CN110411707B - Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft - Google Patents
Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft Download PDFInfo
- Publication number
- CN110411707B CN110411707B CN201910669217.4A CN201910669217A CN110411707B CN 110411707 B CN110411707 B CN 110411707B CN 201910669217 A CN201910669217 A CN 201910669217A CN 110411707 B CN110411707 B CN 110411707B
- Authority
- CN
- China
- Prior art keywords
- aircraft
- data
- unsteady
- performance data
- aerodynamic performance
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the technical field of aircrafts, and discloses a prediction method for the interference quantity of the interstage separation aerodynamic characteristics of series aircrafts. The method comprises the following steps: acquiring unsteady aerodynamic performance data F1 and six-degree-of-freedom motion data M1 of the aircraft corresponding to different physical separation moments in the separation process of the aircraft and the booster stage by using a computational fluid dynamics method; independently carrying out unsteady virtual flight calculation on the aircraft according to the six-degree-of-freedom motion data M1 of the aircraft to obtain unsteady pneumatic performance data F2 corresponding to the physical moment; and determining the inter-stage separation aerodynamic characteristic interference amount data of the aircraft based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2. Therefore, the problems that various support interference errors exist in a ground wind tunnel test, and interference data are difficult to obtain in a flight test are solved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a method for predicting the interference quantity of the interstage separation aerodynamic characteristics of series aircrafts.
Background
In the field of aerospace, the serial connection form of an aircraft/payload and a rocket booster/carrier rocket is one of the most extensive application forms, for example, the serial connection form is widely adopted by long-term carrier rockets in China, and the serial connection form is almost used in strong aerospace countries such as Europe, America and Russia except that space shuttles adopt the parallel connection form. Such as a alliance series carrier rocket, a saturn carrier rocket No. 5, a soviet N-1 carrier rocket, an energy carrier rocket, and a proton carrier rocket, and an airbus alayan carrier rocket.
The amount of interference that the interstage separation process interferes with the aerodynamic performance of the aircraft is an important parameter in the overall design of the aircraft. At present, due to the limitation of the test technical level, various support interference errors exist in the interference amount obtained by the ground wind tunnel test, and the test cost is high; and there is no precedent for obtaining relevant data by means of flight tests.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides a method for predicting the aerodynamic characteristic interference quantity of the series aircraft interstage separation, and can solve the problem that the aerodynamic performance interference quantity of the aircraft in the interstage separation process cannot be accurately obtained in the prior art.
The technical solution of the invention is as follows: a method for predicting the aerodynamic characteristic interference amount of interstage separation of series connection aircrafts, wherein the method comprises the following steps:
acquiring unsteady aerodynamic performance data F1 and six-degree-of-freedom motion data M1 of the aircraft corresponding to different physical separation moments in the separation process of the aircraft and the booster stage by using a computational fluid dynamics method;
independently carrying out unsteady virtual flight calculation on the aircraft according to the six-degree-of-freedom motion data M1 of the aircraft to obtain unsteady pneumatic performance data F2 corresponding to the physical moment;
and determining the inter-stage separation aerodynamic characteristic interference amount data of the aircraft based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2.
Preferably, the determining the aircraft interstage separation aerodynamic characteristic interference amount data based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 comprises:
and determining the difference between the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 as the interference quantity data of the interstage separation aerodynamic characteristics of the aircraft.
Preferably, the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 include a lift coefficient Cy, a drag coefficient Cx, a lateral force coefficient Cz, a pitch moment coefficient mx, a yaw moment coefficient my, and a roll moment coefficient mz.
Preferably, the six-degree-of-freedom motion data M1 of the aircraft comprises displacement data and attitude angle data of the center of mass of the aircraft.
Preferably, the attitude angle data includes a pitch angle, a yaw angle and a roll angle.
By the technical scheme, unsteady aerodynamic performance data F1 and six-degree-of-freedom movement data M1 corresponding to different physical separation moments in the separation process of the aircraft and the boosting stage can be obtained by adopting a Computational Fluid Dynamics (Computational Fluid Dynamics) method, unsteady aerodynamic performance data F2 corresponding to the physical moments can be obtained by performing unsteady virtual flight calculation on the aircraft according to the six-degree-of-freedom movement data M1 of the aircraft, unsteady aerodynamic characteristic interference quantity data of the aircraft in the separation process can be further determined based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2, the problems that various support interference errors exist in a ground wind tunnel test and the interference quantity data are difficult to obtain in a flight test are solved, and the cost benefit is obvious and far lower than that of the ground wind tunnel test.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a flowchart of a method for predicting an interference amount of an interstage separation aerodynamic characteristic of a series aircraft according to an embodiment of the present invention.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the device structures and/or processing steps that are closely related to the scheme according to the present invention are shown in the drawings, and other details that are not so relevant to the present invention are omitted.
