CN107521664A - A kind of anti-frozen structure of aircraft aileron angle compensation leading edge - Google Patents
A kind of anti-frozen structure of aircraft aileron angle compensation leading edge Download PDFInfo
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- CN107521664A CN107521664A CN201710574668.0A CN201710574668A CN107521664A CN 107521664 A CN107521664 A CN 107521664A CN 201710574668 A CN201710574668 A CN 201710574668A CN 107521664 A CN107521664 A CN 107521664A
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- aileron
- leading edge
- angle compensation
- aircraft
- compensation leading
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention relates to a kind of anti-frozen structure of aircraft aileron angle compensation leading edge, and the wing stabilization lower surface before the type general-purpose aircraft aileron angle compensation.The ice prevention structure of the present invention intercepts the super-cooling waterdrop in air-flow before gear ice bar, and the aileron angle compensation leading edge behind gear ice bar is no longer frozen, and aileron control icing clamping stagnation problem is resolved.Aileron angle compensation gear ice bar has the advantages that structure design is simple, in light weight, convenient for installation and maintenance, and does not influence the original aerodynamic characteristic of aircraft.
Description
Technical field
The invention belongs to airplane design technical field, more particularly to a kind of aileron angle compensation leading edge icing safeguard structure.
Background technology
Civil aircraft manufacturer is in order that designed aircraft has use range as big as possible, it will usually works as to seaworthiness
The seaworthiness license that office's application is flown in freezing environment, i.e. civil aircraft need the related icing seaworthiness promulgated according to aiMonhiness authority
The regulation of clause carries out icing seaworthiness checking.For the requirement for the seaworthiness clause for meeting and freezing relevant, civil aircraft generally requires
Icing protection is carried out in some key positions of body surface.Civil aircraft typically freeze protection position include the leading edge of a wing,
Horizontal tail leading edge and vertical fin leading edge, these positions are typically using the anti-icing design skill heated in body metal skin inner surface
Art pastes the designing technique that expandable rubber tube is inflated expansion deicing in body metal skin outer surface.In addition, fly
If also there is icing phenomenon in freezing environment in the control surfaces such as the aileron of machine, elevator and rudder during flight, and manipulate
When face icing may result in manipulation deflecting facet clamping stagnation, then control surface must also carry out icing protection.Aileron, the elevator of aircraft
The position for occurring freezing with control surface most probables such as rudders is angle compensation leading edge.Fig. 1 is given outside certain type general-purpose aircraft wing
The flat shape figure of section and aileron.When aileron zero deflection, aileron up/down surface is that fairing is continuous with wing up/down surface,
Aileron angle compensation leading edge is hided after wing stabilization above, as shown in Fig. 2 therefore awing remote front from origin
Stream will not be directly impinging aileron angle compensation leading edge.As seen from Figure 1, because aileron angle compensation leading edge is apart from aileron rotating shaft phase
To farther out, therefore when aileron deflects up or down around aileron rotating shaft, aileron angle compensation leading edge can substantially protrude machine above
The upper or lower surface of wing stabilization.Fig. 3 gives certain schematic diagram that type general-purpose aircraft aileron deflects down, it can be seen that aileron
Angle compensation leading edge substantially prominent wing stabilization lower surface above, therefore the free incoming in remote front can be directly impinging aileron
Leading edge.If when in the remote free incoming in front containing the super-cooling waterdrop that can cause to freeze, super-cooling waterdrop can be direct with air-flow
The aileron leading edge on prominent wing up/down surface is struck, causes aileron leading edge to freeze.Under normal circumstances, aileron leading edge with above
Wing stabilization have an about 10mm or so structure interval, to ensure aileron free deflection.When the icing of aileron leading edge is thick
When degree exceedes this structure interval width, the free deflection of aileron will be influenceed by freezing, i.e., there occurs aileron control icing clamping stagnation
Problem.Civil aircraft is awing not allow aileron control, elevator control and rudder control that clamping stagnation occurs；Therefore,
If civil aircraft manufacturer cannot ensure that aileron control, elevator control and rudder control are not in freeze in airplane design
During clamping stagnation, typically electricity can be pasted in aileron angle compensation leading edge, elevator angle compensation leading edge and rudder angle compensation leading edge outer surface
Heating film, prevent these positions from freezing.In aileron angle compensation leading edge, elevator angle compensation leading edge and rudder angle compensation leading edge peace
Dress electric heating film is the classical design method for preventing control surface icing clamping stagnation, and this method needs the power bus out of cabin
Special wire is drawn at place, over long distances through organism internal structure, finally with the electric heating film at above-mentioned control surface angle compensation
Connection power supply.The design method of this installation electric heating film can ensure that control surface angle compensation leading edge does not freeze, but add body
Construction weight and power consumption, and the easy aging of electric heating film and generation fault, add line service amount, because
The design method that this planemaker can take other more succinct in the conceived case prevents aileron, elevator and rudder
Angle compensation leading edge Deng control surface freezes.
