limit relation described in step 2.1 are as follows:
Wherein AiIndicate inlet mouth area, A*Indicate throat opening area, Ma∞Indicate free stream Mach number, γ is gas specific heat at constant pressure
CpWith constant volume specific heat CvThe ratio between, the γ value of air is usually taken to be 1.40.
4. a kind of hypersonic inlet as described in claim 1 not self-holding ability quantitative analysis method in starting state Disengagement zone,
It is characterized in that, Mach number described in step 2.2 is with 0.005 to 0.010 for minimum unit increment.
5. a kind of hypersonic inlet as described in claim 1 not self-holding ability quantitative analysis method in starting state Disengagement zone,
It is characterized in that, the specific quantitative analysis method of step 3 are as follows:
Firstly, not opened in the previous air intake duct that air intake duct self-starting free stream Mach number subtracts a Mach number minimum unit increment
Dynamic state, as the Instability state of air intake duct response critical state and Disengagement zone calculate to obtain according to formula (1.1) and divide
The S of Instability state from areaiValue Sic；
Then, according to the self-holding index S of this Disengagement zonei, judge the power of the self-holding ability in Disengagement zone at this time；SicIt is one 0 to 1
Between value, SiValue range be in SicTo between 1, SiValue is bigger, indicates the capacity of self-regulation of Disengagement zone and adapts to come
Stream changing capability is stronger, and air intake duct is more difficult to start；, SiIt is worth the capacity of self-regulation and adaptation of the Disengagement zone of smaller expression at this time
The ability of incoming flow variation is weaker, the easier starting of air intake duct.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112651076A (en) * | 2020-11-20 | 2021-04-13 | 南京航空航天大学 | Binary supersonic speed adjustable air inlet duct non-starting boundary prediction method |
| CN113505551A (en) * | 2021-09-09 | 2021-10-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Simulation method, system, storage medium and terminal for inducing unusual changes in incoming flow |
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| CN102230848A (en) * | 2007-12-03 | 2011-11-02 | 哈尔滨工业大学 | Method for acquiring optimal classification surface of hypersonic speed air inlet starting/non-starting mode |
| CN103953448A (en) * | 2014-04-15 | 2014-07-30 | 南京航空航天大学 | Hypersonic air inlet channel |
| CN104806357A (en) * | 2015-04-16 | 2015-07-29 | 南京航空航天大学 | Two-dimensional variable geometry hypersonic intake port provided with rectangular inlet as well as design method and working method of two-dimensional variable geometry hypersonic intake port |
| CN104863715A (en) * | 2015-04-16 | 2015-08-26 | 南京航空航天大学 | Binary hypersonic-velocity variable-geometry air inlet way with rectangular inlet, design method thereof and working method thereof |
| CN104899418A (en) * | 2015-04-24 | 2015-09-09 | 南京航空航天大学 | Method for predicting unstart oscillation frequency of mixed-compression supersonic and hypersonic speed air inlet passage |
| CN106014683A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Pressurization flow control device-containing SERN structure for TBCC |
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| CN112651076A (en) * | 2020-11-20 | 2021-04-13 | 南京航空航天大学 | Binary supersonic speed adjustable air inlet duct non-starting boundary prediction method |
| CN112651076B (en) * | 2020-11-20 | 2023-05-09 | 南京航空航天大学 | Binary supersonic speed adjustable air inlet channel non-starting boundary prediction method |
| CN113505551A (en) * | 2021-09-09 | 2021-10-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Simulation method, system, storage medium and terminal for inducing unusual changes in incoming flow |
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