CN109543297A - A kind of modification method of airframe to ejector seat aerodynamic interference - Google Patents
A kind of modification method of airframe to ejector seat aerodynamic interference Download PDFInfo
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Abstract
The invention belongs to aviation Aircrew Escape Technology fields, it is related to a kind of airframe to the modification method of ejector seat aerodynamic interference, ejector seat wind tunnel test aerodynamic data is calculated aerodynamic data with Fluid Mechanics Computation (CFD) method first and compared and analyzed by this method, CFD emulation mode is modified in due course perfect, ensure the engineering reasonability of CFD emulation mode, analysis model is determined as three kinds further according to ejector seat simulation analysis demand, and CFD simulation calculation is carried out by the operating condition of simulation analysis demand, multivariate data regression analysis finally is carried out to calculated result, to obtain airframe to the aerodynamic data correction result under ejector seat (no bracket) disturbed condition.The present invention can either instruct ejector seat wind tunnel test conceptual design, aerodynamic interference data of the airframe to ejector seat based on wind tunnel test can be obtained again, ejector seat motion simulation precision can be effectively improved, to improve ejection escape success rate, ensures that the lifesaving safety offer technology of pilot guarantees.
Description
Technical field
The invention belongs to aviation Aircrew Escape Technology field, it is related to a kind of airframe and ejector seat aerodynamic interference is repaired
Correction method.
Background technique
Airplane catapult life saving system is the emergency escape device provided for pilot, is in the presence of not retrieving in aircraft
When guarantee pilot's safe escape.With the raising of In-Flight Performance, the probability launched under the conditions of low altitude and adverse attitude is more next
Bigger, the requirement to ejector seat technical performance is also higher and higher.GJB1800A " ejector-seat chair form occupant's emergency escape lifesaving system
System general specification " to the performance assessment criteria of 120 kinds of states of ejector seat performance provision, this 120 kinds of states are mostly unfavorable
State of flight, existence conditions are unable to complete verification experimental verification.Therefore the means that simulating, verifying is used in engineering, exactly pass through numerical value
The method of emulation carries out the simulation of ejector seat motion simulation to various unfavorable state of flights and reaches and examine to verify its proper property
Core purpose.
The aerial sports situation of ejector seat (also refer to pilot and combine the people-chair system constituted with ejector seat), depends on
In the active force suffered by it.The aerodynamic force that ejector seat is subject to is the important component of its stress, aerodynamic force be it is important and
Complicated active force.The aerodynamic force that ejector seat is subject in the case where flow field velocity has determined situation is determined by its aerodynamic configuration.It wants
Aerodynamic force is solved, the aerodynamic characteristics of ejector seat need to be found out first, the method for generalling use wind tunnel test obtains.Therefore, wind-tunnel
Test becomes the pilot project that each model seat must carry out.
The wind tunnel test that ejector seat carries out, is generally divided into low-speed wind tunnel test and high wind tunnel testing.Low-speed wind tunnel examination
It tests using 1:1 mock-up, high wind tunnel testing is using contracting than (such as 1:5) model.Either low-speed wind tunnel test or high speed
Wind tunnel test is required to that test model is supported in flow field with bracket, and realizes the consecutive variations of various operating conditions, each to obtain
Aerodynamic characteristics under kind operating condition.It is existing for no bracket, in wind tunnel test data application when the true sling movement of ejector seat
In the process, needing to deduct bracket influences the aerodynamic interference of ejector seat.
In addition, due to being limited by wind-tunnel experimental condition (such as tunnel size, test speed), all wind-tunnel examinations of ejector seat
Model is tested comprising the influence of airframe.During wind tunnel test data application, need to increase airframe to ejection
The aerodynamic interference of seat influences.
Obtain through the invention based on the airframe of wind tunnel test to ejector seat aerodynamic interference data, can effectively mention
High ejector seat motion simulation precision ensures that the lifesaving safety offer technology of pilot guarantees to improve ejection escape success rate.
Summary of the invention
The object of the present invention is to provide a kind of airframes to the modification method of ejector seat aerodynamic interference, to solve to launch
Seat wind tunnel test data fail the problem of really reflecting its aerodynamic characteristics.
