CN105129090A - Low resistance and low sonic boom layout supersonic aircraft - Google Patents
Low resistance and low sonic boom layout supersonic aircraft Download PDFInfo
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Abstract
The invention provides a low resistance and low sonic boom layout supersonic aircraft, and relates to the technical field of supersonic aircraft design. According to the low resistance and low sonic boom layout supersonic aircraft, the canard configuration and the large slenderness ratio aircraft body are used, the aircraft head completely droops, the lower edge of the tip portion upturns, the front undercarriage is forward received into the front undercarriage cabin of the aircraft head, the front portion of the middle-front aircraft body is provided with a full-motion trapezoidal canard having a middle sweepback, the back portion of the middle-front aircraft body and the position in front of the wing are the gas inlet channel of the power system, the middle-rear aircraft body adopts the wasp waist design so as to connect the root portions of the upper wing and the lower wing of the aircraft wings, two jet engines are vertically arranged on the rear aircraft body in a side-by-side manner, the trapezoidal vertical tail having a large sweepback is arranged on the upper portion of the rear aircraft body, and the tip portions of the upper wing and the lower wing of the aircraft wings are connected through the end plate. According to the low resistance and low sonic boom layout supersonic aircraft of the present invention, the shock wave generated due to the wing attack angle is weakened, the sonic boom influence of the shock wave on the ground is reduced, the stability is strong, and safety and reliability are provided.
Description
Technical field
The present invention relates to supersonic aircraft design field, in particular to the supersonic aircraft of the low sonic boom layout of a kind of low-resistance.
Background technology
For the aircraft carrying out high-performance cruise in endoatmosphere, there is minimum drag under supersonic speed state, aerodynamic arrangement's profile of maximum lift-drag ratio is its main design objective.But supersonic cruising flight can produce shock wave, the economy problems that wave resistance is brought and the noise emission that sonic boom brings are the yoke of supersonic aircraft development all the time.Especially for supersonic speed commercial aircraft, the impact how weakening shock wave is the focus of its topological design all the time.
The shock strength of supersonic aircraft depends on himself layout and volume.Therefore, fuselage and wing have just become aircraft mainly to generate the parts of shock wave.The fuselage of high-fineness ratio obviously can improve the distribution of shock wave, but is not enough to the change adverse effect of shock wave being produced to matter.Wing, as the topmost lift member of aircraft, is the breakthrough point reducing wave resistance and sonic boom impact.If wing is under identical wing area, can produce enough lift at the less angle of attack, then the shock wave that brings because of the angle of attack of whole body and resistance (comprising wave resistance) all will lower to some extent.In current supersonic aircraft aerodynamic arrangement category, wing area and cruise between the angle of attack and there is certain contradiction, cannot take into account the requirement of the low sonic boom of low wave resistance to little wing area and little flying angle.
The technical matters that present stage needs solution badly how to design a kind of supersonic aircraft, and this supersonic aircraft can overcome the defect existed in above-mentioned prior art.
Summary of the invention
The object of the invention is to solve above-mentioned deficiency of the prior art, a kind of rational in infrastructure, low-resistance low sonic boom requirement when not only can meet supersonic flight is provided, fully can also takes into account the supersonic aircraft of the low sonic boom layouts of the low-resistance of different mission phase to the requirement of aerodynamic force such as low speed landing, transonic acceleration, supersonic cruising.
Object of the present invention is achieved through the following technical solutions: the supersonic aircraft of the low sonic boom layout of a kind of low-resistance, and adopt canard configuration and high-fineness ratio fuselage, head entirety is slightly sagging, slightly upwarps at the Xia Yanchu of head tip; Nose-gear takes in forward the noselanding gear well of head bottom; After head, the complete dynamic trapezoidal canard of moderate sweep is arranged in the front portion of the middle forebody of circular cross section; It is the inlet channel of power system before middle forebody back, wing; Middle rear body adopts wasp waist design, and wasp waist part width is less, highly comparatively large, to connect the upper limb of wing, the root of bottom wing; Rear body is vertical is arranged in juxtaposition two jet engines, and rear body top is provided with highly swept trapezoidal vertical fin; The upper limb of wing, bottom wing tip are by end plate connection.