The content of the invention
Goal of the invention
Solve the ice formation issues of aileron angle compensation leading edge, so as to eliminate aileron control icing catching phenomenon.
Technical scheme
Air freezing environment just refers in air containing liquid super-cooling waterdrop of the temperature less than 0 DEG C.Aircraft freezes in air
In environment during flight, super-cooling waterdrop once strikes body surface and will be attached to body surface immediately and be changed into solid-state
Ice；As super-cooling waterdrop constantly hits a certain surface of body, the icing on the body surface will constantly increase, until
Jeopardize flight safety.Undisturbed super-cooling waterdrop typically moves with the overall flow of air in air, 1 subcooled water
The diameter of drop is generally 0.02~0.05mm, and quality is about 4 × 10-9~7 × 10-8g；Air is mainly by nitrogen and oxygen group
Into, the average quality of 1 air molecule is 4.8 × 10-23G, therefore the quality of super-cooling waterdrop is about the 8 of air molecule quality
×10+13~2 × 10+15Times.If 1 triangle shelter is placed on a flat board, when the remote front containing super-cooling waterdrop
When crossing the triangle shelter following phenomenons can occur for horizontal free incoming：(1) due to the quality very little of air molecule, air
Windward slope of the molecule along triangle shelter can swerve after climbing to shelter top, be then close to triangle and block
The leeward slope of thing flows downward up to flat board, then is flowed backward along flatbed horizontal；(2) super-cooling waterdrop is initially and with air point
Son impacts the windward slope of triangle shelter, and a part of super-cooling waterdrop is directly impinged on the windward slope of triangle shelter,
And condense into the ice of solid-state；Another part super-cooling waterdrop is then as windward slope of the air molecule along triangle shelter climbs to screening
The top of block material, but the quality of super-cooling waterdrop is higher by the several magnitudes of air molecule quality, under the influence of centrifugal force super-cooling waterdrop
It can not possibly be swerved as air molecule, therefore super-cooling waterdrop will not be close to block after the top of shelter is crossed
The leeward slope of thing flows downward, but departs from the leeward slope forward downward flowing of shelter, and the region of numbering 6 is that super-cooling waterdrop is crossed
The position of flat board, that is, the ice forming locations on flat board are finally struck behind shelter top, and against shelter leeward slope
The region of flat board numbering 5 will not freeze.If by aileron angle compensation leading edge behind triangle shelter, flat board numbering 5
Region, then aileron angle compensation leading edge would not freeze, here it is aileron angle compensation gear ice bar design principle.Aileron angle compensation is kept off
Ice bar is actually to be arranged on wing lower surface, is inverted in the following table of flat board using flat board as line of symmetry equivalent to triangle shelter
Face, but its operation principle is identical.
