CN210284611U - A flying-wing solar unmanned aerial vehicle - Google Patents
A flying-wing solar unmanned aerial vehicle Download PDFInfo
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- CN210284611U CN210284611U CN201920813788.6U CN201920813788U CN210284611U CN 210284611 U CN210284611 U CN 210284611U CN 201920813788 U CN201920813788 U CN 201920813788U CN 210284611 U CN210284611 U CN 210284611U
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Abstract
本实用新型公开了一种飞翼布局太阳能无人机，包括：机翼、垂尾、动力吊舱、不可收放式起落架、操纵面和太阳电池阵；其中，操纵面，包括：副翼、方向舵和全动平尾；垂尾采用梯形外形，布置在机翼两侧翼梢；全动平尾采用矩形外形，布置在机翼中段尾部；副翼设置在机翼后缘；方向舵布置在垂尾后缘；动力吊舱吊挂于机翼下方；太阳电池阵铺设在机翼上表面；不可收放式起落架布置在整机下方。本实用新型可以通过高气动升阻比和轻结构重量来减小无人机的规模，通过高飞行速度来增强无人机的抗风能力。
The utility model discloses a solar-powered unmanned aerial vehicle with a flying wing layout, comprising: a wing, a vertical tail, a power pod, a non-retractable landing gear, a control surface and a solar battery array; wherein, the control surface includes: ailerons , rudder and full-moving horizontal tail; vertical tail adopts trapezoidal shape and is arranged on both sides of the wing; full-moving horizontal tail adopts rectangular shape and is arranged at the tail of the middle section of the wing; the aileron is arranged on the trailing edge of the wing; the rudder is arranged behind the vertical tail The power pod is hung under the wing; the solar array is laid on the upper surface of the wing; the non-retractable landing gear is arranged under the whole machine. The utility model can reduce the scale of the unmanned aerial vehicle through high aerodynamic lift-drag ratio and light structural weight, and enhance the wind resistance capability of the unmanned aerial vehicle through high flight speed.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle global design, especially, relate to a flying wing overall arrangement solar energy unmanned aerial vehicle.
Background
The solar unmanned aerial vehicle is an electric aircraft taking solar radiation as an energy source, and is a product combining an aviation scientific technology and a new energy technology. The solar unmanned aerial vehicle has the advantages of long cruising time, high flying height, wide coverage area, low use cost and no pollution to the environment, can execute various tasks such as communication relay, electronic reconnaissance, mobile networking and the like, is an important supplement for flight platforms such as orbit satellites, conventional power unmanned aerial vehicles, high-altitude airships and the like, and is widely concerned at home and abroad.
The conventional layout of 'wing + fuselage + empennage' is mostly adopted by existing solar unmanned aerial vehicles at home and abroad, and is represented by 'Zephyr' series of QinetiQ company in UK and 'Solara' of Google company in America. The conventional layout solar unmanned aerial vehicle has the following defects: (1) the lift coefficient is large, and the flying speed under the same wing-mounted condition is low, so that the wind resistance of the unmanned aerial vehicle is weak; (2) the soaking area of the whole machine is increased by the machine body, so that the lift-drag ratio of the whole machine is reduced; (3) the fuselage has increased the structural weight of whole machine, leaves the wing and has increased the cable weight of whole machine than remote fin, leads to the unmanned aerial vehicle scale grow.
SUMMERY OF THE UTILITY MODEL
The technical problem of the utility model is solved: overcome prior art's not enough, provide a flying wing overall arrangement solar energy unmanned aerial vehicle, can reduce unmanned aerial vehicle's scale through high pneumatic lift-drag ratio and light structure weight, strengthen unmanned aerial vehicle's anti-wind ability through high speed of flight.
