CN114906343A - Belly flap design method suitable for flat fusion layout aircraft - Google Patents
Belly flap design method suitable for flat fusion layout aircraft Download PDFInfo
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- CN114906343A CN114906343A CN202210838998.7A CN202210838998A CN114906343A CN 114906343 A CN114906343 A CN 114906343A CN 202210838998 A CN202210838998 A CN 202210838998A CN 114906343 A CN114906343 A CN 114906343A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a belly flap design method suitable for a flat fusion layout aircraft, which relates to the technical field of aerodynamic design of aircraft and is technically characterized in that: the method comprises the following steps: s1, setting initial parameters of the belly flap; s2, establishing a aerodynamic force evaluation method; s3, setting the installation position, width, height and deflection angle restriction range of the belly flap; s4, carrying out parametric selection on the width and height of the belly flap; s5, carrying out parametric selection on the chord-direction installation position of the belly flap; s6, carrying out parametric selection on the deflection angle of the belly flap; and S7, designing and processing a wind tunnel model, performing a wind tunnel test, and confirming the belly flap scheme. The method can conveniently and accurately research the relation between the parameters of the belly flap and the aerodynamic characteristics of the flat fusion layout aircraft, so that the belly flap which has a good lift-increasing effect and has small influence on the moment characteristics and is suitable for the flat fusion layout aircraft can be designed.
Description
Technical Field
The invention relates to the technical field of aerodynamic design of aircrafts, in particular to a belly flap design method suitable for an aircraft with a flat fusion layout.
Background
The flat fusion body layout aircraft has the advantages of good appearance stealth performance, small resistance, high lift-drag ratio, high structural efficiency and the like, and is an ideal form of the future aircraft. However, the flat fusion layout aircraft has no tail, so that the steering moment is short, and therefore, if the flat fusion layout aircraft wants to obtain the same balancing effect as the conventional layout aircraft, a larger lift loss is needed. This problem is particularly acute during takeoff and landing phases that require high angle of attack flight. When flying at a large angle of attack, the aircraft has a larger moment of low head and correspondingly, the lift force trim loss is also larger. Therefore, the problem of lift reduction during takeoff and landing phases of an aircraft is severe, and generally requires a large approach speed. This increases the risk of the aircraft during the takeoff and landing phases. Therefore, high lift is necessary during the takeoff and landing phases of the aircraft.
For a flat fusion layout aircraft, the belly flap is a relatively effective high lift device. The belly flap lift principle is to increase the lift of an aircraft by increasing the pressure by reducing the airflow velocity ahead of it. However, a large flow separation region will occur behind the belly flap, which on the one hand will impair the lift-increasing effect and on the other hand will also lead to large changes in the pitching moment of the aircraft. In addition, the flow separation region caused by the belly flap will also result in a reduced efficiency of the control surface of the trailing edge of the aircraft wing in a flat fusion layout. If these problems are not solved, the aerodynamic performance of the aircraft is greatly reduced.
Disclosure of Invention
The invention aims to solve the problems and provides a belly flap design method suitable for a flat fusion layout aircraft, which can conveniently and accurately research the relation between belly flap parameters and the aerodynamic characteristics of the flat fusion layout aircraft, so that the belly flap suitable for the flat fusion layout aircraft with good lift-increasing effect and small influence on moment characteristics can be designed.
The technical purpose of the invention is realized by the following technical scheme: a design method of a belly flap suitable for a flat fusion layout aircraft comprises the following steps:
s1, setting initial parameters of the belly flap;
s2, establishing a aerodynamic force evaluation method;
s3, setting the installation position, width, height and deflection angle restriction range of the belly flap;
s4, carrying out parametric selection on the width and height of the belly flap;
s5, carrying out parametric selection on the chord-direction installation position of the belly flap;
s6, carrying out parametric selection on the deflection angle of the belly flap;
and S7, designing and processing a wind tunnel model, carrying out a wind tunnel test, and confirming the belly flap scheme.
Further, the setting of the initial parameters of the belly flap described in step S1 includes:
setting the initial chord-direction installation position of the belly flap as the position of the center of gravity;
setting the initial width of the belly flap to the width of the fuselage of the flat fusion layout aircraft;
setting the initial height of the belly flap to 10% mean aerodynamic chord;
the initial deflection angle of the belly flap is set to 75 °.
Further, the method for establishing aerodynamic force estimation described in step S2 includes:
typical flight conditions were set with a flight speed of 0.2 times the speed of sound and a flight altitude of 0 km.
