CN110057537A - Flight vehicle aerodynamic performance influences prediction technique - Google Patents
Flight vehicle aerodynamic performance influences prediction technique Download PDFInfo
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- CN110057537A CN110057537A CN201910292074.XA CN201910292074A CN110057537A CN 110057537 A CN110057537 A CN 110057537A CN 201910292074 A CN201910292074 A CN 201910292074A CN 110057537 A CN110057537 A CN 110057537A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Abstract
The present invention relates to flight vehicle aerodynamic performance technologies fields, disclose a kind of flight vehicle aerodynamic performance influence prediction technique.This method comprises: determining the initial flight device test model for meeting wind tunnel test requirement；The basic aerodynamic data of the model is obtained by wind tunnel test；The range of Mach numbers of generation air intake duct state change is predicted using numerical computation method；In the range of Mach numbers, air intake duct state of the aircraft test model after inlet throat module is substituted under different Mach number is obtained；Obtain the corresponding flight vehicle aerodynamic force data of air intake duct state under each Mach number；Flight vehicle aerodynamic performance influence amount is determined with the basic aerodynamic data under identical Mach number based on the corresponding flight vehicle aerodynamic force data of air intake duct state under each Mach number.Solve as a result, current existing method due to cannot completely in simulated flight trajectory state and lead to not obtain air intake duct different conditions to this crucial problem of effect of aerodynamic performance.
Description
Technical field
The present invention relates to flight vehicle aerodynamic performance technologies fields more particularly to a kind of flight vehicle aerodynamic performance to influence prediction side
Method.
Background technique
For airbreather, the main effect of air intake duct is capture incoming flow and compresses to it, to start
The other assemblies (such as combustion chamber) of machine provide compressed air.Generally, it is considered that if the traffic capture characteristic of air intake duct is not because inside it
The change of fluidised form and be affected, claim air intake duct be in starting state, be otherwise inoperative state.
In aircraft climb section, as free stream Mach number gradually increases, air intake duct can undergo never starting state to start
The change procedure of state, this process are known as the self-starting of air intake duct.In aircraft cruise section, air intake duct is the case where starting
Under, in fact it could happen that fortuitous event (such as engine oil adjust improper cause that chamber pressure is excessively high, flight attitude angle is excessive),
Cause air intake duct to change to inoperative state from starting state, at this moment needs to study whether air intake duct has self-running energy again
Power, therefore air intake duct is possible to experience and restarts process from starting is -> inoperative ->, restart if can not achieve, engine will
It cannot continue to work normally.In the descending branch of aircraft, flight Mach number can be gradually decreased, and air intake duct can be undergone from starting to not
Starting process.The state change in this stage is opposite with section state change of climbing.Wherein, in section of climbing, air intake duct is from inoperative
Variation of the state to starting state；In descending branch, air intake duct can change to inoperative state from starting state；The two processes are
Necessarily occur.And in cruise section, the case where inoperative state that air intake duct occurs, is relatively fewer.
Since the stagnation pressure of wind tunnel test is subject to certain restrictions, ground experiment can not completely simulated flight device along trajectory shape
State, therefore it is difficult the critical point for accurately predicting that air intake duct changes in climb section and descending branch generating state by ground experiment, than
Such as, ground experiment prediction air intake duct realizes self-starting (never starting state becomes starting state) in Ma3.5 state, and examination of flying
It tests the result shows that air intake duct just realizes self-starting in Ma4.Existing result of study shows that air intake duct state change can be to pneumatic
The influence that performance generates, and changing in different trajectory point generating states also can be different to the influence amount of aeroperformance.Therefore such as
Fruit can not Accurate Prediction air intake duct generating state variation critical point cannot Accurate Prediction flight vehicle aerodynamic performance.However, existing
There is the method in technology to be still unable to trajectory state in simulated flight, leads to not obtain air intake duct different conditions to aeroperformance shadow
It rings.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, a kind of flight vehicle aerodynamic performance influence prediction side is provided
Method is able to solve above-mentioned the problems of the prior art.
A kind of technical solution of the invention: flight vehicle aerodynamic performance influence prediction technique, wherein this method comprises:
Determine the initial flight device test model for meeting wind tunnel test requirement；
The basic aerodynamic data of the model is obtained by wind tunnel test；
The range of Mach numbers of generation air intake duct state change is predicted using numerical computation method；
In the range of Mach numbers, the aircraft test model after inlet throat module is substituted is obtained in different horses
It is conspicuous it is several under air intake duct state；
Obtain the corresponding flight vehicle aerodynamic force data of air intake duct state under each Mach number；
Based on the corresponding flight vehicle aerodynamic force data of air intake duct state and the base under identical Mach number under each Mach number
Plinth aerodynamic data determines flight vehicle aerodynamic performance influence amount.
