CN105251216B - A kind of small aircraft - Google Patents
A kind of small aircraft Download PDFInfo
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- CN105251216B CN105251216B CN201510759025.4A CN201510759025A CN105251216B CN 105251216 B CN105251216 B CN 105251216B CN 201510759025 A CN201510759025 A CN 201510759025A CN 105251216 B CN105251216 B CN 105251216B
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 8
- 229910052799 carbon Inorganic materials 0.000 description 8
- 239000000835 fiber Substances 0.000 description 8
- 239000000123 paper Substances 0.000 description 8
- 238000000465 moulding Methods 0.000 description 5
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- 238000005516 engineering process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000002356 single layer Substances 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 240000007182 Ochroma pyramidale Species 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
The invention discloses a kind of small aircrafts, including fuselage and two wings being arranged symmetrically, fuselage and wing are integrally formed, and the aerofoil support tube assembly for being used to support aerofoil is arranged on each wing, wing is equipped with propeller power assembly, and fuselage is equipped with control assembly.The present invention has the advantages that housing construction is simple, is integrally formed convenient for making, light-weight, intensity is high, rigidity is high, has good flight efficiency, can bring splendid flight experience to user.
Description
Technical field
Present invention relates generally to model plane technical fields, and in particular to a kind of small aircraft.
Background technology
Paper helicopter is a kind of papery aircraft that people are made with a thin paper, previous paper in pervious narrow sense defines
Aircraft can only hand-thrown fly in the air several seconds, and be unable to control.With the prosperity of science and technology, thought of people, the continuous of technology change
Into the definition of present paper helicopter is no longer limited only to papery aircraft, but slowly evolves into and possess the small of different materials making
Type aircraft substitutes papery aircraft.The small aircraft of these novel paper helicopter formulas is widely used, can be used for model plane primary
Train, photography of taking photo by plane, investigation etc..
The small aircraft of existing paper helicopter formula has following technical problem：
（1）Existing most small aircraft is made of cardboard, cork wood, kt plates.The aircraft manufacturing process made in this way
It is unable to one-pass molding, not only cannot directly make the shape of paper helicopter, shape must be formed by multiple adhering components, this to fly
Row device manufacture difficulty is big, and time-consuming；Especially in flight course it cannot be guaranteed that adhering part intensity and structure intensity, ten thousand
One falls off in flight course, it is easy to which aircraft air crash reaches not for a user when encountering barrier also not crashworthiness, cracky
It is experienced to flight optimization.
（2）Existing most small aircraft is unstable because structure design is unreasonable or rigidity not enough causes to fly, and holds
Aircraft vibrations are easily caused, motor is caused to swing up and down, and then upset air-flow, finally so that aircraft is from maintaining steady course to push away
Power is to give one good flight experience of user.
Therefore, a kind of small aircraft how is made, makes it that can not only be convenient for making, and light-weight, high intensity, height
Rigidity has good flight efficiency, brings the splendid flight experience of user, has become a problem urgently to be resolved hurrily.
Invention content
Technical problem solved by the invention is：In view of the problems of the existing technology, a kind of housing construction letter is provided
It is single, can be integrally formed convenient for make and light-weight, high intensity, high rigidity, there is good flight efficiency, can be to user
Bring the small aircraft of splendid flight experience.
In order to solve the above technical problems, the present invention uses following technical scheme：
A kind of small aircraft, including fuselage and two wings being arranged symmetrically, the fuselage and wing are integrally formed, often
The aerofoil support tube assembly for being used to support aerofoil is arranged on a wing, it is total that the wing is equipped with propeller power
At the fuselage is equipped with control assembly.
As a further improvement on the present invention, the aerofoil support tube assembly includes a main stay tube and two or more
Secondary support tube, the main stay tube is parallel and close to the junction of fuselage and wing arrangement, two or more the secondary support tubes
It is arranged on aerofoil surface.
As a further improvement on the present invention, two wings are in triangle aerofoil profile, and the secondary support tube is two, institute
It states first support tube to arrange at the leading edge of a wing of wing, trailing edge of described second support tube close to wing
Place's arrangement.