In order to solve the technical problem, the utility model discloses a flying wing overall arrangement solar energy unmanned aerial vehicle, include: the device comprises wings, a vertical tail, a power pod, a non-retractable landing gear, a control surface and a solar cell array; wherein, control surface includes: ailerons, rudders and full-motion horizontal tails;
the vertical tails are in a trapezoidal shape and are arranged at wing tips at two sides of the wing;
the full-motion horizontal tail adopts a rectangular shape and is arranged at the tail part of the middle section of the wing;
the ailerons are arranged at the rear edge of the wing;
the rudder is arranged at the rear edge of the vertical tail;
the power nacelle is hung below the wing;
the solar cell array is laid on the upper surface of the wing;
the non-retractable landing gear is arranged below the whole machine.
In above-mentioned all-wing aircraft overall arrangement solar energy unmanned aerial vehicle, the wing includes: the wing comprises a middle wing section, a left outer wing section and a right outer wing section, wherein the left outer wing section and the right outer wing section are symmetrically arranged on the left side and the right side of the middle wing section;
the plane shapes of the left outer wing section, the middle wing section and the right outer wing section are all trapezoidal;
the full-motion horizontal tail is arranged at the tail part of the middle wing section.
In the above-described flying wing layout solar drone,
the wings are in pneumatic layout with a large aspect ratio and a small sweepback angle; wherein, the middle wing section adopts a conventional high lift-drag ratio wing section; the left outer wing section and the right outer wing section adopt a reverse-bent wing shape;
in the solar unmanned aerial vehicle with the flying wing layout, the power pod has four groups; the two groups of power pods are hung below the left outer wing section, the other two groups of power pods are hung below the right outer wing section, and the two groups of power pods hung below the left outer wing section and the two groups of power pods hung below the right outer wing section are symmetrical around the center line of the middle wing section.
In above-mentioned flying wing overall arrangement solar energy unmanned aerial vehicle, still include: four groups of propellers; wherein, four groups of propellers are respectively arranged at the front parts of the four groups of power pods.
In the solar unmanned aerial vehicle with the flying wing layout, the motor and the storage battery are arranged in the power nacelle, and the power nacelle is integrally arranged in front of the front edge of the flying wing so as to balance the gravity center of the whole unmanned aerial vehicle and enable the whole unmanned aerial vehicle to be vertically static and stable.
In above-mentioned all-wing aircraft overall arrangement solar energy unmanned aerial vehicle, battery weight accounts for more than 30% of total quick-witted gross weight.
In above-mentioned all-wing aircraft overall arrangement solar energy unmanned aerial vehicle, wing internally mounted has airborne equipment.
In the solar unmanned aerial vehicle with the flying wing layout, the non-retractable landing gear adopts a front two-point and rear two-point layout; the front two points are two main wheels which are respectively half-buried at the lower parts of the two groups of inner side power hanging cabinets; the two rear points are two tail wheels which are respectively half-buried at the lower parts of the left vertical tail and the right vertical tail.
In the above-described flying wing layout solar drone,
the vertical tails comprise a left vertical tail and a right vertical tail which are symmetrically arranged, and the left vertical tail and the right vertical tail are respectively arranged at the wing tip of the left outer wing section and the wing tip of the right outer wing section;
the ailerons comprise a left aileron and a right aileron which are symmetrically arranged, and the left aileron and the right aileron are respectively arranged at the rear edge of the left outer wing section and the rear edge of the right outer wing section;
the rudder comprises a left rudder and a right rudder which are symmetrically arranged, and the left rudder and the right rudder are respectively arranged at the rear edge of the left vertical tail and the rear edge of the right vertical tail.
The utility model has the advantages of it is following:
(1) the utility model discloses a flying wing overall arrangement solar energy unmanned aerial vehicle rises and hinders the relative altitude. The flying wing has clean layout appearance, few additives, small wetted area, small zero lift resistance and high usable lift-drag ratio.
(2) The utility model discloses a flying wing overall arrangement solar energy unmanned aerial vehicle structure light in weight. On one hand, the weight of the structure can be saved due to the elimination of the fuselage, and on the other hand, the weight of the wing can be reduced to a certain extent due to the removal of the concentrated mass caused by the fuselage and the empennage.