Preferably, in the range of Mach numbers, the aircraft test model after inlet throat module is substituted in acquisition
Air intake duct state under different Mach number includes:
Under the different Mach number in the range of Mach numbers, respectively to the aircraft after inlet throat module is substituted
The venturi wall pressure of test model is detected；
The air intake duct state under corresponding Mach number is determined based on the venturi wall pressure detected respectively.
Preferably, in the range of Mach numbers, the aircraft test model after inlet throat module is substituted in acquisition
Air intake duct state under different Mach number includes:
Under the different Mach number in the range of Mach numbers, inlet throat is substituted by the acquisition of wind-tunnel schlieren image
The inlet duct flow field characteristic of aircraft test model after module；
The air intake duct state under corresponding Mach number is determined based on the flow field characteristic.
The corresponding flight vehicle aerodynamic force data of the air intake duct state being preferably based under each Mach number and identical Mach number
Under basic aerodynamic data determine flight vehicle aerodynamic performance influence amount:
By the corresponding flight vehicle aerodynamic force data of air intake duct state and the basis under identical Mach number under each Mach number
The difference of aerodynamic data is determined as flight vehicle aerodynamic performance influence amount.
Preferably, air intake duct state includes intake duct starting state and the inoperative state of air intake duct.
Preferably, the range of Mach numbers is 3Ma~4.5Ma.
Through the above technical solutions, can first determine initial analysis device test model and obtain basic aerodynamic data, so
It can use the range of Mach numbers that air intake duct state change occurs for numerical computation method prediction afterwards, obtain and replace in range of Mach numbers
Air intake duct state of the aircraft test model under different Mach number after having changed inlet throat module, and obtain each Mach
The corresponding flight vehicle aerodynamic force data of air intake duct state under several, and then can be based on the air intake duct state pair under each Mach number
The flight vehicle aerodynamic force data answered obtains air intake duct state change to pneumatic property with the basic aerodynamic data under identical Mach number
The influence amount of energy, so as to improve the precision of ground prediction aeroperformance data conscientiously.Method of the present invention can as a result,
With solve current existing method due to cannot completely in simulated flight trajectory state and lead to not obtain air intake duct different conditions
To this crucial problem of effect of aerodynamic performance.
Detailed description of the invention
Included attached drawing is used to provide to be further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together to illustrate the principle of the present invention with verbal description.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, be also possible to obtain other drawings based on these drawings.
Fig. 1 is the flow chart that a kind of flight vehicle aerodynamic performance provided in an embodiment of the present invention influences prediction technique；
Fig. 2A and 2B be respectively in the embodiment of the present invention under different Mach number aircraft resistance with angle of attack variation schematic diagram；
Fig. 3 A and 3B be respectively in the embodiment of the present invention under different Mach number aircraft lift with angle of attack variation schematic diagram；
Fig. 4 A and 4B are respectively aircraft pitching moment showing with angle of attack variation under different Mach number in the embodiment of the present invention
It is intended to.
Specific embodiment
Specific embodiments of the present invention are described in detail below in conjunction with attached drawing.In the following description, for solution
Purpose and not restrictive is released, elaborates detail, to help to be apparent from the present invention.However, to those skilled in the art
It is readily apparent that the present invention can also be practiced in the other embodiments departing from these details for member.
It should be noted that only showing in the accompanying drawings in order to avoid having obscured the present invention because of unnecessary details
Gone out with closely related device structure and/or processing step according to the solution of the present invention, and be omitted with relationship of the present invention not
Big other details.
Fig. 1 is the flow chart that a kind of flight vehicle aerodynamic performance provided in an embodiment of the present invention influences prediction technique.
As shown in Figure 1, the embodiment of the invention provides a kind of flight vehicle aerodynamic performances to influence prediction technique, wherein the party
Method includes:
S100 determines the initial flight device test model for meeting wind tunnel test requirement；
For example, it can be based on existing testing equipment, design determines that meets the initial winged of wind tunnel test requirement
Row device test model.
S102 obtains the basic aerodynamic data of the model by wind tunnel test；
It is, the aeroperformance data of the model can be obtained by wind tunnel test, using the data as aircraft gas
The basic data of dynamic performance.
S104 predicts the range of Mach numbers that air intake duct state change occurs using numerical computation method；
S106 obtains the aircraft test model after inlet throat module is substituted and exists in the range of Mach numbers
Air intake duct state under different Mach number；
It is, can be replaced with inlet throat of the inlet throat replacement module to initial flight device test model
It changes, thus obtains the aircraft test different from the inlet throat module of initial flight device test model of inlet throat module
Model.