As a further improvement on the present invention, two wings are in triangle aerofoil profile, and the secondary support tube is two, institute
First time support tube and main stay tube are stated in the setting of the angles of 35 o~45, the angle is towards heading, described second
One end of secondary support tube is connect with the midpoint of first support tube, and the other end of described second support tube is close to wing
It is arranged at wing tip.
As a further improvement on the present invention, two wings are in triangle aerofoil profile, and the secondary support tube is three, institute
It states first support tube to arrange at the leading edge of a wing of wing, trailing edge of described second support tube close to wing
Place's arrangement, one end of the third root time support tube and first support tube vertical connection, the third root time support tube
The other end is arranged at the tail portion of fuselage.
As a further improvement on the present invention, each direction of the wing from fuselage towards wing tip raises up, and raise up angle
Degree is 1o~10o, and inclined winglet upward is equipped at the wing tip of each wing.
As a further improvement on the present invention, the leading edge of each wing includes first leading edge of a wing and the second wing
Leading edge, angle is 35 o~45 between two first leading edges of a wing at the head, each second leading edge of a wing
Angle of sweep is 50o~60o.
As a further improvement on the present invention, the empennage of protrusion, the empennage are equipped at the rear of each wing
It tilts upwards, forms the first recessed portion between the empennage and winglet, be all provided with that there are one propellers on each empennage
Power assembly.
As a further improvement on the present invention, the second recessed portion, second recessed portion are equipped between described two empennages
Interior to be equipped with aircraft geometrical clamp, the aircraft geometrical clamp includes the fuselage fixed part being connected and two wing support portions to raise up,
A wing clamping part is respectively provided on the wing support portion, the angle degree between two wing support portions is equal to two machines
Angle degree between the wing, when fixed, the fuselage is inserted into fuselage fixed part, and correspondence is clamped in two to two wings respectively
Between a wing support portion and wing clamping part.
As a further improvement on the present invention, the fuselage, wing and aerofoil support tube assembly are carbon fibre material system
At.
As a further improvement on the present invention, the head protective shell being detachably connected, institute are equipped at the head of the fuselage
It states control assembly to be installed in head protective shell, camera mounting hole, GPS mounting holes and electricity is installed on the head protective shell
Source switch.
As a further improvement on the present invention, the front end of the head protective shell is equipped with buffer part.
Compared with the prior art, the advantages of the present invention are as follows：
（1）Fuselage and wing integrated molding are made, improve the rigidity of small aircraft by the small aircraft of the present invention
And stability；Meanwhile the aerofoil support tube assembly for being used to support aerofoil is also arranged on each wing, solve aircraft
Light weight but the inadequate contradiction of rigidity so that the rigidity of frivolous wing greatly enhances, and is not only hardly damaged, and is flying
It will not occur to shake and cause aircraft unstable in journey so that not only there is this small aircraft body to be integrally formed, convenient for system
The advantages of making also has the advantages that light-weight, high intensity, high rigidity；In conjunction with excessively to the preferred arrangement of airframe components so that this is small
Type aircraft obtains good aerodynamic arrangement, and flight is more stablized, and user can obtain splendid flight experience.
（2）The small aircraft of the present invention, structure design is simple, rationally, science, pass through and the arrangement of airframe components carried out
Optimization, such as to aerofoil support tube assembly position, wing setting, the wing upper counterangle, the winglet elevation angle, empennage, aircraft
Geometrical clamp etc. is a series of to carry out specific scientific offering so that the moulding of this small aircraft is unique, beautiful, while having very
Good aerodynamic arrangement, flight attitude is graceful, flight stability, has good flight efficiency, it is splendid further to bring user
Flight experience.
Description of the drawings
Fig. 1 is the stereochemical structure principle schematic of small aircraft of the present invention.
Fig. 2 is the plan structure principle schematic of small aircraft of the present invention.
Fig. 3 be small aircraft of the present invention in embodiment 1 look up principle schematic diagram.
Fig. 4 be small aircraft of the present invention in example 2 look up principle schematic diagram.
Fig. 5 be small aircraft of the present invention in embodiment 3 look up principle schematic diagram.
Fig. 6 is the Facad structure principle schematic of small aircraft of the present invention.
Fig. 7 is the sectional structure principle schematic of small aircraft propeller power assembly of the present invention.