Further, step S3 specifically includes:
setting the front limit of the chord-direction installation position of the belly flap not to exceed the center of gravity, and determining the rear limit of the chord-direction installation position of the belly flap by the positions of a belly flap steering engine and a spray pipe;
setting the upper limit of the width of the belly flap to be less than or equal to the width of the airplane body, and the belly flap is not interfered with the undercarriage when being opened, so that the rudder effect of the elevator is not influenced;
setting the upper height limit of the belly flap to be smaller than or equal to the connecting line distance between the main wheel and the tail;
and setting the upper limit of the deflection angle of the belly flap to be less than or equal to 75 degrees, and fitting the belly flap with the flat fusion layout aircraft when the deflection angle of the belly flap is 0 degree.
Further, the parametric selection of the width and height of the belly flap, the parametric selection of the chord-direction installation position of the belly flap and the parametric selection of the deflection angle of the belly flap comprise the following steps:
and analyzing parameter selection and determining the aerodynamic characteristic change rule of the flat fusion layout aircraft by adopting a CFD (computational fluid dynamics) method.
Further, step S7 specifically includes: designing and processing a wind tunnel model, carrying out a wind tunnel test, verifying the accuracy of CFD calculation, and selecting an abdomen flap scheme which has excellent lift-increasing effect and little damage to moment characteristics according to a parameterization research rule.
In conclusion, the invention has the following beneficial effects: the belly flap design method is suitable for the flat fusion layout aircraft, and by the method, the relation between the belly flap parameter and the aerodynamic characteristic of the flat fusion layout aircraft can be conveniently and accurately researched, so that the belly flap which is good in lift-increasing effect and small in influence on the moment characteristic and is suitable for the flat fusion layout aircraft can be designed.
Drawings
FIG. 1 is a flow chart of a method in an embodiment of the invention;
FIG. 2 is a schematic view of different chord-wise mounting positions for a 75 ° offset angle of the belly flap according to an embodiment of the present invention;
FIG. 3 is a schematic view of a selected chordwise mounting position of a belly flap according to an embodiment of the invention at various declination angles;
FIG. 4 is a comparison graph of calculated values and experimental values of the lift enhancement effect of the belly flap in the embodiment of the invention.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions of the present invention will be described in further detail below with reference to the embodiments of the present invention and the accompanying drawings. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail with reference to examples.
Example (b):
as shown in fig. 1, a method for designing a belly flap for a flat fusion layout aircraft comprises the following steps:
s1, setting initial parameters of the belly flap;
s2, establishing a aerodynamic force evaluation method;
s3, setting the constraint ranges of the installation position, width, height and deflection angle of the belly flap;
s4, parameterizing and selecting the width and height of the belly flap;
s5, parameterizing and selecting the chord-direction installation position of the belly flap;
s6, parameterizing and selecting the deflection angle of the belly flap;
and S7, designing and processing a wind tunnel model, carrying out a wind tunnel test, and confirming the belly flap scheme.
Wherein initial parameters for the belly flap are given, including:
the initial chord-direction installation position of the belly flap is the position of the gravity center;
the initial width of the belly flap is the width of the fuselage of the flat fusion layout aircraft;
the initial height of the belly flap is 10% of the average aerodynamic chord length;
the initial deflection angle of the belly flap is 75 °.
The method for establishing the aerodynamic force evaluation specifically comprises the following steps:
and setting a typical flight state, wherein the flight speed is 0.2 times of the sound speed, and the flight height is 0 km.
Wherein, set for belly flap mounted position, width, height, angle of deflection restraint scope, include:
the front limit of the chord direction installation position of the belly flap does not exceed the gravity center, and the rear limit is determined by the positions of the belly flap steering engine and the spray pipe;
the width of the belly flap does not exceed the width of the airplane body to the maximum extent, and the belly flap does not interfere with the landing gear when being opened, so that the rudder effect of the elevator is not influenced;
the height of the belly flap does not exceed the connecting line of the main wheel and the tail to the maximum extent;
the maximum deflection angle of the belly flap does not exceed 75 degrees, and when the deflection angle of the belly flap is 0 degree, the belly flap is attached to the flat fusion layout aircraft.
In addition, based on CFD method to belly flap width and height parameterization lectotype, chord direction installation position parameterization lectotype, deflection angle parameterization lectotype, study parameter selection and flat fusion body layout aircraft aerodynamic characteristic change's law. In order to further explain the parameterization type selection process of the chord-direction installation position and the deflection angle of the belly flap, a schematic diagram of different chord-direction installation positions and a schematic diagram of different deflection angles of the belly flap at a chord-direction installation position selected when the opening angle of the belly flap is 75 degrees are given, and are shown in fig. 2 and 3.