The technical scheme is that airframe includes the following steps: the modification method of ejector seat aerodynamic interference
Step 1: the changing rule and data magnitude of wind-tunnel test data, the data pair under analysis each operating condition of ejector seat
Ejector seat wind tunnel test real conditions are answered (to fail to simulate due airframe under practical ejection situation, but contain reality
The bracket not having under border ejection situation), including six degree of freedom under the operating condition of test described with the angle of attack and yaw angle and corresponding operating condition
Aerodynamic force component data；
Step 2: corresponding CFD emulation is carried out according to the model of ejector seat wind tunnel test and operating condition, and CFD is emulated
Data are compared with wind tunnel test data, and single degree of freedom aerodynamic data each in each operating condition, six degree of freedom is constituted
Dynamic data variation tendency and magnitude judge CFD emulation data as judgment criteria, carry out in due course to CFD emulation mode
Feedback and amendment guarantee CFD until CFD simulation result is consistent with the dynamic data variation tendency and magnitude of results of wind tunnel
The engineering reasonability of emulation mode；
Step 3: analysis ejector seat emulates demand, designs three kinds of simulation models: model A, Model B and MODEL C, model A
For seat and stent model, Model B be seat model and MODEL C is seat and airframe models；
Step 4: demand, flying speed needed for determining simulation analysis operating condition, the angle of attack and sideslip are emulated according to ejector seat
The value range at angle, wherein flying speed V=250km/h~1300km/h, angle of attack=0 °~360 °, yaw angle β=0 °~
180°.Further according to engineering it is practical determine these parameters specific value, wherein flying speed press altogether 250km/h, 450km/h,
850km/h, 1000km/h, 1300km/h value；When angle of attack=0 °~90 °, Δ α=10 °, when angle of attack=90 °~270 °, Δ
α=20 °, when angle of attack=270 °~360 °, Δ α=10 °；When yaw angle β=0 °~50 °, Δ β=5 °, yaw angle β=50 °~
At 90 °, Δ β=10 °, when yaw angle β=90 °~180 °, Δ β=15 °；
Step 5: the CFD emulation mode determined using step 2 carries out three kinds by the simulation analysis operating condition that step 4 determines
The CFD simulation calculation of model forms CFD emulation data of three kinds of simulation models under operating condition described in step 4；
Step 6: regression analysis is carried out to the CFD simulation calculation data of bis- kinds of models of A, B, is obtained from seat+stent model
The middle modification method for deducting support interferences carries out regression analysis to the CFD simulation calculation data of bis- kinds of models of B, C, is present
Increase the modification method of fuselage interference on the basis of chair model；
Step 7: the modification method for the deduction support interferences that step 6 determines is applied to wind tunnel test data, is detained
Except the wind tunnel test data after support interferences；
Step 8: the modification method for increasing fuselage interference that step 6 is determined is applied to the resulting wind tunnel test of step 7
Data obtain the wind tunnel test data for deducting support interferences and increasing fuselage interference.
Further, ejector seat wind tunnel test time of day described in step 1 is due to by wind tunnel test existence conditions
Limitation, due airframe under practical ejection situation can not be simulated, but containing always does not have under practical ejection situation
The bracket to play a supportive role to test model.
Further, CFD emulation mode described in step 2 is to carry out aerodynamic characteristics numerical simulation in object in flow field
Universal method.
Further, CFD simulation modification method described in step 2 is that the true wind tunnel test data of ejector seat is combined to carry out
Engineering method after data Fitting Analysis.
Further, three kinds of models described in step 3 are to meet emulation needs and can obtain in engineering
Model, wherein seat+airframe models include ejector seat different ejection travels (not with airframe distance and relative attitude
Together) the case where.
Further, the value range of flying speed, the angle of attack determined by step 4 and yaw angle is according to being both able to satisfy
Emulation demand, but can save computing resource, shorten research cycle principle determine.
Further, CFD described in step 5 emulate data, be tri- kinds of models of A, B, C correspond to step 4 in flying speed,
The value range of the angle of attack and yaw angle is combined included various operating conditions.
Further, data regression method is calculated described in step 6, including refers to linear regression analysis method or non-thread
Property approximating method (alternative manner etc. based on least square method).
