CN205131674U - Small -size all -wing aircraft overall arrangement unmanned aerial vehicle - Google Patents
Small -size all -wing aircraft overall arrangement unmanned aerial vehicle Download PDFInfo
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- CN205131674U CN205131674U CN201520889503.9U CN201520889503U CN205131674U CN 205131674 U CN205131674 U CN 205131674U CN 201520889503 U CN201520889503 U CN 201520889503U CN 205131674 U CN205131674 U CN 205131674U
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Abstract
The utility model discloses a small -size all -wing aircraft overall arrangement unmanned aerial vehicle, including fuselage and the wing of locating the fuselage both sides, being wing body fusion structure between fuselage and the wing, the screw has been arranged to the rear end of fuselage, and the design of sweepback formula wing is taked to the wing, and the leading edge sweep angle is 28o~32o, and wing trailing edge sweep angle is 18o~21o. The utility model has the advantages of light in weight, the operation of being convenient for, flight efficiency be good, can bring splendid flight to experience for the user.
Description
Technical field
The utility model is mainly concerned with unmanned plane field, is specifically related to a kind of small-sized Flying-wing unmanned plane.
Background technology
Conventional civilian unmanned plane, more such as aerial mapping, takes photo by plane, and the unmanned plane of pipeline patrol all have employed the normal arrangement of larger fuselage.So, airframe is longer, and needs tailplane and vertical tail, and equipment box goes to place unmanned plane with regard to needing larger space, greatly reduces the portability of aircraft; Adopt the unmanned plane of normal arrangement, pneumatic efficiency is lower than Flying-wing, and therefore the cruise duration of Flying-wing's unmanned plane, comparatively normal arrangement unmanned plane was more of a specified duration, and voyage is also farther, can embody stronger duration performance in actual job.
" all-wing aircraft (FlyingWing) " layout is a kind of aerodynamic configuration of aircraft mode being different from Conventional pneumatic layout.All-wing aircraft does not have conventional fuselage and empennage, and its fuselage and wing combine together, are often called BWB(Blended-wingbody) blended wing-body.Some all-wing aircraft fuselages still retain, but certainly do not have empennage.Germany " Wal is many. and water is graceful " brother is considered to the earliest all-wing aircraft designer.The stealthy strategic bomber B2 of the U.S. is exactly the Flying-wing adopted.The aerodynamic efficiency of this layout of all-wing aircraft is very high, because airframe structure is all wing, all can be used for producing lift, and farthest reduce flight resistance, its reflection of radar waves simultaneously is also smaller, and Stealth Fighter is given prominence to.
There is following technical matters in existing civilian unmanned plane:
(1) have employed normal arrangement, the span is very long, not portable, and unmanned plane packing chest needs very large space just can load a whole set of aircraft, brings a lot of inconvenience to user.
(2) UAV aerodynamic layout, structure design are unreasonable, and can not obtain good flight usefulness, user's flight experience is not good.
(3) unmanned plane had is obtain larger flight time and flight range, have to strengthen the size of unmanned plane and relevant device weight, this makes unmanned plane need launching cradle in use, employing is launched and just can be taken off, also need during landing to release a parachute or use unmanned plane catch net to reclaim, such operation brings a lot of trouble to user, not easily carries, setup time is oversize, also can not one man operation.
Therefore, how to be a kind of good aerodynamic arrangement of unmanned aerial vehicle design, to make it under the prerequisite of miniaturization, lightweight, handled easily, good flight usefulness can also be obtained, splendid flight experience can be brought to user, become a problem urgently to be resolved hurrily.
Utility model content
The technical matters that the utility model solves is: for prior art Problems existing, provide a kind of lightweight, convenient operation, flight usefulness are good, can bring the small-sized Flying-wing unmanned plane of splendid flight experience to user.
For solving the problems of the technologies described above, the utility model by the following technical solutions:
A kind of small-sized Flying-wing unmanned plane, comprise fuselage and the wing being located at fuselage both sides, it is blended wing-body body structure between described fuselage and wing, the rear end of described fuselage is furnished with screw propeller, described wing takes aft swept wings to design, described leading edge of a wing sweepback angle is 28o ~ 32o, and described trailing edge sweepback angle is 18o ~ 21o.
