CN210047622U - Unmanned aerial vehicle pneumatic layout - Google Patents
Unmanned aerial vehicle pneumatic layout Download PDFInfo
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- CN210047622U CN210047622U CN201920869567.0U CN201920869567U CN210047622U CN 210047622 U CN210047622 U CN 210047622U CN 201920869567 U CN201920869567 U CN 201920869567U CN 210047622 U CN210047622 U CN 210047622U
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Abstract
The embodiment of the utility model discloses a pneumatic overall arrangement of unmanned aerial vehicle, the pneumatic overall arrangement of unmanned aerial vehicle includes: the aircraft comprises an aircraft body, main wings are arranged on two sides of the middle of the aircraft body, horizontal tails are arranged on two sides of the tail of the aircraft body, and two vertical tails are arranged at the top of the tail of the aircraft body; the air inlet channel is arranged on the airplane body, the air inlet channel is a Jialaite air inlet channel, and a nozzle of the air inlet channel is arranged at the tail part of the airplane body; the nose of the fuselage is ship-shaped, and the main wing and the horizontal tail are connected to the fuselage at the same front edge sweepback angle and rear edge sweepback angle. This pneumatic overall arrangement of unmanned aerial vehicle makes unmanned aerial vehicle stealth performance better, can improve unmanned aerial vehicle viability, the initiative right of fighting.
Description
Technical Field
The utility model relates to an aircraft field, concretely relates to pneumatic overall arrangement of unmanned aerial vehicle.
Background
Unmanned aerial vehicles are in fact a general term for unmanned aerial vehicles, and can be defined from a technical perspective as follows: unmanned fixed wing aircraft, unmanned helicopter, unmanned multi-rotor aircraft, and the like. In the Afghanistan battle of 2001-2002, the unmanned plane of the American predator performs a striking task for the first time, and becomes a milestone in the development history of the unmanned plane. In the iraq war of 2003, the army deployed and used about 90 drones, which were mainly responsible for tactical reconnaissance, battlefield patrol, and special target attack. The military unmanned aerial vehicle plays an important role in the air attack of Libiya. With the rapid development of high and new military technologies, unmanned military equipment almost permeates into various fields of battlefield spaces, unmanned aerial vehicles become important and critical forces influencing the battle progress and are paid more and more attention by countries, and military departments of many countries place the development of unmanned aerial vehicles in priority. The research and development of the unmanned aerial vehicle enter a new stage, the type and the model of the unmanned aerial vehicle achieve unprecedented prosperity, and the application is developing from the fighting support action of single reconnaissance and early warning and the like in the past to the direction of fighting, ensuring and supporting multiple purposes. At present, stealth and high-altitude penetration attack adopted in actual combat become the main means for solving the unfavorable situation of modern wars, and stealth performance becomes important performance of the unmanned aerial vehicle.
Therefore, it is necessary to develop a pneumatic layout of the unmanned aerial vehicle with better stealth effect.
The information disclosed in this background section of the invention is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information constitutes prior art already known to a person skilled in the art.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a pneumatic overall arrangement of unmanned aerial vehicle, this pneumatic overall arrangement stealthy performance of unmanned aerial vehicle is better.
In order to achieve the above object, according to the utility model provides a pneumatic overall arrangement of unmanned aerial vehicle, the pneumatic overall arrangement of unmanned aerial vehicle includes:
the aircraft comprises an aircraft body, main wings are arranged on two sides of the middle of the aircraft body, horizontal tails are arranged on two sides of the tail of the aircraft body, and two vertical tails are arranged at the top of the tail of the aircraft body;
the air inlet channel is arranged on the machine body, the air inlet channel is a Jialaite air inlet channel, and a nozzle of the air inlet channel is arranged at the tail part of the machine body;
the nose of the fuselage is ship-shaped, and the main wing and the horizontal tail are connected to the fuselage at the same front edge sweepback angle and rear edge sweepback angle.
Preferably, the main wings and the flat tails are in the shape of a trapezoid with a mini-chord ratio.
Preferably, the main wing and the horizontal tail wing are supersonic wing profiles with the maximum thickness of 2.5% -4.5%.