The present invention have the advantage that and the utility model has the advantages that
The present invention devises a kind of airframe to the modification method of ejector seat aerodynamic interference, can effectively improve ejector-seat
Chair motion simulation precision is conducive to explore ejector seat inherent technology performance, reaches and carry out ejector seat performance with simulation means
The purpose of operation index.The present invention is based on the wind tunnel test of ejector seat (no airframe interference, there is support interferences) pneumatic numbers
According to a kind of design method being modified under airframe disturbed condition to its aerodynamic data being devised, to reach raising bullet
Penetrate the purpose of seat Multiple Purpose Simulation precision.This method by ejector seat wind tunnel test aerodynamic data and calculates fluid force first
Aerodynamic data is calculated obtained by (CFD) method to compare and analyze, CFD emulation mode is modified in due course, it is ensured that CFD emulation
Analysis model is determined as three kinds of (seats+bracket mould further according to ejector seat simulation analysis demand by the engineering reasonability of method
Type, seat model, seat+airframe models), and carry out the CFD under three kinds of model states by the operating condition of simulation analysis demand and emulate
It calculates, multivariate data regression analysis finally is carried out to calculated result of three kinds of models under each emulation operating condition, to obtain aircraft
Fuselage is to the aerodynamic data correction result under ejector seat (no bracket) disturbed condition.
The present invention had both deducted wind tunnel test bracket to bullet relative to existing ejector seat wind tunnel test data application situation
The aerodynamic interference of seat is penetrated, and increases airframe to the aerodynamic interference of ejector seat, makes ejector seat wind tunnel test data
More accurately reflect its aerodynamic characteristics.
Present invention application easy to spread, may be directly applied to grinding and newly grinding model ejector seat, can either instruct to launch
Seat wind tunnel test conceptual design, and the airframe based on wind tunnel test can be obtained to ejector seat aerodynamic interference data, energy
Ejector seat motion simulation precision is effectively improved, to improve ejection escape success rate, ensures that the lifesaving of pilot provides safely skill
Art support has important military significance to enhancing pilot's confidence and fighting capacity.
Detailed description of the invention
Fig. 1 is the working principle diagram of the embodiment of the present invention.Wherein:
Wind tunnel test data variation rule refers in ejector seat six degree of freedom each aerodynamic characteristics with the angle of attack and side
The rule of the posture range of sliding angle characterization, the changing rule can intuitively evaluate the static-stability area of ejector seat.
CFD emulation of the ejector seat under each operating condition of wind tunnel test, be strictly by the operating condition of ejector seat wind tunnel test, into
Row ejector seat CFD emulation, the purpose is to facilitate the comparative analysis for carrying out wind tunnel test data and CFD emulation data.
The comparative analysis of wind tunnel test data and CFD emulation data, is respectively to each in ejector seat six degree of freedom
Aerodynamic characteristics are compared and analyzed with the rule of the angle of attack and the posture range of yaw angle characterization, and the purpose is to imitate for CFD
True result judge and is modified offer foundation to CFD emulation mode.
The reasonable sex determination of CFD simulation result, according to wind tunnel test data in changing rule, static-stability area, data volume
The goodness of fit of grade etc. is as judgment criteria.
According to seat simulation analysis demand, determines analysis model and analysis operating condition, be to meet GJB1800A and model seat
The demand of chair engineering development is as basic principle.
In three kinds of simulation models, seat model is designed (single model) for concrete model seat, seat+bracket mould
Type need to be designed (single model) in conjunction with bracket used in wind tunnel test, and seat+airframe models need to be directed to concrete model seat
Chair and equipped airframe are designed, and need to consider ejector seat in different ejection travels (with airframe distance and phase
To posture difference) the case where (multiple models).
Multivariate data regression analysis refers to linear regression analysis method or non-linear fitting method (based on least square method
Alternative manner etc.).