(3) The utility model discloses a flying wing overall arrangement solar energy unmanned aerial vehicle anti-wind ability reinforce. The cruise lift coefficient is small, the cruise speed is increased, and the wind resistance in the flight process is high.
(4) The utility model discloses a flying wing overall arrangement solar energy unmanned aerial vehicle impels efficiently. Because the cruising lift coefficient is small, the cruising speed is increased, and the Reynolds number can be increased by about 30 percent through preliminary evaluation, so that the pneumatic design difficulty of the propeller is reduced, and the comprehensive performance of the propulsion system is improved.
Drawings
Fig. 1 is an overall effect diagram of a flying wing layout solar unmanned aerial vehicle in an embodiment of the present invention;
fig. 2 is a top view of a solar drone with a flying wing layout according to an embodiment of the present invention;
fig. 3 is a front view of a solar drone with a flying wing layout according to an embodiment of the present invention;
fig. 4 is a side view of a solar drone with a flying wing layout according to an embodiment of the present invention;
wherein: 1-wing, 2-vertical tail, 3-power nacelle, 4-non-retractable landing gear, 5-solar battery array, 6-aileron, 7-rudder, 8-full-motion horizontal tail, 101-left outer wing section, 102-middle wing section, 103-right outer wing section, 201-left vertical tail, 202-right vertical tail, 301-power nacelle I, 302-power nacelle II, 303-power nacelle III, 304-power nacelle IV, 401-main wheel I, 402-main wheel II, 403-tail wheel I, 404-tail wheel II, 601-left aileron, 602-right aileron, 701-left rudder, 702-right rudder, 801-propeller I, 802-propeller II, 803-propeller III and 804-propeller IV.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1-4, in this embodiment, this flying wing layout solar unmanned aerial vehicle includes: wing 1, vertical fin 2, power nacelle 3, non-retractable undercarriage 4, control surface and solar array 5, wherein, the control surface specifically can include: ailerons 6, rudders 7 and full-motion horizontal tails 8. The vertical tails 2 are in a trapezoidal shape and are arranged at wing tips on two sides of the wing 1; the full-motion horizontal tail 8 adopts a rectangular shape and is arranged at the tail part of the middle section of the wing 1; the ailerons 6 are arranged at the rear edge of the wing 1; the rudder 7 is arranged at the rear edge of the vertical tail 2; the power nacelle 3 is hung below the wing 1; the solar cell array 5 is laid on the upper surface of the wing 1; the non-retractable landing gear 4 is arranged below the whole machine.
Preferably, the wing 1 may in particular comprise: a middle wing section 102, and a left outer wing section 101 and a right outer wing section 103 symmetrically arranged on the left and right sides of the middle wing section. Wherein the planar shapes of the left outer wing section 101, the middle wing section 102 and the right outer wing section 103 are all trapezoids; the full-motion horizontal tail 8 is arranged aft of the center panel 102.
Preferably, the wing 1 adopts a pneumatic layout with a large aspect ratio and a small sweep angle. Wherein, the middle wing panel 102 adopts a conventional high lift-drag ratio wing type; the left outer wing section 101 and the right outer wing section 103 are of a recurved wing type.
Preferably, the power pod 3 has four sets (e.g., power pod i 301, power pod ii 302, power pod iii 303, and power pod iv 304 as shown in fig. 2). Two groups of power pods (a power pod I301 and a power pod II 302) are hung below the left outer wing section 101, the other two groups of power pods (a power pod III 303 and a power pod IV 304) are hung below the right outer wing section 103, and the two groups of power pods hung below the left outer wing section 101 and the two groups of power pods hung below the right outer wing section 103 are symmetrical around the middle wing section midline. Further, this flying wing overall arrangement solar energy unmanned aerial vehicle can also include: four sets of propellers (e.g., propeller i 801, propeller ii 802, propeller iii 803, and propeller iv 804 shown in fig. 2). Wherein, four groups of propellers are respectively arranged at the front parts of the four groups of power pods.
