CN101850843A - Canard configuration airplane with variable coupling distance between front airfoil and main airfoil - Google Patents
Canard configuration airplane with variable coupling distance between front airfoil and main airfoil Download PDFInfo
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- CN101850843A CN101850843A CN200910131800A CN200910131800A CN101850843A CN 101850843 A CN101850843 A CN 101850843A CN 200910131800 A CN200910131800 A CN 200910131800A CN 200910131800 A CN200910131800 A CN 200910131800A CN 101850843 A CN101850843 A CN 101850843A
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- wing
- distance
- coupling
- moving track
- airfoil
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Abstract
The invention discloses a design of a canard configuration airplane with a variable coupling distance between a front airfoil and a delta airfoil. In the invention, since the distance between the front airfoil and the main airfoil of the airplane is changed, near-range coupling, middle-range coupling and even long-range coupling of the front airfoil and the main airfoil can be realized, thus improving the optimal coupling distance between the front airfoil and a delta airfoil of the airplane at different speeds.
Description
Technical field
The present invention relates to a kind of preceding wing design that is used for canard configuration airplane, especially be different from known China destroy-10 in closely wing design before the coupling, France " fitful wind " and Sweden " hawk lion " is Coupling Design closely, wing before the remote coupling of " typhoon " in Europe.
Background technology
At present, the preceding wing of known canard configuration airplane and host wing distance be the Europe " typhoon " of remote coupling, closely Ou He France " fitful wind " and Sweden " hawk lion ", and have both both in China of closely being coupled destroy-10.
" the long distance coupling " that be based on preceding wing and host wing apart from each other that adopt in Europe " typhoon ", its benefit is to reduce the supersonic flight resistance of aircraft; But the takeoff and landing distance is grown up, and has under the low speed flexible not as the mode of closely coupling.
The preceding wing of France " fitful wind " and Sweden " hawk lion " and host wing distance are " closely coupling ", the preceding wing that can move deflection entirely will produce very strong favourable interference to the aerodynamic force of host wing, thereby can improve low speed, the high-angle-of-attack flight characteristic of aircraft; But the supersonic flight resistance is bigger.
In closely the China of coupling destroy-10 characteristics of taking into account both.
Summary of the invention
For the long distance that solves existing preceding wing and host wing, the excellent scarce problem of low coverage coupling, low coverage coupling advantage is outstanding under the low speed, but high-speed resistance is big; The long distance coupling efficiency is not high under the low speed, but high-speed resistance problem of smaller.The mode of wing and host wing variable coupling distance before the invention provides makes the preceding wing coupling distance of aircraft be fit to flight characteristic under the friction speed, the flight aerodynamic condition of accomplishing optimum.
The present invention solves the scheme that its technical matters adopts: before preceding wing is placed on the wing moving track, preceding wing can parallel motion, and the distance of wing and host wing changes as required before making.During current wing parallel motion, make the center of gravity of aircraft keep stable.
The invention has the beneficial effects as follows, the preceding wing that employing can parallel motion, wing changes the distance of itself and host wing as required before making; Thereby reach closely coupling, middle distance coupling and remote coupling; Aircraft can all possess best preceding wing and host wing coupling distance under any speed like this.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is the preceding wing moving track scheme drawing among the present invention.
Fig. 2 is the closely coupling scheme drawing among the present invention.
Fig. 3 is the middle distance coupling scheme drawing among the present invention.
Fig. 4 is the remote coupling scheme drawing among the present invention.
The specific embodiment
In Fig. 1 to Fig. 4,1. preceding wing, 2. preceding wing moving track, 3. fuselage, 4. host wing.
In Fig. 1, two preceding wing moving tracks (2) are in the both sides of fuselage (3) first half, and are parallel to each other, and the length of preceding wing moving track (2) is more than or equal to the movable distance of preceding wing (1).
In Fig. 2, the rear end of wing moving track (2) was nearest with host wing (4) before preceding wing (1) moved to, and was closely coupling; And make the steadily of centre of gravity of fuselage (3).
In Fig. 3, the mid point of wing moving track (2) before preceding wing (1) moves to, placed in the middle with host wing (4) distance, be the middle distance coupling; And make the steadily of centre of gravity of fuselage (3).
In Fig. 4, the front end of wing moving track (2) before preceding wing (1) moves to, with host wing (4) distance farthest, be remote coupling; And make the steadily of centre of gravity of fuselage (3).
Claims (5)
1. the canard configuration airplane of wing and host wing variable coupling distance before a kind comprises preceding wing (1), preceding wing moving track (2), fuselage (3), host wing (4);
It is characterized in that:
Two preceding wing moving tracks (2) are in the both sides of fuselage (3) first half, and are parallel to each other, and the length of preceding wing moving track (2) is more than or equal to the movable distance of preceding wing (1);
Before wing (1) move to before the front end of wing moving track (2), with host wing (4) distance farthest, be remote coupling; And the center of gravity that makes fuselage (3) keeps stable;
The rear end of wing moving track (2) was nearest with host wing (4) before preceding wing (1) moved to, and was closely coupling; And the center of gravity that makes fuselage (3) keeps stable;
The mid point of wing moving track (2) before preceding wing (1) moves to, placed in the middle with host wing (4) distance is the middle distance coupling; And the center of gravity that makes fuselage (3) keeps stable.
2. canard configuration airplane according to claim 1, it is characterized in that: make two preceding wing moving tracks (2) be in the both sides of fuselage (3) first half, parallel to each other, the length of preceding wing moving track (2) is more than or equal to the movable distance of preceding wing (1).
3. canard configuration airplane according to claim 1 is characterized in that: make preceding wing (1) but mmi machine wing moving track (2) go up to move.
4. canard configuration airplane according to claim 1 is characterized in that: the assigned address before preceding wing (1) is moved to as required on the wing moving track (2).
5. canard configuration airplane according to claim 1 is characterized in that: during any position of wing moving track (2), keep the center of gravity of fuselage (3) to keep stable before fuselage (3) the mmi machine wing (1) is positioned at.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910131800A CN101850843A (en) | 2009-04-02 | 2009-04-02 | Canard configuration airplane with variable coupling distance between front airfoil and main airfoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910131800A CN101850843A (en) | 2009-04-02 | 2009-04-02 | Canard configuration airplane with variable coupling distance between front airfoil and main airfoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101850843A true CN101850843A (en) | 2010-10-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910131800A Pending CN101850843A (en) | 2009-04-02 | 2009-04-02 | Canard configuration airplane with variable coupling distance between front airfoil and main airfoil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101850843A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
| CN105228901A (en) * | 2013-02-14 | 2016-01-06 | 湾流航空航天公司 | For controlling the system and method for sonic boom amplitude |
-
2009
- 2009-04-02 CN CN200910131800A patent/CN101850843A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105228901A (en) * | 2013-02-14 | 2016-01-06 | 湾流航空航天公司 | For controlling the system and method for sonic boom amplitude |
| CN105228901B (en) * | 2013-02-14 | 2017-04-12 | 湾流航空航天公司 | Systems and methods for controlling a magnitude of a sonic boom |
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20101006 |