Fuselage and support interferences modification method are first return to the CFD simulation calculation data of bis- kinds of models of A, B dividing
Analysis obtains the modification method that support interferences are deducted from seat+stent model, then the CFD simulation calculation number to bis- kinds of models of B, C
According to regression analysis is carried out, the modification method for increasing fuselage interference on the basis of seat model is obtained；
Fuselage is the amendment side that will first deduct support interferences to the pneumatic correction result under seat (no bracket) disturbed condition
Method is applied to wind tunnel test data, obtains deducting the wind tunnel test data after support interferences；The amendment of fuselage interference will be increased again
Method is applied to deduct resulting wind tunnel test data after support interferences, obtains deducting support interferences and increases fuselage interference
Wind tunnel test data.The data reflect aerodynamic characteristics of the ejector seat under true ejection situation.
Specific embodiment
Technical method through the invention, obtaining the wind tunnel test based on ejector seat, (no airframe interference, there is bracket
Interference) aerodynamic data airframe to the modification method of ejector seat aerodynamic interference, can reach and solve the true shape of ejector seat
Aerodynamic characteristics, the purpose of raising ejector seat Multiple Purpose Simulation precision under condition.This method is first by ejector seat wind tunnel test
Aerodynamic data is compared and analyzed with calculating aerodynamic data obtained by Fluid Mechanics Computation (CFD) method, in due course to CFD emulation mode
It is modified, it is ensured that the engineering reasonability of CFD emulation mode determines analysis model further according to ejector seat simulation analysis demand
For three kinds (seat+stent model, seat model, seats+airframe models), and three kinds of moulds are carried out by the operating condition of simulation analysis demand
CFD simulation calculation under type state finally carries out multivariate data recurrence to calculated result of three kinds of models under each emulation operating condition
Analysis, to obtain airframe to the aerodynamic data correction result under ejector seat (no bracket) disturbed condition.
On the one hand the present invention has deducted wind tunnel test bracket relative to existing ejector seat wind tunnel test data application situation
To the aerodynamic interference of ejector seat, while airframe is increased again to the aerodynamic interference of ejector seat, make ejector seat wind-tunnel
Test data more accurately reflects its aerodynamic characteristics.The present invention can effectively improve ejector seat motion simulation precision, to mention
High ejection escape success rate ensures that the lifesaving of pilot provides safely technical support.
Airframe includes the following steps: the modification method of ejector seat aerodynamic interference
Step 1: the changing rule and data magnitude of wind-tunnel test data, the data pair under analysis each operating condition of ejector seat
Ejector seat wind tunnel test time of day is answered (not simulate due airframe under practical ejection situation, but contain reality
The bracket not having under border ejection situation), including six degree of freedom under the operating condition of test described with the angle of attack and yaw angle and corresponding operating condition
Pneumatic force component.Ejector seat wind tunnel test time of day is that it is real to fail simulation due to the limitation by wind tunnel test existence conditions
Due airframe under border ejection situation, but contain always do not have under practical ejection situation to test model rise support make
Bracket.
Step 2: corresponding CFD emulation is carried out according to the model of ejector seat wind tunnel test and operating condition, and CFD is emulated
Data are compared with wind tunnel test data, and the dynamic data that each operating condition, each single degree of freedom aerodynamic data are constituted is become
Change trend and magnitude judge CFD emulation data as judgment criteria, and CFD emulation mode is fed back and repaired in due course
Just, until CFD simulation result is consistent with the dynamic data variation tendency and magnitude of results of wind tunnel, guarantee CFD emulation mode
Engineering reasonability.CFD emulation mode is to the universal method for carrying out aerodynamic characteristics numerical simulation in object in flow field.CFD
Simulation modification method is the engineering method carried out after data Fitting Analysis in conjunction with the true wind tunnel test data of ejector seat.
Step 3: analysis ejector seat simulation analysis demand, by simulation analysis model be determined as model A (seat+bracket),
Totally three kinds of Model B (seat) and MODEL C (seat+fuselage), and design three kinds of simulation models.Three kinds of simulation models are in order to full
The model that foot emulation is needed and can be obtained in engineering, wherein seat+airframe models include ejector seat in different ejections
The case where stroke (different from airframe distance and relative attitude).