Preferably, the front edge sweepback angle of the main wing and the horizontal tail is 39-45 degrees, and the rear edge sweepback angle is 16-20 degrees.
Preferably, the machine head further comprises a front flap and a rear flap, the front flap is arranged on one side, close to the machine head, of the main wing, and the rear flap is arranged on one side, far away from the machine head, of the main wing.
Preferably, the front part has an extended length of 28% -35% of that of the unmanned aerial vehicle, and the rear part has an extended length of 14% -18% of that of the unmanned aerial vehicle.
Preferably, the vertical-fin wing profile is a supersonic wing profile with a maximum thickness of 2.5% -4.5%.
Preferably, the single-sided vertical tail is camber-inclined at 25-29 deg.
Preferably, the aircraft further comprises a rudder arranged on the side of the vertical tail far away from the aircraft nose.
Preferably, the extended length of the rudder is 85% to 90% of the vertical tail.
Preferably, still include outer aileron, outer aileron sets up the main wing is kept away from one side of fuselage, the expansion of outer vice is 11% -14% of unmanned aerial vehicle expansion.
Preferably, the nozzle is a conical vector nozzle.
Preferably, the nozzle is a rectangular nozzle.
Has the advantages that: through the setting of main wing, flat tail and vertical fin, the main wing reaches flat tail with the same leading edge sweepback angle and trailing edge sweepback angle connect in the fuselage makes unmanned aerial vehicle stealth performance better, can improve unmanned aerial vehicle viability, fight initiative.
Drawings
Fig. 1 is the structural schematic diagram of the pneumatic layout of the unmanned aerial vehicle according to an embodiment of the present invention.
Fig. 2 is a plan view of the aerodynamic layout of the unmanned aerial vehicle according to an embodiment of the present invention.
Fig. 3 is a rear view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention.
Fig. 4 is a side view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention.
Fig. 5 is a front view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention.
Fig. 6 is a bottom view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention.
Fig. 7 is a schematic structural diagram of an aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention.
Fig. 8 is a top view of an aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention.
Fig. 9 is a rear view of the aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention.
Fig. 10 is a side view of an aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the invention.
Fig. 11 is a front view of an unmanned aerial vehicle aerodynamic configuration of another embodiment of the present invention.
Fig. 12 is a bottom view of the aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention.
Fig. 13 is a schematic structural view of a spout according to another embodiment of the present invention.
Description of reference numerals:
1. a body; 2. a front opening; 3. a main wing; 4. hanging a tail; 5. a rudder; 6. flattening the tail; 7. a rear flap; 8. an outer flap; 9. an air inlet channel; 10. and (4) a nozzle.
Detailed Description
The technical scheme of the utility model is described in detail with the accompanying drawings.
The utility model provides an unmanned aerial vehicle pneumatic layout, unmanned aerial vehicle pneumatic layout includes:
the aircraft comprises an aircraft body, main wings are arranged on two sides of the middle of the aircraft body, horizontal tails are arranged on two sides of the tail of the aircraft body, and two vertical tails are arranged at the top of the tail of the aircraft body;
the air inlet channel is arranged on the machine body, the air inlet channel is a Jialaite air inlet channel, and a nozzle of the air inlet channel is arranged at the tail part of the machine body;
the nose of the fuselage is ship-shaped, and the main wing and the horizontal tail are connected to the fuselage at the same front edge sweepback angle and rear edge sweepback angle.
Specifically, through the setting of main wing, horizontal tail and vertical fin, the main wing reaches horizontal tail with the same leading edge sweepback angle and trailing edge sweepback angle connect in the fuselage makes unmanned aerial vehicle stealth performance better, can improve unmanned aerial vehicle viability, fight initiative. The high-speed invisible clothes have excellent high-speed performance, and meanwhile, the invisible design is carried out on the appearance, so that the invisible effect is excellent. The utility model discloses a conventional pneumatic overall arrangement of two vertical tails of extroversion, fuselage are the ship type and according to the lift body structural design, and the aircraft nose cross-section is the ship type. The horizontal tail is cut into the wing, the resistance characteristic of the whole aircraft is similar to that of a tailless delta wing during horizontal flight, the resistance is small, and the pneumatic efficiency is high.
