CN106902522A - A kind of wing for being applied to ejection type soaring aeroplane model - Google Patents
A kind of wing for being applied to ejection type soaring aeroplane model Download PDFInfo
- Publication number
- CN106902522A CN106902522A CN201610925158.9A CN201610925158A CN106902522A CN 106902522 A CN106902522 A CN 106902522A CN 201610925158 A CN201610925158 A CN 201610925158A CN 106902522 A CN106902522 A CN 106902522A
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- China
- Prior art keywords
- wing
- stage casing
- ladder platform
- tip
- ejection type
- 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.)
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Classifications
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/02—Model aircraft
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/007—Collapsible wings, e.g. for catapult aeroplanes
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- Toys (AREA)
Abstract
The invention discloses a kind of wing for being applied to ejection type soaring aeroplane model, it is made up of wing stage casing and 2 wing tips, 2 wing tips are packed in the two ends in the wing stage casing respectively, the wing tip upper counterangle is 15~25 degree, wherein, wing tip trailing edge positioned at wing stage casing left end misplaces 0.8~1mm upwards in vertical direction, and the wing tip trailing edge positioned at wing stage casing right-hand member misplaces downwards 0.8~1mm in vertical direction；And it is formed with a ladder platform along the wing length direction in the upper surface of the wing, the ladder platform is located at position at chord length 45~55%, and the shoulder height of the ladder platform is 4% the 6% of chord length.Wing tip arranged in dislocation makes ejection type soaring aeroplane model vertical ascent, and rising trace is stable, and climb altitude can be more than 30 meters.Ladder platform of the invention makes wing form " step wing ", improves the lift-drag ratio of wing, increases the stalling angle of wing.
Description
Technical field
The invention belongs to scientific and technological activities vehicle technology field, relate in particular to one kind and be applied to ejection type soaring aeroplane mould
The wing of type.
Background technology
Ejection type soaring aeroplane model is as toy or begins to learn the teaching aid history very long of aviation knowledge.Traditional bullet
Penetrating aerodone and running into ascending air automatically to enter, and running into down current can not automatically leave, and be unfavorable for that aircraft is left a blank
The extension of time.
The content of the invention
In view of the shortcomings of the prior art, it is an object of the invention to provide a kind of machine for being applied to ejection type soaring aeroplane model
The wing, this kind of wing can improve the airborne period of ejection type soaring aeroplane model.
The purpose of the present invention is achieved by following technical proposals.
A kind of wing for being applied to ejection type soaring aeroplane model, is made up of, 2 wing tips wing stage casing and 2 wing tips
The two ends in the wing stage casing are packed in respectively, and the wing tip upper counterangle is 15~25 degree, wherein, positioned at the wing tip of wing stage casing left end
Trailing edge misplaces 0.8~1mm upwards in vertical direction, and the wing tip trailing edge positioned at wing stage casing right-hand member misplaces downwards in vertical direction
0.8~1mm；And a ladder platform is formed with along the wing length direction in the upper surface of the wing, the ladder platform is located at the wing
Position at chord length 45~55%, the shoulder height of the ladder platform is the 4%--6% of chord length.
In the above-mentioned technical solutions, the wing tip upper counterangle is 20 degree.
In the above-mentioned technical solutions, the wing stage casing is arranged on the fuselage by mortise and tenon mechanism.
In the above-mentioned technical solutions, the wing tip is packed in the two ends in the wing stage casing by way of bonding.
In the above-mentioned technical solutions, the ladder platform is located at the position where at chord length 50%.
Compared to prior art, beneficial effects of the present invention are：
1st, wing tip arranged in dislocation makes ejection type soaring aeroplane model vertical ascent, rising trace stabilization, climb altitude to surpass
Cross 30 meters.
2nd, ladder platform of the invention makes wing form " step wing ", improves the lift-drag ratio of wing, increases wing
Stalling angle.
3rd, the making of step wing is simple, time saving and energy saving, and the processing and control of aerofoil profile are accurate.
4th, step wing can reduce the weight of wing.
Brief description of the drawings
Fig. 1 is that the conventional airplane upper counterangle uses the folding wing of two-part one；
Fig. 2 is the rearview of wing of the invention；
Fig. 3 is the sectional view of ejection type soaring aeroplane model；
Fig. 4 is the partial enlarged drawing of Fig. 3；
Fig. 5 is the schematic diagram of rotating vortex behind ladder platform；
Fig. 6 is the wing of traditional ejection aerodone；
Fig. 7 is the dimensional structure diagram of ejection type soaring aeroplane model；
Fig. 8 takes off mode for tradition ejection aerodone；
Fig. 9 is the front view of wing of the invention.
Wherein, 1 is wing, and 1-1 is wing tip, and 1-2 is wing stage casing, and 1-3 is wing tip trailing edge, and 1-4 is wing tip leading edge, and 2 are
Fuselage, 3 is empennage, and 4 is ladder platform.