Step 4: demand, flying speed needed for determining simulation analysis operating condition, the angle of attack and sideslip are emulated according to ejector seat
The value range at angle, wherein flying speed V=0~1300km/h, angle of attack=0 °~360 °, yaw angle β=0 °~180 °.Again
According to engineering it is practical determine these parameters change step, wherein flying speed press altogether 250km/h, 450km/h, 850km/h,
1000km/h, 1300km/h value；When angle of attack=0 °~90 °, Δ α=10 °, when angle of attack=90 °~270 °, Δ α=20 °,
When angle of attack=270 °~360 °, Δ α=10 °；When yaw angle β=0 °~50 °, Δ β=5 °, when yaw angle β=50 °~90 °,
Δ β=10 °, when yaw angle β=90 °~180 °, Δ β=15 °.The value range of flying speed, the angle of attack and yaw angle, be according to
Not only be able to satisfy emulation demand, but can save computing resource, shorten research cycle principle determine.
Step 5: the CFD emulation mode determined using step 2, the simulation analysis operating condition progress A, B determined by step 4,
The CFD simulation calculation of tri- kinds of models of C forms CFD emulation data of three kinds of simulation models under the determined operating condition of step 4.CFD
Data are emulated, are that tri- kinds of models of A, B, C are combined corresponding to the value range of flying speed, the angle of attack and yaw angle in step 4
Included various operating conditions.
Step 6: regression analysis is carried out to the CFD simulation calculation data of bis- kinds of models of A, B, is obtained from seat+stent model
The middle modification method for deducting support interferences carries out regression analysis to the CFD simulation calculation data of bis- kinds of models of B, C, is present
Increase the modification method of fuselage interference on the basis of chair model.Data regression method is calculated, including refers to linear regression analysis side
Method or non-linear fitting method (alternative manner etc. based on least square method).
Step 7: the modification method for the deduction support interferences that step 6 determines is applied to wind tunnel test data, is detained
Except the wind tunnel test data after support interferences.
Step 8: the modification method for increasing fuselage interference that step 6 is determined is applied to the resulting wind tunnel test of step 7
Data obtain the wind tunnel test data for deducting support interferences and increasing fuselage interference.
Working principle according to figure 1, the present invention devise a kind of airframe and repair to ejector seat aerodynamic interference
Correction method can effectively improve ejector seat motion simulation precision, be conducive to explore ejector seat inherent technology performance, realize with imitative
True means achieve the purpose that ejector seat performance indicator is examined.The present invention is based on the wind tunnel test of ejector seat (no airframes
Interference, there is support interferences) aerodynamic data, it devises and a kind of under airframe disturbed condition its aerodynamic data is modified
Design method, to achieve the purpose that improve ejector seat Multiple Purpose Simulation precision.This method first tries ejector seat wind-tunnel
It tests aerodynamic data to compare and analyze with calculating aerodynamic data obtained by Fluid Mechanics Computation (CFD) method, in due course to the emulation side CFD
Method is modified, it is ensured that the engineering reasonability of CFD emulation mode, it is further according to ejector seat simulation analysis demand that analysis model is true
It is set to three kinds (seat+stent model, seat model, seats+airframe models), and carries out three kinds by the operating condition of simulation analysis demand
CFD simulation calculation under model state finally carries out multivariate data to calculated result of three kinds of models under each emulation operating condition and returns
Return analysis, to obtain airframe to the aerodynamic data correction result under ejector seat (no bracket) disturbed condition.The present invention
It may be directly applied to grinding and newly grinding model ejector seat, ejector seat wind tunnel test conceptual design can either be instructed, and can obtain
To the airframe based on wind tunnel test to ejector seat aerodynamic interference data, ejector seat motion simulation essence can be effectively improved
Degree ensures that the lifesaving of pilot has safely important military significance to ejection escape success rate is improved.The present invention is relative to existing
Ejector seat wind tunnel test data application situation, has on the one hand deducted wind tunnel test bracket to the aerodynamic interference of ejector seat, together
When increase airframe again to the aerodynamic interference of ejector seat, reflect ejector seat wind tunnel test data more accurately
Its aerodynamic characteristics, its working principles are as follows:
The changing rule and data magnitude of wind-tunnel test data under each operating condition of ejector seat are analyzed first, which corresponds to bullet
Seat wind tunnel test time of day is penetrated (not simulate due airframe under practical ejection situation, but contain practical bullet
Penetrate the bracket not having under situation), including pneumatic with six degree of freedom under the operating condition of test of the angle of attack and yaw angle description and corresponding operating condition