, wing is double-vane airfoil structure, and the aerofoil profile of upper limb and bottom wing is equicrural triangle in such scheme preferably, and the drift angle of upper limb, bottom wing is relative in inner side, base is parallel to each other.The spacing of upper Airfoil, determines according to the toe angle of triangle aerofoil profile and the design cruising speed of aircraft.
In above-mentioned either a program preferably, upper limb, lower wing span, determine according to the toe angle of triangle aerofoil profile and the design cruising speed of aircraft.
In above-mentioned either a program preferably, wing arranges first deviation leading edge, second can to deflect leading edge, first and can deflect trailing edge by deviation trailing edge, second, first can deviation leading edge, first can the first rotating shaft position of deviation trailing edge between 10% ~ 35% of wing chord length, second can deflect leading edge, second can deflect the second rotating shaft position of trailing edge between 65% ~ 75% of wing chord length.
In above-mentioned either a program preferably, aircraft carries out in subsonic acceleration and transonic flight process, first deviation leading edge, second can deflect leading edge respectively simultaneously around the first rotating shaft and the inside deviation of the second rotating shaft, makes first can deviation leading edge, the second inner side edge that can deflect leading edge be parallel to each other; First can deflect trailing edge simultaneously inwardly deviation by deviation trailing edge, second, makes first can deviation trailing edge, the second inner side edge that can deflect trailing edge be parallel to each other, forms transonic configuration.
In above-mentioned either a program preferably, carry out in landing process at aircraft, first deviation leading edge, second can deflect leading edge difference inclined certain angle under the first rotating shaft simultaneously, first can deflect trailing edge difference inclined certain angle under the second rotating shaft simultaneously by deviation trailing edge, second, forms takeoff configuration.
In above-mentioned either a program preferably, carry out in subsonic acceleration and transonic flight process at aircraft, first deviation leading edge, second can deflect leading edge and first and can deflect trailing edge and also recover normal condition simultaneously by deviation trailing edge, second, forms supersonic cruising configuration.
The beneficial effect of the supersonic aircraft of the low sonic boom layout of low-resistance provided by the present invention is, dual wing configuration adds one times relative to monoplane blade area, the angle of attack producing same lift can will be original half in theory, obviously can weaken the shock wave because the wing angle of attack generates; The shock wave reflection that the downward rear that dual wing configuration can make lower aerofoil be produced by top airfoil is propagated is to direction, high-altitude, and can reduce shock wave further affects the sonic boom on ground; Triangle (half rhombus) aerofoil profile that dual wing configuration adopts, can utilize the shock wave between double-vane to interfere the drag due to shock wave brought by wing thickness obviously to weaken.Dual wing configuration have employed adaptive can deviation front and rear edge, not only can increase wing camber in the landing stage, the low speed aerodynamic characteristic that compensate for unconventional aerofoil profile is not enough, can also make the leading edge of a wing interior inclined time, leading edge inside edge is parallel to each other, and the bow shock that when largely avoiding transonic, flow choking is formed, reduces wave resistance now, the breakthrough transonic stage of dual wing configuration is made to become possibility, safe and reliable.