More preferably, the main wing is provided with a small-angle dihedral angle, and the vertical tail adopts a supersonic airfoil with the maximum thickness of 2.5-4.5 percent and the camber ranges from 25 degrees to 29 degrees.
Further, the main wings and the flat tails are in a trapezoid shape with a small span ratio. More preferably, the main wing and the horizontal tail adopt supersonic airfoil profiles with the maximum thickness of 2.5% -4.5%, so that the unmanned aerial vehicle has high-speed performance and better stealth effect.
Furthermore, the front edge sweepback angle of the main wing and the horizontal tail is 39-45 degrees, and the rear edge sweepback angle is 16-20 degrees.
Specifically, the main wing, the horizontal tail and the vertical tail adopt supersonic airfoil shapes with the maximum thickness of 2.5-4.5%, so that the resistance generated by shock waves during supersonic flight can be effectively reduced, the unmanned aerial vehicle has excellent high-speed performance, and the stealth effect is better. The main wing and the horizontal tail have the leading edge sweepback angle of 39-45 degrees, the trailing edge sweepback angle of 16-20 degrees, the wing surface is trapezoidal, the leading edge sweepback can avoid the frontal surface of a shock cone, the shock resistance is reduced, the trailing edge sweepback can increase the wing chord length, increase the wing area and ensure that enough lift force is provided.
Furthermore, the novel aircraft further comprises a front flap and a rear flap, wherein the front flap is arranged on one side, close to the aircraft nose, of the main wing, and the rear flap is arranged on one side, far away from the aircraft nose, of the main wing.
Further, the front part has an extended length of 28% -35% of that of the unmanned aerial vehicle, and the rear part has an extended length of 14% -18% of that of the unmanned aerial vehicle.
Further, the aircraft further comprises a rudder, and the rudder is arranged on one side, away from the aircraft nose, of the vertical tail.
Further, the extended length of the rudder is 85% -90% of the extended length of the vertical tail.
Further, still include outer aileron, outer aileron sets up the main wing is kept away from one side of fuselage, the span length of outer aileron is 11% -14% of unmanned aerial vehicle span length.
Specifically, the vertical tail is camber-inclined by 25-29 degrees, and can play a role in stabilizing the longitudinal direction (pitching) and the course at the same time. The span length of the front fly is 28% -35% of that of the unmanned aerial vehicle, the span length of the rear fly is 14% -18% of that of the unmanned aerial vehicle, the span length of the outer aileron is 11% -14% of that of the unmanned aerial vehicle, and the span length of the rudder is 85% -90% of that of the vertical tail, so that the unmanned aerial vehicle can be guaranteed to have excellent control performance and aerodynamic performance.
Further, the nozzle is a conical vector nozzle.
Specifically, the conical vector nozzle has the advantages that the ternary vector control capability is realized, the nozzle can rotate by 360 degrees, the maneuvering capability of the unmanned aerial vehicle can be effectively enhanced, and the operation efficiency of the unmanned aerial vehicle can be improved; the disadvantage is poor stealth performance. When the unmanned aerial vehicle emphasizes the first maneuvering performance and the second stealth performance, the conical vector nozzle is installed.
Further, the nozzle is a rectangular nozzle.
Specifically, the rectangular nozzle has the advantages that the comprehensive stealth performance of the unmanned aerial vehicle can be improved, on one hand, infrared radiation can be inhibited, and the distance found by infrared tracking is reduced, and on the other hand, the rectangular nozzle effectively reduces the radar reflection section no matter in side view or rear view, so that the purpose of radar stealth is achieved; the disadvantage is that more than 10% of the engine thrust is lost. When the unmanned aerial vehicle emphasizes that stealth performance is the first and mobility performance is the second, a rectangular nozzle is installed.
Example 1
Fig. 1 is the structural schematic diagram of the pneumatic layout of the unmanned aerial vehicle according to an embodiment of the present invention. Fig. 2 is a plan view of the aerodynamic layout of the unmanned aerial vehicle according to an embodiment of the present invention. Fig. 3 is a rear view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention. Fig. 4 is a side view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention. Fig. 5 is a front view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention. Fig. 6 is a bottom view of the aerodynamic layout of an unmanned aerial vehicle according to an embodiment of the present invention.
