CN108583849B - Pneumatic overall arrangement of supersonic speed silence unmanned aerial vehicle - Google Patents
Pneumatic overall arrangement of supersonic speed silence unmanned aerial vehicle Download PDFInfo
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- CN108583849B CN108583849B CN201810514477.XA CN201810514477A CN108583849B CN 108583849 B CN108583849 B CN 108583849B CN 201810514477 A CN201810514477 A CN 201810514477A CN 108583849 B CN108583849 B CN 108583849B
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Abstract
The invention discloses a pneumatic layout of a supersonic mute unmanned aerial vehicle, which comprises the following components: the aircraft nose, two duck wings, strake, two wings, air inlet channel, fuselage and two empennages; the machine head is connected with the front end of the machine body and is a conical-like hollow cylinder which is tilted upwards near the top point of the head and has a downward inclination angle; the two duck wings are arranged on two sides of the machine head; the edge strips are fused with the fuselage, and the edge strips are positioned at the rear part of the fuselage; the two wings are arranged on two sides of the fuselage, and the wings are positioned at the rear part of the edge strip; the back of the fuselage is provided with an air inlet channel which is positioned at the rear part of the wing; the two tail wings are arranged on two sides of the machine body, and the tail wings are positioned at the tail end of the machine body. The invention solves the problem that the hypersonic unmanned aerial vehicle flying in the air has a vacancy.
Description
Technical Field
The invention belongs to the field of design of pneumatic layout of unmanned aerial vehicles, and particularly relates to a pneumatic layout of a supersonic-speed mute unmanned aerial vehicle.
Background
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. At present, 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 past single fighting support effects such as reconnaissance and early warning to the direction of fighting, ensuring and supporting multiple purposes.
The use relation of the existing man-machine and unmanned aerial vehicle in the battle mainly includes two types: the first is a task substitution relationship, and the key point is that in the field of indirect attacks such as information, monitoring and investigation, the unmanned aerial vehicle gradually substitutes a man-machine to independently undertake single or multiple tasks. The second type is a cooperative relationship, mainly in the direct attack field of ground attack, air-to-ground combat and the like, the unmanned aerial vehicle and the human machine cooperate with each other to perform cooperative combat under the support of an air-to-ground information network, so as to form a combat system. Unmanned aerial vehicle need carry out the task under the command of someone, and both sides can form the advantage complementary, promote the ability of fighting.
Modern war models require that at the beginning of a battle the fighter be able to gain control of the air space under a defense system where the enemy is not completely paralyzed. In order to avoid radar detection, the traditional combat strategy relies on rapid and low-altitude penetration, and the effect of the strategy in symmetric warfare is gradually reduced when the increasingly advanced radar anti-stealth technology and relatively cheap surface-air missiles are faced.
With the development of high-precision guidance and target precise positioning technology, stealth and high-altitude penetration striking adopted in actual combat has become a main means for the adverse situation of modern war, however, although the mode enables the combat aircraft to avoid being hit down by small low-end-face air missiles in low and medium altitude, the combat aircraft still needs to be threatened by more advanced defense weapons. Therefore, it is still necessary to perform high-risk tasks with unmanned aerial vehicles instead of human. The effect of the character execution of the subsonic unmanned combat aircraft is not very satisfactory, and the characters are represented by weak maneuvering capacity during sudden prevention and escape and low navigational speed during high-altitude penetration. In contrast, the adoption of the supersonic unmanned combat aircraft has obvious advantages on both mobility and the task execution cycle of the target area.
In view of the speed development of the unmanned aerial vehicles, a large number of unmanned aerial vehicles which are successfully developed at present are concentrated in low-speed and subsonic range, and the hypersonic unmanned aerial vehicles flying in the sky have the defects.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the pneumatic layout of the supersonic-speed mute unmanned aerial vehicle is provided, and the problem that the high supersonic-speed unmanned aerial vehicle flying in the sky is vacant is solved.
The purpose of the invention is realized by the following technical scheme: a supersonic mute unmanned aerial vehicle aerodynamic configuration, comprising: the aircraft nose, two duck wings, strake, two wings, air inlet channel, fuselage and two empennages; the machine head is connected with the front end of the machine body and is a conical-like hollow cylinder which is tilted upwards near the top point of the head and has a downward inclination angle; the two duck wings are arranged on two sides of the machine head; the edge strips are fused with the fuselage, and the edge strips are positioned at the rear part of the fuselage; the two wings are arranged on two sides of the fuselage, and the wings are positioned at the rear part of the edge strip; the back of the fuselage is provided with an air inlet channel which is positioned at the rear part of the wing; the two tail wings are arranged on two sides of the machine body, and the tail wings are positioned at the tail end of the machine body.
