CN105251216A - Small size air vehicle - Google Patents
Small size air vehicle Download PDFInfo
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- CN105251216A CN105251216A CN201510759025.4A CN201510759025A CN105251216A CN 105251216 A CN105251216 A CN 105251216A CN 201510759025 A CN201510759025 A CN 201510759025A CN 105251216 A CN105251216 A CN 105251216A
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Abstract
The invention discloses a small size air vehicle, comprising a vehicle body and two wings arranged symmetrically, wherein the vehicle body and the wings are formed as a whole; each wing is uniformly provided with a wing surface supporting tube assembly for supporting the wing surface and a propeller power assembly; the vehicle body is provided with a control assembly. The small size air vehicle disclosed by the invention has the advantages of being simple in structure, convenient to manufacture due to molding to one, light in weight, high in strength and rigidity, good flight performance, and the small size air vehicle can bring excellent flight experience to a user.
Description
Technical field
The present invention is mainly concerned with model plane technical field, is specifically related to a kind of small aircraft.
Background technology
Paper helicopter, be a kind of papery aircraft that people make with a thin paper in former narrow sense definition, paper helicopter in the past can only aloft fly a few second by hand-thrown, and uncontrollable.Along with the prosperity of science and technology, updating of thought of people, technology, present paper helicopter definition is no longer only confined to papery aircraft, but slowly develops into and have the small aircraft that different materials makes and carry out alternative papery aircraft.The small aircraft of these novel paper helicopter formulas is of many uses, can be used for the elementary coach of model plane, 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 adopts cardboard, cork wood, kt plate to make.The aircraft manufacturing process of such making can not one-shot forming, and not only directly can not make the profile of paper helicopter, profile must be formed by multiple adhering components, and this makes aircraft manufacture difficulty large, length consuming time; Especially can not ensure the intensity of adhering part and the intensity of structure in flight course, just in case come off in flight course, be easy to aircraft air crash, when running into barrier also not crashworthiness, cracky, flight optimization not reached for user and experiences.
(2) existing most small aircraft is because structural design is unreasonable or rigidity causes flight not steady not, aircraft is easily caused to shake, motor is caused to swing up and down, and then upset air-flow, finally make aircraft can not maintain steady course thrust thus can not to the good flight experience of user one.
Therefore, how to make a kind of small aircraft, make it can not only be convenient to make, and lightweight, high strength, high rigidity, there is good flight usefulness, bring user splendid flight experience, become a problem urgently to be resolved hurrily.
Summary of the invention
Technical problem solved by the invention is: for prior art Problems existing, provide a kind of housing construction simple, can one-body moldedly be convenient to make and lightweight, high strength, high rigidity, the small aircraft that there is good flight usefulness, splendid flight experience can be brought to user.
For solving the problems of the technologies described above, the present invention by the following technical solutions:
A kind of small aircraft, two wings comprising fuselage and be arranged symmetrically with, described fuselage and wing one-body molded, each described wing is all furnished with the aerofoil stay pipe assembly for supporting aerofoil, described wing is provided with screw power assembly, and described fuselage is provided with Control Component.
As a further improvement on the present invention, described aerofoil stay pipe assembly comprises the secondary stay pipe of a main stay pipe and more than two, described main stay pipe is parallel and arrange near the junction of fuselage and wing, and described the stay pipe of more than two is arranged on aerofoil surface.
As a further improvement on the present invention, two described wings are all in triangle aerofoil profile, and described time stay pipe is two, and described first stay pipe is arranged near the leading edge of a wing place of wing, and described second stay pipe is arranged near the trailing edge place of wing.
As a further improvement on the present invention, two described wings are all in triangle aerofoil profile, described time stay pipe is two, described first stay pipe and main stay pipe are that 35o ~ 45 angle is arranged, described angle is towards heading, one end of described second stay pipe is connected with the mid point of first stay pipe, and the other end of described second stay pipe is arranged near the wing tip place of wing.