As shown in fig. 1-6, the aerodynamic layout of the drone comprises:
the airplane comprises an airplane body 1, main wings 3 are arranged on two sides of the middle of the airplane body 1, horizontal tails 7 are arranged on two sides of the tail of the airplane body 1, and two vertical tails 5 are arranged at the top of the tail of the airplane body 1;
the air inlet 9 is arranged on the inside of the machine body 1, the air inlet 9 is a Jialaite air inlet 9, and a nozzle 10 of the air inlet 9 is arranged at the tail part of the machine body 1;
the nose of the fuselage 1 is ship-shaped, and the main wing 3 and the horizontal tail 7 are connected to the fuselage 1 at the same front edge sweepback angle and rear edge sweepback angle.
Wherein, the main wings 3 and the flat tails 7 are in the shape of a trapezoid with a small span ratio.
The novel aircraft nose structure further comprises a front flap 2 and a rear flap 7, wherein the front flap 2 is arranged on one side, close to the aircraft nose, of the main wing 3, and the rear flap 7 is arranged on one side, far away from the aircraft nose, of the main wing 3.
The aircraft further comprises a rudder 5, and the rudder 5 is arranged on one side, away from the aircraft nose, of the vertical tail 5.
Wherein, the spout 10 is a rectangular spout.
The main wing 3 adopts a supersonic airfoil with the maximum thickness of 3.8%, the horizontal tail 7 adopts a supersonic airfoil with the maximum thickness of 3%, the swept angle of the front edge of the main wing 3 and the horizontal tail 7 is 42%, the swept angle of the rear edge is 18%, the vertical tail 5 adopts a supersonic airfoil with the maximum thickness of 3%, the camber is 27%, the spanwise length of the rudder 5 is 87.5% of that of the vertical tail 5, the spanwise length of the front flap 2 is 31.6% of that of the unmanned aerial vehicle, the spanwise length of the rear flap 7 is 16.7% of that of the unmanned aerial vehicle, and the spanwise length of the aileron 8 is 12.6% of that of the unmanned aerial vehicle.
Example 2
Fig. 7 is a schematic structural diagram of an aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention. Fig. 8 is a top view of an aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention. Fig. 9 is a rear view of the aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention. Fig. 10 is a side view of an aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the invention. Fig. 11 is a front view of an unmanned aerial vehicle aerodynamic configuration of another embodiment of the present invention. Fig. 12 is a bottom view of the aerodynamic layout of an unmanned aerial vehicle according to another embodiment of the present invention. Fig. 13 is a schematic structural view of a spout according to another embodiment of the present invention
As shown in fig. 7-13, the aerodynamic layout of the drone comprises:
the airplane comprises an airplane body 1, main wings 3 are arranged on two sides of the middle of the airplane body 1, horizontal tails 7 are arranged on two sides of the tail of the airplane body 1, and two vertical tails 5 are arranged at the top of the tail of the airplane body 1;
the air inlet 9 is arranged on the inside of the machine body 1, the air inlet 9 is a Jialaite air inlet 9, and a nozzle 10 of the air inlet 9 is arranged at the tail part of the machine body 1;
the nose of the fuselage 1 is ship-shaped, and the main wing 3 and the horizontal tail 7 are connected to the fuselage 1 at the same front edge sweepback angle and rear edge sweepback angle.
Wherein, the main wings 3 and the flat tails 7 are in the shape of a trapezoid with a small span ratio.
The novel aircraft nose structure further comprises a front flap 2 and a rear flap 7, wherein the front flap 2 is arranged on one side, close to the aircraft nose, of the main wing 3, and the rear flap 7 is arranged on one side, far away from the aircraft nose, of the main wing 3.
The aircraft further comprises a rudder 5, and the rudder 5 is arranged on one side, away from the aircraft nose, of the vertical tail 5.
Wherein the nozzle is a conical vector nozzle.