On the basis, a wind tunnel model is designed and processed, a wind tunnel test is carried out, the accuracy of CFD calculation is verified, and the result is shown in FIG. 4. In fig. 4, the variation trend of the CFD calculation result is substantially consistent with that of the wind tunnel test result, and the magnitude is also substantially close, which indicates that the CFD calculation is more accurate.
And according to a parameterized research rule, selecting a scheme of the belly flap which has the best lift increasing effect and has the least damage to the moment characteristic.
Through the embodiment of the invention, the belly flap design method is suitable for the flat fusion layout aircraft, and the relation between the belly flap parameter and the aerodynamic characteristic of the flat fusion layout aircraft can be conveniently and accurately researched by using the method, so that the belly flap which has a good lift-increasing effect and has small influence on the moment characteristic and is suitable for the flat fusion layout aircraft can be designed.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications of the present embodiment without inventive contribution as needed after reading the present specification, but all of them are protected by patent law within the scope of the claims of the present invention.
Claims (6)
1. A design method of a belly flap suitable for a flat fusion layout aircraft is characterized by comprising the following steps: the method comprises the following steps:
s1, setting initial parameters of the belly flap;
s2, establishing an aerodynamic force evaluation method;
s3, setting the installation position, width, height and deflection angle restriction range of the belly flap;
s4, carrying out parametric selection on the width and height of the belly flap;
s5, carrying out parametric selection on the chord-direction installation position of the belly flap;
s6, carrying out parametric selection on the deflection angle of the belly flap;
and S7, designing and processing a wind tunnel model, performing a wind tunnel test, and confirming the belly flap scheme.
2. The method for designing the belly flap of the flat fusion layout aircraft according to claim 1, wherein the method comprises the following steps: the setting of the initial parameters of the belly flap described in step S1 includes:
setting the initial chord-direction installation position of the belly flap as the position of the center of gravity;
setting the initial width of the belly flap to the width of the fuselage of the flat fusion layout aircraft;
setting the initial height of the belly flap to 10% mean aerodynamic chord;
the initial deflection angle of the belly flap is set to 75 °.
3. The method for designing the belly flap of the flat fusion layout aircraft according to claim 1, wherein the method comprises the following steps: the method for establishing aerodynamic force estimation described in step S2 includes:
typical flight conditions were set with a flight speed of 0.2 times the speed of sound and a flight altitude of 0 km.
4. The method for designing the belly flap of the flat fusion layout aircraft according to claim 1, wherein the method comprises the following steps: step S3 specifically includes:
setting the front limit of the chord-direction installation position of the belly flap not to exceed the center of gravity, and determining the rear limit of the chord-direction installation position of the belly flap by the positions of a belly flap steering engine and a spray pipe;
setting the upper limit of the width of the belly flap to be less than or equal to the width of the airplane body, and the belly flap is not interfered with the undercarriage when being opened, so that the rudder effect of the elevator is not influenced;
setting the upper height limit of the belly flap to be smaller than or equal to the connecting line distance between the main wheel and the tail;
and setting the upper limit of the deflection angle of the belly flap to be less than or equal to 75 degrees, and fitting the belly flap with the flat fusion layout aircraft when the deflection angle of the belly flap is 0 degree.
5. The method for designing the belly flap of the flat fusion layout aircraft according to claim 1, wherein the method comprises the following steps: the parametric selection of the width and height of the belly flap, the parametric selection of the chord direction installation position of the belly flap and the parametric selection of the deflection angle of the belly flap comprise the following steps:
and analyzing parameter selection and determining the aerodynamic characteristic change rule of the flat fusion layout aircraft by adopting a CFD (computational fluid dynamics) method.