Fig. 8 is the plan structure principle schematic of small aircraft propeller power assembly of the present invention.
Fig. 9 is the stereochemical structure principle schematic of small aircraft aircraft geometrical clamp of the present invention.
Figure 10 is the Facad structure principle schematic of small aircraft aircraft geometrical clamp of the present invention
Figure 11 is the side structure principle schematic of small aircraft aircraft geometrical clamp of the present invention.
Figure 12 is the stereochemical structure principle schematic of small aircraft head protective shell of the present invention.
Figure 13 is the plan structure principle schematic of small aircraft head protective shell of the present invention.
Marginal data：
1, head protective shell；11, camera mounting hole；12, GPS mounting holes；13, power switch；14, buffer part；2, machine
Body；3, wing；31, winglet；32, first leading edge of a wing；33, second leading edge of a wing；34, empennage；4, aerofoil support tube group
Part；41, main stay tube；42, secondary support tube；5, aircraft geometrical clamp；51, fuselage fixed part；52, wing support portion；53, wing presss from both sides
Hold portion；6, propeller power assembly；61, motor cabinet；611, preceding engine base；612, rear engine base；62, motor；63, output shaft；64, small
Gear；65, gear wheel；66, propeller；67, sliding bearing；68, plug is limited；7, control assembly；8, the first recessed portion；9,
Two recessed portions.
Specific implementation mode
Below in conjunction with specific embodiments and the drawings, invention is further described in detail.
As shown in figure 1 to figure 13, the present invention provides a kind of small aircraft, including fuselage 2 and two machines being arranged symmetrically
The wing 3, fuselage 2 and wing 3 are integrally formed, and the aerofoil support tube assembly 4 for being used to support aerofoil, machine are arranged on each wing 3
The wing 3 is equipped with propeller power assembly 6, and fuselage 2 is equipped with control assembly 7.
Fuselage 2 and the integrated molding of wing 3 are made the present invention, and integrally formed mode is convenient for the making of small aircraft,
The shape of small aircraft can directly be produced；Particular, it is important that this mode ensure that it is most heavy as small aircraft
The three big components wanted（Fuselage 2 and two wings 3）Between bonding strength, improve the rigidity and stabilization of small aircraft
Property.Further, it is well known that weight is particularly important for small aircraft, in order to mitigate itself weight of small aircraft
Amount, people aircraft components can be done as possible it is thin, with reduction with material mitigate weight；But frivolous wing but there are rigidity
Low, flimsy problem, while frivolous wing be easy to cause vibrations, destroys pneumatically, causes to fly unstable, cannot give and use
One good flight experience of person.To solve this technical problem, fuselage 2 and wing 3 made of being integrally formed by the present invention
Meanwhile the aerofoil support tube assembly 4 for being used to support aerofoil is also arranged on each wing 3.Aerofoil supports tube assembly 4 can
The supporting role of reinforcing rib is played, will not only increase very much the weight of small aircraft, but also can be carried out to frivolous 3 aerofoil of wing
Support so that the rigidity of frivolous wing 3 greatly enhances, and is not only hardly damaged, and will not be shaken in flight course
And cause aircraft unstable, splendid flight experience can be brought to user.Fuselage 2 and the integrally formed design of wing 3 are again
In addition on wing 3 be arranged aerofoil support tube assembly 4 mode so that this small aircraft solve well light weight but just
Spend inadequate contradiction so that this small aircraft not only has the advantages that body is integrally formed, convenient for making, and also has weight
Gently, the advantages of high intensity, high rigidity.To obtain more preferably flight experience, while taking above structure, the present invention is also to machine
The arrangement of body component optimizes, and propeller power assembly 6 is arranged at wing 3, and control assembly 7 is arranged at fuselage 2,
This set balances the whole center of gravity of small aircraft well so that and this small aircraft obtains good aerodynamic arrangement,
Flight is more stablized, and user can obtain splendid flight experience.