Fig. 1 is a flowchart of a method for predicting an interference amount of an interstage separation aerodynamic characteristic of a series aircraft according to an embodiment of the present invention.
As shown in fig. 1, an embodiment of the present invention provides a method for predicting an amount of disturbance of aerodynamic characteristics of interstage separation of series-connected aircraft, where the method includes:
s100, acquiring unsteady pneumatic performance data (for example, unsteady six-component pneumatic performance data) F1 and six-degree-of-freedom motion data M1 corresponding to different physical separation moments in the process of separating the aircraft from the boosting stage by using a computational fluid dynamics method;
in this step, data is acquired during separation of the aircraft from the booster stage, taking into account the motion of the booster stage.
S102, independently carrying out unsteady virtual flight calculation on the aircraft according to the six-degree-of-freedom motion data M1 of the aircraft to obtain unsteady pneumatic performance data F2 corresponding to the physical moment;
in this step, only the course of the movement of the aircraft is taken into account, in which case there is no booster-level disturbance, i.e. the movement of the aircraft virtually without booster-level disturbance.
Wherein, the motion rule of the aircraft can be determined according to the six-degree-of-freedom motion data M1 of the aircraft.
For example, by using the constraint of the forced motion law, unsteady virtual flight calculation can be independently performed on the aircraft according to the motion law of the aircraft determined by the six-degree-of-freedom motion data M1 of the aircraft, the complete motion of the aircraft in the inter-stage separation process is reproduced, and unsteady aerodynamic performance data F2 corresponding to the physical moment and under the same motion law is acquired.
And S104, determining the inter-stage separation aerodynamic characteristic interference amount data of the aircraft based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2.
By the technical scheme, unsteady aerodynamic performance data F1 and six-degree-of-freedom movement data M1 corresponding to different physical separation moments in the separation process of the aircraft and the boosting stage can be obtained by adopting a Computational Fluid Dynamics (Computational Fluid Dynamics) method, unsteady aerodynamic performance data F2 corresponding to the physical moments can be obtained by performing unsteady virtual flight calculation on the aircraft according to the six-degree-of-freedom movement data M1 of the aircraft, unsteady aerodynamic characteristic interference quantity data of the aircraft in the separation process can be further determined based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2, the problems that various support interference errors exist in a ground wind tunnel test and the interference quantity data are difficult to obtain in a flight test are solved, and the cost benefit is obvious and far lower than that of the ground wind tunnel test.
In addition, the interference data obtained by the method can ensure the corresponding relation of the aerodynamic performance of the aircraft at all separated moments, and numerical errors introduced by interpolation are eliminated.
According to one embodiment of the invention, the determining the inter-stage separation aerodynamic characteristic disturbance variable data of the aircraft based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 comprises:
and determining the difference as the interference data of the inter-stage separation aerodynamic characteristics of the aircraft.
That is, the data of the disturbance variable of the inter-stage separation aerodynamic characteristics of the aircraft are obtained by subtracting the unsteady aerodynamic performance data F1 from the unsteady aerodynamic performance data F2.
According to an embodiment of the invention, the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 include a lift coefficient Cy, a drag coefficient Cx, a lateral force coefficient Cz, a pitch moment coefficient mx, a yaw moment coefficient my, and a roll moment coefficient mz.
For example, the interference amount of the inter-stage separation lift coefficient Cy of the aircraft can be obtained by subtracting the lift coefficient Cy in the unsteady aerodynamic performance data F1 from the lift coefficient Cy in the unsteady aerodynamic performance data F2. Similarly, the disturbance quantity of the aircraft interstage separation resistance coefficient Cx, the disturbance quantity of the aircraft interstage separation lateral force coefficient Cz, the disturbance quantity of the aircraft interstage separation pitch moment coefficient mx, the disturbance quantity of the aircraft interstage separation yaw moment coefficient my and the disturbance quantity of the aircraft interstage separation roll moment coefficient mz can be obtained in sequence.
According to one embodiment of the invention, the aircraft six-degree-of-freedom motion data M1 includes displacement data and attitude angle data for the aircraft center of mass.