Specific embodiment
Technical scheme is further illustrated below in conjunction with the accompanying drawings.
As shown in Fig. 1~9, wing 1 (wing is horizontally mounted) and empennage 3 are installed on fuselage 2, are formed in the front portion of fuselage
There are the through hole (not shown) for adjusting ejection type soaring aeroplane model center of gravity and the hook portion for launching (not to show in figure
Go out).
The conventional airplane upper counterangle uses the folding wing of two-part one, as shown in figure 1, the assembling of this wing is easily askew, assembling is difficult
Degree is big.In the present invention, wing is installed using three-stage, and wing is made up of wing stage casing 1-2 and 2 wing tip 1-1, such as Fig. 2 institutes
Show, wing stage casing is arranged on fuselage by mortise and tenon mechanism, making the connection of wing and fuselage becomes very simple and accurate, connects by hand
Speed is connect to only need to 20 seconds；2 wing tips are packed in the two ends in wing stage casing by way of bonding respectively, and the wing tip upper counterangle is 20
Degree, the wing tip upper counterangle is installed using angle device is determined, and makes two wing tip upper counterangle errors less than 2~3 °, and uniformity is strong.
Wherein, wing tip (port wingtip) the trailing edge 1-3 positioned at wing stage casing left end misplaces 0.8~1mm upwards in vertical direction,
Wing tip (right flank point) trailing edge positioned at wing stage casing right-hand member misplaces downwards 0.8~1mm (backsight), wing tip leading edge 1- in vertical direction
4 not arranged in dislocation, the i.e. installations of wing tip leading edge alignment, as shown in Figure 9.The advantage of the arranged in dislocation of wing tip is：First, bullet can be made
Penetrate when formula aerodone model is launched and rolling counterclockwise occur, rolling counterclockwise makes ejection type soaring aeroplane model be produced in high-speed flight
The dead axle effect of raw gyro, makes ejection type soaring aeroplane model vertical ascent, and rising trace is stable, and climbing can be more than 30 meter.The
Two, when ascending air is run into, because the port wingtip angle of attack is small, right flank point meets larger, and right flank point is easier stall, slides ejection type
The right flank point of Xiang machine model sinks, and causes ejection type soaring aeroplane model to be spiraled to the right with smaller radius, it is easier to enter and rise
Air-flow.When down current is run into, the lift that port wingtip is produced is small, and the lift that right flank point is produced is big, makes aircraft rectilinear flight, this
Sample can just be escaped from down current, increase the airborne period of aircraft.And traditional ejection aerodone run into ascending air can not
Automatically enter, running into down current can not automatically leave, and be unfavorable for the extension of aircraft airborne period.
As shown in figure 3, being formed with a ladder platform 4 (in wing tip and wing tip along wing length direction in the upper surface of the wing
The upper surface of section is each formed with ladder platform), ladder platform is located at position, the shoulder height of ladder platform at chord length about 50%
It is the 4%-6% of chord length.Ladder platform makes wing form " step wing ", and step wing mainly utilizes the rank in wing chord
Rotating vortex behind halfpace makes the laminar flow of airfoil surface become turbulent flow, and the rotating vortex makes stream as the ball in bearing
Air-flow velocity through aerofoil surface does not subtract, and is difficult to be separated with aerofoil surface, so, can nearly all be produced from the leading edge of a wing to trailing edge
Lift reduces resistance, as shown in Figure 5.Lift increase, drag reduction improve the lift-drag ratio of wing, and the stall for increasing wing is met
Angle.In addition, the wing that step wing has the effect of traditional airfoil, traditional ejection aerodone typically uses the plano-convex wing
Type, as shown in Figure 6, it is necessary to conscientious careful polishing, loses time very much, precision is difficult to grasp, it is necessary in advance by the aerofoil profile of wing
Work it out, this needs grinding tool or unified production line, take very much energy, and wing of the invention makes simple, time saving and energy saving, the wing
The processing and control of type are accurate, easy, meanwhile, have the advantages that to reduce wing weight.The aircraft of this aerofoil profile is by tentative
The ejection aerodone of traditional airfoil can be better than.
Traditional ejection aerodone takes off mode typically using following several ways：1st, the ejection of fuselage level of incline, spirals
The mode of rising, 2, weight draw rudder mode, as shown in figure 8,3, movable elastic lifting rudder mode (" small flying dragon " launch
The model of an airplane is exactly this mode).Spiral rising deficiency be height be not easy improve；It is needs that weight draws the deficiency of rudder
Constant weight, is not suitable for small cataplane；The deficiency of movable elastic lifting rudder is that elasticity is not easily controlled, it is necessary to repeatedly
Conscientious debugging, and difficulty is very big.The ejection mode for being provided with the ejection type soaring aeroplane model of wing of the present invention is：Using a left side
Hand-held ejection rod, the right hand takes ejection type soaring aeroplane model (left hand is in the oblique upper of the right hand), (with ground) wide-angle (75~85 °)
Ejection mode takes off.Ejection type soaring aeroplane model when taking off almost vertically upward, while rolling counterclockwise, is changed into peak
Level is glided.Adopting take off in this way can make aircraft straight line vertically climb, almost can be by the energy of elastic all for carrying
The height of aircraft high, climb altitude is more than 30 meters.Highly increasing can also increase the chance that aircraft runs into overdraught simultaneously, and aircraft is again
Ascending air can actively be entered, two kinds of advantage superpositions, the airborne period of aircraft just can increase more.
