CN113291457B - Aircraft nose fairing structure and aircraft attitude control method - Google Patents
Aircraft nose fairing structure and aircraft attitude control method Download PDFInfo
- Publication number
- CN113291457B CN113291457B CN202110545604.4A CN202110545604A CN113291457B CN 113291457 B CN113291457 B CN 113291457B CN 202110545604 A CN202110545604 A CN 202110545604A CN 113291457 B CN113291457 B CN 113291457B
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- fairing
- wing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
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Abstract
The application provides an aircraft nose fairing structure and an aircraft attitude control method, wherein the front end of the fairing is of a conical fairing structure, the fairing body is of a cylindrical fairing, radial fairing wings are arranged on the outer side of the rear end of the cylindrical fairing, each fairing wing comprises a fixed wing and a movable wing, the fixed wings are connected with the movable wings through transmission shafts, a driving device of the movable wings is arranged in the cylindrical fairing, and the driving device drives the movable wings to deflect relative to the fixed wings through the transmission shafts, so that the upward tilting, downward pitching, left turning, right turning, clockwise turning and anticlockwise turning movements of the aircraft nose are realized, and the aircraft maneuverability is improved.
Description
Technical Field
The application relates to an aircraft design technology, in particular to an aircraft nose fairing structure and an aircraft attitude control method.
Background
The existing aircraft nose fairing is of an integral fairing line structure, mainly adopts an airflow post-control technology, and aircraft maneuvering flight control is mainly carried out by virtue of wings and tail wings.
The aircraft in the prior art adopts an airflow post-control technology, and the performance of the aircraft is seriously limited.
Disclosure of Invention
The application aims to provide an aircraft nose fairing structure and an aircraft attitude control method, which are used for realizing quick maneuvering conversion of the upward, downward, leftward, rightward, clockwise and anticlockwise overturning attitudes of an aircraft nose by adding a front-end airflow control device while maintaining maneuvering flight control of an existing aircraft by virtue of wings and tail wings, and improving the countermeasure capability of the aircraft.
The utility model provides an aircraft nose radome structure, its characterized in that, the front end of radome is the toper cover structure, and the radome body is the cylindrical cover, is equipped with radial fairing wing in the rear end outside of cylindrical cover, and this fairing wing contains fixed wing and movable wing, and fixed wing and movable wing pass through the transmission shaft and connect, are equipped with the drive arrangement of movable wing in the cylindrical cover, and drive arrangement passes through the transmission shaft and drives movable wing and take place the deflection relative to fixed wing.
The fixed wing of the preferred fairing wing is a wedge-shaped airfoil, the outer edge of the wedge-shaped airfoil is consistent with the extension line of the conical cover at the front end of the fairing, and the movable wing airfoil is rectangular.
Preferably, four uniformly arranged rectifying wings are arranged on the outer side of the rear end of the cylindrical cover, and each movable wing of each rectifying wing corresponds to one driving device.
The application also provides a method for controlling the attitude of the aircraft, which is characterized in that the aircraft nose fairing of the aircraft is arranged on the aircraft nose, the movable wings of the fairing wings are controlled to deflect through a driving device in the aircraft nose fairing, and then the air attitude of the aircraft is controlled, when the movable wings deflect above the aircraft body, the aircraft nose is downward pushed down; when the movable wing leans to the lower part of the machine body, the machine head leans upwards; when the movable wing deviates to the left of the machine body, the machine head deviates to the right; when the movable wing deviates to the right of the machine body, the machine head deviates to the left; when the movable wing is clockwise deflected by taking the central shaft of the fairing as the center, the airframe turns over anticlockwise; when the movable wing is anticlockwise deflected by taking the central shaft of the fairing as the center, the airframe turns clockwise.
The application has the beneficial effects that: the application provides a fairing for controlling the attitude of an airplane by airflow at the front end of the airplane, which is characterized in that a fairing wing is arranged on the fairing, and a driving device is used for controlling the movable wing of the fairing wing to deflect so as to control the aerial attitude of the airplane, so that the control of the position of the fairing at the front end of the airplane is realized, the upward, downward and downward turning, left turning, right turning, clockwise turning and anticlockwise turning movements of a nose of the airplane are realized, and the maneuverability of the airplane is improved.
The present application is described in further detail below with reference to the accompanying drawings.
Drawings
Fig. 1 is a schematic diagram of an aircraft nose fairing.