Further, in the preferred embodiment, aerofoil support tube assembly 4 includes time of a main stay tube 41 and two or more
Support tube 42, main stay tube 41 is parallel and close to the junction of fuselage 2 and wing 3 arrangement, two or more 42 cloth of secondary support tube
It is placed on 3 aerofoil of wing.Although being integrally formed, fuselage 2 and two wings 3 be after all the most important of aircraft, volume most
Bear very big active force in the junction of three big components, fuselage 2 and two wings 3.Aerofoil cloth of the present invention in wing 3
The secondary support tube 42 for setting two or more while being specially supported to aerofoil, is arranged in the junction of fuselage 2 and wing 3 and is led
Support tube 41,41 length of main stay tube are preferably equal to the length of the junction of fuselage 2 and two wings 3, and main stay tube 41 exists
While being supported to 3 aerofoil of wing, also the junction of wing 3 and fuselage 2 is supported, further ensures fuselage 2
With being reliably connected for wing 3.Pass through this unique layout, the rigidity of the entire body of general warranty small aircraft.
The specific arrangement form that tube assembly 4 is supported about aerofoil, herein proposes three kinds of preferred embodiments, it should be pointed out that
It is that under the inspiration of above structure, protection scope of the present invention is not limited in following three kinds of embodiments：
Embodiment 1：As shown in figure 3, two wings 3 of the present embodiment are in triangle aerofoil profile, arranged on each wing 3
Time support tubes 42 of a piece main stay tube 41 and two, main stay tube 41 arrange parallel and close to the junction of fuselage 2 and wing 3,
First time support tube 42 is arranged at the leading edge of a wing of wing 3, trailing edge of second support tube 42 close to wing 3
Place's arrangement.
Embodiment 2：As shown in figure 4, the present embodiment 2 is only that twice support tubes 42 with not existing together for above-described embodiment 1
Arrangement, in the present embodiment, first time support tube 42 is with main stay tube 41 in the setting of the o angles of 35 o~45, angle
Towards heading, one end of second support tube 42 is connect with the midpoint of first support tube 42, second support
The other end of pipe 42 is arranged at the wing tip of wing 3.
Embodiment 3：As shown in figure 5, the difference of the present embodiment 3 and above-described embodiment 2 be in：The quantity of secondary support tube 42
And its arrangement, in the present embodiment, secondary support tube 42 is three, wing of first support tube 42 close to wing 3
Edge arranges that second time support tube 42 arrange at the trailing edge of wing 3, one end of third root time support tube 42 and
The other end of first 42 vertical connection of support tube, third root time support tube 42 is arranged at the tail portion of fuselage 2.
It should be noted that although the wing 3 of above-mentioned three kinds of preferred embodiments is all triangle aerofoil profile, in above structure
Under inspiration, those skilled in the art easily can expect taking the aerofoil profile of other modes or can easily think
To taking other arrangements to be arranged aerofoil support tube assembly 4 on aerofoil, this should all belong to the guarantor of the present invention
Protect range.
Further, in the preferred embodiment, direction of each wing 3 from fuselage 2 towards wing tip raises up, and the angle that raises up is
1o~10o（It is preferred that 6o）, inclined winglet 31 upward is equipped at the wing tip of each wing 3, and the leading edge of each wing 3 is equal
Including first leading edge of a wing 32 and second leading edge of a wing 33, angle is 35 between two first leading edges of a wing 32 at head
O~45o, each second leading edge of a wing, 33 angle of sweep is 50o~60o.It is arranged in this way, the form of aircraft is more excellent
U.S., while this small aircraft being made to obtain more good aerodynamic arrangement, flight is more stablized, and user can obtain splendid flight
Experience.
Further, in the preferred embodiment, the empennage 34 of protrusion is equipped at the rear of each wing 3, empennage 34 is upward
Tilt, the first recessed portion 8 is formed between empennage 34 and winglet 31, be all provided on each empennage 34 there are one propeller power it is total
At 6.By the way that the die surface at 3 rear of wing is done camber, by 3 rear of wing from tablet become having camber to updip
Oblique aerofoil profile forms acclivitous empennage 34 at the rear of wing 3.Empennage 34 is used for increasing slope of lift curve, carries
The lift of high wing 3 further increases the Lateral static stability of small aircraft.I.e.：Since aircraft lift center is flying
After row thinks highly of the heart, during aircraft flight, centre of lift can give center of gravity one torque of bowing, and aircraft is made to fly downwards,
And the empennage 34 that the upper counterangle is done in aircraft tail portion can just balance bow torque of the centre of lift to center of gravity.At the same time,
The empennage 34 of straight forming can reinforce the rigidity at this and intensity here, and empennage 34 is mounted on convenient for propeller power assembly 6
On, ensure the stability of motor 62.Due to the plank being integrated between empennage 34 and winglet 31, in order to reach the upper of the two
Reverse gantry will certainly do an airfoil between them, and the setting of airfoil can increase movable surface area, to lose course
Power.To solve this technical problem, the present invention carries out subtracting material between empennage 34 and winglet 31, that is, forms the first recess
Portion 8.