Force component.Ejector seat wind tunnel test time of day is can not to simulate practical bullet due to the limitation by wind tunnel test existence conditions
Due airframe under situation is penetrated, but contains playing a supportive role to test model of not having under practical ejection situation always
Bracket.Secondly corresponding CFD emulation is carried out according to the model and operating condition of ejector seat wind tunnel test, and by CFD emulation data with
Wind tunnel test data are compared, the dynamic data variation tendency that each operating condition, each single degree of freedom aerodynamic data are constituted
And magnitude judges CFD emulation data as judgment criteria, and CFD emulation mode is fed back and corrected in due course, until
CFD simulation result is consistent with the dynamic data variation tendency and magnitude of results of wind tunnel, guarantees that the engineering of CFD emulation mode is closed
Rationality.Third analyzes ejector seat simulation analysis demand, simulation analysis model is determined as model A (seat+bracket), Model B
Totally three kinds of (seat) and MODEL C (seat+fuselage), and design three kinds of simulation models.Three kinds of simulation models are imitative in order to meet
The true model that needs and can obtain in engineering, wherein seat+airframe models include ejector seat in different ejection travels
The case where (different from airframe distance and relative attitude).4th, demand is emulated according to ejector seat, determines simulation analysis work
The value range of flying speed needed for condition, the angle of attack and yaw angle, wherein flying speed V=0~1300km/h, angle of attack=0 °
~360 °, yaw angle β=0 °~180 °.Further according to the practical change step for determining these parameters of engineering, wherein flying speed is total
By 250km/h, 450km/h, 850km/h, 1000km/h, 1300km/h value；When angle of attack=0 °~90 °, Δ α=10 ° are attacked
When α=90 °~270 ° of angle, Δ α=20 °, when angle of attack=270 °~360 °, Δ α=10 °；When yaw angle β=0 °~50 °, Δ β
=5 °, when yaw angle β=50 °~90 °, Δ β=10 °, when yaw angle β=90 °~180 °, Δ β=15 °.Flying speed, the angle of attack
It is but also the principle that computing resource can be saved, shorten research cycle according to being not only able to satisfy emulation demand with the value range of yaw angle
Determining.5th, using fixed CFD emulation mode, by the CFD for having determined simulation analysis operating condition progress tri- kinds of models of A, B, C
Simulation calculation forms the CFD emulation data of three kinds of simulation models.6th, to the CFD simulation calculation data of bis- kinds of models of A, B into
Row regression analysis obtains the modification method for deducting support interferences from seat+stent model, emulates to the CFD of bis- kinds of models of B, C
It calculates data and carries out regression analysis, obtain the modification method for increasing fuselage interference on the basis of seat model.Calculate data regression
Analysis method, including referring to linear regression analysis method or non-linear fitting method (alternative manner etc. based on least square method).
7th, the fixed modification method for deducting support interferences is applied to wind tunnel test data, is obtained after deducting support interferences
Wind tunnel test data.8th, the modification method of fixed increase fuselage interference is resulting applied to support interferences have been deducted
Wind tunnel test data obtain the wind tunnel test data for deducting support interferences and increasing fuselage interference.The data reflect ejection
The real motion aerodynamic characteristics of seat.
Claims (8)
1. a kind of airframe is to the modification method of ejector seat aerodynamic interference, which comprises the steps of:
Step 1: the changing rule and data magnitude of wind-tunnel test data, the data correspond to bullet under analysis each operating condition of ejector seat
Seat wind tunnel test real conditions are penetrated, including six degree of freedom gas under the operating condition of test described with the angle of attack and yaw angle and corresponding operating condition
Powertrain components data；
Step 2: corresponding CFD emulation is carried out according to the model of ejector seat wind tunnel test and operating condition, and CFD is emulated into data
It is compared with wind tunnel test data, the dynamic that single degree of freedom aerodynamic data each in each operating condition, six degree of freedom is constituted
Data variation trend and magnitude judge CFD emulation data as judgment criteria, feed back in due course to CFD emulation mode
Guarantee CFD emulation until CFD simulation result is consistent with the dynamic data variation tendency and magnitude of results of wind tunnel with amendment
The engineering reasonability of method；
Step 3: simulation analysis model is determined as model A (seat+bracket), model by analysis ejector seat simulation analysis demand
Totally three kinds of B (seat) and MODEL C (seat+fuselage), and design three kinds of simulation models；
Step 4: emulating demand according to ejector seat, flying speed needed for determining simulation analysis operating condition, the angle of attack and yaw angle
Value range, wherein flying speed V=250km/h~1300km/h, angle of attack=0 °~360 °, yaw angle β=0 °~180 °.
