CN103043207A - Airplane with back flap - Google Patents
Airplane with back flap Download PDFInfo
- Publication number
- CN103043207A CN103043207A CN2012105679683A CN201210567968A CN103043207A CN 103043207 A CN103043207 A CN 103043207A CN 2012105679683 A CN2012105679683 A CN 2012105679683A CN 201210567968 A CN201210567968 A CN 201210567968A CN 103043207 A CN103043207 A CN 103043207A
- Authority
- CN
- China
- Prior art keywords
- wing
- airplane
- flap
- back flap
- wing flap
- 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.)
- Pending
Links
Images
Landscapes
- Adjustment And Processing Of Grains (AREA)
Abstract
The invention aims to provide an airplane with a back flap, which comprises the back flap, an airplane body, aerofoils, front wings, a vertical tail, ailerons and flaps, wherein the aerofoils are connected with the airplane body; the ailerons and the flaps are arranged at the trailing edges of the aerofoils; the front wings are arranged in the front of the airplane body; and the back flap and the vertical tail are arranged at the back of the airplane body; and when the airplane is in a cruise posture, the back flap is folded, when the airplane is in a landing posture, the back flap is opened. According to the invention, with the back flap on the back of the airplane, the nose-up moment of the whole plane is increased, which increases the available skewness of the flaps at the trailing edges of the aerofoils; and the trim lift of the whole plane in a landing state is increased.
Description
Technical field
The invention belongs to aviation aeromechanics technology field, be specifically related to a kind of aircraft with 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 larger 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 larger 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.
Summary of the invention
For overcoming above-mentioned the deficiencies in the prior art, the purpose of this invention is to provide a kind of aircraft with the back wing flap.
The present invention is achieved in that a kind of aircraft with the back wing flap, comprise back wing flap, fuselage, wing, front wing, vertical tail, aileron and wing flap, wing is connected with fuselage, and 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 present invention also has like this some technical characterictics: 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 present invention 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 invention;
Fig. 2 is lateral plan of the present invention.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing:
As shown in Figure 1, a kind of aircraft with 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 present invention 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 (2)
1. aircraft with 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).
2. a kind of aircraft with the back wing flap as claimed in claim 1, it is characterized in that: 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105679683A CN103043207A (en) | 2012-12-14 | 2012-12-14 | Airplane with back flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105679683A CN103043207A (en) | 2012-12-14 | 2012-12-14 | Airplane with back flap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103043207A true CN103043207A (en) | 2013-04-17 |
Family
ID=48056111
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105679683A Pending CN103043207A (en) | 2012-12-14 | 2012-12-14 | Airplane with back flap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103043207A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115214839A (en) * | 2022-07-25 | 2022-10-21 | 深圳市苇渡智能科技有限公司 | Flight attitude adjustable hydrofoil, carrier, control system and method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4913378A (en) * | 1986-04-22 | 1990-04-03 | Calvert Galen E | Airplane with transonic/hypersonic to short take off and landing (STOL) flight capability |
| CN101454201A (en) * | 2006-05-31 | 2009-06-10 | 空中客车德国有限公司 | Method of and apparatus for producing aerodynamic resistanceon an aircraft |
| US20110127384A1 (en) * | 2008-12-01 | 2011-06-02 | Sergey Nikolaevich Afanasyev | Flying vehicle |
| CN203199175U (en) * | 2012-12-14 | 2013-09-18 | 中国航空工业空气动力研究院 | Aircraft with back flap |
-
2012
- 2012-12-14 CN CN2012105679683A patent/CN103043207A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4913378A (en) * | 1986-04-22 | 1990-04-03 | Calvert Galen E | Airplane with transonic/hypersonic to short take off and landing (STOL) flight capability |
| CN101454201A (en) * | 2006-05-31 | 2009-06-10 | 空中客车德国有限公司 | Method of and apparatus for producing aerodynamic resistanceon an aircraft |
| US20110127384A1 (en) * | 2008-12-01 | 2011-06-02 | Sergey Nikolaevich Afanasyev | Flying vehicle |
| CN203199175U (en) * | 2012-12-14 | 2013-09-18 | 中国航空工业空气动力研究院 | Aircraft with back flap |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115214839A (en) * | 2022-07-25 | 2022-10-21 | 深圳市苇渡智能科技有限公司 | Flight attitude adjustable hydrofoil, carrier, control system and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202320772U (en) | High lift device of double-aisle large-type passenger plane | |
| CN106163919A (en) | Including the aircraft of foldable air dynamical structure and the method manufacturing the foldable air dynamical structure for aircraft | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN103171766A (en) | Short distance rising and landing unmanned all-wing aircraft | |
| CN105366049A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN106005366A (en) | Pneumatic layout of dual flying wings of UAV (Unmanned Aerial Vehicle) | |
| US8109473B2 (en) | Slotted high lift aerofoils | |
| CN102826216A (en) | Aerodynamic configuration of aircraft | |
| CN204399465U (en) | A kind of anury all-wing aircraft many controlsurfaces unmanned plane | |
| CN107757871A (en) | A kind of small-sized fixed-wing unmanned plane aerofoil profile | |
| CN202966654U (en) | Fixed wing unmanned aerial vehicle for engineer operation | |
| CN202609085U (en) | Aircraft aerodynamic configuration with blended wing body | |
| CN110104160B (en) | A mid-range coupled folding biplane aircraft | |
| CN112660381A (en) | Laminar flow control technology-based wing body fusion layout passenger plane layout method | |
| CN204264444U (en) | Joined wing configuration aircraft during high lift length boat | |
| CN106741919A (en) | A kind of fixed-wing unmanned plane of VTOL | |
| CN111017185B (en) | Laminar flow technology verification machine | |
| CN103523223B (en) | Transverse course control system and transverse course control method for flying wing configuration | |
| CN203558201U (en) | Airplane wing | |
| CN109677587B (en) | Control method of oblique wing aircraft capable of flying at high and low speeds | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN110775296A (en) | Design method for pressure center backward movement of reusable aerospace vehicle | |
| CN204507270U (en) | Novel high lift joined wing configuration aircraft | |
| CN105460202A (en) | Variable-wing unmanned aerial vehicle | |
| CN203199175U (en) | Aircraft with back flap |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C05 | Deemed withdrawal (patent law before 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130417 |