CN206152341U - Launch formula glider model - Google Patents
Launch formula glider model Download PDFInfo
- Publication number
- CN206152341U CN206152341U CN201621150209.7U CN201621150209U CN206152341U CN 206152341 U CN206152341 U CN 206152341U CN 201621150209 U CN201621150209 U CN 201621150209U CN 206152341 U CN206152341 U CN 206152341U
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- CN
- China
- Prior art keywords
- wing
- empennage
- fuselage
- ejection type
- fin
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Abstract
The utility model discloses a launch formula glider model, include: fuselage and install wing and the fin on the fuselage, the wing comprises wing middle section and 2 wing tips, and 2 wing tips are adorned admittedly respectively and are in the both ends in wing middle section, the wing tip upper counterangle is 15~25 degrees, and the wing tip trailing edge that is located wing middle section left end is at vertical the direction 0.8~1mm that upwards misplaces, and the wing tip trailing edge that is located wing middle section right -hand member is at vertical the direction 0.8~1mm that misplaces downwards, and the upper surface at this wing is followed wing length direction is formed with the first -order halfpace, the fin comprises first fin and vertical second fin, and first fin uses the fuselage to use the horizontal plane not install on this fuselage as starting point rotatory 2~3 ground as the center pin, and the lower extreme of second fin is adorned with the upper surface of first fin admittedly, the side of second fin with the fuselage is adorned admittedly. The dislocation installation of wing tip makes launch formula glider model vertical rise, and lifting track is stable, and it highly can be above 30 meter to climb.
Description
Technical field
The utility model belongs to scientific and technological activities vehicle technology field, relates in particular to a kind of ejection type soaring aeroplane mould
Type.
Background technology
Ejection type soaring aeroplane model is as toy or begins to learn the very long history of teaching aid 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 prolongation of time.
The content of the invention
For the deficiencies in the prior art, the purpose of this utility model is to provide a kind of ejection type soaring aeroplane model, the bullet
Penetrating formula aerodone model can realize, automatically into ascending air, down current being left automatically.
The purpose of this utility model is achieved by following technical proposals.
A kind of ejection type soaring aeroplane model, including：Fuselage and wing and empennage on the fuselage, the machine
The wing is made up of wing stage casing and 2 wing tips, and 2 wing tips are packed in respectively the two ends in the wing stage casing, the wing tip upper counterangle
For 15～25 degree, wherein, the wing tip trailing edge positioned at wing stage casing left end misplaces upwards 0.8～1mm in vertical direction, positioned at wing
The wing tip trailing edge of stage casing right-hand member misplaces downwards 0.8～1mm in vertical direction；And in the upper surface of the wing along the wing length
Direction is formed with a ladder platform, and the ladder platform is located at position at chord length 45～55%, the step of the ladder platform
It is highly the 4%--6% of chord length；The empennage is made up of the first empennage and the second vertical empennage, first empennage
Axle rotates 2～3 ° of ground and is arranged on the fuselage with horizontal plane as starting point centered on the fuselage, the lower end of second empennage
It is fixedly mounted with the upper surface of first empennage, side and the fuselage of second empennage are fixedly mounted with.
In above-mentioned technical proposal, the wing tip upper counterangle is 20 degree.
In above-mentioned technical proposal, the wing stage casing is arranged on the fuselage by mortise and tenon mechanism.
In above-mentioned technical proposal, the wing tip is packed in the two ends in the wing stage casing by way of bonding.
In above-mentioned technical proposal, the ladder platform is located at the position being located at chord length 50%.
In above-mentioned technical proposal, it is formed with for adjusting ejection type soaring aeroplane model center of gravity in the front portion of the fuselage
Through hole.
In above-mentioned technical proposal, second empennage is located at the right side of the center line of first empennage.
In above-mentioned technical proposal, the left end of first empennage is located at the lower section of the right-hand member of first empennage.
In above-mentioned technical proposal, first empennage axle centered on the fuselage revolves counterclockwise by starting point of horizontal plane
Turn 2～3 ° of ground to be arranged on the fuselage.