As further improvement of the utility model, the trailing edge of two described wings is equipped with elevon, and the area of each described elevon accounts for 14% ~ 20% of affiliated gross wing area.
As further improvement of the utility model, the junction of two described elevons and fuselage all tilts to make to form notch part between two elevons towards respective wing tip direction, described screw propeller rotates in notch part space.
As further improvement of the utility model, the wing tip place of two described wings is equipped with the winglet towards surface thereof.
As further improvement of the utility model, the bottom of described fuselage is provided with the landing buffer part towards outer lug.
As further improvement of the utility model, the top of described fuselage is provided with antenna and pitot.
As further improvement of the utility model, the front portion of described fuselage is towards projection, described fuselage interior is from first to last furnished with GPS sensor module, battery component, control assembly and photomoduel successively, a digital rudder controller assembly is respectively provided with about the rear portion of photomoduel, the rear portion of described digital rudder controller assembly is provided with electricity tune cabin and for driving the drive motor of screw propeller, described photomoduel is arranged in the middle part of fuselage.
As further improvement of the utility model, the end face correspondence of described fuselage is provided with removable battery hatch and phase cabin cover.
As further improvement of the utility model, described fuselage and wing all adopt lightweighting materials to make.
Compared with prior art, the utility model has the advantage of:
(1) small-sized Flying-wing of the present utility model unmanned plane, by taking the blended wing-body body structure of fuselage and wing, aft swept wings again in conjunction with angle uniqueness designs, this unmanned plane is made to have good aerodynamic arrangement, usefulness of well flying can be obtained, splendid flight experience can be brought to user.
(2) small-sized Flying-wing of the present utility model unmanned plane, by carrying out multinomial optimal design and specific scientific offering to aspects such as elevon, winglet and fuselage device arrangements, further increase the flight usefulness of unmanned plane, simultaneously by adopting lightweighting materials to make, aircraft is made to be easy to operation, and without the need to using other to let fly away and regenerative apparatus, bring better flight experience to user further.
Accompanying drawing explanation
Fig. 1 is the spatial structure principle schematic of the utility model small-sized Flying-wing unmanned plane.
Fig. 2 be the utility model small-sized Flying-wing unmanned plane look up structural principle schematic diagram.
Fig. 3 is the side-looking structural principle schematic diagram of the utility model small-sized Flying-wing unmanned aerial vehicle body.
Fig. 4 is the major elements schematic diagram of the utility model small-sized Flying-wing unmanned aerial vehicle body components and parts.
Marginal data:
1, fuselage; 10, control assembly; 11, photomoduel; 12, digital rudder controller assembly; 13, electricity adjusts cabin; 14, drive motor; 15, battery hatch; 16, phase cabin cover; 2, wing; 21, elevon; 22, winglet; 3, screw propeller; 4, notch part; 5, landing buffer part; 6, antenna; 7, pitot; 8, GPS sensor module; 9, battery component.
Detailed description of the invention
Below in conjunction with specific embodiments and the drawings, the utility model is described in further detail.