Although the transversal profile of aileron angle compensation gear ice bar is a simple triangle, in order that gear ice bar has most
The effect of good interception super-cooling waterdrop, and the original aerodynamic characteristic of aircraft is influenceed minimum, it is necessary to keeping off ice bar transversal profile
It is triangular shaped and gear ice bar length optimize design.By using " Lagrange " Particles Moving in multiphase flow flow field
Equation analysis calculates 0.02~0.05mm of diameter super-cooling waterdrop around the movement locus after gear ice bar, draws the excellent of gear ice bar
It is as follows to change design conclusion：
1) gear ice bar triangular cross section windward slope angle is not to be exceeded 40 °；Windward slope angle more than 40 ° after aircraft fly
The increase of row resistance is more apparent；But windward slope angle can not be too small, otherwise triangle base size is elongated, makes gear ice bar size mistake
Greatly；Therefore the optimal design angle of gear ice bar triangular cross section windward slope should be close to 40 °.
2) keeping off ice bar triangular cross section leeward slope optimal design angle should be between 45 °~60 °；If leeward slope angle
Super-cooling waterdrop can be made together to be close to triangle leeward slope with air molecule less than 45 ° to flow downward, gear ice bar is lost interception
The effect of super-cooling waterdrop；Leeward slope angle can then make air molecule to be equally close to carry on the back also like super-cooling waterdrop if greater than 60 °
Wind slope flowed downward, i.e. air-flow is flowed through there occurs flow separation phenomenon after gear ice bar, and this can not only increase the flight resistance of aircraft,
And destroy the original aerodynamic characteristic of aircraft.
3) height for keeping off ice bar triangular cross section is the design parameter of most critical, and height more high gear ice effect is better, but
Gear ice bar size can become big, and the influence to the original aerodynamic characteristic of aircraft can also increase；It is computed analyzing, only need to keeps triangle
Height protrudes equal can be substantially assured that of both height of wing lower surface with aileron angle compensation leading edge and abutted behind gear ice bar
Aileron angle compensation leading edge is not hit by super-cooling waterdrop, i.e. aileron angle compensation leading edge will not freeze.
4) be computed analyzing, keep off ice bar length and aileron angle compensation open up to width keep it is isometric can basic guarantee aileron
Angle compensation leading edge entirely open up do not hit in the range of by super-cooling waterdrop, i.e. aileron angle compensation leading edge will not freeze.
A kind of anti-frozen structure of aircraft aileron angle compensation leading edge, including wing and aileron are specifically provided；Aileron, which rotates, to be connected
It is connected on wing, and gap is present between aileron angle compensation leading edge and trailing edge；Raised hide is formed on the aerofoil of wing
Structure is kept off, the barrier structure is located at the front of aileron angle compensation leading edge, is met for awing being blocked for aileron angle compensation leading edge
The cold airflow in face.
Further, described barrier structure section is triangular in shape.
Further, described barrier structure is formed at trailing edge position.
Further, the triangular cross section windward slope angle of the gear ice structure is 36.9 °, leeward slope angle is 53.1 °,
Top angle is 90 °.
Further, a height of 45mm of ice structure is kept off, the length for keeping off ice structure is 60mm.
Technique effect
Maximum icing thickness on the windward slope surface of the gear ice structure of the present invention reaches 100mm, but it is leeward to keep off ice structure
Aileron angle compensation leading edge surface behind slope is without icing, and aileron control is without icing catching phenomenon.In addition, without in icing atmospheric environment
Result of taking a flight test also indicate that：Install aileron angle compensation additional and keep off ice structure to the original aerodynamic characteristic of type general-purpose aircraft without influence.
Brief description of the drawings
Fig. 1 is the outer section of wing and aileron structural representation of prior art；
Fig. 2 is the outer section of wing and aileron structural representation of prior art；
Fig. 3 is the outer section of wing and aileron structural representation of the present invention；
Fig. 4 is the anti-icing schematic diagram of barrier structure；
Wherein：1 leading edge of a wing, 2 wing stabilizations, 3 aileron angle compensation leading edges, 4 aileron angle compensations, 5 aileron rotating shafts, 6 pairs
The wing, 7 barrier structures, 8 super-cooling waterdrop movement locus, 9 air molecule movement locus,.