As shown in Figure 7 and Figure 8, further, in the preferred embodiment, propeller power assembly 6 includes motor cabinet 61 and sets
It is equipped with pinion gear 64 in the rotary shaft of motor 62 and output shaft 63 on motor cabinet 61, motor 62, output shaft 63 is equipped with big
Gear 65 and propeller 66, pinion gear 64 is connected with gear wheel 65 so that motor 62 drives propeller 66 to rotate.Output shaft 63 is logical
It crosses sliding bearing 67 to be inserted into motor cabinet 61, one end that output shaft 63 is inserted into motor cabinet 61 is additionally provided with limit plug 68.Motor
Seat 61 is composed of preceding engine base 611 and rear engine base 612, and the surface of preceding engine base 611 is arc-shaped, plays the role of shunting, subtracts
Few resistance；Driving group and the setting of deceleration group are integral by engine base 612 afterwards, i.e.,：Motor 62 is arranged in the inside of rear engine base 612,
After output shaft 63 is inserted by sliding bearing 67 in engine base 612, the rotation of motor 62 simultaneously drives propeller 66 to revolve by output shaft 63
Turn；The effect of limit plug 68 on output shaft 63 is that limitation output shaft 63 moves left and right under high rotating speed, high thrust, to not
It can influence flight stability performance.By by driving group and reduction combinations and being arranged on motor cabinet 61, reduce the space occupied,
The weight for alleviating small aircraft improves cruise duration and stability.
As shown in Fig. 2, Fig. 9, Figure 10, Figure 11, further, in the preferred embodiment, second is equipped between two empennages 34
Recessed portion 9, the second recessed portion 9 are interior equipped with aircraft geometrical clamp 5.Since wing 3 itself has certain upper counterangle when die sinking
（Best angle is 6 °）, it is to enhance the rigidity of wing 3, but aerofoil supports tube assembly 4 that setting aerofoil, which supports the purpose of tube assembly 4,
With certain weight, wing 3 can be made to generate certain deformation, cause wing 3 that cannot maintain the best elevation angle, so by setting
Aircraft geometrical clamp 5 is set, the aerofoil of fuselage 2 and wing 3 is inserted into fixation respectively, it is ensured that fuselage 2 keeps former with 3 aerofoil of wing
Begin the best elevation angle.
The implementation principle of the concrete structure of aircraft geometrical clamp 5 is as follows：Aircraft geometrical clamp 5 includes the fuselage fixed part being connected
51 and two wing support portions 52 to raise up, a wing clamping part 53, two wings supports are respectively provided on wing support portion 52
Angle degree between portion 52 is equal to the angle degree between two wings 3, and when fixed, fuselage 2 is inserted into fuselage fixed part 51, and two
Correspondence is clamped between two wing support portions 52 and wing clamping part 53 a wing 3 respectively so that wing support portion 52 is to machine
3 aerofoil of the wing is supported, to keep the original best elevation angle.
Further, in the preferred embodiment, fuselage 2, wing 3 and aerofoil support tube assembly 4 are that carbon fibre material is made.
Carbon fibre material has the characteristics that high intensity, high-modulus, rub resistance, using aircraft made of this material than homogenous quantities its
The advantages of he will have easy processing, thickness thin by aircraft, small, impact resistant, rub resistance, this can bring good to user
Flight experience.