Fig. 2 is a front view of the position of the movable wing on the fairing in the direction of airflow.
Figure 3 is a front view of the position of the movable wing on the fairing when the movable wing is deflected to the lower part of the airframe to control the upward elevation of the airflow.
FIG. 4 is a front view of the position of the movable wing on the fairing when it is deflected over the body to control the downward flow of air.
FIG. 5 is a front view of the position of the movable wing on the fairing when the movable wing is deflected to the right of the body to control the left turn of the airflow.
FIG. 6 is a front view of the position of the movable wing on the fairing when the movable wing is deflected to the left of the body to control the right turn of the airflow.
FIG. 7 is a front elevational view of the movable wing on the fairing in a position to deflect the entire counter-clockwise control airflow clockwise.
FIG. 8 is a front elevational view of the movable wing on the fairing in a position to deflect the entire clockwise control airflow counter-clockwise.
The numbering in the figures illustrates: 1 a conical cover, 2 a cylindrical cover, 3 a fixed wing, 4 a movable wing, 5 a transmission shaft and 6 a driving device.
Detailed Description
Referring to the attached drawings, in the aircraft nose fairing structure, the front end of the fairing is in a conical fairing 1 structure, the fairing body is a cylindrical fairing 2, radial fairing wings are arranged on the outer side of the rear end of the cylindrical fairing 2, each fairing wing comprises a fixed wing 3 and a movable wing 4, the fixed wings 3 and the movable wings 4 are connected through a transmission shaft 5, a driving device 6 of the movable wings 4 is arranged in the cylindrical fairing 2, and the driving device 6 drives the movable wings 4 to deflect relative to the fixed wings through the transmission shaft 5.
The fixed wing 3 of the preferred fairing wing is a wedge-shaped airfoil, the outer edge of the wedge-shaped airfoil is consistent with the extension line of the conical cover 1 at the front end of the fairing, and the airfoil of the movable wing 4 is rectangular.
Four uniformly arranged rectifying wings are preferably arranged outside the rear end of the cylindrical cover 2, and each movable wing 4 of the rectifying wings corresponds to one driving device 6.
When the aircraft nose fairing structure is used for controlling the aircraft attitude, the aircraft nose fairing is arranged at the aircraft nose of the aircraft and is in butt joint with the aircraft body, the movable wings 4 on the fairing are in a state along the airflow direction as shown in fig. 2, the movable wings do not influence the aircraft attitude, and only the movable wings 4 of the fairing are controlled to deflect by the driving device 6 in the aircraft nose fairing, the air attitude of the aircraft can be controlled by the movable wings 4 of the fairing. When the movable wing 4 is deflected above the machine body, the machine head is downward pushed down as shown in fig. 4; when the movable wing 4 is biased to the lower part of the machine body, the machine head is upward leaned as shown in figure 3; when the movable wing 4 is deviated to the left of the machine body, as shown in fig. 6, the machine head is deviated to the right; when the movable wing 4 is deviated to the right of the machine body, as shown in fig. 5, the machine head is deviated to the left; when the movable wing 4 is clockwise deviated by taking the central shaft of the fairing as the center, the airframe turns over anticlockwise as shown in figure 7; when the movable wing 4 is biased counterclockwise about the center axis of the fairing, the fuselage is flipped clockwise as shown in fig. 8.
According to the application, the arrow-shaped fairing controlled by the air flow is adopted at the front end of the aircraft, the movable wings are arranged outside the fairing, and electric power or hydraulic drive is adopted as a power source of the movable wings, so that the air flow can be controlled at the position of the fairing at the front end of the aircraft, the upward, downward, leftward, rightward, clockwise and anticlockwise turning movements of the aircraft nose are realized, and the maneuverability of the aircraft is improved.
Claims (4)
1. The utility model provides an aircraft nose radome structure, its characterized in that, the front end of radome is the toper cover structure, and the radome body is the cylindrical cover, is equipped with radial fairing wing in the rear end outside of cylindrical cover, and this fairing wing contains fixed wing and movable wing, and fixed wing and movable wing pass through the transmission shaft and connect, are equipped with the drive arrangement of movable wing in the cylindrical cover, and drive arrangement passes through the transmission shaft and drives movable wing and take place the deflection relative to fixed wing.
2. The aircraft nose fairing structure of claim 1, wherein the fixed wing of the fairing wing is a wedge-shaped airfoil, the outer edge of the wedge-shaped airfoil is consistent with the extension line of the cone-shaped cover at the front end of the fairing, and the movable wing airfoil is rectangular.