Embodiment
A kind of anti-frozen structure of aircraft aileron angle compensation leading edge, including wing and aileron are provided；Aileron is rotatably connected on
On wing, and gap be present between aileron angle compensation leading edge and trailing edge；Projection is formed on the aerofoil of wing and blocks knot
Structure, the barrier structure are located at the front of aileron angle compensation leading edge, for being awing that aileron angle compensation leading edge is blocked head-on
Cold airflow；Described barrier structure section is triangular in shape；Described barrier structure is formed at trailing edge position；The gear ice structure
Triangular cross section windward slope angle be 36.9 °, leeward slope angle is 53.1 °, top angle is 90 °；It is a height of to keep off ice structure
45mm, the length for keeping off ice structure are 60mm.
Claims (5)
1. a kind of anti-frozen structure of aircraft aileron angle compensation leading edge, including wing and aileron；Aileron is rotatably connected on wing,
And gap be present between aileron angle compensation leading edge and trailing edge；Raised barrier structure is formed on the aerofoil of wing, the screening
Gear structure be located at the front of alieron angle compensation leading edge, for awing blocking cold airflow head-on for aileron angle compensation leading edge.
A kind of 2. anti-frozen structure of aircraft aileron angle compensation leading edge as claimed in claim 1, it is characterised in that：Described screening
It is triangular in shape to keep off structural section.
A kind of 3. anti-frozen structure of aircraft aileron angle compensation leading edge as claimed in claim 1 or 2, it is characterised in that：It is described
Barrier structure be formed at trailing edge position.
A kind of 4. anti-frozen structure of aircraft aileron angle compensation leading edge as claimed in claim 1 or 2, it is characterised in that：The gear
The triangular cross section windward slope angle of ice structure is 36.9 °, leeward slope angle is 53.1 °, top angle is 90 °.
A kind of 5. anti-frozen structure of aircraft aileron angle compensation leading edge as claimed in claim 1 or 2, it is characterised in that：Keep off ice
The a height of 45mm of structure, the length for keeping off ice structure are 60mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710574668.0A CN107521664A (en) | 2017-07-14 | 2017-07-14 | A kind of anti-frozen structure of aircraft aileron angle compensation leading edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710574668.0A CN107521664A (en) | 2017-07-14 | 2017-07-14 | A kind of anti-frozen structure of aircraft aileron angle compensation leading edge |
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| Publication Number | Publication Date |
|---|---|
| CN107521664A true CN107521664A (en) | 2017-12-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710574668.0A Pending CN107521664A (en) | 2017-07-14 | 2017-07-14 | A kind of anti-frozen structure of aircraft aileron angle compensation leading edge |
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| CN (1) | CN107521664A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86102063A (en) * | 1985-03-29 | 1986-09-24 | 福克公司 | The aileron of wing |
| CN102811907A (en) * | 2010-01-29 | 2012-12-05 | 吉凯恩航空服务有限公司 | Electrothermal heater mat |
| CN103048109A (en) * | 2012-11-28 | 2013-04-17 | 中国商用飞机有限责任公司 | Wing test element for ice wind tunnel of anti-icing system for aircraft wing |
| CN103153788A (en) * | 2010-09-28 | 2013-06-12 | 萨博公司 | Method and arrangement for de-icing a structural element |
-
2017
- 2017-07-14 CN CN201710574668.0A patent/CN107521664A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86102063A (en) * | 1985-03-29 | 1986-09-24 | 福克公司 | The aileron of wing |
| CN102811907A (en) * | 2010-01-29 | 2012-12-05 | 吉凯恩航空服务有限公司 | Electrothermal heater mat |
| CN103153788A (en) * | 2010-09-28 | 2013-06-12 | 萨博公司 | Method and arrangement for de-icing a structural element |
| CN103048109A (en) * | 2012-11-28 | 2013-04-17 | 中国商用飞机有限责任公司 | Wing test element for ice wind tunnel of anti-icing system for aircraft wing |
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Application publication date: 20171229 |
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| RJ01 | Rejection of invention patent application after publication |