Preferably, the non-retractable landing gear 4 is in a two-point-front and two-point-rear configuration. The first two points are two main wheels (such as a main wheel I401 and a main wheel II 402 shown in FIG. 4) which are respectively half-buried at the lower parts of two groups of inner power pods (a power pod II 302 and a power pod III 303); the two rear points are two tail wheels (such as a tail wheel I403 and a tail wheel II 404 shown in FIG. 4) which are respectively half-buried at the lower parts of the left vertical tail and the right vertical tail.
Preferably, the vertical fin 2 comprises a left vertical fin 201 and a right vertical fin 202 which are symmetrically arranged, and the left vertical fin 201 and the right vertical fin 202 are respectively arranged at the wing tip of the left outer wing section 101 and the wing tip of the right outer wing section 103. The aileron 6 comprises a left aileron 601 and a right aileron 602 which are symmetrically arranged, and the left aileron 601 and the right aileron 602 are respectively arranged at the rear edge of the left outer wing section 101 and the rear edge of the right outer wing section 103. The rudder 7 includes a left rudder 701 and a right rudder 702 which are symmetrically disposed, and the left rudder 701 and the right rudder 702 are disposed at the rear edge of the left vertical tail 201 and the rear edge of the right vertical tail 202, respectively.
Preferably, the power pod 3 is internally provided with a motor and a storage battery, and the whole power pod is arranged in front of the front edge of the wing so as to balance the gravity center of the whole aircraft and enable the whole aircraft to be vertically stable. Wherein, the weight of the storage battery accounts for more than 30 percent of the total weight of the whole machine.
Preferably, the wing 1 is internally equipped with onboard equipment.
From the above description it follows that:
wing: the large-aspect-ratio pneumatic layout can improve the lift-drag ratio of the whole unmanned aerial vehicle and reduce energy consumption in the flight process; the small sweepback angle pneumatic layout can increase the control force arm of the control surface, and make the focus of the whole machine move backwards, and the focus is configured in front of the focus by the front-mounted centralized mass such as a storage battery, so that the whole machine is vertically stable. Furthermore, the middle wing section adopts a conventional high lift-drag ratio wing section, and the left/right outer wing sections adopt a reverse-bending wing section so as to improve the lift coefficient of the whole aircraft and balance the longitudinal moment.
Full-motion horizontal tail: by adopting a full-motion mode, on one hand, partial longitudinal balancing moment is provided, and on the other hand, the pitching control surface is made, so that the problems of lateral course coupling and nonlinearity during longitudinal attitude control are reduced.
Hanging a tail: the vertical stabilizer is used as a vertical stabilizer of the unmanned aerial vehicle and also used as a wingtip winglet, so that the heading of the whole unmanned aerial vehicle is statically stable, and the lift-drag ratio of the whole unmanned aerial vehicle is improved.
A power pod: as a loading structure of the unmanned aerial vehicle power system, four groups are provided, the four groups are respectively extended forwards and hung below the wings, a motor and a storage battery are arranged in the four groups, and a propeller is arranged at the front part of the four groups. The weight of the storage battery accounts for more than 30% of the total weight of the whole machine, and the power pod is integrated in front of the front edge of the wing so as to balance the gravity center of the whole machine.
Control surface: as the control surface of the unmanned aerial vehicle, the control surface comprises an aileron positioned at the rear edge of an outer wing section and a rudder positioned at the rear edge of a vertical tail, the horizontal course control of the whole unmanned aerial vehicle is realized, and the aileron and the rudder are respectively controlled by two pieces so as to improve the redundancy of the control surface.
Non-retractable landing gear: the main wheel is positioned below the power pod at the inner side, and the tail wheel is positioned below the vertical tail.
The embodiments in the present description are all described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The above description is only for the best embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are all covered by the protection scope of the present invention.
The details of the present invention not described in detail in the specification are well known to those skilled in the art.