Exemplary description is done to the present invention above, it should explanation, do not departed from the situation of core of the invention
Under, any simple deformation, modification or other skilled in the art can not spend the equivalent of creative work equal
Fall into protection scope of the present invention.
Claims (5)
1. a kind of wing for being applied to ejection type soaring aeroplane model, it is characterised in that by wing stage casing (1-2) and 2 wing tip (1-
1) constitute, 2 wing tips (1-1) are packed in the two ends of the wing stage casing (1-2) respectively, wing tip (1-1) upper counterangle is 15
~25 degree, wherein, wing tip (1-1) trailing edge positioned at wing stage casing (1-2) left end misplaces 0.8~1mm, position upwards in vertical direction
Misplaced downwards 0.8~1mm in vertical direction in wing tip (1-1) trailing edge of wing stage casing (1-2) right-hand member；And in the wing (1)
Upper surface is formed with a ladder platform (4) along the wing (1) length direction, the ladder platform (4) positioned at chord length 45~
Position at 55%, the shoulder height of the ladder platform (4) is the 4%--6% of chord length.
2. wing according to claim 1, it is characterised in that wing tip (1-1) upper counterangle is 20 degree.
3. wing according to claim 1, it is characterised in that the wing stage casing (1-2) is arranged on by mortise and tenon mechanism
On the fuselage (2).
4. wing according to claim 1, it is characterised in that the wing tip (1-1) is packed in institute by way of bonding
State the two ends of wing stage casing (1-2).
5. wing according to claim 1, it is characterised in that the ladder platform (4) is where at chord length 50%
Position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610925158.9A CN106902522A (en) | 2016-10-30 | 2016-10-30 | A kind of wing for being applied to ejection type soaring aeroplane model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610925158.9A CN106902522A (en) | 2016-10-30 | 2016-10-30 | A kind of wing for being applied to ejection type soaring aeroplane model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106902522A true CN106902522A (en) | 2017-06-30 |
Family
ID=59206678
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610925158.9A Withdrawn CN106902522A (en) | 2016-10-30 | 2016-10-30 | A kind of wing for being applied to ejection type soaring aeroplane model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106902522A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110624256A (en) * | 2019-10-18 | 2019-12-31 | 深圳市道通智能航空技术有限公司 | Aeromodelling glider |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2145633Y (en) * | 1992-12-30 | 1993-11-10 | 陈聪海 | Ejection toy glider |
| CN200963523Y (en) * | 2006-11-06 | 2007-10-24 | 厦门市嘉滨小学 | Device for manufacturing and detecting spotting hand-thrown model aeroplane |
| CN101254753A (en) * | 2007-02-28 | 2008-09-03 | 西北工业大学 | Solar pilotless plane |
| CN102837819A (en) * | 2012-07-22 | 2012-12-26 | 王运举 | Wing surface increased flow short distance takeoff and landing carrier-based airplane |
| CN203666968U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Negative dihedral aerofoil winglet structure |
| CN104174171A (en) * | 2013-05-21 | 2014-12-03 | 李文奇 | Model airplane non-adhesive wing table |
| CN206334349U (en) * | 2016-10-30 | 2017-07-18 | 天津师范大学 | Wing applied to ejection type soaring aeroplane model |
-
2016
- 2016-10-30 CN CN201610925158.9A patent/CN106902522A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2145633Y (en) * | 1992-12-30 | 1993-11-10 | 陈聪海 | Ejection toy glider |
| CN200963523Y (en) * | 2006-11-06 | 2007-10-24 | 厦门市嘉滨小学 | Device for manufacturing and detecting spotting hand-thrown model aeroplane |
| CN101254753A (en) * | 2007-02-28 | 2008-09-03 | 西北工业大学 | Solar pilotless plane |
| CN102837819A (en) * | 2012-07-22 | 2012-12-26 | 王运举 | Wing surface increased flow short distance takeoff and landing carrier-based airplane |
| CN104174171A (en) * | 2013-05-21 | 2014-12-03 | 李文奇 | Model airplane non-adhesive wing table |
| CN203666968U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Negative dihedral aerofoil winglet structure |
| CN206334349U (en) * | 2016-10-30 | 2017-07-18 | 天津师范大学 | Wing applied to ejection type soaring aeroplane model |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110624256A (en) * | 2019-10-18 | 2019-12-31 | 深圳市道通智能航空技术有限公司 | Aeromodelling glider |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170630 |
|
| WW01 | Invention patent application withdrawn after publication |