For example, the inlet throat without absorbing hole of initial flight device test model can be replaced with to have and inhaled
Except the inlet throat in hole (for example, by there is the inlet throat module for absorbing hole to obtain the starting state of air intake duct, passes through nothing
The inlet throat module for absorbing hole obtains the inoperative state of air intake duct)；Alternatively, can be by suitably adjusting air intake duct larynx
Road size, respectively obtain air intake duct starting and inoperative two states.
S108 obtains the corresponding flight vehicle aerodynamic force data of air intake duct state under each Mach number；
For example, the aeroperformance under air intake duct different conditions is obtained by wind tunnel test.
S110, based under each Mach number the corresponding flight vehicle aerodynamic force data of air intake duct state under identical Mach number
Basic aerodynamic data determine flight vehicle aerodynamic performance influence amount.
Through the above technical solutions, can first determine initial analysis device test model and obtain basic aerodynamic data, so
It can use the range of Mach numbers that air intake duct state change occurs for numerical computation method prediction afterwards, obtain and replace in range of Mach numbers
Air intake duct state of the aircraft test model under different Mach number after having changed inlet throat module, and obtain each Mach
The corresponding flight vehicle aerodynamic force data of air intake duct state under several, and then can be based on the air intake duct state pair under each Mach number
The flight vehicle aerodynamic force data answered obtains air intake duct state change to pneumatic property with the basic aerodynamic data under identical Mach number
The influence amount of energy, so as to improve the precision of ground prediction aeroperformance data conscientiously.Method of the present invention can as a result,
With solve current existing method due to cannot completely in simulated flight trajectory state and lead to not obtain air intake duct different conditions
To this crucial problem of effect of aerodynamic performance.
According to an embodiment of the present invention, in the range of Mach numbers, after inlet throat module is substituted in acquisition
Air intake duct state of the aircraft test model under different Mach number include:
Under the different Mach number in the range of Mach numbers, respectively to the aircraft after inlet throat module is substituted
The venturi wall pressure of test model is detected；
The air intake duct state under corresponding Mach number is determined based on the venturi wall pressure detected respectively.
It is, can determine the state of air intake duct according to venturi wall pressure.
According to an embodiment of the present invention, in the range of Mach numbers, after inlet throat module is substituted in acquisition
Air intake duct state of the aircraft test model under different Mach number include:
Under the different Mach number in the range of Mach numbers, inlet throat is substituted by the acquisition of wind-tunnel schlieren image
The inlet duct flow field characteristic of aircraft test model after module；
The air intake duct state under corresponding Mach number is determined based on the flow field characteristic.
It is, can determine the state of air intake duct according to wind-tunnel schlieren image in wind tunnel test.
According to an embodiment of the present invention, based on the corresponding flight vehicle aerodynamic power number of air intake duct state under each Mach number
Flight vehicle aerodynamic performance influence amount is determined according to the basic aerodynamic data under identical Mach number:
By the corresponding flight vehicle aerodynamic force data of air intake duct state and the basis under identical Mach number under each Mach number
The difference of aerodynamic data is determined as flight vehicle aerodynamic performance influence amount.
According to an embodiment of the present invention, air intake duct state includes intake duct starting state and the inoperative state of air intake duct.
According to an embodiment of the present invention, the range of Mach numbers is 3Ma~4.5Ma.
It will be appreciated by those skilled in the art that above-mentioned range of Mach numbers is only exemplary, it is not intended to limit this
Invention.
Fig. 2 to Fig. 4 shows initial flight device test model and replaced aircraft test model in different Mach number
The variation schematic diagram of lower flight vehicle aerodynamic force data.Specifically:
In Fig. 2 into Fig. 4, initial flight device test model is for non-porous venturi；Replaced aircraft test
Model is for having hole venturi.
Fig. 2A and 2B be respectively in the embodiment of the present invention under different Mach number aircraft resistance with angle of attack variation schematic diagram.
In fig. 2a, it shows initial flight device test model and replaced aircraft test model are in Mach 2 ship 4
When aircraft resistance (cx) change with angle of attack.
In fig. 2b, initial flight device test model and replaced aircraft test model are shown in Mach 2 ship
Aircraft resistance (cx) changes with angle of attack when 3.5.
Fig. 3 A and 3B be respectively in the embodiment of the present invention under different Mach number aircraft lift with angle of attack variation schematic diagram；
In figure 3 a, initial flight device test model and replaced aircraft test model are shown in Mach 2 ship 4
When aircraft lift (cy) change with angle of attack.