The main wing 3 adopts a supersonic airfoil with the maximum thickness of 3.2%, the horizontal tail 7 adopts a supersonic airfoil with the maximum thickness of 3%, the swept angle of the front edge of the main wing 3 and the horizontal tail 7 is 40%, the swept angle of the rear edge is 16%, the vertical tail 5 adopts a supersonic airfoil with the maximum thickness of 4.5%, the camber is 29%, the spanwise length of the rudder 5 is 86.5% of that of the vertical tail 5, the spanwise length of the front flap 2 is 32.4% of that of the unmanned aerial vehicle, the spanwise length of the rear flap 7 is 17.6% of that of the unmanned aerial vehicle, and the spanwise length of the outer aileron 8 is 14% of that of the unmanned aerial vehicle.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle pneumatic layout, its characterized in that, unmanned aerial vehicle pneumatic layout includes:
the aircraft comprises an aircraft body, main wings are arranged on two sides of the middle of the aircraft body, horizontal tails are arranged on two sides of the tail of the aircraft body, and two vertical tails are arranged at the top of the tail of the aircraft body;
the air inlet channel is arranged on the machine body, the air inlet channel is a Jialaite air inlet channel, and a nozzle of the air inlet channel is arranged at the tail part of the machine body;
the nose of the fuselage is ship-shaped, and the main wing and the horizontal tail are connected to the fuselage at the same front edge sweepback angle and rear edge sweepback angle.
2. An unmanned aerial vehicle aerodynamic configuration according to claim 1, wherein the main wings and the flat tails are trapezoidal in shape with a mini-span ratio.
3. The aerodynamic layout of unmanned aerial vehicles of claim 2, wherein the leading-edge sweep angle of the main wing and the horizontal tail is 39 ° -45 ° and the trailing-edge sweep angle is 16 ° -20 °.
4. The aerodynamic layout of unmanned aerial vehicle of claim 1, further comprising a front flap and a rear flap, wherein the front flap is disposed on a side of the main wing close to the nose, and the rear flap is disposed on a side of the main wing far from the nose.
5. The aerodynamic layout of unmanned aerial vehicles of claim 4, wherein the span length of the front flap is 28% -35% of the span length of unmanned aerial vehicles, and the span length of the rear flap is 14% -18% of the span length of unmanned aerial vehicles.
6. An aerodynamic layout of unmanned aerial vehicles according to claim 1, further comprising a rudder disposed on a side of the vertical tail remote from the nose.
7. An unmanned aerial vehicle aerodynamic layout according to claim 6, wherein the spanwise length of the rudder is 85% to 90% of the vertical tail.
8. The aerodynamic layout of unmanned aerial vehicle of claim 1, further comprising an outer flap, the outer flap being disposed on a side of the main wing remote from the fuselage, the outer flap having a span length of 11% -14% of the span length of the unmanned aerial vehicle.
9. An aerodynamic layout of unmanned aerial vehicles according to claim 1, wherein the jets are conical vector jets.
10. An aerodynamic layout of unmanned aerial vehicles according to claim 1, wherein the nozzle is a rectangular nozzle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920869567.0U CN210047622U (en) | 2019-06-11 | 2019-06-11 | Unmanned aerial vehicle pneumatic layout |
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| CN201920869567.0U CN210047622U (en) | 2019-06-11 | 2019-06-11 | Unmanned aerial vehicle pneumatic layout |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110077589A (en) * | 2019-06-11 | 2019-08-02 | 四川垚磊科技有限公司 | UAV aerodynamic layout |
| CN112173068A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Adjustable helicopter side end plate structure |
-
2019
- 2019-06-11 CN CN201920869567.0U patent/CN210047622U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110077589A (en) * | 2019-06-11 | 2019-08-02 | 四川垚磊科技有限公司 | UAV aerodynamic layout |
| CN112173068A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Adjustable helicopter side end plate structure |
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Effective date of registration: 20231114 Address after: No. 278, West Section of Jianmen Road, Fucheng City, Mianyang City, Sichuan Province, 621000 Patentee after: COMPUTATIONAL AERODYNAMICS INSTITUTE OF CHINA AERODYNAMICS RESEARCH AND DEVELOPMENT CENTER Address before: 621000 No. 35 Mian'an Road, Fucheng District, Mianyang City, Sichuan Province (Software Industry Park, China (Mianyang) Science and Technology City) Patentee before: SICHUAN YAOLEI TECHNOLOGY Co.,Ltd. |