As a further improvement on the present invention, two described wings are all in triangle aerofoil profile, described time stay pipe is three, described first stay pipe is arranged near the leading edge of a wing place of wing, described second stay pipe is arranged near the trailing edge place of wing, one end of described 3rd time stay pipe is connected with first time stay pipe is vertical, and the other end of described 3rd secondary stay pipe is arranged near the afterbody place of fuselage.
As a further improvement on the present invention, each described wing all raises up from fuselage towards the direction of wing tip, and the angle that raises up is 1o ~ 10o, and the wing tip place of each described wing is equipped with the winglet towards surface thereof.
As a further improvement on the present invention, the leading edge of each described wing includes first leading edge of a wing and second leading edge of a wing, between two described first leading edges of a wing at head place, angle is 35o ~ 45, and each described second leading edge of a wing angle of sweep is 50o ~ 60o.
As a further improvement on the present invention, the trailing edge place of each described wing is equipped with the empennage of protrusion, and described empennage is inclined upwardly, and forms the first depressed part between described empennage and winglet, each described empennage is equipped with a screw power assembly.
As a further improvement on the present invention, the second depressed part is provided with between described two empennages, aircraft geometrical clamp is provided with in described second depressed part, described aircraft geometrical clamp comprises the fuselage fixed part and two wing support portions raised up that are connected, described wing support portion is respectively provided with a wing clamping part, angle degree between two described wing support portions equals the angle degree between two wings, time fixing, described fuselage inserts in fuselage fixed part, and two described wings respectively corresponding clip be held between two wing support portions and wing clamping part.
As a further improvement on the present invention, described fuselage, wing and aerofoil stay pipe assembly are carbon fibre material and make.
As a further improvement on the present invention, the head place of described fuselage is provided with the head containment vessel removably connected, and described Control Component is installed in head containment vessel, described head containment vessel is equiped with camera installing hole, GPS installing hole and power switch.
As a further improvement on the present invention, described head containment vessel be provided with buffer part foremost.
Compared with prior art, the invention has the advantages that:
(1) small aircraft of the present invention, by fuselage with wing is one-body molded makes, improves rigidity and the stability of small aircraft; Simultaneously, each wing is also all furnished with the aerofoil stay pipe assembly for supporting aerofoil, solve the light but contradiction that rigidity is inadequate of vehicle mass, the rigidity of frivolous wing is strengthened greatly, not only not fragile, and vibrations can not be there are and cause aircraft steady in flight course, make this small aircraft not only have body one-body molded, be convenient to the advantage that makes, also there is lightweight, high strength, high rigidity advantage; In conjunction with the preferred arrangement crossed airframe components, make this small aircraft obtain good aerodynamic arrangement, fly more stable, user can obtain splendid flight experience.
(2) small aircraft of the present invention, structural design is simple, reasonable, science, by being optimized the layout of airframe components, as carried out specific scientific offering to aerofoil stay pipe arrangement of components position, wing setting, the wing upper counterangle, the winglet elevation angle, empennage, aircraft geometrical clamp etc. are a series of, make the moulding of this small aircraft unique, attractive in appearance, there is very good aerodynamic arrangement simultaneously, flight attitude is graceful, flight stability, there is good flight usefulness, can bring user splendid flight experience further.
Accompanying drawing explanation
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 structural principle schematic diagram.
Fig. 4 be small aircraft of the present invention in example 2 look up structural principle schematic diagram.
Fig. 5 be small aircraft of the present invention in embodiment 3 look up structural 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 screw power assembly of the present invention.
Fig. 8 is the plan structure principle schematic of small aircraft screw 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 containment vessel of the present invention.
Figure 13 is the plan structure principle schematic of small aircraft head containment vessel of the present invention.
Marginal data:
1, head containment vessel; 11, camera installing hole; 12, GPS installing hole; 13, power switch; 14, buffer part; 2, fuselage; 3, wing; 31, winglet; 32, first leading edge of a wing; 33, second leading edge of a wing; 34, empennage; 4, aerofoil stay pipe assembly; 41, main stay pipe; 42, secondary stay pipe; 5, aircraft geometrical clamp; 51, fuselage fixed part; 52, wing support portion; 53, wing clamping part; 6, screw power assembly; 61, motor cabinet; 611, front support; 612, rear support; 62, motor; 63, output shaft; 64, pinion; 65, gear wheel; 66, screw; 67, sliding bearing; 68, spacing plug; 7, Control Component; 8, the first depressed part; 9, the second depressed part.
Detailed description of the invention
Below in conjunction with specific embodiments and the drawings, the present invention is described in further detail.
As shown in figure 1 to figure 13, the invention provides a kind of small aircraft, two wings 3 comprising fuselage 2 and be arranged symmetrically with, fuselage 2 and wing 3 one-body molded, each wing 3 is all furnished with the aerofoil stay pipe assembly 4 for supporting aerofoil, wing 3 is provided with screw power assembly 6, and fuselage 2 is provided with Control Component 7.
The present invention is by fuselage 2 and wing 3 is one-body molded makes, and integrated mode is convenient to the making of small aircraft, directly can produce the profile of small aircraft; Significantly, the bonding strength between this mode ensure that as most important three the large parts of small aircraft (fuselage 2 and two wings 3), improves rigidity and the stability of small aircraft.Further, as everyone knows, weight is for particularly important small aircraft, and in order to alleviate the own wt of small aircraft, the parts of aircraft can do thin by people as far as possible, use material weight reduction to reduce; But but frivolous wing exists low, the flimsy problem of rigidity, frivolous wing easily causes vibrations, destroys pneumatic simultaneously, cause flight not steady, can not give user one good flight experience.For solving this technical problem, the present invention by fuselage 2 and wing 3 is one-body molded make while, each wing 3 is also all furnished with the aerofoil stay pipe assembly 4 for supporting aerofoil.Aerofoil stay pipe assembly 4 can play the supporting role of reinforcement, it both can not increase very much the weight of small aircraft, frivolous wing 3 aerofoil can be supported again, the rigidity of frivolous wing 3 is strengthened greatly, not only not fragile, and vibrations can not occur in flight course and cause aircraft not steady, splendid flight experience can be brought to user.The mode arranging aerofoil stay pipe assembly 4 on wing 3 is added in fuselage 2 and the integrated design of wing 3, this small aircraft is made well to solve the light but contradiction that rigidity is inadequate of quality, make this small aircraft not only have body one-body molded, be convenient to make advantage, also there is lightweight, high strength, high rigidity advantage.For obtaining better flight experience, while taking said structure, the present invention is also optimized the layout of airframe components, screw power assembly 6 is arranged in wing 3 place, Control Component 7 is arranged in fuselage 2 place, this set well balances the overall center of gravity of small aircraft, makes this small aircraft obtain good aerodynamic arrangement, fly more stable, user can obtain splendid flight experience.
Further, in the preferred embodiment, aerofoil stay pipe assembly 4 comprises the secondary stay pipe 42 of a main stay pipe 41 and more than two, and main stay pipe 41 is parallel and arrange near the junction of fuselage 2 and wing 3, and the secondary stay pipe 42 of more than two is arranged on wing 3 aerofoil.Although be one-body molded, fuselage 2 and two wings 3 are most important, three parts that volume is maximum of aircraft after all, and very large active force is born in the junction of fuselage 2 and two wings 3.The present invention arranges the secondary stay pipe 42 of more than two at the aerofoil of wing 3, while specially aerofoil being supported, main stay pipe 41 is arranged in the junction of fuselage 2 and wing 3, main stay pipe 41 length is preferably equal to the length of the junction of fuselage 2 and two wings 3, main stay pipe 41 is while supporting wing 3 aerofoil, also the junction of wing 3 and fuselage 2 is supported, further ensure the reliable connection of fuselage 2 and wing 3.By the layout of this uniqueness, the rigidity of the whole body of general warranty small aircraft.