According to one embodiment of the invention, the attitude angle data includes a pitch angle, a yaw angle, and a roll angle.
Wherein the corresponding angular velocity can be obtained based on the pitch angle, yaw angle and roll angle. Based on the displacement data, a corresponding velocity can be derived.
The embodiment shows that the method for predicting the inter-stage separation aerodynamic characteristic interference quantity of the series aircraft can solve the problems that errors exist in the interference quantity obtained by a ground wind tunnel test and aerodynamic performance interference quantity data are difficult to obtain by a flight test, has higher theoretical accuracy, can reduce cost and has engineering practicability.
Features that are described and/or illustrated above with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein, is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
The above methods of the present invention may be implemented by hardware, or may be implemented by hardware in combination with software. The present invention relates to a computer-readable program which, when executed by a logic section, enables the logic section to realize the above-described apparatus or constituent section, or to realize the above-described various methods or steps. The present invention also relates to a storage medium such as a hard disk, a magnetic disk, an optical disk, a DVD, a flash memory, or the like, for storing the above program.
The many features and advantages of these embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of these embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope thereof.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (4)
1. A method for predicting the aerodynamic characteristic interference quantity of interstage separation of series aircraft is characterized by comprising the following steps:
acquiring unsteady aerodynamic performance data F1 and six-degree-of-freedom motion data M1 of the aircraft corresponding to different physical separation moments in the separation process of the aircraft and the booster stage by using a computational fluid dynamics method;
independently carrying out unsteady virtual flight calculation on the aircraft according to the six-degree-of-freedom motion data M1 of the aircraft to obtain unsteady pneumatic performance data F2 corresponding to the physical moment;
determining the inter-stage separation aerodynamic characteristic interference amount data of the aircraft based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2,
wherein the determining of the inter-stage separation aerodynamic characteristic disturbance variable data of the aircraft based on the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 comprises:
and determining the difference between the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 as the interference quantity data of the interstage separation aerodynamic characteristics of the aircraft.
2. The method of claim 1, wherein the unsteady aerodynamic performance data F1 and the unsteady aerodynamic performance data F2 include lift coefficients Cy, drag coefficients Cx, lateral force coefficients Cz, pitch moment coefficients mx, yaw moment coefficients my, and roll moment coefficients mx.
3. The method of claim 2, wherein the aircraft six degree of freedom motion data M1 includes displacement data and attitude angle data for the aircraft center of mass.
4. The method of claim 3, wherein the attitude angle data includes pitch angle, yaw angle, and roll angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910669217.4A CN110411707B (en) | 2019-07-24 | 2019-07-24 | Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910669217.4A CN110411707B (en) | 2019-07-24 | 2019-07-24 | Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110411707A CN110411707A (en) | 2019-11-05 |
| CN110411707B true CN110411707B (en) | 2021-02-05 |
Family
ID=68362752
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910669217.4A Active CN110411707B (en) | 2019-07-24 | 2019-07-24 | Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110411707B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112733471B (en) * | 2021-01-11 | 2023-08-29 | 北京临近空间飞行器***工程研究所 | Method for separating two-body unsteady aerodynamic properties |
| CN112504613B (en) * | 2021-02-03 | 2021-05-28 | 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 |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4698997A (en) * | 1985-03-14 | 1987-10-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Oscillation pressure device for dynamic calibration of pressure transducers |
| CN101915655A (en) * | 2010-07-15 | 2010-12-15 | 吉林大学 | Method for subtracting aerodynamic interference of model support in automotive wind tunnel based on tests and emulation |
| CN102012953A (en) * | 2010-11-04 | 2011-04-13 | 西北工业大学 | CFD (computational fluid dynamics)/CSD (circuit switch data) coupled solving nonlinear aeroelasticity simulation method |
| CN105975658A (en) * | 2016-04-27 | 2016-09-28 | 北京空间飞行器总体设计部 | Takeoff stability modeling method |
| CN107391858A (en) * | 2017-07-27 | 2017-11-24 | 空气动力学国家重点实验室 | A kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount |
| CN107480347A (en) * | 2017-07-24 | 2017-12-15 | 湖北航天技术研究院总体设计所 | A kind of chorista dispersion characteristic predicting method |
| CN109250149A (en) * | 2018-09-26 | 2019-01-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation |
| CN110057537A (en) * | 2019-04-12 | 2019-07-26 | 北京空天技术研究所 | Flight vehicle aerodynamic performance influences prediction technique |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107782526B (en) * | 2017-11-07 | 2019-05-24 | 中国航天空气动力技术研究院 | Mass center is located at separation free flight flow tunnel testing device between the parallel level at interface |
-
2019
- 2019-07-24 CN CN201910669217.4A patent/CN110411707B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4698997A (en) * | 1985-03-14 | 1987-10-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Oscillation pressure device for dynamic calibration of pressure transducers |
| CN101915655A (en) * | 2010-07-15 | 2010-12-15 | 吉林大学 | Method for subtracting aerodynamic interference of model support in automotive wind tunnel based on tests and emulation |
| CN102012953A (en) * | 2010-11-04 | 2011-04-13 | 西北工业大学 | CFD (computational fluid dynamics)/CSD (circuit switch data) coupled solving nonlinear aeroelasticity simulation method |
| CN105975658A (en) * | 2016-04-27 | 2016-09-28 | 北京空间飞行器总体设计部 | Takeoff stability modeling method |
| CN107480347A (en) * | 2017-07-24 | 2017-12-15 | 湖北航天技术研究院总体设计所 | A kind of chorista dispersion characteristic predicting method |
| CN107391858A (en) * | 2017-07-27 | 2017-11-24 | 空气动力学国家重点实验室 | A kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount |
| CN109250149A (en) * | 2018-09-26 | 2019-01-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation |
| CN110057537A (en) * | 2019-04-12 | 2019-07-26 | 北京空天技术研究所 | Flight vehicle aerodynamic performance influences prediction technique |
Non-Patent Citations (4)
| Title |
|---|
| The interference aerodynamics caused by the wing elasticity during store separation;Yang Lei等;《Acta Astronautica》;20160531;116-129 * |
| 火箭级间分离过程流场数值模拟;李超等;《宇航总体技术》;20170331;第1卷(第1期);49-53 * |
| 非对称飞行器级间分离时喷流干扰特性试验研究;罗金玲等;《实验流体力学》;20081231;第22卷(第4期);15-18 * |
| 高超声速飞行器级间分离非定常数值研究;郭庆阳;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20150115(第01期);C031-270 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110411707A (en) | 2019-11-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110411707B (en) | Method for predicting aerodynamic characteristic interference quantity of interstage separation of series aircraft | |
| CN110610065A (en) | Aircraft multi-body separation CFD simulation method and system based on hybrid dynamic grid technology | |
| Takizawa et al. | Fluid–structure interaction modeling of clusters of spacecraft parachutes with modified geometric porosity | |
| CN110794864B (en) | Aircraft stability control method based on attitude angle rate and attack angle measurement | |
| CN110398340A (en) | The simplified wind tunnel test parameter determination method of the class wind tunnel free flight test law of similitude is separated based on launching | |
| CN109540459B (en) | Pneumatic characteristic numerical calculation result correction method | |
| CN109634306B (en) | Aircraft control parameter determination method and device | |
| CN111964862A (en) | Similar wind tunnel test method for separation dynamics of machine and projectile | |
| CN104931250A (en) | High-lift system whole-aircraft loading dynamic test method | |
| CN107831653B (en) | Hypersonic aircraft instruction tracking control method for inhibiting parameter perturbation | |
| CN110057537B (en) | Aircraft aerodynamic performance influence prediction method | |
| CN111158391A (en) | Control surface control method based on discrete system direct control distribution | |
| CN112307683A (en) | Rocket lateral jet interference determination method, terminal and storage medium | |
| CN110850715A (en) | Anti-interference control method of singular perturbation system | |
| CN110069842B (en) | Quick estimation method for rudder efficiency | |
| CN115145300B (en) | Carrier rocket attitude control method and related equipment | |
| CN106919747B (en) | Prediction method for pressure in aircraft cabin | |
| CN114528692A (en) | Reusable rocket landing stage feasible region calculation method based on numerical optimization | |
| CN106802226B (en) | position error compensation method caused by length change of tail strut of decoupling six-degree-of-freedom mechanism | |
| CN105160084A (en) | Ejection escape simulation method | |
| CN105588568B (en) | Rocket launching unpowered flight section trajectory extrapolation and filter value method | |
| Wartmann et al. | Identification and selection of rotorcraft candidate models to predict handling qualities and dynamic stability | |
| CN112270046B (en) | Separation track simulation method for air inlet channel protective cover | |
| CN109612675B (en) | Ground test method for verifying stability of full-bomb servo aeroelastic | |
| CN112989497B (en) | Tight branch radial basis function data transfer method based on geometric space main feature extraction |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |