CN102975849A - Front detection type front wing leading edge flap structure - Google Patents
Front detection type front wing leading edge flap structure Download PDFInfo
- Publication number
- CN102975849A CN102975849A CN2012105392768A CN201210539276A CN102975849A CN 102975849 A CN102975849 A CN 102975849A CN 2012105392768 A CN2012105392768 A CN 2012105392768A CN 201210539276 A CN201210539276 A CN 201210539276A CN 102975849 A CN102975849 A CN 102975849A
- Authority
- CN
- China
- Prior art keywords
- wing
- front wing
- leading edge
- edge flap
- gear
- 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
- Toys (AREA)
Abstract
The invention aims to provide a front detection type front wing leading edge flap structure which comprises a leading edge flap, a front wing, a wing, an auxiliary wing, a flap, an airplane body, a vertical tail, a telescopic supporting rod, a gear and a power transmission shaft, wherein the leading edge flap is connected with the front wing; the vertical tail is connected with the rear end of the airplane body; the wing is connected with the airplane body; the auxiliary wing and the flap are arranged on the wing; the gear is arranged on the front wing; the telescopic supporting rod is connected with the front wing through the gear; and the leading edge flap is connected with the telescopic supporting rod. When an airplane is in a patrolling posture, the leading edge flap does not extend out; and when the airplane is in a landing posture, the gear drives the telescopic supporting rod to forwards extend out, so that the leading edge flap is driven to forwards extend out. According to the front detection type front wing leading edge flap structure, a complicated driving mechanism in the common leading edge wing is not required, the structure is simple and the leading edge flap can forwards extend out only by leading suction force of the front wing, and additional energy is not required; the lifting force of the front wing can be increased by circulation, and the head-up torque of the front wing can be increased; and therefore, the low-speed leveling capacity of the front wing, namely the landing capacity, is improved.
Description
Technical field
The present invention relates to aviation field, be specifically related to a kind of front spy formula front wing droope snoot structure.
Background technology
Front wing layout aircraft 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 landing (or the warship) degradation 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, and the resultant lift of full machine equally 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 multirole strike fighter Saab-37 of Sweden saab company (" thunder ") has installed the low speed trim ability that the front wing trailing edge flap improves the front wing layout, but the size of front wing itself is less, the trailing edge flap inflector assembly not only increases the complexity of manufacture difficulty and use, and has increased structural weight.
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 front spy formula front wing droope snoot structure.
The present invention is achieved in that a kind of front spy formula front wing droope snoot structure, comprise droope snoot, front wing, wing, aileron, wing flap, fuselage, vertical tail, telescopic strut, gear and power drive shaft, droope snoot is connected with front wing, vertical tail is connected with the rear end of fuselage, wing is connected with fuselage, and wing is provided with aileron and wing flap, and front wing is provided with gear, telescopic strut is connected with front wing by gear, and droope snoot is connected with telescopic strut.
When aircraft was in cruise attitude, droope snoot did not stretch out, and when aircraft was in landing attitude, the gear driven telescopic strut stretched out forward, stretched out forward thereby drive droope snoot.
The present invention does not need the complicated driver train of common droope snoot to drive, and simple in structure, only relying on the front wing leading-edge suction can stretch out forward, need not use additional-energy; Utilize circular rector to improve front wing lift, increase the front wing nose-up pitching moment, and then improve front wing layout low speed trim ability, i.e. throwing power.
Description of drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is the connection diagram of telescopic strut of the present invention and droope snoot.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing:
As shown in Figure 1 and Figure 2, a kind of front spy formula front wing droope snoot structure, comprise droope snoot 1, front wing 2, wing 3, aileron 4, wing flap 5, fuselage 6, vertical tail 7, telescopic strut 8, gear 9 and power drive shaft 10, droope snoot 1 is connected with front wing 2, and vertical tail 7 is connected with the rear end of fuselage 6, and wing 3 is connected with fuselage 6, wing 3 is provided with aileron 4 and wing flap 5, front wing 2 is provided with gear 9, and telescopic strut 8 is connected with front wing 2 by gear 9, and droope snoot 1 is connected with telescopic strut 8.
When aircraft was in cruise attitude, droope snoot 1 did not stretch out, and when aircraft was in landing attitude, gear 9 drove telescopic strut 8 and stretches out forward, stretches out forward thereby drive droope snoot 1.
The present invention does not need the complicated driver train of common droope snoot to drive, and simple in structure, only relying on the front wing leading-edge suction can stretch out forward, need not use additional-energy; Utilize circular rector to improve front wing lift, increase the front wing nose-up pitching moment, and then improve front wing layout low speed trim ability, i.e. throwing power.