About the concrete arrangement form of aerofoil stay pipe assembly 4, propose three kinds of preferred embodiments at this, it is pointed out that under the inspiration of said 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 all in triangle aerofoil profile, each wing 3 all arranges a main stay pipe 41 and twice stay pipes 42, main stay pipe 41 is parallel and arrange near the junction of fuselage 2 and wing 3, first time stay pipe 42 is arranged near the leading edge of a wing place of wing 3, and second time stay pipe 42 is arranged near the trailing edge place of wing 3.
Embodiment 2: as shown in Figure 4, the present embodiment 2 is only the arrangement of twice stay pipes 42 with not existing together of above-described embodiment 1, in the present embodiment, first time stay pipe 42 is arranged in 35o ~ 45o angle with main stay pipe 41, angle is towards heading, one end of second stay pipe 42 is connected with the mid point of first stay pipe 42, and the other end of second stay pipe 42 is arranged near the wing tip place of wing 3.
Embodiment 3: as shown in Figure 5, the present embodiment 3 and above-described embodiment 2 different are in the quantity of secondary stay pipe 42 and its arrangement, in the present embodiment, secondary stay pipe 42 is three, first time stay pipe 42 is arranged near the leading edge of a wing place of wing 3, second time stay pipe 42 is arranged near the trailing edge place of wing 3, one end of the 3rd stay pipe 42 with first secondary stay pipe 42 is vertical is connected, the other end of the 3rd secondary stay pipe 42 is arranged near the afterbody place 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; but under the inspiration of said structure; those of ordinary skill in the art can expect taking the aerofoil profile of other modes or can expecting easily on aerofoil, take other arrangement to arrange aerofoil stay pipe assembly 4 easily, and this all should belong to protection scope of the present invention.
Further, in the preferred embodiment, each wing 3 all raises up from fuselage 2 towards the direction of wing tip, the angle that raises up is the preferred 6o of 1o ~ 10o(), the wing tip place of each wing 3 is equipped with the winglet 31 towards surface thereof, the leading edge of each wing 3 includes first leading edge of a wing 32 and second leading edge of a wing 33, and between two first leading edges of a wing 32 at head place, angle is 35o ~ 45o, and each second leading edge of a wing 33 angle of sweep is 50o ~ 60o.By such setting, the form of aircraft is more graceful, and make this small aircraft obtain better aerodynamic arrangement, fly more stable, user can obtain splendid flight experience simultaneously.
Further, in the preferred embodiment, the trailing edge place of each wing 3 is equipped with the empennage 34 of protrusion, and empennage 34 is inclined upwardly, and forms the first depressed part 8 between empennage 34 and winglet 31, each empennage 34 is equipped with a screw power assembly 6.By the die surface at wing 3 trailing edge place is done camber, wing 3 trailing edge place is become from flat board the acclivitous aerofoil profile having camber, namely define acclivitous empennage 34 at the trailing edge place of wing 3.Empennage 34 is used for increasing slope of lift curve, improves the lift of wing 3, further increases the Lateral static stability of small aircraft.That is: because aircraft lift center is after aircraft center of gravity, in aircraft flight process, centre of lift can give center of gravity moment of torsion of bowing, and aircraft is flown downwards, and just in time can balance centre of lift to the moment of torsion of bowing of center of gravity at the empennage 34 that aircraft afterbody does the upper counterangle.Meanwhile, the empennage 34 of straight forming can strengthen the Rigidity and strength at this place herein, is convenient to screw power assembly 6 and is arranged on empennage 34, ensures the stability of motor 62.Due to the sheet material be integrated between empennage 34 and winglet 31, in order to reach both upper counterangle degree, will certainly do an airfoil between them, arranging of airfoil can increase movable surface area, thus can lose course power.For solving this technical problem, the present invention carries out subtracting material between empennage 34 and winglet 31, namely forms the first depressed part 8.
As shown in Figure 7 and Figure 8, further, in the preferred embodiment, screw power assembly 6 comprises motor cabinet 61 and the motor 62 be located on motor cabinet 61 and output shaft 63, the rotating shaft of motor 62 is provided with pinion 64, output shaft 63 is provided with gear wheel 65 and screw 66, and pinion 64 is connected with gear wheel 65 to make motor 62 drive screw 66 to rotate.Output shaft 63 inserts in motor cabinet 61 by sliding bearing 67, and output shaft 63 one end of inserting in motor cabinet 61 is also provided with spacing plug 68.Motor cabinet 61 is combined by front support 611 and rear support 612, and the surface of front support 611 is circular arc, plays the effect of shunting, reduces resistance; Driving group and deceleration group are set to an entirety by rear support 612, that is: motor 62 is arranged on the inside of rear support 612, and output shaft 63 inserts in rear support 612 by sliding bearing 67, and motor 62 is rotated and rotated by output shaft 63 carrying screws 66; The effect of the spacing plug 68 on output shaft 63 is that restriction output shaft 63 moves left and right under high rotating speed, high thrust, thus can not affect flight stability performance.By driving group and reduction combinations are arranged on motor cabinet 61, decrease the space taken, alleviate the weight of small aircraft, improve cruising time and stability.
As shown in Fig. 2, Fig. 9, Figure 10, Figure 11, further, in the preferred embodiment, be provided with between two empennages 34 in second depressed part 9, second depressed part 9 and be provided with aircraft geometrical clamp 5.Due to 3, wing in die sinking time have certain upper counterangle (best angle is 6 °), the object arranging aerofoil stay pipe assembly 4 is the rigidity strengthening wing 3, but aerofoil stay pipe assembly 4 has certain weight, wing 3 can be made to produce certain deformation, cause wing 3 can not maintain the best elevation angle, so by arranging aircraft geometrical clamp 5, the aerofoil of fuselage 2 and wing 3 being inserted fixing respectively, just can ensure that fuselage 2 and wing 3 aerofoil keep the original best elevation angle.
The enforcement principle of the concrete structure of aircraft geometrical clamp 5 is as follows: aircraft geometrical clamp 5 comprises the fuselage fixed part 51 and two wing support portions 52 raised up that are connected, wing support portion 52 is respectively provided with a wing clamping part 53, angle degree between two wing support portions 52 equals the angle degree between two wings 3, time fixing, fuselage 2 inserts in fuselage fixed part 51, and two wings 3 respectively corresponding clip be held between two wing support portions 52 and wing clamping part 53,52 pairs, wing support portion wing 3 aerofoil is supported, to keep the original best elevation angle.
Further, in the preferred embodiment, fuselage 2, wing 3 and aerofoil stay pipe assembly 4 are carbon fibre material and make.Carbon fibre material has the feature of high strength, high-modulus, rub resistance, the aircraft adopting this material to make will have easy processing than other aircraft of homogenous quantities, thickness is thin, volume is little, the advantage of impact resistant, rub resistance, and this can bring good flight experience to user.
But it is important to note that be not only adopt this material just can produce the miniaturized aircraft that can bring good flight experience to user.This is because: although the miniaturized aircraft that the carbon fiber of multilayer makes can one-shot forming, ensure that profile and the rigidity of aircraft, but because carbon fibre material self proportion also weighs than materials such as cork wood, kt plates, the thickness of itself and weight can affect the climb rate and the flight time of miniaturized aircraft greatly, can not give user one good flight experience; And if be made into the carbon fibre material paper helicopter of individual layer, although paper helicopter itself is thin, lightweight, the carbon fibre material poor rigidity of individual layer, aircraft substantially also can not fly, and does not more talk flight time and flight experience.