As shown in Figures 1 to 4, the utility model provides a kind of small-sized Flying-wing unmanned plane, comprise fuselage 1 and the wing 2 being located at fuselage 1 both sides, it is blended wing-body body structure between fuselage 1 and wing 2, the rear end of fuselage 1 is furnished with screw propeller 3, wing 2 takes aft swept wings to design, and wing 2 leading edge sweep is 28o ~ 32o, and wing 2 trailing sweep is 18o ~ 21o.In the present embodiment, the shape of fuselage 1 is preferably revised a little by the lines of NACA2412 aerofoil profile and is drawn, relative camber gets 1.4 ~ 1.8%, and relative thickness gets 7 ~ 9%, and wing 2 leading edge sweep is preferably 30o, and wing 2 trailing sweep is preferably 20o.The utility model by taking the blended wing-body body structure between fuselage 1 and wing 2, then designs and rear end screw propeller driving design in conjunction with the aft swept wings of angle uniqueness, is conducive to the pneumatic efficiency increasing unmanned plane, improves the 1ift-drag ratio of fuselage 1.The unique design at wing 2 sweepback angle, can make lift coefficient slope reduce on the one hand, and can increase the horizontal course stability of aircraft when unmanned plane is put down and flown, aircraft is more difficult to stall; Can allow on the other hand after the center of gravity of airplane and move, be conducive to center of gravity of airplane trim.Especially the design of wing 2 trailing sweep, also further reduces the aerofoil area of wing 2, alleviates the complete machine weight of unmanned plane, and screw propeller 3 driving design of tie tail, makes flight more flexible simultaneously.In a word, make this Flying-wing unmanned plane have good aerodynamic arrangement by comprehensive with the design of last each parts uniqueness, usefulness of well flying can be obtained, splendid flight experience can be brought to user.
Further, in the preferred embodiment, the trailing edge of two wings 2 is equipped with elevon 21, and the area of each elevon 21 accounts for 14% ~ 20% of affiliated wing 2 gross area.Two elevons 21 are as primary control surface, and rudder face area is comparatively large, are conducive to the maneuverability improving unmanned plane.When left and right rudder face oppositely deflects, it is motor-driven that unmanned plane carries out rolling, and when left and right rudder face deflects in the same way, it is motor-driven that unmanned plane carries out pitching, and flight usefulness is better.
Further, in the preferred embodiment, the junction of two elevons 21 and fuselage 1 all tilts to make to form notch part 4 between two elevons 21 towards respective wing tip direction, screw propeller 3 rotates in notch part 4 space.Because this small-sized Flying-wing unmanned plane takes hand throwing type very easily to let pattern fly away, when namely unmanned plane is let fly away, hold wing 2 by operator's both hands, unmanned plane is dished out forward and lets fly away.Therefore between two elevons 21, form notch part 4, rotate in the notch part 4 of screw propeller 3 between two elevons 21, when unmanned plane is let fly away, have enough safety distances between operator and screw propeller 3, screw propeller 3 can not scratch people.
Further, in the preferred embodiment, the wing tip place of two wings 2 is equipped with the winglet 22 towards surface thereof.Winglet 22 is conducive to reducing unmanned plane and equals induced drag when flying, and provides enough directional static stability, and user can obtain better flight experience.
Further, in the preferred embodiment, the bottom of fuselage 1 is provided with the landing buffer part 5 towards outer lug, and the top of fuselage 1 is provided with antenna 6 and pitot 7.Because this small-sized Flying-wing unmanned plane takes hand throwing type very easily let pattern fly away and slide from landing mode, when unmanned plane needs landing, himself slowly slide and contact to earth finally to complete landing by fuselage 1.For to alleviate when unmanned plane contacts to earth in the face of the impulsive force of fuselage 1, avoid causing damage to unmanned plane, therefore protruding landing buffer part 5 is set in the bottom of fuselage 1, buffer part 5 of landing during landing takes the lead in contacting to earth with the impulsive force of attenuate ground to fuselage 1, and after steadily contacting to earth, unmanned plane is again by progressively having slowed down landing with the friction on ground.Landing buffer part 5 can be made for flexible material, or is designed to compressible buffer structure form.Meanwhile, antenna 6 and pitot 7 are arranged at the top of fuselage 1, avoid causing damage to antenna 6 and pitot 7 during landing.
