CN111216873A - Design method of aircraft direction-finding antenna array fairing - Google Patents
Design method of aircraft direction-finding antenna array fairing Download PDFInfo
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- CN111216873A CN111216873A CN201911125463.XA CN201911125463A CN111216873A CN 111216873 A CN111216873 A CN 111216873A CN 201911125463 A CN201911125463 A CN 201911125463A CN 111216873 A CN111216873 A CN 111216873A
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- fairing
- antenna array
- aircraft
- finding antenna
- designing
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000013461 design Methods 0.000 title claims abstract description 15
- 238000012360 testing method Methods 0.000 claims abstract description 7
- 238000012795 verification Methods 0.000 claims abstract description 7
- 238000004088 simulation Methods 0.000 claims abstract description 6
- 239000012530 fluid Substances 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims 1
- 238000000926 separation method Methods 0.000 abstract description 3
- 230000002411 adverse Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000012216 screening Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Details Of Aerials (AREA)
Abstract
The invention belongs to the field of aircraft aerodynamic design, and relates to a design method of an aircraft direction-finding antenna array fairing, which is characterized in that in the shape design of the fairing, a quadratic curve is adopted as a control line for a plurality of sections in three directions of a space X, Y, Z, and a generated curved surface is intersected with an aircraft body to form a plurality of antenna array fairing shape schemes with streamline; and finally, determining the shape scheme of the antenna array fairing with the optimal aerodynamic characteristics by a method combining numerical simulation and wind tunnel test verification. The fairing obtained by the design method provided by the invention has the advantages of being capable of completely enveloping the antenna array, meeting a certain gap requirement, not influencing the normal use of electrical performance, having small aerodynamic resistance, weak local airflow separation, no local eddy and the like, and test flight verification shows that the aerodynamic characteristics of the antenna array fairing are excellent.
Description
Technical Field
The invention belongs to the field of aircraft aerodynamic design, and relates to a design method of a fairing of an aircraft direction-finding antenna array.
Background
For special aircraft, in order to meet a certain combat mission requirement, a plurality of mission system antenna devices need to be carried on the aircraft, and an antenna device protruding out of the aircraft body is usually unavoidable. For the task system antenna array device protruding out of the machine body, the antenna electrical performance requirements are considered at the beginning of design, and the influence of the antenna electrical performance requirements on the aerodynamic characteristics of the carrier is considered, so that the task system antenna fairing is required to be designed generally. The antenna fairing protruding out of the body may deteriorate the flow state of the airflow in the vicinity thereof, particularly in the rear local area with respect to the incoming flow, such as the generation of airflow separation, the formation of local vortex, the generation of airflow pulsation, and other adverse problems. In order to solve the aerodynamic problem, the shape and the position of the antenna fairing need to be designed and optimized, so that the adverse effect of the antenna fairing on the aerodynamic characteristics of the whole machine is reduced as much as possible.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a direction-finding antenna array fairing with better aerodynamic characteristics under the conditions of meeting various requirements that a direction-finding antenna array can be normally enveloped, a certain gap requirement is ensured, and the electrical performance of the antenna can be normally used.
Technical scheme
A design method of the aircraft direction finding antenna array fairing, in the shape design of the fairing, adopt the quadratic curve as the control line of multiple sections of three directions of space X, Y, Z, produce the curved surface and intersect with aircraft fuselage, form the various antenna array fairing shape schemes with flow linearity; and finally, determining the shape scheme of the antenna array fairing with the optimal aerodynamic characteristics by a method combining numerical simulation and wind tunnel test verification.
The method for determining the optimal aerodynamic characteristics comprises the following steps: in the obtained various antenna array fairing appearance schemes, the increase of the aerodynamic resistance of the whole aircraft caused by screening of the fairings is minimum; and the flow field characteristic analysis result of the local airflow of the fairing is taken into consideration for determination.
The X axis is a course direction, the Y axis is a vertical direction, the Z axis is a spreading direction, and a central point at the bottom of the fairing is taken as an origin.
The beneficial technical effects are as follows: the fairing obtained by the design method provided by the invention has the advantages of being capable of completely enveloping the antenna array, meeting a certain gap requirement, not influencing the normal use of electrical performance, having smaller aerodynamic resistance, weaker local airflow separation, having no local eddy and the like, and the test flight verification shows that the aerodynamic characteristics of the fairing of the antenna array are excellent.
Drawings
FIG. 1 is a schematic view of a coordinate system of a radome of an aircraft direction-finding antenna array;
wherein, the central point of the bottom plane is taken as the origin of coordinates, the X axis is positive backwards, the Y axis is positive upwards, and the Z axis meets the right-hand rule.
Detailed Description
An aircraft direction finding antenna array radome is smoothly transitioned to an aircraft fuselage by a curved surface formed by an optimized quadratic curve around the radome. The central point of the bottom plane is taken as the origin of coordinates, the X axis is positive backwards, the Y axis is positive upwards, the Z axis meets the right-hand rule, and the measurement unit is mm.