And if adopt fuselage 2 of the present invention and wing 3 is one-body molded, on wing 3, arrange the production method of the aerofoil stay pipe assembly 4 for supporting, then just in time can be fine solve the problems of the technologies described above: utilize the carbon fibre material of high strength by fuselage 2 and wing 3 one-body molded, wing 3 adopts the carbon fibre material of individual layer to make, to alleviate the weight of wing 3; Meanwhile, wing 3 arranges the aerofoil stay pipe assembly 4 for supporting aerofoil, aerofoil stay pipe assembly 4 is made for carbon fiber pipe, and the weight of himself can not be very heavy, well can support again, strengthen the rigidity of frivolous aerofoil to frivolous aerofoil.In sum, by adopting design of the present invention, producer can take much different lightweighting materials to be used for making this miniaturized aircraft, though well solve the light problem that still rigidity is inadequate of aircraft weight that light basis weight material is made, make that aircraft weight is light, rigidity is strong, can obtain usefulness of well flying, operator can obtain good flight experience.
Further; in the preferred embodiment; the head place of fuselage 2 is provided with the head containment vessel 1 removably connected; Control Component 7 is installed in head containment vessel 1; head containment vessel 1 is equiped with camera installing hole 11, GPS installing hole 12 and power switch 13, head containment vessel 1 be provided with buffer part 14 foremost.
As shown in Figure 12 and Figure 13, head containment vessel 1 adopts pc material to make, and is divided into removable two halves housing, and after Control Component 7 installs, close two halves housing forming machine head protection shell 1, then tighten with screw and nut.Head containment vessel 1 is provided with head mounting groove 15 and fuselage mounting groove 16; during assembling; chain-drive section inserts in head mounting groove 15, fuselage 2 is arranged in fuselage mounting groove 16 and is fixedly connected with; the below of head containment vessel 1 is equiped with camera installing hole 11, GPS installing hole 12; so that shoot with video-corder information downwards during flight, switching manipulation is convenient in the side that power switch 13 is arranged on head containment vessel 1.Be provided with buffer part 14 foremost at head containment vessel 1, buffer part 14 or can use other flexible materials to make for Rubber end, and when collision appears in head, soft buffer part 14 can play cushioning effect, reduces the impaired impact to small aircraft.
Below be only the preferred embodiment of the present invention, protection scope of the present invention be not only confined to above-described embodiment, all technical schemes belonged under thinking of the present invention all belong to protection scope of the present invention.It should be pointed out that for those skilled in the art, some improvements and modifications without departing from the principles of the present invention, should be considered as protection scope of the present invention.
Claims (12)
1. a small aircraft, two wings (3) comprising fuselage (2) and be arranged symmetrically with, it is characterized in that, described fuselage (2) and wing (3) one-body molded, each described wing (3) is all furnished with the aerofoil stay pipe assembly (4) for supporting aerofoil, described wing (3) is provided with screw power assembly (6), and described fuselage (2) is provided with Control Component (7).
2. small aircraft according to claim 1, it is characterized in that, described aerofoil stay pipe assembly (4) comprises the secondary stay pipe (42) of a main stay pipe (41) and more than two, described main stay pipe (41) is parallel and near the junction of fuselage (2) and wing (3) layout, described the stay pipe (42) of more than two is arranged on wing (3) aerofoil.
3. small aircraft according to claim 2, it is characterized in that, two described wings (3) are all in triangle aerofoil profile, described time stay pipe (42) is two, described first stay pipe (42) is arranged near the leading edge of a wing place of wing (3), and described second stay pipe (42) is arranged near the trailing edge place of wing (3).
4. small aircraft according to claim 2, it is characterized in that, two described wings (3) are all in triangle aerofoil profile, described time stay pipe (42) is two, described first stay pipe (42) is arranged in 35o ~ 45o angle with main stay pipe (41), described angle is towards heading, one end of described second stay pipe (42) is connected with the mid point of first stay pipe (42), and the other end of described second stay pipe (42) is arranged near the wing tip place of wing (3).
