CN203199175U - Aircraft with back flap - Google Patents
Aircraft with back flap Download PDFInfo
- Publication number
- CN203199175U CN203199175U CN2013200460769U CN201320046076U CN203199175U CN 203199175 U CN203199175 U CN 203199175U CN 2013200460769 U CN2013200460769 U CN 2013200460769U CN 201320046076 U CN201320046076 U CN 201320046076U CN 203199175 U CN203199175 U CN 203199175U
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- China
- Prior art keywords
- wing
- aircraft
- flap
- fuselage
- increase
- 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.)
- Expired - Fee Related
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Abstract
The utility model aims to provide an aircraft with a back flap. The aircraft comprises the back flap, an aircraft body, a wing, a front wing, a vertical tail, an aileron and a flap, wherein the wing is connected with the aircraft body, the aileron and the flap are arranged at the back ends of the wing, the front wing is arranged at the front part of the aircraft body, and the back flap and the vertical tail are arranged on the aircraft body. When the aircraft is at a cruise attitude, the back flap is folded up; and when the aircraft is at a landing attitude, the back flap is unfolded. According to the aircraft, the back flap is arranged at the back of the aircraft body to increase the rising torque of the whole aircraft, and the available skewness of the flap at the back edge of the wing is increased with the increase of the rising torque of the whole aircraft, so as to increase the trim lift of the whole aircraft at the landing attitude.
Description
Technical field
The utility model belongs to aviation aeromechanics technology field, is specifically related to a kind of aircraft that has the back wing flap.
Background technology
The front wing layout is in landing mission, inclined to one side front wing produces the nose-down pitching moment that nose-up pitching moment comes the trim main wing to produce on the needs, at this moment, the local angle of attack of front wing is bigger than full machine (main plane) angle of attack, and wing is to washing the further local angle of attack that has increased front wing on the front wing, thereby cause front wing stall, and then cause the nose-down pitching moment of main wing to can not get trim, the main wing trailing edge flap can not the bigger degree of bias of deflection, this has just limited the raising of the trim lift coefficient of full machine, thereby makes the landing data variation of front wing layout aircraft.The huge nose-down pitching moment that blade area can the trim high-lift wing system produces before increasing, but along with the enhancing of front wing to washing under the main wing also can strengthen the weakening effect of airfoil lift.The resultant lift of full machine can be very not high.Therefore, front wing stall is the maximum constraints factor of front wing layout low speed trim ability, also is one of subject matter of front wing layout.
The utility model content
For overcoming above-mentioned the deficiencies in the prior art, the purpose of this utility model provides a kind of aircraft that has the back wing flap.
The utility model is achieved in that a kind of aircraft that has the back wing flap, comprise back wing flap, fuselage, wing, front wing, vertical tail, aileron and wing flap, wing is connected with fuselage, the trailing edge of wing is provided with aileron and wing flap, the front portion of fuselage is provided with front wing, and fuselage is provided with back wing flap and vertical tail.
The utility model also has some technical characterictics like this: when aircraft was in cruise attitude, the back wing flap was packed up; When aircraft was in landing attitude, the back wing flap was opened.
The utility model arranges the back wing flap at fuselage back, complete can increase the machine nose-up pitching moment, with the increase of full machine nose-up pitching moment, the trailing edge wing flap can increase with the degree of bias, has increased full machine at the trim lift of landing state.
Description of drawings
Fig. 1 is structural representation of the present utility model;
Fig. 2 is lateral plan of the present utility model.
The specific embodiment
The utility model is described in further detail below in conjunction with accompanying drawing:
As shown in Figure 1, a kind of aircraft that has the back wing flap, comprise back wing flap 1, fuselage 2, wing 3, front wing 4, vertical tail 5, aileron 6 and wing flap 7, wing 3 is connected with fuselage 2, the trailing edge of wing 3 is provided with aileron 6 and wing flap 7, the front portion of fuselage is provided with front wing 4, and fuselage is provided with back wing flap 1 and vertical tail 5.When aircraft was in cruise attitude, back wing flap 1 was packed up; When aircraft was in landing attitude, back wing flap 1 was opened.
The utility model arranges the back wing flap at fuselage back, complete can increase the machine nose-up pitching moment, with the increase of full machine nose-up pitching moment, the trailing edge wing flap can increase with the degree of bias, has increased full machine at the trim lift of landing state.
Claims (1)
1. aircraft that has the back wing flap, comprise back wing flap (1), fuselage (2), wing (3), front wing (4), vertical tail (5), aileron (6) and wing flap (7), it is characterized in that: wing (3) is connected with fuselage (2), the trailing edge of wing (3) is provided with aileron (6) and wing flap (7), the front portion of fuselage is provided with front wing (4), and fuselage is provided with back wing flap (1) and vertical tail (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013200460769U CN203199175U (en) | 2012-12-14 | 2013-01-29 | Aircraft with back flap |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201220754378 | 2012-12-14 | ||
| CN201220754378.7 | 2012-12-14 | ||
| CN2013200460769U CN203199175U (en) | 2012-12-14 | 2013-01-29 | Aircraft with back flap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203199175U true CN203199175U (en) | 2013-09-18 |
Family
ID=49143309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013200460769U Expired - Fee Related CN203199175U (en) | 2012-12-14 | 2013-01-29 | Aircraft with back flap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203199175U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103043207A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业空气动力研究院 | Airplane with back flap |
-
2013
- 2013-01-29 CN CN2013200460769U patent/CN203199175U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103043207A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业空气动力研究院 | Airplane with back flap |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130918 Termination date: 20140129 |