As shown in Figure 4, further, in the preferred embodiment, the front portion of fuselage 1 is towards projection, fuselage 1 inside is from first to last furnished with GPS sensor module 8, battery component 9, control assembly 10 and photomoduel 11 successively, about the rear portion of photomoduel 11, be respectively provided with a digital rudder controller assembly 12, the rear portion of digital rudder controller assembly 12 is provided with electricity tune cabin 13 and for driving the drive motor 14 of screw propeller 3, photomoduel 11 is arranged in the middle part of fuselage 1.Components and parts due to unmanned plane are all arranged on fuselage 1, in order to obtain optimum aerodynamic arrangement, improve the flight usefulness of unmanned plane, the utility model adopts above-mentioned compact device arrangements design in fuselage 1 inside, under the condition considering gravity allocation, all components and parts are arranged within this aerodynamic configuration optimized, so both meet the loading of equipment, also achieve the trim of unmanned plane center of gravity, the aerodynamic configuration of unmanned plane also obtains actv. optimization simultaneously.The reason of above-mentioned compact device arrangements design is as follows:
Due to the pattern taking rear end screw propeller 3 to drive, electricity adjusts cabin 13 and the most afterbody for driving drive motor 14 position of screw propeller 3 to be located at fuselage 1; Electricity adjusts cabin 13 to be connected by electric wire with drive motor 14, as far as possible close to the weight that can reduce wire rod; Photomoduel 11 and battery component 9 are two parts the heaviest in fuselage, and counterweight adjustment is main by these two parts, and photomoduel 11 considers that the convenience of taking pictures preferably is placed on aircraft midway location, therefore battery component 9 can only be placed on head position; After these parts arrange, remaining position is just as the putting position of other parts.Complete center of gravity trim after putting, center of gravity is in the camera near the heart, and before aerodynamic center a bit, complete machine is the state of static-stability.
Further, in the preferred embodiment, the end face correspondence of fuselage 1 is provided with removable battery hatch 15 and phase cabin cover 16.Removable battery hatch 15 is convenient to carry out replacing charging to battery component 9 or directly charge; Openable phase cabin cover 16 is convenient to photomoduel 11 to take out carry out changing or obtaining photographic information.
Further, in the preferred embodiment, fuselage 1 and wing 2 all adopt lightweighting materials to make.In the present embodiment, fuselage 1 and wing 2 all adopt good springiness, lightweight EPP foamed materials is made (in other embodiments, also other lightweighting materials can be adopted to make), substantially reduce size and the weight of unmanned plane, the span of wing 2 is designed to 0.98 ~ 1.05 meter by this preferred embodiment simultaneously, maximum take-off weight is designed to 700g ~ 750g, coordinates the blended wing-body Flying-wing of unique optimization, makes unmanned plane airborne period of the present utility model can reach 30 ~ 45 minutes.Meanwhile, due to lightweight, wing load is little, and hand can be adopted to throw the mode flown, and eliminates complicated launching cradle device, allows user use more convenient; When needs land, unmanned plane can according to predetermined course line under the control of flight control system, to contact to earth landing, eliminate parachuting or the catch net system of unmanned plane recovery, be conducive to user more efficient, safer, reclaim unmanned plane more easily, the user of making easy and simple to handle can obtain better flight experience.
Below be only preferred implementation of the present utility model, protection domain of the present utility model be not only confined to above-described embodiment, all technical schemes belonged under the utility model thinking all belong to protection domain of the present utility model.It should be pointed out that for those skilled in the art, not departing from the some improvements and modifications under the utility model principle prerequisite, protection domain of the present utility model should be considered as.
Claims (9)
1. a small-sized Flying-wing unmanned plane, comprise fuselage (1) and be located at the wing (2) of fuselage (1) both sides, be blended wing-body body structure between described fuselage (1) and wing (2), the rear end of described fuselage (1) is furnished with screw propeller (3), it is characterized in that, described wing (2) takes aft swept wings to design, and described wing (2) leading edge sweep is 28o ~ 32o, and described wing (2) trailing sweep is 18o ~ 21o.
2. small-sized Flying-wing according to claim 1 unmanned plane, is characterized in that, the trailing edge of two described wings (2) is equipped with elevon (21), and the area of each described elevon (21) accounts for 14% ~ 20% of affiliated wing (2) gross area.
3. small-sized Flying-wing according to claim 2 unmanned plane, it is characterized in that, the junction of two described elevons (21) and fuselage (1) all tilts to make to form notch part (4) between two elevons (21) towards respective wing tip direction, described screw propeller (3) rotates in notch part (4) space.
4. small-sized Flying-wing according to claim 1 unmanned plane, is characterized in that, the wing tip place of two described wings (2) is equipped with the winglet (22) towards surface thereof.
