CN110411707A - Series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique - Google Patents
Series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique Download PDFInfo
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- CN110411707A CN110411707A CN201910669217.4A CN201910669217A CN110411707A CN 110411707 A CN110411707 A CN 110411707A CN 201910669217 A CN201910669217 A CN 201910669217A CN 110411707 A CN110411707 A CN 110411707A
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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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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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
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to vehicle technology fields, disclose a kind of series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique.This method comprises: obtaining aircraft unsteady aeroperformance data F1 and aircraft six-degree-of-freedomovement movement data M1 corresponding from the physical separation moment different in booster separation process using Fluid Mechanics Computation method；The unsteady aeroperformance data F2 that unsteady virtual flight calculates the corresponding time of day of acquisition individually is carried out to aircraft according to aircraft six-degree-of-freedomovement movement data M1；Flight Vehicle Stage Separation aerodynamic characteristic interference volume data are determined based on unsteady aeroperformance data F1 and unsteady aeroperformance data F2.Solving the problems, such as ground wind tunnel test as a result, there are all kinds of support interference errors, flight tests to be difficult to obtain interference volume data.
Description
Technical field
The present invention relates to vehicle technology field more particularly to a kind of series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volumes
Prediction technique.
Background technique
In space industry, aircraft/payload is most extensively using cascade with rocket booster/carrier rocket
One of application form, if cascade is widely used in China's "Long March" series of carrier rockets, the astropowers such as American-European Russia remove space flight
Aircraft nearly all uses cascade using parallel form outside.Such as alliance's Launch Vehicle Series, Saturn V, the Soviet Union
N-1 carrier rocket, energy carrier rocket and Proton Carrier Rocket and European Space Agency A Liyana carrier rocket.
Stage separation process is the important parameter of Aircraft Conceptual Design to the interference volume of flight vehicle aerodynamic performance.Currently,
Due to the limitation of experimental technique level, there are all kinds of support interference errors for the interference volume obtained by ground wind tunnel test, and try
It is high to test funds；And rely on flight test also without the precedent for obtaining related data.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, a kind of series connection Flight Vehicle Stage Separation aerodynamic characteristic is provided
Interference volume prediction technique is able to solve the above-mentioned stage separation process that can not accurately obtain in the prior art to flight vehicle aerodynamic performance
Interference volume the problem of.
Technical solution of the invention: a kind of series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique,
In, this method comprises:
Aircraft is obtained using Fluid Mechanics Computation method and the physical separation moment different in booster separation process are corresponding
Unsteady aeroperformance data F1 and aircraft six-degree-of-freedomovement movement data M1；
Unsteady virtual flight individually is carried out to aircraft according to aircraft six-degree-of-freedomovement movement data M1 and calculates acquisition pair
Answer the unsteady aeroperformance data F2 of time of day；
Determine that Flight Vehicle Stage Separation is pneumatic based on unsteady aeroperformance data F1 and unsteady aeroperformance data F2
Characteristic interference volume data.
It is preferably based between unsteady aeroperformance data F1 and unsteady aeroperformance data F2 determines aircraft grade and divides
Include: from aerodynamic characteristic interference volume data
The difference of unsteady aeroperformance data F1 and unsteady aeroperformance data F2 are determined as Flight Vehicle Stage Separation
Aerodynamic characteristic interference volume data.
Preferably, the unsteady aeroperformance data F1 and unsteady aeroperformance data F2 includes lift coefficient
Cy, resistance coefficient Cx, sideway force coefficient Cz, pitching moment coefficient mx, yawing moment coefficient my and rolling moment Coefficient m z.
Preferably, the aircraft six-degree-of-freedomovement movement data M1 includes the displacement data and attitude angle number of aircraft mass center
According to.
Preferably, the attitude angle data includes pitch angle, yaw angle and roll angle.