Accompanying drawing explanation
Fig. 1 is the structural representation of a preferred embodiment of supersonic aircraft according to the low sonic boom layout of low-resistance of the present invention;
Fig. 2 is the aerofoil profile schematic diagram of the wing embodiment illustrated in fig. 1 of supersonic aircraft according to low-resistance of the present invention low sonic boom layout;
Fig. 3 is the aerofoil profile schematic diagram of wing in the landing process embodiment illustrated in fig. 1 according to the supersonic aircraft of low-resistance of the present invention low sonic boom layout;
Fig. 4 accelerates according to the subsonic embodiment illustrated in fig. 1 of the supersonic aircraft of low-resistance of the present invention low sonic boom layout and the aerofoil profile schematic diagram of wing in transonic process;
Fig. 5 is the aerofoil profile schematic diagram of wing in the supersonic flight process embodiment illustrated in fig. 1 according to the supersonic aircraft of low-resistance of the present invention low sonic boom layout.
Reference numeral:
In 1-head, 2-canard, 3-inlet channel, 4-wing, the trapezoidal vertical fin of 5-, 6-rear body, 7-, rear body, 8-first can deflect trailing edge, 8a-second can deflect trailing edge, 9-end plate, 10-first can deviation leading edge, 10a-second can deviation leading edge, forebody, 13-jet engine, 21-upper limb, 22-bottom wing, 23-shock wave, 24-backward wave, 27-first rotating shaft, 27a-second rotating shaft in 11-.
Detailed description of the invention
In order to understand the supersonic aircraft according to the low sonic boom layout of the low-resistance of the present invention program better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to the supersonic aircraft of the low sonic boom layout of low-resistance of the present invention.
As Figure 1-Figure 5, the supersonic aircraft of the low sonic boom layout of low-resistance provided by the invention, adopt canard configuration and high-fineness ratio fuselage, head 1 entirety is slightly sagging, slightly upwarps at the Xia Yanchu of head 1 tip; Nose-gear takes in forward the noselanding gear well of head 1 bottom; After head 1, the complete dynamic trapezoidal canard 2 of moderate sweep is arranged in the front portion of the middle forebody 11 of circular cross section; It is the inlet channel 3 of power system before middle forebody 11 back, wing 4; Middle rear body 7 adopts wasp waist to design, and wasp waist part width is less, highly comparatively large, to connect the upper limb 21 of wing 4, the root of bottom wing 22; Rear body 6 is vertical is arranged in juxtaposition two jet engines 13, and highly swept trapezoidal vertical fin 5 is arranged on rear body 6 top; Upper limb 21, bottom wing 22 tip of wing 4 are connected by end plate 9.Wing 4 is double-vane airfoil structure, and upper limb 21 is equicrural triangle with the aerofoil profile of bottom wing 22, and the drift angle of upper limb 21, bottom wing 22 is relative in inner side, base is parallel to each other.The spacing of upper limb 21, bottom wing 22, determines according to the toe angle of triangle aerofoil profile and the design cruising speed of aircraft.Spacing between upper limb 21, bottom wing 22 is determined according to the design cruising speed of the toe angle of triangle aerofoil profile and aircraft.
Wing 4 arranges first deviation leading edge 10, second can to deflect leading edge 10a, first and can deflect trailing edge 8a by deviation trailing edge 8, second, first can deviation leading edge 10, first can the first rotating shaft 27 position of deviation trailing edge 8 between 10% ~ 35% of described wing 4 chord length, second can deflect leading edge 10a, second can deflect the second rotating shaft 27a position of trailing edge 8a between 65% ~ 75% of described wing 4 chord length.Aircraft carries out in subsonic acceleration and transonic flight process, first deviation leading edge 10, second can deflect leading edge 10a respectively simultaneously around the first rotating shaft 27 and the inside deviation of the second rotating shaft 27a, makes first can be parallel to each other by deviation leading edge 10, second inner side edge that can deflect leading edge 10a; First can deflect trailing edge 8a simultaneously inwardly deviation by deviation trailing edge 8, second, makes first can be parallel to each other by deviation trailing edge 8, second inner side edge that can deflect trailing edge 8a, forms transonic configuration.
Carry out in landing process at aircraft, first deviation leading edge 10, second can deflect leading edge 10a respectively simultaneously around the first rotating shaft 27 times inclined certain angles, first can deflect trailing edge 8a difference inclined certain angle under the second rotating shaft 27a simultaneously by deviation trailing edge 8, second, forms takeoff configuration.