5. small-sized Flying-wing according to claim 1 unmanned plane, is characterized in that, the bottom of described fuselage (1) is provided with the landing buffer part (5) towards outer lug.
6. small-sized Flying-wing according to claim 1 unmanned plane, is characterized in that, the top of described fuselage (1) is provided with antenna (6) and pitot (7).
7. according to the small-sized Flying-wing unmanned plane in claim 1 ~ 6 described in any one, it is characterized in that, the front portion of described fuselage (1) is towards projection, described fuselage (1) inside is from first to last furnished with GPS sensor module (8) successively, battery component (9), control assembly (10) and photomoduel (11), a digital rudder controller assembly (12) is respectively provided with about the rear portion of photomoduel (11), the rear portion of described digital rudder controller assembly (12) is provided with electricity and adjusts cabin (13) and for driving the drive motor (14) of screw propeller (3), described photomoduel (11) is arranged in the middle part of fuselage (1).
8. small-sized Flying-wing according to claim 7 unmanned plane, is characterized in that, the end face correspondence of described fuselage (1) is provided with removable battery hatch (15) and phase cabin cover (16).
9. according to the small-sized Flying-wing unmanned plane in claim 1 ~ 6 described in any one, it is characterized in that, described fuselage (1) and wing (2) all adopt lightweighting materials to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520889503.9U CN205131674U (en) | 2015-11-10 | 2015-11-10 | Small -size all -wing aircraft overall arrangement unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520889503.9U CN205131674U (en) | 2015-11-10 | 2015-11-10 | Small -size all -wing aircraft overall arrangement unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN205131674U true CN205131674U (en) | 2016-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520889503.9U Expired - Fee Related CN205131674U (en) | 2015-11-10 | 2015-11-10 | Small -size all -wing aircraft overall arrangement unmanned aerial vehicle |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347663A (en) * | 2016-09-22 | 2017-01-25 | 北京尖翼科技有限公司 | Unmanned aerial vehicle with wing body and flying wing blended layout |
| CN106394856A (en) * | 2016-10-28 | 2017-02-15 | 北京尖翼科技有限公司 | Composite wing unmanned aerial vehicle |
| CN106394866A (en) * | 2016-11-21 | 2017-02-15 | 顺丰科技有限公司 | Wing of unmanned aerial vehicle and unmanned aerial vehicle |
| CN107200117A (en) * | 2017-04-12 | 2017-09-26 | 杭州迅蚁网络科技有限公司 | A kind of aircraft that easing gear is filled with recession formula |
| CN109823516A (en) * | 2019-02-14 | 2019-05-31 | 成都飞机工业（集团）有限责任公司 | A kind of stealthy steering engine bulge of aircraft |
-
2015
- 2015-11-10 CN CN201520889503.9U patent/CN205131674U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347663A (en) * | 2016-09-22 | 2017-01-25 | 北京尖翼科技有限公司 | Unmanned aerial vehicle with wing body and flying wing blended layout |
| CN106394856A (en) * | 2016-10-28 | 2017-02-15 | 北京尖翼科技有限公司 | Composite wing unmanned aerial vehicle |
| CN106394856B (en) * | 2016-10-28 | 2019-07-02 | 北京尖翼科技有限公司 | A kind of composite wing unmanned plane |
| CN106394866A (en) * | 2016-11-21 | 2017-02-15 | 顺丰科技有限公司 | Wing of unmanned aerial vehicle and unmanned aerial vehicle |
| CN107200117A (en) * | 2017-04-12 | 2017-09-26 | 杭州迅蚁网络科技有限公司 | A kind of aircraft that easing gear is filled with recession formula |
| CN109823516A (en) * | 2019-02-14 | 2019-05-31 | 成都飞机工业（集团）有限责任公司 | A kind of stealthy steering engine bulge of aircraft |
| CN109823516B (en) * | 2019-02-14 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Airplane stealth steering engine bulge |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160406 Termination date: 20211110 |
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| CF01 | Termination of patent right due to non-payment of annual fee |