Through the above technical solutions, can be using the side Fluid Mechanics Computation (Computational Fluid Dynamics)
Method obtains aircraft unsteady aeroperformance data F1 corresponding from the physical separation moment different in booster separation process and flies
Row device six-degree-of-freedomovement movement data M1, and can be individually non-fixed to aircraft progress according to aircraft six-degree-of-freedomovement movement data M1
Normal virtual flight calculates the unsteady aeroperformance data F2 for obtaining corresponding time of day, and then can be based on unsteady pneumatic property
Energy data F1 and unsteady aeroperformance data F2 determines the unsteady aerodynamic characteristic interference volume number of aircraft during the separation process
According to, solve the problems, such as that ground wind tunnel test is difficult to obtain interference volume data there are all kinds of support interference errors, flight test, and
Cost-effectiveness is obvious, is far below ground wind tunnel test.
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 a kind of series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique provided in an embodiment of the present invention
Flow chart.
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 a kind of series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique provided in an embodiment of the present invention
Flow chart.
As shown in Figure 1, the embodiment of the invention provides a kind of predictions of series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume
Method, wherein this method comprises:
S100 obtains aircraft and physical separation moment different in booster separation process using Fluid Mechanics Computation method
Corresponding unsteady aeroperformance data (for example, unsteady six components aeroperformance data) F1 and aircraft six-freedom motion
Data M1；
In this step, acquisition is aircraft and the data in booster separation process, it is contemplated that the movement of booster
Situation.
S102 individually carries out unsteady virtual flight calculating to aircraft according to aircraft six-degree-of-freedomovement movement data M1 and obtains
Take the unsteady aeroperformance data F2 of corresponding time of day；
In this step, the motion process of consideration aircraft is interfered without booster at this time, i.e., does not have booster virtually
The aircraft of interference moves.
Wherein it is possible to determine the characteristics of motion of aircraft according to aircraft six-degree-of-freedomovement movement data M1.
For example, it using positive motion rule constraint, can be determined according to by aircraft six-degree-of-freedomovement movement data M1
Aircraft the characteristics of motion individually to aircraft using unsteady virtual flight calculate, reappear stage separation during aircraft
Entire motion, obtain the unsteady aeroperformance data F2 under corresponding time of day and same movement rule.
S104 determines Flight Vehicle Stage Separation based on unsteady aeroperformance data F1 and unsteady aeroperformance data F2
Aerodynamic characteristic interference volume data.
Through the above technical solutions, can be using the side Fluid Mechanics Computation (Computational Fluid Dynamics)
Method obtains aircraft unsteady aeroperformance data F1 corresponding from the physical separation moment different in booster separation process and flies
Row device six-degree-of-freedomovement movement data M1, and can be individually non-fixed to aircraft progress according to aircraft six-degree-of-freedomovement movement data M1
Normal virtual flight calculates the unsteady aeroperformance data F2 for obtaining corresponding time of day, and then can be based on unsteady pneumatic property
Energy data F1 and unsteady aeroperformance data F2 determines the unsteady aerodynamic characteristic interference volume number of aircraft during the separation process
According to, solve the problems, such as that ground wind tunnel test is difficult to obtain interference volume data there are all kinds of support interference errors, flight test, and
Cost-effectiveness is obvious, is far below ground wind tunnel test.
In addition, the interference volume data that the method for the invention obtains can guarantee flight vehicle aerodynamic at all moment of separation
The corresponding relationship of performance eliminates the numerical error of interpolation introducing.
According to an embodiment of the present invention, true based on unsteady aeroperformance data F1 and unsteady aeroperformance data F2
Determining Flight Vehicle Stage Separation aerodynamic characteristic interference volume data includes:
Its difference is determined as Flight Vehicle Stage Separation aerodynamic characteristic interference volume data.
It is, it is poor by making unsteady aeroperformance data F1 and unsteady aeroperformance data F2, it is flown
Device stage separation aerodynamic characteristic interference volume data.