In figure 3b, initial flight device test model and replaced aircraft test model are shown in Mach 2 ship
Aircraft lift (cy) changes with angle of attack when 3.5.
Fig. 4 A and 4B are respectively aircraft pitching moment showing with angle of attack variation under different Mach number in the embodiment of the present invention
It is intended to.
In Figure 4 A, initial flight device test model and replaced aircraft test model are shown in Mach 2 ship 4
When aircraft pitching moment (mz) change with angle of attack.
In figure 4b, initial flight device test model and replaced aircraft test model are shown in Mach 2 ship
Aircraft pitching moment (mz) changes with angle of attack when 3.5.
From above-described embodiment as can be seen that air intake duct different conditions are to aeroperformance shadow described in the above embodiment of the present invention
The ground prediction aeroperformance precision of interior outflow coupling aircraft can be improved in loud prediction technique, has reached desired effect.
As above it describes for a kind of embodiment and/or the feature that shows can be in a manner of same or similar at one or more
It is used in a number of other embodiments, and/or combines or substitute the feature in other embodiments with the feature in other embodiments
It uses.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when using herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step, component or combinations thereof.
The method more than present invention can be by hardware realization, can also be by combination of hardware software realization.The present invention relates to this
The computer-readable program of sample can be such that the logical block realizes described above when the program is performed by logical block
Device or component parts, or the logical block is made to realize various method or steps described above.The invention further relates to for depositing
Store up the storage medium of procedure above, such as hard disk, disk, CD, DVD, flash memory.
The many features and advantage of these embodiments are clear according to the detailed description, therefore appended claims are intended to
Cover all these feature and advantage of these embodiments fallen into its true spirit and range.Further, since this field
Technical staff is readily apparent that many modifications and changes, therefore is not meant to for the embodiment of the present invention to be limited to illustrated and description essence
Really structurally and operationally, but all suitable modifications and the equivalent fallen within the scope of its can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (6)
1. a kind of flight vehicle aerodynamic performance influences prediction technique, which is characterized in that this method comprises:
Determine the initial flight device test model for meeting wind tunnel test requirement；
The basic aerodynamic data of the model is obtained by wind tunnel test；
The range of Mach numbers of generation air intake duct state change is predicted using numerical computation method；
In the range of Mach numbers, the aircraft test model after inlet throat module is substituted is obtained in different Mach number
Under air intake duct state；
Obtain the corresponding flight vehicle aerodynamic force data of air intake duct state under each Mach number；
Based on the corresponding flight vehicle aerodynamic force data of air intake duct state and the basic gas under identical Mach number under each Mach number
Dynamic date determines flight vehicle aerodynamic performance influence amount.
2. the method according to claim 1, wherein air intake duct is substituted in acquisition in the range of Mach numbers
Air intake duct state of the aircraft test model under different Mach number after venturi module include:
Under the different Mach number in the range of Mach numbers, test respectively to the aircraft after inlet throat module is substituted
The venturi wall pressure of model is detected；
The air intake duct state under corresponding Mach number is determined based on the venturi wall pressure detected respectively.
3. the method according to claim 1, wherein air intake duct is substituted in acquisition in the range of Mach numbers
Air intake duct state of the aircraft test model under different Mach number after venturi module include:
Under the different Mach number in the range of Mach numbers, inlet throat module is substituted by the acquisition of wind-tunnel schlieren image
The inlet duct flow field characteristic of aircraft test model afterwards；
The air intake duct state under corresponding Mach number is determined based on the flow field characteristic.
4. the method according to claim 1, wherein corresponding winged based on the air intake duct state under each Mach number
Row device aerodynamic data determines flight vehicle aerodynamic performance influence amount with the basic aerodynamic data under identical Mach number:
The corresponding flight vehicle aerodynamic force data of air intake duct state under each Mach number and the basis under identical Mach number is pneumatic
The difference of force data is determined as flight vehicle aerodynamic performance influence amount.
5. the method according to claim 1, wherein air intake duct state includes intake duct starting state and air intake duct
Inoperative state.
6. the method according to claim 1, wherein the range of Mach numbers is 3Ma~4.5Ma.
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| CN110411707A (en) * | 2019-07-24 | 2019-11-05 | 北京空天技术研究所 | Series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique |
| CN112964450A (en) * | 2021-02-07 | 2021-06-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for predicting trajectory of wind tunnel multi-body separation test model |
| CN115371933A (en) * | 2022-10-24 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Method for testing aerodynamic coupling between air inlet channel and aircraft forebody |
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