6. The method for designing the belly flap of the flat fusion layout aircraft according to claim 1, wherein the method comprises the following steps: step S7 specifically includes: designing and processing a wind tunnel model, carrying out a wind tunnel test, verifying the accuracy of CFD calculation, and selecting an abdomen flap scheme which has excellent lift-increasing effect and little damage to moment characteristics according to a parameterization research rule.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210838998.7A CN114906343A (en) | 2022-07-18 | 2022-07-18 | Belly flap design method suitable for flat fusion layout aircraft |
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| CN202210838998.7A CN114906343A (en) | 2022-07-18 | 2022-07-18 | Belly flap design method suitable for flat fusion layout aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115221639A (en) * | 2022-08-30 | 2022-10-21 | 中国空气动力研究与发展中心空天技术研究所 | Backpack semi-embedded inlet lip parametric design method suitable for flying wing layout |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1276319A (en) * | 2000-08-10 | 2000-12-13 | 贾书翰 | Wing-varying aircraft |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| US20100106380A1 (en) * | 2008-10-29 | 2010-04-29 | Kambiz Salari | Articulating base flaps for aerodynamic base drag reduction and stability of a bluff body vehicle |
| WO2011017071A2 (en) * | 2009-07-28 | 2011-02-10 | University Of Kansas | Method and apparatus for pressure adaptive morphing structure |
| CN106353065A (en) * | 2016-09-12 | 2017-01-25 | 中国商用飞机有限责任公司 | Stepless regulation device for regulating wing flaps in wind tunnel experiments and aircraft |
| CN107220415A (en) * | 2017-05-08 | 2017-09-29 | 西北工业大学 | A kind of two-dimentional high lift device parameterization design method for meeting Engineering constraint based on nurbs curve |
| CN108928490A (en) * | 2018-07-13 | 2018-12-04 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of Horizontal Take-off and Landing two-stage enters the aerodynamic arrangement of orbit aerocraft |
| CN109408987A (en) * | 2018-11-01 | 2019-03-01 | 西北工业大学 | A kind of three-dimensional high lift device parametric method for meeting Engineering constraint based on FFD method |
| CN109515739A (en) * | 2018-11-21 | 2019-03-26 | 中国航天空气动力技术研究院 | A kind of Quick prediction method for aerodynamic property |
| CN109614644A (en) * | 2018-11-02 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Externally Blown Flap airplane power-boosting effect evaluation method |
| CN109632243A (en) * | 2018-12-30 | 2019-04-16 | 南京航空航天大学 | The device and method of wing flap parameter state in a kind of change wind-tunnel |
| CN112722241A (en) * | 2021-02-02 | 2021-04-30 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| CN114056551A (en) * | 2022-01-12 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual wing belly flap and wing body fusion airplane, constant air blowing method and variable-angle air blowing method |
-
2022
- 2022-07-18 CN CN202210838998.7A patent/CN114906343A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1276319A (en) * | 2000-08-10 | 2000-12-13 | 贾书翰 | Wing-varying aircraft |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| US20100106380A1 (en) * | 2008-10-29 | 2010-04-29 | Kambiz Salari | Articulating base flaps for aerodynamic base drag reduction and stability of a bluff body vehicle |
| WO2011017071A2 (en) * | 2009-07-28 | 2011-02-10 | University Of Kansas | Method and apparatus for pressure adaptive morphing structure |
| CN106353065A (en) * | 2016-09-12 | 2017-01-25 | 中国商用飞机有限责任公司 | Stepless regulation device for regulating wing flaps in wind tunnel experiments and aircraft |
| CN107220415A (en) * | 2017-05-08 | 2017-09-29 | 西北工业大学 | A kind of two-dimentional high lift device parameterization design method for meeting Engineering constraint based on nurbs curve |
| CN108928490A (en) * | 2018-07-13 | 2018-12-04 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of Horizontal Take-off and Landing two-stage enters the aerodynamic arrangement of orbit aerocraft |
| CN109408987A (en) * | 2018-11-01 | 2019-03-01 | 西北工业大学 | A kind of three-dimensional high lift device parametric method for meeting Engineering constraint based on FFD method |
| CN109614644A (en) * | 2018-11-02 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Externally Blown Flap airplane power-boosting effect evaluation method |
| CN109515739A (en) * | 2018-11-21 | 2019-03-26 | 中国航天空气动力技术研究院 | A kind of Quick prediction method for aerodynamic property |
| CN109632243A (en) * | 2018-12-30 | 2019-04-16 | 南京航空航天大学 | The device and method of wing flap parameter state in a kind of change wind-tunnel |
| CN112722241A (en) * | 2021-02-02 | 2021-04-30 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| CN114056551A (en) * | 2022-01-12 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual wing belly flap and wing body fusion airplane, constant air blowing method and variable-angle air blowing method |
Non-Patent Citations (5)
| Title |
|---|
| 冯志高等: "《高超声速飞行器概论》", 31 December 2016, 北京理工大学出版社 * |
| 康辉: "提高飞翼飞行器起降性能的腹部襟翼", 《国际航空》 * |
| 张同鑫等: "飞翼布局无人机腹襟翼气动设计研究", 《空气动力学学报》 * |
| 石钧之等: "二维翼型下表面增升辅助装置仿真及设计", 《飞机设计》 * |
| 陈宪等: "腹部襟翼对飞翼布局飞行器起降气动特性的影响", 《航空学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115221639A (en) * | 2022-08-30 | 2022-10-21 | 中国空气动力研究与发展中心空天技术研究所 | Backpack semi-embedded inlet lip parametric design method suitable for flying wing layout |
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