Aircraft carry out subsonic accelerate and transonic flight time, first can deviation leading edge 10, second can deflect leading edge 10a while around 27 and the inside deviation of 27a, make first can be parallel to each other by deviation leading edge 10, second inner side edge that can deflect leading edge 10a; First can deflect trailing edge 8a also simultaneously inwardly deviation by deviation trailing edge 8, second, the inner side edge of upper and lower two trailing edges is parallel to each other, forms transonic configuration
Carry out in supersonic flight process at aircraft, first deviation leading edge 10, second can deflect leading edge 10a and first and can deflect trailing edge 8a and also recover normal condition simultaneously by deviation trailing edge 8, second, forms supersonic cruising configuration.
The supersonic aircraft aerodynamic arrangement of low-resistance provided by the invention low sonic boom layout is symmetrical.Wing 4 adopts double-vane aerofoil profile, and upper aerofoil profile 21 is equicrural triangle with Airfoil 22, and relative thickness is 4%-6%.In inner side relatively, base is parallel to each other the drift angle of upper Airfoil.The spacing of upper Airfoil, determines according to the toe angle of triangle aerofoil profile and the design cruising speed of aircraft.Under design cruising speed, the shock wave 23 that upper limb 21 leading edge cusp place generates, just in time reaches the summit of bottom wing 22.Shock wave 23 produces backward wave 24 through summit, and backward wave 24 just in time reaches the trailing edge cusp of upper limb.The shock wave that bottom wing 22 produces is identical with the situation of upper limb 21 with backward wave.Under design cruising speed, the mutual shock wave reflection between aerofoil profile makes the drag due to shock wave of aerofoil profile greatly reduce.
Supersonic aircraft specific embodiment more than in conjunction with the low sonic boom layout of low-resistance of the present invention is described in detail, but be not limitation of the present invention, everyly according to technical spirit of the present invention, technical scope of the present invention is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of the supersonic aircraft technical scheme of the low sonic boom layout of low-resistance of the present invention.
Claims (7)
1. a supersonic aircraft for the low sonic boom layout of low-resistance, is characterized in that: adopt canard configuration and high-fineness ratio fuselage, and head (1) is overall sagging, upwarps on the lower edge of head (1) tip; Nose-gear takes in forward the noselanding gear well of head (1) bottom; After head (1), the complete dynamic trapezoidal canard (2) of moderate sweep is arranged in the front portion of the middle forebody (11) of circular cross section; It is the inlet channel (3) of power system before middle forebody (11) back, wing (4); Middle rear body (7) adopts wasp waist design, and wasp waist part width is less, highly comparatively large, to connect the upper limb (21) of wing (4), the root of bottom wing (22); Rear body (6) is vertical is arranged in juxtaposition two jet engines (13), and highly swept trapezoidal vertical fin (5) is arranged on rear body 6 top; Upper limb (21), bottom wing (22) tip of wing (4) are connected by end plate (9).
2. the supersonic aircraft of the low sonic boom layout of low-resistance as claimed in claim 1, it is characterized in that: described wing (4) is double-vane airfoil structure, described upper limb (21) is equicrural triangle with the aerofoil profile of described bottom wing (22), and the drift angle of described upper limb (21), described bottom wing (22) is relative in inner side, base is parallel to each other.
3. the supersonic aircraft of the low sonic boom layout of low-resistance as claimed in claim 2, is characterized in that: described upper limb (21), described bottom wing (22) spacing are determined according to the design cruising speed of the toe angle of triangle aerofoil profile and aircraft.