In the pneumatic layout of the supersonic mute unmanned aerial vehicle, the tail wing comprises a vertical tail and a horizontal tail; one end of the horizontal tail is connected with the side wall of the machine body; the other end of the horizontal tail is connected with the vertical tail, and the vertical tail inclines outwards.
In the pneumatic layout of the supersonic mute unmanned aerial vehicle, the nose is a low-pitch explosion nose, the integral downdip angle is 8 degrees, and the head area is 5 degrees.
In the aerodynamic layout of the supersonic mute unmanned aerial vehicle, the canard wing is a swept-back canard wing with a small aspect ratio, the aspect ratio is 3.1, the sweep angle of the leading edge is 40 degrees, and the sweep angle of the trailing edge is 9.3 degrees.
In the pneumatic layout of the supersonic mute unmanned aerial vehicle, the strake sweepback angle is 80 degrees, and the length of the strake sweepback angle accounts for 25 percent of the length of the body.
In the aerodynamic layout of the supersonic mute unmanned aerial vehicle, the wings are swept-back wings with a small aspect ratio of 3.1, the sweep angle of the leading edge is 40 degrees, and the sweep angle of the trailing edge is-9.3 degrees.
In the aerodynamic layout of the supersonic mute unmanned aerial vehicle, the tail wing is U-shaped, the horizontal tail span length of the tail wing is greater than the width of the vortex system of the duck wing and the strake wing, the aspect ratio of the tail wing is 1.8, the front edge sweepback angle is 40 degrees, and the rear edge sweepback angle is-9.3 degrees.
In the pneumatic layout of the supersonic mute unmanned aerial vehicle, the vertical tail is positioned at the wing tip of the horizontal tail, the camber angle is 45 degrees, the sweep angle of the front edge is 45 degrees, and the sweep angle of the rear edge is 11 degrees.
In the aerodynamic layout of the supersonic mute unmanned aerial vehicle, the canard wing, the wing and the horizontal tail leading edge sweepback angle are consistent, and the wing and the horizontal tail trailing edge sweepback angle are consistent.
In the pneumatic overall arrangement of above-mentioned supersonic speed silence unmanned aerial vehicle, two duck wings are followed the central axis symmetry of fuselage, two wings are followed the central axis symmetry of fuselage, two fin edges the central axis symmetry of fuselage.
Compared with the prior art, the invention has the following beneficial effects:
(1) the pneumatic layout of the supersonic silent unmanned aerial vehicle solves the problem that a hypersonic unmanned aerial vehicle flying in the sky is vacant;
(2) the stealth characteristic of the pneumatic layout is superior to that of the conventional subsonic unmanned aerial vehicle, and the forward RCS is not more than 0.02m through measures such as 40-degree front edge sweepback wings, 40-degree front edge sweepback horizontal tails, 45-degree front edge sweepback and 45-degree outward-inclined vertical tails, full-wing body fusion and the like2；
(3) The supersonic sonic boom noise level of the pneumatic layout is superior to that of the conventional supersonic fighter, and the sonic boom strength is not higher than 80PLdB through the application of the low-pitch boom head and the low-pitch boom wing profile.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
fig. 1 is an outline view of a supersonic mute unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a front view of a supersonic mute unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a rear view of a supersonic mute unmanned aerial vehicle according to an embodiment of the present invention;
fig. 4 is a side view of a supersonic mute unmanned aerial vehicle provided in an embodiment of the present invention;
fig. 5 is a bottom view of a supersonic mute unmanned aerial vehicle provided in an embodiment of the present invention;
fig. 6 is a top view of a supersonic mute unmanned aerial vehicle provided by the embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is an outline view of a supersonic mute unmanned aerial vehicle according to an embodiment of the present invention; fig. 2 is a front view of a supersonic mute unmanned aerial vehicle according to an embodiment of the present invention; fig. 3 is a rear view of a supersonic mute unmanned aerial vehicle according to an embodiment of the present invention; fig. 4 is a side view of a supersonic mute unmanned aerial vehicle provided in an embodiment of the present invention; fig. 5 is a bottom view of a supersonic mute unmanned aerial vehicle provided in an embodiment of the present invention; fig. 6 is a top view of a supersonic mute unmanned aerial vehicle provided by the embodiment of the present invention.