5. small aircraft according to claim 2, it is characterized in that, two described wings (3) are all in triangle aerofoil profile, described time stay pipe (42) is three, described first stay pipe (42) is arranged near the leading edge of a wing place of wing (3), described second stay pipe (42) is arranged near the trailing edge place of wing (3), one end of described 3rd time stay pipe (42) is connected with first time stay pipe (42) is vertical, and the other end of described 3rd secondary stay pipe (42) is arranged near the afterbody place of fuselage (2).
6. according to the small aircraft in Claims 1 to 5 described in any one, it is characterized in that, each described wing (3) all raises up from fuselage (2) towards the direction of wing tip, the angle that raises up is 1o ~ 10o, and the wing tip place of each described wing (3) is equipped with the winglet (31) towards surface thereof.
7. small aircraft according to claim 6, it is characterized in that, the leading edge of each described wing (3) includes first leading edge of a wing (32) and second leading edge of a wing (33), between two described first leading edges of a wing (32) at head place, angle is 35o ~ 45o, and each described second leading edge of a wing (33) angle of sweep is 50o ~ 60o.
8. small aircraft according to claim 7, it is characterized in that, the trailing edge place of each described wing (3) is equipped with the empennage (34) of protrusion, described empennage (34) is inclined upwardly, form the first depressed part (8) between described empennage (34) and winglet (31), each described empennage (34) is equipped with a screw power assembly (6).
9. small aircraft according to claim 8, it is characterized in that, the second depressed part (9) is provided with between described two empennages (34), aircraft geometrical clamp (5) is provided with in described second depressed part (9), described aircraft geometrical clamp (5) comprises the fuselage fixed part (51) and two wing support portions (52) raised up that are connected, described wing support portion (52) is respectively provided with a wing clamping part (53), angle degree between two described wing support portions (52) equals the angle degree between two wings (3), time fixing, described fuselage (2) inserts in fuselage fixed part (51), and two described wings (3) respectively corresponding clip be held between two wing support portions (52) and wing clamping part (53).
10. according to the small aircraft in Claims 1 to 5 described in any one, it is characterized in that, described fuselage (2), wing (3) and aerofoil stay pipe assembly (4) are carbon fibre material and make.
11. according to the small aircraft in Claims 1 to 5 described in any one; it is characterized in that; the head place of described fuselage (2) is provided with the head containment vessel (1) removably connected; described Control Component (7) is installed in head containment vessel (1), described head containment vessel (1) is equiped with camera installing hole (11), GPS installing hole (12) and power switch (13).
12. small aircrafts according to claim 11, is characterized in that, described head containment vessel (1) be provided with buffer part (14) foremost.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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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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| CN105251216A true CN105251216A (en) | 2016-01-20 |
| CN105251216B CN105251216B (en) | 2018-10-02 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| KR20040046628A (en) * | 2002-11-28 | 2004-06-05 | 이영범 | a remote control for aplaying flapping bug |
| US20040195438A1 (en) * | 2003-01-09 | 2004-10-07 | Chamberlain Mark Spencer | Electric powered flying wing toy |
| CN2662966Y (en) * | 2003-11-25 | 2004-12-15 | 熊耀华 | Flight track adjustable toy plane |
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| CN102092474A (en) * | 2011-01-28 | 2011-06-15 | 曾道强 | Novel airplane |
| CN103600835A (en) * | 2013-11-29 | 2014-02-26 | 石家庄飞机工业有限责任公司 | Aerodynamic configuration of bionic flying wing unmanned aerial vehicle (UAV) |
| 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 |
| CN204637575U (en) * | 2015-04-23 | 2015-09-16 | 西北工业大学明德学院 | A kind of portable paper helicopter aircraft |
| CN205127400U (en) * | 2015-11-10 | 2016-04-06 | 湖南云顶智能科技有限公司 | Small aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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