3. An aircraft nose fairing structure as claimed in claim 1 or claim 2, in which four evenly arranged fairing wings are provided on the outboard side of the aft end of the cylindrical fairing, one drive means for each fairing wing.
4. The aircraft nose fairing of claim 1, 2 or 3 is arranged on the aircraft nose, the movable wings of the fairing wings are controlled to deflect by a driving device in the aircraft nose fairing, and then the air attitude of the aircraft is controlled, when the movable wings deflect above the aircraft body, the aircraft nose is downward pushed down; when the movable wing leans to the lower part of the machine body, the machine head leans upwards; when the movable wing deviates to the left of the machine body, the machine head deviates to the right; when the movable wing deviates to the right of the machine body, the machine head deviates to the left; when the movable wing is clockwise deflected by taking the central shaft of the fairing as the center, the airframe turns over anticlockwise; when the movable wing is anticlockwise deflected by taking the central shaft of the fairing as the center, the airframe turns clockwise.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110545604.4A CN113291457B (en) | 2021-05-19 | 2021-05-19 | Aircraft nose fairing structure and aircraft attitude control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110545604.4A CN113291457B (en) | 2021-05-19 | 2021-05-19 | Aircraft nose fairing structure and aircraft attitude control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113291457A CN113291457A (en) | 2021-08-24 |
| CN113291457B true CN113291457B (en) | 2023-09-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN202110545604.4A Active CN113291457B (en) | 2021-05-19 | 2021-05-19 | Aircraft nose fairing structure and aircraft attitude control method |
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| CN (1) | CN113291457B (en) |
Citations (9)
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| CN103612769A (en) * | 2013-10-24 | 2014-03-05 | 中国商用飞机有限责任公司 | Fairing structure of hanging structure in wing-suspension layout plane |
| CN204250356U (en) * | 2014-05-14 | 2015-04-08 | 刘新广 | New fan wing aircraft |
| CN106143911A (en) * | 2016-07-13 | 2016-11-23 | 西藏长源动力科技有限公司 | A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched |
| CN208665528U (en) * | 2018-07-26 | 2019-03-29 | 成都飞机工业（集团）有限责任公司 | A kind of plane wing-body fairing |
| CN209795809U (en) * | 2019-04-10 | 2019-12-17 | 珠海市海卫科技有限公司 | Flap control mechanism of light sport aircraft |
| CN110901889A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Variant aircraft |
| CN111204465A (en) * | 2020-01-21 | 2020-05-29 | 大连理工大学 | Design method of pneumatic self-separation fairing of ramjet engine air inlet |
| CN111247068A (en) * | 2017-10-19 | 2020-06-05 | 庞巴迪公司 | Aircraft pylon fairing |
| CN212890898U (en) * | 2020-08-14 | 2021-04-06 | 广州极飞科技有限公司 | Aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11492097B2 (en) * | 2019-08-30 | 2022-11-08 | Airbus Operations Gmbh | Wing and aircraft |
-
2021
- 2021-05-19 CN CN202110545604.4A patent/CN113291457B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103612769A (en) * | 2013-10-24 | 2014-03-05 | 中国商用飞机有限责任公司 | Fairing structure of hanging structure in wing-suspension layout plane |
| CN204250356U (en) * | 2014-05-14 | 2015-04-08 | 刘新广 | New fan wing aircraft |
| CN106143911A (en) * | 2016-07-13 | 2016-11-23 | 西藏长源动力科技有限公司 | A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched |
| CN111247068A (en) * | 2017-10-19 | 2020-06-05 | 庞巴迪公司 | Aircraft pylon fairing |
| CN208665528U (en) * | 2018-07-26 | 2019-03-29 | 成都飞机工业（集团）有限责任公司 | A kind of plane wing-body fairing |
| CN209795809U (en) * | 2019-04-10 | 2019-12-17 | 珠海市海卫科技有限公司 | Flap control mechanism of light sport aircraft |
| CN110901889A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Variant aircraft |
| CN111204465A (en) * | 2020-01-21 | 2020-05-29 | 大连理工大学 | Design method of pneumatic self-separation fairing of ramjet engine air inlet |
| CN212890898U (en) * | 2020-08-14 | 2021-04-06 | 广州极飞科技有限公司 | Aircraft |
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| Publication number | Publication date |
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| CN113291457A (en) | 2021-08-24 |
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