As shown in fig. 1-6, the pneumatic layout of supersonic mute unmanned aerial vehicle comprises: the aircraft nose 1, two duck wings 2, strake 3, two wings 4, intake duct 5, fuselage 8 and two fin 9. Wherein the content of the first and second substances,
the machine head 1 is connected with the front end of the machine body 8, and the machine head is a conical-like hollow cylinder which is tilted upwards near the top point of the head and has a downward inclination angle; the two duck wings 2 are arranged on two sides of the machine head 1; the edge strip 3 and the machine body 8 are fused into a wing body, and the edge strip 3 is positioned at the rear part of the machine head 1; the two wings 4 are arranged on two sides of the fuselage 8, and the wings 4 are positioned at the rear part of the edge strip 3; the back of the fuselage 8 is provided with an air inlet 5, and the air inlet 5 is positioned at the rear part of the wing 4; two tail wings 9 are provided on both sides of the body 8, and the tail wings 9 are provided at the end of the body 8. The two canard wings 2 are symmetrical along the central axis of the fuselage 8, the two wings 4 are symmetrical along the central axis of the fuselage 8, and the two tail wings 9 are symmetrical along the central axis of the fuselage 8.
The tail wing 9 comprises a vertical tail 6 and a horizontal tail 7; wherein, one end of the horizontal tail 7 is connected with the side wall of the machine body 8; the other end of the horizontal tail 7 is connected with the vertical tail 6, and the vertical tail 6 inclines outwards.
Specifically, the nose 1 is arranged at the front section of the aerodynamic shape of the unmanned aerial vehicle, and the nose is a conical-like hollow cylinder which slightly upwarps near the vertex area of the head and has a downward inclination angle as a whole; the duck wings 2 are arranged on two sides of the unmanned aerial vehicle head; the edge strip 3 is arranged in the middle of the fuselage and is fused with the fuselage; the wing 4 is arranged in the middle of the fuselage, is positioned behind the edge strips and is fused with the fuselage; and the air inlet 5 is arranged at the middle rear part of the machine body and is fully fused with the machine body. The fin, it sets up at the pneumatic appearance back end of unmanned aerial vehicle, and vertical fin 6 is located 7 wingtips of horizontal tail and is the U type, just two vertical fin extroversions.
The head 1 is a low-pitch explosive head, the whole declination angle is about 8 degrees, and the head area declination is about 5 degrees.
The canard wing 2 is a swept-back canard wing with a small aspect ratio, the aspect ratio is about 3.1, the sweep angle of the leading edge is about 40 degrees, and the sweep angle of the trailing edge is about 9.3 degrees.
The sweep angle of the edge strips 3 is about 80 degrees, and the length of the edge strips accounts for about 25 percent of the length of the fuselage.
The wing 4 is a swept-back wing with a small aspect ratio, the aspect ratio is about 3.1, the leading edge sweep angle is about 40 degrees, and the trailing edge sweep angle is about-9.3 degrees.
The air inlet 5 is positioned at the rear part of the machine head, and the machine head partially shields the air inlet so as to be beneficial to forward stealth of the pneumatic layout.
The tail wing is U-shaped, the expansion length of a flat tail 7 of the tail wing is larger than the vortex width of a duck wing and a strake wing, the aspect ratio is about 1.8, the front edge sweepback angle is about 40 degrees, and the rear edge sweepback angle is about-9.3 degrees; the vertical tail 6 is positioned at the wing tip of the horizontal tail 7, and the camber angle is about 45 degrees, the leading edge sweep angle is about 45 degrees, and the trailing edge sweep angle is about 11 degrees.