Claims (2)
1. visit formula front wing droope snoot structure before one kind, comprise droope snoot (1), front wing (2), wing (3), aileron (4), wing flap (5), fuselage (6), vertical tail (7), telescopic strut (8), gear (9) and power drive shaft (10), it is characterized in that: droope snoot (1) is connected with front wing (2), vertical tail (7) is connected with the rear end of fuselage (6), wing (3) is connected with fuselage (6), wing (3) is provided with aileron (4) and wing flap (5), front wing (2) is provided with gear (9), telescopic strut (8) is connected with front wing (2) by gear (9), and droope snoot (1) is connected with telescopic strut (8).
2. a kind of front spy formula front wing droope snoot structure as claimed in claim 1, it is characterized in that: when aircraft is in cruise attitude, droope snoot (1) does not stretch out, when aircraft is in landing attitude, gear (9) drives telescopic strut (8) and stretches out forward, stretches out forward thereby drive droope snoot (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105392768A CN102975849A (en) | 2012-12-14 | 2012-12-14 | Front detection type front wing leading edge flap structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105392768A CN102975849A (en) | 2012-12-14 | 2012-12-14 | Front detection type front wing leading edge flap structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102975849A true CN102975849A (en) | 2013-03-20 |
Family
ID=47850282
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105392768A Pending CN102975849A (en) | 2012-12-14 | 2012-12-14 | Front detection type front wing leading edge flap structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102975849A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920870A (en) * | 2019-11-18 | 2020-03-27 | 北京航空航天大学 | Method for restraining rock motion of sharp-edge fuselage layout through leading edge flap |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101674980A (en) * | 2007-05-04 | 2010-03-17 | 空中客车营运有限公司 | High lift system on the airfoil of an aircraft |
| WO2010040501A2 (en) * | 2008-10-06 | 2010-04-15 | Airbus Operations Gmbh | Fore flap disposed on the wing of an aircraft |
| US20110036944A1 (en) * | 2008-03-28 | 2011-02-17 | Airbus Uk Limited | Slat deployment mechanism |
| US20110163204A1 (en) * | 2008-08-28 | 2011-07-07 | Airbus Operations Gmbh | High lift system for an aircraft with a high lift flap and method for adjusting the high lift flap |
| CN102405173A (en) * | 2009-04-23 | 2012-04-04 | 空中客车操作有限公司 | Aircraft assembly and spar |
-
2012
- 2012-12-14 CN CN2012105392768A patent/CN102975849A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101674980A (en) * | 2007-05-04 | 2010-03-17 | 空中客车营运有限公司 | High lift system on the airfoil of an aircraft |
| US20110036944A1 (en) * | 2008-03-28 | 2011-02-17 | Airbus Uk Limited | Slat deployment mechanism |
| US20110163204A1 (en) * | 2008-08-28 | 2011-07-07 | Airbus Operations Gmbh | High lift system for an aircraft with a high lift flap and method for adjusting the high lift flap |
| WO2010040501A2 (en) * | 2008-10-06 | 2010-04-15 | Airbus Operations Gmbh | Fore flap disposed on the wing of an aircraft |
| CN102405173A (en) * | 2009-04-23 | 2012-04-04 | 空中客车操作有限公司 | Aircraft assembly and spar |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920870A (en) * | 2019-11-18 | 2020-03-27 | 北京航空航天大学 | Method for restraining rock motion of sharp-edge fuselage layout through leading edge flap |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107176286B (en) | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle | |
| CN104276284B (en) | A kind of series type fan rotor aircraft layout | |
| CN203666966U (en) | Canard wing configuration aircraft provided with movable strakes | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN103072688A (en) | Tiltable four-rotor wing aircraft | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN103395492A (en) | STOL (short take off and landing) unmanned aerial vehicle with unpowered-driven rotor wing | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN202728571U (en) | Private aircraft | |
| CN104108464A (en) | Double-layer-wing aircraft | |
| CN108082471B (en) | Variant supersonic aircraft | |
| CN204264444U (en) | Joined wing configuration aircraft during high lift length boat | |
| CN102089209A (en) | Aircraft with at least two propeller drives arranged at a distance from one another in the span width direction of the wings | |
| CN203845012U (en) | Rotary flapping wing type driving airplane | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN105346725A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN209176908U (en) | A kind of rotor fixed-wing unmanned plane of composite drive | |
| CN204507270U (en) | Novel high lift joined wing configuration aircraft | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN102975849A (en) | Front detection type front wing leading edge flap structure | |
| CN205098475U (en) | Vertical take -off and landing aircraft | |
| CN203127139U (en) | Forepoling type front wing leading edge flap structure | |
| CN208419754U (en) | High speed per hour unmanned plane target drone | |
| CN202379089U (en) | Novel unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130320 |