4. the supersonic aircraft of the low sonic boom layout of low-resistance as claimed in claim 2, it is characterized in that: on described wing (4), arrange first can deviation leading edge (10), second can deflect leading edge (10a), first can deviation trailing edge (8), second can deflect trailing edge (8a), first can deviation leading edge (10), first can the first rotating shaft (27) position of deviation trailing edge (8) between the 10%-35% of described wing (4) chord length, second can deflect leading edge (10a) second can deflect the second rotating shaft (27a) position of trailing edge (8a) between the 65%-75% of described wing (4) chord length.
5. the supersonic aircraft of the low sonic boom layout of low-resistance as claimed in claim 4, it is characterized in that: aircraft carries out in subsonic acceleration and transonic flight process, first deviation leading edge (10), second can deflect leading edge (10a) respectively simultaneously around the first rotating shaft (27) and the inside deviation of the second rotating shaft (27a), makes first can be parallel to each other by deviation leading edge (10), second inner side edge that can deflect leading edge (10a); First can deflect trailing edge (8a) simultaneously inwardly deviation by deviation trailing edge (8), second, makes first can be parallel to each other by deviation trailing edge (8), second inner side edge that can deflect trailing edge (8a), forms transonic configuration.
6. the supersonic aircraft of the low sonic boom layout of low-resistance as claimed in claim 4, it is characterized in that: carry out in landing process at aircraft, first can deviation leading edge (10), second can deflect the while that leading edge (10a) being distinguished inclined under the first rotating shaft (27), first can deflect the while that trailing edge (8a) being distinguished inclined under the second rotating shaft (27a) by deviation trailing edge (8), second, forms takeoff configuration.
7. the supersonic aircraft of the low sonic boom layout of low-resistance as claimed in claim 4, it is characterized in that: carrying out in subsonic acceleration and transonic flight process, first deviation leading edge (10), second can deflect leading edge (10a) and first and can deflect trailing edge (8a) and also recover normal condition simultaneously by deviation trailing edge (8), second, forms supersonic cruising configuration.
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| CN106043668A (en) * | 2016-07-06 | 2016-10-26 | 中国人民解放军海军航空工程学院 | Aerodynamic configuration of three-surface aircraft |
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| CN110979721B (en) * | 2019-12-24 | 2021-06-08 | 郑州航空工业管理学院 | Optimization method for double-wing layout time-limited carrying of air-drop aircraft |
| CN111634408A (en) * | 2020-06-03 | 2020-09-08 | 西北工业大学 | Supersonic double-wing and design method thereof |
| CN112550678A (en) * | 2020-12-10 | 2021-03-26 | 西北工业大学 | Supersonic aircraft sonic boom suppression method based on blowing and sucking flow control |
| CN112550678B (en) * | 2020-12-10 | 2021-10-15 | 西北工业大学 | Supersonic aircraft sonic boom suppression method based on blowing and sucking flow control |
| CN113859511A (en) * | 2021-09-29 | 2021-12-31 | 中国空气动力研究与发展中心空天技术研究所 | Low-resistance low-sonic-explosion supersonic civil aircraft pneumatic layout structure |
| CN113859511B (en) * | 2021-09-29 | 2023-10-31 | 中国空气动力研究与发展中心空天技术研究所 | Pneumatic layout structure of low-resistance low-acoustic explosion supersonic civil aircraft |
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| CN116101475A (en) * | 2022-09-07 | 2023-05-12 | 清华大学 | Wide-speed-domain variant double-wing structure and wide-speed-domain aircraft |
| CN116101475B (en) * | 2022-09-07 | 2023-08-25 | 清华大学 | Wide-speed-domain variant double-wing structure and wide-speed-domain aircraft |
| CN115432171A (en) * | 2022-11-07 | 2022-12-06 | 中国航空工业集团公司沈阳空气动力研究所 | Rear propulsion truss support wing layout suitable for hypersonic transport plane |
| CN115432171B (en) * | 2022-11-07 | 2023-01-03 | 中国航空工业集团公司沈阳空气动力研究所 | Rear propulsion truss support wing layout suitable for hypersonic transport plane |
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