Further according to the practical specific value for determining these parameters of engineering, wherein flying speed presses 250km/h, 450km/h, 850km/ altogether
H, 1000km/h, 1300km/h value；When angle of attack=0 °~90 °, Δ α=10 °, when angle of attack=90 °~270 °, Δ α=
20 °, when angle of attack=270 °~360 °, Δ α=10 °；When yaw angle β=0 °~50 °, Δ β=5 °, yaw angle β=50 °~90 °
When, Δ β=10 °, when yaw angle β=90 °~180 °, Δ β=15 °；
Step 5: the CFD emulation mode determined using step 2 carries out A, B, C tri- by the simulation analysis operating condition that step 4 determines
The CFD simulation calculation of kind model forms CFD emulation data of three kinds of simulation models under operating condition described in step 4；
Step 6: regression analysis is carried out to the CFD simulation calculation data of bis- kinds of models of A, B, obtains buckleing from seat+stent model
Except the modification method of support interferences, regression analysis is carried out to the CFD simulation calculation data of bis- kinds of models of B, C, is obtained in seat mould
Increase the modification method of fuselage interference on the basis of type；
Step 7: the modification method for the deduction support interferences that step 6 determines is applied to wind tunnel test data, obtains deducting branch
Wind tunnel test data after frame interference；
Step 8: the modification method for increasing fuselage interference that step 6 is determined is applied to the resulting wind tunnel test number of step 7
According to, obtain deduct support interferences and increase fuselage interference wind tunnel test data.
2. a kind of airframe according to claim 1 is to the modification method of ejector seat aerodynamic interference, which is characterized in that
Ejector seat wind tunnel test time of day described in step 1 is can not to simulate reality due to the limitation by wind tunnel test existence conditions
Due airframe under border ejection situation, but contain always do not have under the practical ejection situation of ejector seat to test model
The bracket to play a supportive role.
3. a kind of airframe according to claim 1 is to the modification method of ejector seat aerodynamic interference, which is characterized in that
CFD emulation mode described in step 2 is to the peculiar method for carrying out aerodynamic characteristics numerical simulation in object in flow field.
4. a kind of airframe according to claim 1 is to the modification method of ejector seat aerodynamic interference, which is characterized in that
CFD simulation modification method described in step 2 is after combining the true wind tunnel test data of ejector seat to carry out data Fitting Analysis
Engineering method.
5. a kind of airframe according to claim 1 is to the modification method of ejector seat aerodynamic interference, which is characterized in that
Three kinds of models described in step 3 are the models in order to meet emulation needs and can obtain in engineering, wherein seat+fuselage
Model includes ejector seat different ejection travels (different from airframe distance and relative attitude) the case where.
6. a kind of airframe according to claim 1 is to the modification method of ejector seat aerodynamic interference, which is characterized in that
The value range of flying speed, the angle of attack determined by step 4 and yaw angle but also can be saved according to being not only able to satisfy emulation demand
Computing resource, the principle for shortening research cycle determine.
7. a kind of airframe according to claim 1 is to the modification method of ejector seat aerodynamic interference, which is characterized in that
CFD described in step 5 emulates data, is that tri- kinds of models of A, B, C correspond to taking for flying speed in step 4, the angle of attack and yaw angle
Value range is combined included various operating conditions.
8. a kind of airframe according to claim 1 is to the modification method of ejector seat aerodynamic interference, which is characterized in that
Data regression method is calculated described in step 6, including refers to linear regression analysis method or non-linear fitting method (based on most
The alternative manner etc. of small square law).
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