But it is important to note that it is not that only can produce and can be brought to user using this material
The miniaturization aircraft of good flight experience.This is because：Although the miniaturization aircraft that the carbon fiber of multilayer makes can
One-pass molding ensure that the shape and rigidity of aircraft, but since carbon fibre material itself proportion is than materials such as cork wood, kt plates
Also heavy, itself thickness and weight can largely effect on the climb rate and the flight time of the aircraft of miniaturization, cannot give and use
One good flight experience of person；And if being fabricated to the carbon fibre material paper helicopter of single layer, although paper helicopter itself is thin, weight
Gently, but the carbon fibre material poor rigidity of single layer, aircraft also can not fly substantially, not talk flight time and flight experience more.
And if fuselage using the present invention 2 and wing 3 are integrally formed, the aerofoil branch being used to support are arranged on wing 3
The production method of stay tube component 4 then can just be well understood that certainly above-mentioned technical problem：It will using the carbon fibre material of high intensity
Fuselage 2 and wing 3 are integrally formed, and wing 3 is made of the carbon fibre material of single layer, to mitigate the weight of wing 3；Meanwhile
Setting is used to support the aerofoil support tube assembly 4 of aerofoil on wing 3, and aerofoil support tube assembly 4 is made of carbon fiber pipe, its own
Weight will not be very heavy, and frivolous aerofoil can be supported well, reinforce the rigidity of frivolous aerofoil.To sum up institute
It states, by using the design of the present invention, producer can take many different lightweighting materials to fly for making this miniaturization
Row device, though solving the problems, such as that the light rigidity of aircraft weight made of light basis weight material is inadequate well so that flight is thought highly of
Amount is light, rigidity is strong, can obtain good flight efficiency, operator can obtain good flight experience.
Further, in the preferred embodiment, the head protective shell 1 being detachably connected, control group are equipped at the head of fuselage 2
Part 7 is installed in head protective shell 1, and camera mounting hole 11, GPS mounting holes 12 and power supply are installed on head protective shell 1 and is opened
13 are closed, the front end of head protective shell 1 is equipped with buffer part 14.
As shown in Figure 12 and Figure 13, head protective shell 1 is made of pc materials, is divided into removable two half shell, is worked as control
After component 7 processed installs, two half shells are closed to form head protective shell 1, then tightened with screw and nut.On head protective shell 1
Equipped with head mounting groove 15 and fuselage mounting groove 16, when assembly, chain-drive section is inserted into head mounting groove 15, fuselage 2 is located at fuselage
In mounting groove 16 and it is fixedly connected, the lower section of head protective shell 1 is installed with camera mounting hole 11, GPS mounting holes 12, in order to
Information is shot with video-corder when flight downwards, power switch 13 is arranged is convenient for switching manipulation in the side of head protective shell 1.In head protective shell
1 front end is equipped with buffer part 14, and buffer part 14 can be made by Rubber end or using other flexible materials, when head occurs
When collision, soft buffer part 14 can play a buffer role in, and reduce the impaired impact to small aircraft.
The above is only the preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-described embodiment,
All technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It should be pointed out that for the art
For those of ordinary skill, several improvements and modifications without departing from the principles of the present invention should be regarded as the protection of the present invention
Range.
Claims (11)
1. a kind of small aircraft, including fuselage（2）With two wings being arranged symmetrically（3）, which is characterized in that the fuselage
（2）And wing（3）It is integrally formed, each wing（3）On be arranged be used to support aerofoil aerofoil support tube assembly
（4）, the wing（3）It is equipped with propeller power assembly（6）, the fuselage（2）It is equipped with control assembly（7）, each described
Wing（3）Wing tip at be equipped with inclined winglet upward（31）, each wing（3）Rear at be equipped with protrusion
Empennage（34）, the empennage（34）It tilts upwards, the empennage（34）With winglet（31）Between form the first recessed portion
（8）, each empennage（34）On be all provided with there are one propeller power assembly（6）；The fuselage（2）Head at be equipped with head
Protective shell（1）.
2. small aircraft according to claim 1, which is characterized in that the aerofoil supports tube assembly（4）Including one
Main stay tube（41）With two or more secondary support tubes（42）, the main stay tube（41）Parallel and close to fuselage（2）And wing
（3）Junction arrangement, two or more the secondary support tubes（42）It is arranged in wing（3）On aerofoil.