According to an embodiment of the present invention, the unsteady aeroperformance data F1 and the unsteady aeroperformance data
F2 includes lift coefficient Cy, resistance coefficient Cx, sideway force coefficient Cz, pitching moment coefficient mx, yawing moment coefficient my and rolling
Torque coefficient mz.
For example, can by unsteady aeroperformance data F1 lift coefficient Cy and unsteady aeroperformance data
It is poor that lift coefficient Cy in F2 makees, and obtains Flight Vehicle Stage Separation lift coefficient Cy interference volume.Similarly, can successively be flown
Row device stage separation resistance coefficient Cx interference volume, Flight Vehicle Stage Separation sideway force coefficient Cz interference volume, Flight Vehicle Stage Separation
Pitching moment coefficient mx interference volume, Flight Vehicle Stage Separation yawing moment coefficient my interference volume and Flight Vehicle Stage Separation rolling power
Moment coefficient mz interference volume.
According to an embodiment of the present invention, the aircraft six-degree-of-freedomovement movement data M1 includes the displacement of aircraft mass center
Data and attitude angle data.
According to an embodiment of the present invention, the attitude angle data includes pitch angle, yaw angle and roll angle.
Wherein, the pitch angle, yaw angle and the available corresponding angular speed of roll angle are based on.It can based on displacement data
To obtain corresponding speed.
It is from above-described embodiment as can be seen that pneumatic using series connection Flight Vehicle Stage Separation described in the above embodiment of the present invention
Characteristic interference volume prediction technique, being able to solve ground wind tunnel test acquisition interference volume, there are errors and flight test to be difficult to obtain gas
The problem of dynamic performance interference volume data, and theoretical accuracy is higher, and can reduce cost, has engineering practicability.
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 (5)
1. a kind of series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique, which is characterized in that this method comprises:
Aircraft is obtained using Fluid Mechanics Computation method and the physical separation moment different in booster separation process are corresponding non-
Permanent aeroperformance data F1 and aircraft six-degree-of-freedomovement movement data M1；
Unsteady virtual flight individually is carried out to aircraft according to aircraft six-degree-of-freedomovement movement data M1 and calculates acquisition counterpart
Manage the unsteady aeroperformance data F2 at moment；
Flight Vehicle Stage Separation aerodynamic characteristic is determined based on unsteady aeroperformance data F1 and unsteady aeroperformance data F2
Interference volume data.
2. the method according to claim 1, wherein based on unsteady aeroperformance data F1 and unsteady pneumatic
Performance data F2 determines that Flight Vehicle Stage Separation aerodynamic characteristic interference volume data include:
It is pneumatic that the difference of unsteady aeroperformance data F1 and unsteady aeroperformance data F2 are determined as Flight Vehicle Stage Separation
Characteristic interference volume data.
3. method according to claim 1 or 2, which is characterized in that the unsteady aeroperformance data F1 and described non-
Permanent aeroperformance data F2 includes lift coefficient Cy, resistance coefficient Cx, sideway force coefficient Cz, pitching moment coefficient mx, yaw
Torque coefficient my and rolling moment Coefficient m x.
4. according to the method described in claim 3, it is characterized in that, the aircraft six-degree-of-freedomovement movement data M1 includes flight
The displacement data and attitude angle data of device mass center.
5. according to the method described in claim 4, it is characterized in that, the attitude angle data includes pitch angle, yaw angle and rolling
Corner.
Priority Applications (1)
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| CN201910669217.4A CN110411707B (en) | 2019-07-24 | 2019-07-24 | Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft |
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| CN201910669217.4A CN110411707B (en) | 2019-07-24 | 2019-07-24 | Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112504613A (en) * | 2021-02-03 | 2021-03-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Parallel aircraft interstage separation test method and device and readable storage medium |
| CN112733471A (en) * | 2021-01-11 | 2021-04-30 | 北京临近空间飞行器***工程研究所 | Method for separating two-body unsteady aerodynamic properties |
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