In the shape design of the fairing, a quadratic curve is used as a control line for a plurality of sections in three directions of a space X, Y, Z, a curved surface is generated to penetrate through an airplane body, and a plurality of antenna array fairing shape schemes with streamline are formed; and finally, determining the shape scheme of the antenna array fairing with the optimal aerodynamic characteristics by a method combining numerical simulation and wind tunnel test verification. The numerical simulation is carried out by using fluid simulation software, and the method is efficient and rapid. The optimal antenna array fairing appearance scheme is a scheme with the smallest increase of the aerodynamic resistance of the whole airplane caused by screening of the fairings and the optimal local airflow field characteristic of the fairings on the basis of various antenna array fairing appearance schemes.
The specific implementation case is as follows: use bottom plane central point as the origin of coordinates, X axial is positive backward, and Y axial is upwards positive, and the Z axle satisfies the right hand rule, selects according to following table coordinate point, and the measurement unit is mm:
all coordinate points are connected into a smooth curve and a curved surface is generated, and the method is characterized in that the middle area of the bottom is a plane with the length of 1115mm and the width of 300mm, and the curved surface formed by the optimized quadratic curve on the periphery is smoothly transited to the airplane body. Forming a direction-finding antenna array fairing. Finally, the length of the fairing of the antenna array is about 2137mm, the width is about 1102mm, the height is about 269mm, and the infiltration area is about 3.328m2The frontal area is about 0.297m2. Test flight verification shows that the aerodynamic characteristics of the antenna array radome are excellent.
Claims (8)
1. A design method of a fairing of an airplane direction-finding antenna array is characterized by comprising the following steps: in the shape design of the fairing, a quadratic curve is used as a control line for a plurality of sections in three directions of a space X, Y, Z, a curved surface is generated to penetrate through an airplane body, and a plurality of antenna array fairing shape schemes with streamline are formed; and finally, determining the shape scheme of the antenna array fairing with the optimal aerodynamic characteristics by a method combining numerical simulation and wind tunnel test verification.
2. The method of designing an aircraft direction finding antenna array fairing of claim 1, wherein: the method for determining the optimal aerodynamic characteristics comprises the following steps: the fairing causes the least increase in the aerodynamic drag of the entire aircraft.
3. The method of designing an aircraft direction finding antenna array fairing of claim 1, wherein: the numerical simulation was performed using fluid simulation software.
4. The method of designing an aircraft direction finding antenna array fairing of claim 1, wherein: x, Y, Z the central point of the bottom plane is used as the origin of coordinates in three directions, the X axis is positive backwards, the Y axis is positive upwards, and the Z axis meets the right-hand rule.
5. The method of designing an aircraft direction finding antenna array fairing of claim 4, wherein: the X axis is a course direction, the Y axis is a vertical direction, the Z axis is a spreading direction, and a central point at the bottom of the fairing is taken as an origin.
6. The method of designing an aircraft direction finding antenna array fairing of claim 1, wherein: the curved surface smoothly transitions to the aircraft fuselage.
7. The method of designing an aircraft direction finding antenna array fairing of claim 1, wherein: the number of cross sections in the X direction is not less than 25.
8. The method of designing an aircraft direction finding antenna array fairing of claim 1, wherein: y, Z the number of the two direction cross sections is not less than 20.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911125463.XA CN111216873A (en) | 2019-11-15 | 2019-11-15 | Design method of aircraft direction-finding antenna array fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911125463.XA CN111216873A (en) | 2019-11-15 | 2019-11-15 | Design method of aircraft direction-finding antenna array fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111216873A true CN111216873A (en) | 2020-06-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911125463.XA Pending CN111216873A (en) | 2019-11-15 | 2019-11-15 | Design method of aircraft direction-finding antenna array fairing |
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| Country | Link |
|---|---|
| CN (1) | CN111216873A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100038488A1 (en) * | 2004-01-16 | 2010-02-18 | The Boeing Company | Antenna fairing and method |
| US20170129588A1 (en) * | 2015-09-25 | 2017-05-11 | Howard R. Verillion, JR. | Truss-Reinforced Radome Crown Structure |
| CN207417117U (en) * | 2017-09-12 | 2018-05-29 | 陕西飞机工业（集团）有限公司 | A kind of ventral RECTIFYING ANTENNA cover shape |
| CN108860567A (en) * | 2017-05-09 | 2018-11-23 | 波音公司 | Aircraft radome device and method |
| CN208216975U (en) * | 2018-03-16 | 2018-12-11 | 陕西飞机工业（集团）有限公司 | A kind of fuselage side RECTIFYING ANTENNA cover |
-
2019
- 2019-11-15 CN CN201911125463.XA patent/CN111216873A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100038488A1 (en) * | 2004-01-16 | 2010-02-18 | The Boeing Company | Antenna fairing and method |
| US20170129588A1 (en) * | 2015-09-25 | 2017-05-11 | Howard R. Verillion, JR. | Truss-Reinforced Radome Crown Structure |
| CN108860567A (en) * | 2017-05-09 | 2018-11-23 | 波音公司 | Aircraft radome device and method |
| CN207417117U (en) * | 2017-09-12 | 2018-05-29 | 陕西飞机工业（集团）有限公司 | A kind of ventral RECTIFYING ANTENNA cover shape |
| CN208216975U (en) * | 2018-03-16 | 2018-12-11 | 陕西飞机工业（集团）有限公司 | A kind of fuselage side RECTIFYING ANTENNA cover |
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Application publication date: 20200602 |
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| RJ01 | Rejection of invention patent application after publication |