Claims (10)
1. The utility model provides a flying wing overall arrangement solar energy unmanned aerial vehicle which characterized in that includes: the device comprises wings, a vertical tail, a power pod, a non-retractable landing gear, a control surface and a solar cell array; wherein, control surface includes: ailerons, rudders and full-motion horizontal tails;
the vertical tails are in a trapezoidal shape and are arranged at wing tips at two sides of the wing;
the full-motion horizontal tail adopts a rectangular shape and is arranged at the tail part of the middle section of the wing;
the ailerons are arranged at the rear edge of the wing;
the rudder is arranged at the rear edge of the vertical tail;
the power nacelle is hung below the wing;
the solar cell array is laid on the upper surface of the wing;
the non-retractable landing gear is arranged below the whole machine.
2. The flying wing layout solar drone of claim 1, wherein the wing includes: the wing comprises a middle wing section, a left outer wing section and a right outer wing section, wherein the left outer wing section and the right outer wing section are symmetrically arranged on the left side and the right side of the middle wing section;
the plane shapes of the left outer wing section, the middle wing section and the right outer wing section are all trapezoidal;
the full-motion horizontal tail is arranged at the tail part of the middle wing section.
3. The flying wing layout solar drone of claim 2,
the wings are in pneumatic layout with a large aspect ratio and a small sweepback angle; wherein, the middle wing section adopts a conventional high lift-drag ratio wing section; the left outer wing section and the right outer wing section adopt a reverse-bent wing shape.
4. The flying wing layout solar drone of claim 2, wherein the power pod has four sets; the two groups of power pods are hung below the left outer wing section, the other two groups of power pods are hung below the right outer wing section, and the two groups of power pods hung below the left outer wing section and the two groups of power pods hung below the right outer wing section are symmetrical around the center line of the middle wing section.
5. The flying wing layout solar drone of claim 4, further comprising: four groups of propellers; wherein, four groups of propellers are respectively arranged at the front parts of the four groups of power pods.
6. The flying wing layout solar unmanned aerial vehicle of claim 1, wherein the power pod is internally provided with a motor and a storage battery, and the power pod is integrated in front of the front edge of the flying wing to balance the gravity center of the whole aircraft so as to enable the whole aircraft to be vertically and statically stable.
7. The flying wing layout solar unmanned aerial vehicle of claim 6, wherein the weight of the battery accounts for more than 30% of the total weight of the whole unmanned aerial vehicle.
8. The flying wing layout solar unmanned aerial vehicle of claim 1, wherein airborne equipment is mounted inside the wings.
9. The flying wing layout solar unmanned aerial vehicle of claim 3, wherein the non-retractable landing gear is in a two-point-front and two-point-rear layout; the front two points are two main wheels which are respectively half-buried at the lower parts of the two groups of inner side power hanging cabinets; the two rear points are two tail wheels which are respectively half-buried at the lower parts of the left vertical tail and the right vertical tail.
10. The flying wing layout solar drone of claim 2,
the vertical tails comprise a left vertical tail and a right vertical tail which are symmetrically arranged, and the left vertical tail and the right vertical tail are respectively arranged at the wing tip of the left outer wing section and the wing tip of the right outer wing section;
the ailerons comprise a left aileron and a right aileron which are symmetrically arranged, and the left aileron and the right aileron are respectively arranged at the rear edge of the left outer wing section and the rear edge of the right outer wing section;
the rudder comprises a left rudder and a right rudder which are symmetrically arranged, and the left rudder and the right rudder are respectively arranged at the rear edge of the left vertical tail and the rear edge of the right vertical tail.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920813788.6U CN210284611U (en) | 2019-05-31 | 2019-05-31 | A flying-wing solar unmanned aerial vehicle |
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| CN201920813788.6U CN210284611U (en) | 2019-05-31 | 2019-05-31 | A flying-wing solar unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110254720A (en) * | 2019-05-31 | 2019-09-20 | 中国航天空气动力技术研究院 | A flying wing layout solar unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110254720A (en) * | 2019-05-31 | 2019-09-20 | 中国航天空气动力技术研究院 | A flying wing layout solar unmanned aerial vehicle |
| CN110254720B (en) * | 2019-05-31 | 2024-08-06 | 中国航天空气动力技术研究院 | A flying wing layout solar-powered drone |
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