Compared to prior art, the beneficial effects of the utility model are：
1st, the arranged in dislocation of wing tip makes ejection type soaring aeroplane model vertical ascent, and rising trace is stable, and climb altitude can be with
More than 30 meters.
2nd, ladder platform of the present utility model makes wing form " step wing ", improves the lift-drag ratio of wing, increases machine
The stalling angle of the wing.
3rd, the making of step wing is simple, time saving and energy saving, and the processing and control of aerofoil profile is accurate.
4th, step wing can reduce the weight of wing.
5th, the lift that the first empennage is produced is to left avertence, even if the afterbody of aircraft is to left avertence, the Airplane Nose Right of aircraft partially, is realized
The spiraling to the right of aircraft.
6th, empennage of the present utility model is avoided and is deflected to the right to make aircraft spiral by the second empennage, it is to avoid aircraft bullet
Penetrate attitude confusion when taking off to be difficult to adjust.
7th, ejection type soaring aeroplane model of the present utility model is easier into ascending air and is easier to escape lower sending down abnormally ascending
Stream, increases airborne period.
Description of the drawings
Fig. 1 is that the conventional airplane upper counterangle adopts the folding wing of two-part one；
Fig. 2 is the rearview of wing of the present utility model；
Fig. 3 is the sectional view of ejection type soaring aeroplane model of the present utility 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 of the present utility model；
Fig. 8 is the rearview of ejection type soaring aeroplane model of the present utility model；
Fig. 9 is the sectional view of empennage in ejection type soaring aeroplane model of the present utility model；
Figure 10 takes off mode for tradition ejection aerodone；
Figure 11 is the front view of wing of the present utility model.
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 3-1 is the second empennage, and 3-2 is the first empennage, and 4 is ladder platform.
Specific embodiment
The technical solution of the utility model is further illustrated below in conjunction with the accompanying drawings.
As shown in Fig. 1～11, including：Fuselage 2 and the wing on fuselage 1 (wing is horizontally mounted) and empennage 3,
The through hole (not shown) for adjusting ejection type soaring aeroplane model center of gravity is formed with the front portion of fuselage and for launching
Hook portion (not shown).
The conventional airplane upper counterangle adopts the folding wing of two-part one, as shown in figure 1, this wing assembly precision is not easy to carry
High, it is easy to fill askew, assembly difficulty is big.In the utility model, wing is installed using three-stage, and wing is by wing stage casing 1-2
With 2 wing tip 1-1 compositions, as shown in Fig. 2 wing stage casing is arranged on fuselage by mortise and tenon mechanism, the company of wing and fuselage is made
Connecing becomes very simple and accurate, and manual connection speed only needs to 20 seconds；2 wing tips are packed in respectively wing by way of bonding
The two ends in stage casing, the wing tip upper counterangle is 20 degree, and using angle device is determined the wing tip upper counterangle is installed, and is less than two wing tip upper counterangle errors
2～3 °, uniformity is strong.
Wherein, wing tip (port wingtip) the trailing edge 1-3 positioned at wing stage casing left end misplaces upwards 0.8～1mm in vertical direction,
Wing tip (right flank point) trailing edge positioned at wing stage casing right-hand member misplaces downwards 0.8～1mm (backsight) in vertical direction, wing tip leading edge 1-
4 not arranged in dislocation, the i.e. installations of wing tip leading edge alignment, as shown in figure 11.The advantage of the arranged in dislocation of wing tip is：First, can make
There is rolling counterclockwise when launching in ejection type soaring aeroplane model, and rolling counterclockwise makes ejection type soaring aeroplane model in high-speed flight
The dead axle effect of gyro is produced, ejection type soaring aeroplane model vertical ascent is made, rising trace is stable, and climbing can be more than 30 meter.