The maneuverability of the aerodynamic layout of the unmanned aerial vehicle is superior to that of the existing subsonic unmanned aerial vehicle, and the wing area of the unmanned aerial vehicle is 63m2The over loading coefficient of the aircraft reaches-3- +7G (half oil half load state) under the condition of 0.85Ma transonic speed;the flight speed of the pneumatic layout is superior to that of the existing subsonic unmanned aerial vehicle, the cruising speed of the 1 WS-15 engine reaches 1.2Ma, and the maximum speed reaches 1.6 Ma; the stealth characteristic of the pneumatic layout is superior to that of the existing subsonic unmanned aerial vehicle, and the forward RCS is no more than 0.02m through measures such as 40-degree front edge sweepback wings, 40-degree front edge sweepback horizontal tails, 45-degree front edge sweepback and 45-degree outward-inclined vertical tails, full-wing body fusion and the like2(ii) a The supersonic sonic boom noise level of the pneumatic layout is superior to that of the existing supersonic fighter, and the sonic boom strength is not higher than 80PLdB through the application of the low-pitch boom nose and the wing profile of the low-pitch boom.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (2)
1. The utility model provides a pneumatic overall arrangement of supersonic speed silence unmanned aerial vehicle which characterized in that includes: the aircraft comprises a nose (1), two duck wings (2), an edge strip (3), two wings (4), an air inlet channel (5), an aircraft body (8) and two tail wings (9); wherein the content of the first and second substances,
the machine head (1) is connected with the front end of the machine body (8), and the machine head is a conical-like hollow cylinder which is tilted upwards near the top point area of the head and has a downward inclination angle;
the two duck wings (2) are arranged on two sides of the machine head (1);
the edge strip (3) and the machine body (8) are fused into a wing body, and the edge strip (3) is positioned at the rear part of the machine head (1);
the two wings (4) are arranged on two sides of the fuselage (8), and the wings (4) are positioned at the rear parts of the edge strips (3);
an air inlet channel (5) is formed in the back of the airplane body (8), and the air inlet channel (5) is located at the rear part of the wing (4);
the two tail wings (9) are arranged on two sides of the machine body (8), and the tail wings (9) are positioned at the tail end of the machine body (8); wherein the content of the first and second substances,
the tail wing (9) comprises a vertical tail (6) and a horizontal tail (7); wherein the content of the first and second substances,
one end of the horizontal tail (7) is connected with the side wall of the machine body (8);
the other end of the horizontal tail (7) is connected with the vertical tail (6), and the vertical tail (6) inclines outwards;
the handpiece (1) is a low-pitch explosive handpiece, the whole declination angle is 8 degrees, and the head area is declined upwards by 5 degrees;
the duck wing (2) is a swept-back duck wing with a small aspect ratio, the aspect ratio is 3.1, the sweep angle of the front edge is 40 degrees, and the sweep angle of the rear edge is 9.3 degrees;
the sweepback angle of the edge strip (3) is 80 degrees, and the length of the edge strip accounts for 25 percent of the length of the machine body (8);
the wing (4) is a swept-back wing with a small aspect ratio, the aspect ratio is 3.1, the leading edge sweep angle is 40 degrees, and the trailing edge sweep angle is-9.3 degrees;
the tail wing is U-shaped, the horizontal tail span length of the tail wing is larger than the vortex width of the duck wing and the strake wing, the aspect ratio of the tail wing is 1.8, the front edge sweepback angle is 40 degrees, and the rear edge sweepback angle is-9.3 degrees;
the vertical tail is positioned at the wing tip of the horizontal tail, the camber angle is 45 degrees, the sweepback angle of the front edge is 45 degrees, and the sweepback angle of the rear edge is 11 degrees.
2. The aerodynamic layout of supersonic velocity silence unmanned aerial vehicle of claim 1, characterized in that: two duck wings (2) are followed the central axis symmetry of fuselage (8), two wings (4) are followed the central axis symmetry of fuselage (8), two fin (9) are followed the central axis symmetry of fuselage (8).
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| CN110077589A (en) * | 2019-06-11 | 2019-08-02 | 四川垚磊科技有限公司 | UAV aerodynamic layout |
| CN110775273A (en) * | 2019-11-29 | 2020-02-11 | 西安航空学院 | Unmanned aerial vehicle |
| CN114537636B (en) * | 2022-03-25 | 2023-03-24 | 西北工业大学 | Low-sonic-explosion low-resistance pneumatic layout configuration for large supersonic civil aircraft |
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| US20120032033A1 (en) * | 2010-08-03 | 2012-02-09 | Jason Everett Cole | Wing piercing airplane |
| RU2614438C1 (en) * | 2015-11-03 | 2017-03-28 | Дмитрий Сергеевич Дуров | Supersonic convertible low-noise aircraft |
| CN106043668B (en) * | 2016-07-06 | 2019-07-19 | 中国人民解放军海军航空大学 | A kind of aerodynamic arrangement of three-control aircraft |
| CN106516086A (en) * | 2016-10-19 | 2017-03-22 | 戈晓宁 | High-invisibility lifting-body configuration aircraft without horizontal tail |
| CN107685868B (en) * | 2017-08-15 | 2023-12-12 | 浙江大学 | High subsonic stealth unmanned aerial vehicle |
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