3. small aircraft according to claim 2, which is characterized in that two wings（3）It is in triangle aerofoil profile, institute
State time support tube（42）It is two, described first support tube（42）Close to wing（3）The leading edge of a wing at arrange, described the
Two support tubes（42）Close to wing（3）Trailing edge at arrange.
4. small aircraft according to claim 2, which is characterized in that two wings（3）It is in triangle aerofoil profile, institute
State time support tube（42）It is two, described first support tube（42）With main stay tube（41）It is arranged in 35o~45o angles,
The angle is towards heading, described second support tube（42）One end and first time support tube（42）Midpoint connect
It connects, described second support tube（42）The other end close to wing（3）Wing tip at be arranged.
5. small aircraft according to claim 2, which is characterized in that two wings（3）It is in triangle aerofoil profile, institute
State time support tube（42）It is three, described first support tube（42）Close to wing（3）The leading edge of a wing at arrange, described the
Two support tubes（42）Close to wing（3）Trailing edge at arrange, the third root time support tube（42）One end and the
One support tube（42）Vertical connection, the third root time support tube（42）The other end close to fuselage（2）Tail portion at set
It sets.
6. the small aircraft according to any one of Claims 1 to 5, which is characterized in that each wing（3）
From fuselage（2）It raises up towards the direction of wing tip, the angle that raises up is 1o~10o.
7. small aircraft according to claim 6, which is characterized in that each wing（3）Leading edge include the
One leading edge of a wing（32）With second leading edge of a wing（33）, two first leading edges of a wing at head（32）Between angle
For 35o~45o, each second leading edge of a wing（33）Angle of sweep is 50o~60o.
8. small aircraft according to claim 1, which is characterized in that described two empennages（34）Between be equipped with it is second recessed
Concave portion（9）, second recessed portion（9）It is interior to be equipped with aircraft geometrical clamp（5）, the aircraft geometrical clamp（5）Including the machine being connected
Body fixed part（51）The wing support portion to raise up with two（52）, the wing support portion（52）On be respectively provided with the clamping of wing
Portion（53）, two wing support portions（52）Between angle degree be equal to two wings（3）Between angle degree, when fixed,
The fuselage（2）It is inserted into fuselage fixed part（51）It is interior, and two wings（3）Correspondence is clamped in two wing support portions respectively
（52）With wing clamping part（53）Between.
9. the small aircraft according to any one of Claims 1 to 5, which is characterized in that the fuselage（2）, wing
（3）Tube assembly is supported with aerofoil（4）It is that carbon fibre material is made.
10. the small aircraft according to any one of Claims 1 to 5, which is characterized in that the fuselage（2）And machine
Head protection shell（1）It is detachably connected, the control assembly（7）It is installed on head protective shell（1）It is interior, the head protective shell（1）
On be installed with camera mounting hole（11）, GPS mounting holes（12）And power switch（13）.
11. small aircraft according to claim 10, which is characterized in that the head protective shell（1）Front end set
There is buffer part（14）.
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| CN201510759025.4A CN105251216B (en) | 2015-11-10 | 2015-11-10 | A kind of small aircraft |
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| CN201510759025.4A CN105251216B (en) | 2015-11-10 | 2015-11-10 | A kind of small aircraft |
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| CN105251216B true CN105251216B (en) | 2018-10-02 |
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| CN201510759025.4A Active CN105251216B (en) | 2015-11-10 | 2015-11-10 | A kind of small aircraft |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105920853A (en) * | 2016-06-14 | 2016-09-07 | 夏烬楚 | Control booster for aircraft toy, control terminal and control method |
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| CN2213013Y (en) * | 1994-11-19 | 1995-11-22 | 陈宗荣 | Ejection model airplane |
| CN2560405Y (en) * | 2002-07-09 | 2003-07-16 | 楼英俊 | Collision-proof wireless remote control electric model airplane |
| CN201807189U (en) * | 2010-10-19 | 2011-04-27 | 林伯修 | Lightweight structure of remote control aircraft |
| CN203698647U (en) * | 2014-01-16 | 2014-07-09 | 江苏中科遥感信息技术有限公司 | Low-wind-resistance and high-balance light flying wing type unmanned aerial vehicle |
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|---|---|
| CN105251216A (en) | 2016-01-20 |
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