Second, when ascending air is run into, because the port wingtip angle of attack is little, right flank point meets larger, and right flank point is easier stall, makes ejection type
The right flank point of aerodone model sinks, and causes ejection type soaring aeroplane model to spiral to the right with less radius, it is easier to into upper
Rise air-flow.When down current is run into, the lift that port wingtip is produced is little, and the lift that right flank point is produced is big, makes aircraft rectilinear flight,
Thus can escape from down current, increase the airborne period of aircraft.And traditional ejection aerodone runs into ascending air not
Can automatically enter, running into down current can not automatically leave, and be unfavorable for the prolongation 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 at chord length about 50%, the shoulder height of ladder platform
For the 4%--6% of chord length.Ladder platform makes wing form " step wing ", and step wing is mainly utilized in wing chord
Rotating vortex behind ladder platform makes the laminar flow of airfoil surface become turbulent flow, and the rotating vortex makes as the ball in bearing
The air-flow velocity for flowing through aerofoil surface does not subtract, and is difficult to be separated with aerofoil surface, so, nearly all can produce from the leading edge of a wing to trailing edge
Raw lift reduces resistance, as shown in Figure 5.Lift increase, drag reduction improve the lift-drag ratio of wing, increase the stall of wing
The angle of attack.In addition, the wing that step wing has the effect of traditional airfoil, traditional ejection aerodone typically adopts the plano-convex wing
Type, as shown in fig. 6, needing conscientious careful polishing, loses time very much, and precision is difficult to grasp, and needs 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 present utility model makes simple, save time province
Power, the processing and control of aerofoil profile is accurate, easy, meanwhile, have the advantages that to reduce wing weight.The aircraft of this aerofoil profile is through examination
Test the ejection aerodone that performance is better than traditional airfoil.
Empennage is made up of the first empennage 3-2 and the second vertical empennage 3-1, the first empennage centered on fuselage axle with level
Face is packed on the fuselage (with the certain point at ejection type soaring aeroplane model rear as observation for 2～3 ° of ground of starting point rotate counterclockwise
Point), i.e., the left end of the first empennage is located at (oblique) lower section of the right-hand member of first empennage.Second empennage is located at the center of the first empennage
The right side of line.The lower end of the second empennage is fixedly mounted with the upper surface of the first empennage, and left surface and the fuselage of the second empennage are fixedly mounted with.Tradition
The helical fashion of aircraft typically makes aircraft turn spiral by adjustment direction rudder or aileron.This mode makes flying for aircraft
Row control becomes complicated, and state is difficult to analyze during ejection.In the utility model, as shown in figs. 7-9, the first empennage is with fuselage
Centered on axle be by the advantage that 2～3 ° of ground of starting point rotate counterclockwise are packed on fuselage of horizontal plane：Firstth, the first empennage is produced
Lift to left avertence, make the afterbody of aircraft to left avertence, the head of aircraft realizes spiraling to the right for aircraft just to right avertence；Second,
Avoid and deflect to the right to make aircraft spiral by the second empennage, it is to avoid attitude confusion is difficult to adjust when airplane catapult takes off.
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 the mode of rudder, as shown in Figure 10,3, mode (" little flying dragon " bullet of movable elastic lifting rudder
It is exactly this mode to penetrate the model of an airplane).Spiral rising deficiency be height be not easy improve；It is to need that weight draws the deficiency of rudder
Constant weight is wanted, is not suitable for little cataplane；The deficiency of movable elastic lifting rudder is that elasticity is not easily controlled, and is needed many
Secondary conscientious debugging, and difficulty is very big.It is in the ejection mode of ejection type soaring aeroplane model of the present utility model：Using left hand
Ejection rod is held, 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 °) bullet
The mode of penetrating is taken off.Ejection type soaring aeroplane model of the present utility model when taking off almost vertically upward, while counterclockwise rolling, arrives
Peak is changed into level gliding.Ejection type soaring aeroplane model of the present utility model to be adopted take off in this way can make aircraft straight line
Vertically climb, almost can be by the energy of elastic all for improving the height of aircraft, climb altitude is more than 30 meters.Highly increase same
When can also increase the chance that aircraft runs into overdraught, aircraft can actively enter ascending air again, two kinds of advantages superpositions, and aircraft is stayed
Just can increase more between space-time.
Exemplary description is done to the utility model above, it should explanation, without departing from core of the present utility model
In the case of the heart, any simple deformation, modification or other skilled in the art can not spend creative work etc.
Protection domain of the present utility model is each fallen within replacing.
Claims (9)
1. a kind of ejection type soaring aeroplane model, including：Fuselage (2) and wing (1) and empennage on the fuselage (2)
(3), it is characterised in that the wing (1) is made up of wing stage casing (1-2) and 2 wing tips (1-1), 2 wing tips (1-1)
The two ends of the wing stage casing (1-2) are packed in respectively, and wing tip (1-1) upper counterangle is 15～25 degree, wherein, positioned at wing stage casing
(1-2) wing tip (1-1) trailing edge of left end misplaces upwards 0.8～1mm in vertical direction, positioned at the wing of wing stage casing (1-2) right-hand member
Sharp (1-1) trailing edge misplaces downwards 0.8～1mm in vertical direction；And in the upper surface of the wing (1) along the wing (1) length
Direction is formed with a ladder platform (4), ladder platform (4) position at chord length 45～55%, the ladder platform
(4) shoulder height is the 4%--6% of chord length；The empennage (3) is by the first empennage (3-2) and the second vertical empennage
(3-1) constitute, first empennage (3-2) axle centered on the fuselage (2) rotates 2～3 ° of ground and installs with horizontal plane as starting point
On the fuselage (2), the lower end of second empennage (3-1) is fixedly mounted with the upper surface of first empennage (3-2), and described second
The side of empennage (3-1) is fixedly mounted with the fuselage (2).
2. ejection type soaring aeroplane model according to claim 1, it is characterised in that wing tip (1-1) upper counterangle is 20
Degree.
3. ejection type soaring aeroplane model according to claim 1, it is characterised in that the wing stage casing (1-2) passes through the fourth of the twelve Earthly Branches
Tenon mechanism is arranged on the fuselage (2).
4. ejection type soaring aeroplane model according to claim 1, it is characterised in that the wing tip (1-1) is by bonding
Mode is packed in the two ends of the wing stage casing (1-2).
5. ejection type soaring aeroplane model according to claim 1, it is characterised in that the ladder platform (4) is positioned at chord-length
Spend the position being located at 50%.
6. ejection type soaring aeroplane model according to claim 1, it is characterised in that formed in the front portion of the fuselage (2)
There is the through hole for adjusting ejection type soaring aeroplane model center of gravity.
7. ejection type soaring aeroplane model according to claim 1, it is characterised in that second empennage (3-1) is located at institute
State the right side of the center line of the first empennage (3-2).
8. ejection type soaring aeroplane model according to claim 1, it is characterised in that the left end of first empennage (3-2)
Positioned at the lower section of the right-hand member of first empennage (3-2).
9. ejection type soaring aeroplane model according to claim 1, it is characterised in that first empennage (3-2) is with described
Axle is arranged on the fuselage (2) by 2～3 ° of ground of starting point rotate counterclockwise of horizontal plane centered on fuselage (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621150209.7U CN206152341U (en) | 2016-10-30 | 2016-10-30 | Launch formula glider model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621150209.7U CN206152341U (en) | 2016-10-30 | 2016-10-30 | Launch formula glider model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206152341U true CN206152341U (en) | 2017-05-10 |
Family
ID=58655598
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621150209.7U Expired - Fee Related CN206152341U (en) | 2016-10-30 | 2016-10-30 | Launch formula glider model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206152341U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106914021A (en) * | 2016-10-30 | 2017-07-04 | 天津师范大学 | A kind of ejection type soaring aeroplane model |
-
2016
- 2016-10-30 CN CN201621150209.7U patent/CN206152341U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106914021A (en) * | 2016-10-30 | 2017-07-04 | 天津师范大学 | A kind of ejection type soaring aeroplane model |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170510 Termination date: 20191030 |