CN105129090B - A kind of supersonic aircraft of low-resistance quick-fried layout in a low voice - Google Patents
A kind of supersonic aircraft of low-resistance quick-fried layout in a low voice Download PDFInfo
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- CN105129090B CN105129090B CN201510496120.XA CN201510496120A CN105129090B CN 105129090 B CN105129090 B CN 105129090B CN 201510496120 A CN201510496120 A CN 201510496120A CN 105129090 B CN105129090 B CN 105129090B
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Abstract
A kind of supersonic aircraft of low-resistance quick-fried layout in a low voice, is related to supersonic aircraft design field, and using canard configuration and high-fineness ratio fuselage, head is integrally sagging, and the lower edge of tip is upwarped；Nose-gear takes in forward the noselanding gear well of head；The entirely dynamic trapezoidal canard of the anterior arrangement moderate sweep of middle forebody；Before the back of middle forebody, wing for dynamical system air intake duct；Middle rear body is designed using wasp waist, to connect the root of the upper limb of wing, bottom wing；Rear body is vertical to be arranged in juxtaposition two jet engines, and highly swept trapezoidal vertical fin is arranged on rear body top；The upper limb of wing, bottom wing tip are by end plate connection.The supersonic aircraft of the low-resistance quick-fried layout in a low voice that the present invention is provided reduces shock wave because the wing angle of attack is generated, reduce shock wave affects on the sonic boom on ground, and stability is strong, safe and reliable.
Description
Technical field
The present invention relates to supersonic aircraft design field, in particular to a kind of low-resistance quick-fried layout in a low voice
Supersonic aircraft.
Background technology
For in the aircraft that endoatmosphere carries out high-performance cruise, with minimum drag under supersonic speed state, most
Aerodynamic arrangement's profile of big lift-drag ratio is its main design object.But supersonic cruising flight can produce shock wave, wave resistance band
The noise pollution that the economy problems that comes and sonic boom bring is the yoke of supersonic aircraft development all the time.Particularly with supersonic speed business
With aircraft, the impact for how weakening shock wave is the focus of its layout designs all the time.
The shock strength of supersonic aircraft is depending on its own layout and volume.Therefore, fuselage and wing just become
Aircraft mainly generates the part of shock wave.The fuselage of high-fineness ratio can be obviously improved the distribution of shock wave, but be not enough to shock wave
Adverse effect produce matter change.Wing, as the topmost lift member of aircraft, is reduce wave resistance and sonic boom impact one
Individual break-through point.If wing is under identical wing area, enough lift can be produced in the less angle of attack, then whole body because
The shock wave that the angle of attack brings and resistance (including wave resistance) will all lower.In current supersonic aircraft aerodynamic arrangement category
Interior, there is certain contradiction between wing area and the cruise angle of attack, it is impossible to take into account low wave resistance in a low voice quick-fried to little wing area and
The requirement of little flying angle.
The technical problem of urgent need to resolve is how to design a kind of supersonic aircraft at this stage, and the supersonic aircraft can
Overcome defect present in above-mentioned prior art.
Content of the invention
It is an object of the invention to solve above-mentioned deficiency of the prior art, provide a kind of rational in infrastructure, be not only able to full
Low-resistance quick-fried requirement in a low voice during sufficient supersonic flight, moreover it is possible to fully take into account the differences such as low speed landing, transonic speed acceleration, supersonic cruising
The supersonic aircraft of the low-resistance of requirement of the mission phase to aerodynamic force quick-fried layout in a low voice.
The purpose of the present invention is achieved through the following technical solutions：A kind of supersonic aircraft of low-resistance quick-fried layout in a low voice, adopts
With canard configuration and high-fineness ratio fuselage, head is integrally slightly sagging, slightly upwarps at the lower edge of head tip；Nose-gear to
The noselanding gear well of front income head bottom；After head, the anterior arrangement moderate sweep of the middle forebody of circular cross section
Entirely move trapezoidal canard；Before middle forebody back, wing for dynamical system air intake duct；Middle rear body is designed using wasp waist,
And wasp waist part width is less, highly larger, to connect the root of the upper limb of wing, bottom wing；Rear body is vertical to be arranged in juxtaposition two
Jet engine, rear body top are provided with highly swept trapezoidal vertical fin；The upper limb of wing, bottom wing tip are connected by end plate
Connect.
In such scheme preferably, wing is double-vane airfoil structure, and upper limb is isosceles triangle with the aerofoil profile of bottom wing,
Upper limb, the drift angle of bottom wing are inner side is relative, base is parallel to each other.The spacing of upper Airfoil, according to the toe angle of triangle aerofoil profile
Determine with the design cruising speed of aircraft.
In any of the above-described scheme preferably, upper limb, lower wing span, according to the toe angle of triangle aerofoil profile and aircraft
Design cruising speed is determining.
In any of the above-described scheme preferably, arrange on wing first can deviation leading edge, the second deflectable leading edge, first
Can deviation trailing edge, the second deflectable trailing edge, first can deviation leading edge, first can deviation trailing edge first rotating shaft position in airfoil chord
Between long 10%～35%, the second deflectable leading edge, the second rotating shaft position of the second deflectable trailing edge are in wing chord length
Between 65%～75%.
In any of the above-described scheme preferably, during aircraft carries out subsonic speed acceleration and transonic flight, first can
Deviation leading edge, the second deflectable leading edge respectively while around first rotating shaft and the inside deviation of the second rotating shaft, make first can deviation leading edge,
The inner side edge of the second deflectable leading edge is parallel to each other；First can deviation trailing edge, the second deflectable trailing edge while inside deviation, make the
One can deviation trailing edge, the inner side edge of the second deflectable trailing edge be parallel to each other, form transonic speed configuration.
In any of the above-described scheme preferably, during aircraft carries out landing, first can deviation leading edge, second can be inclined
Turn leading edge respectively and meanwhile under first rotating shaft inclined certain angle, first can deviation trailing edge, the second deflectable trailing edge respectively and meanwhile around
Inclined certain angle under second rotating shaft, forms takeoff configuration.
In any of the above-described scheme preferably, during aircraft carries out subsonic speed acceleration and transonic flight, first
Can deviation leading edge, the second deflectable leading edge and first can deviation trailing edge, the second deflectable trailing edge also and meanwhile recover normal condition, shape
Become supersonic cruising configuration.
The beneficial effect of the low-resistance provided by the present invention supersonic aircraft of quick-fried layout in a low voice is that dual wing configuration is relative
One times be increased in single-blade wing area, the angle of attack for producing same lift can substantially can subtract for original half in theory
The weak shock wave because of the generation of the wing angle of attack；Dual wing configuration can make the shock wave that the downward rear that top airfoil is produced by lower aerofoil is propagated anti-
High-altitude direction is mapped to, can reduce shock wave further affects on the sonic boom on ground；The triangle (half rhombus) that dual wing configuration is adopted
Aerofoil profile, it is possible to use the shock wave between double-vane interferes the drag due to shock wave for bringing wing thickness substantially to weaken.Dual wing configuration is employed
Adaptive can deviation front and rear edge, not only can the landing stage increase wing camber, compensate for the low speed of unconventional aerofoil profile
Aerodynamic characteristic is not enough, can also make the leading edge of a wing when interior inclined, and leading edge inside edge is parallel to each other, and largely avoids across sound
The bowshock that flow choking is formed when fast, reduces wave resistance now, and becoming the breakthrough transonic speed stage of dual wing configuration can
Can, safe and reliable.
Description of the drawings
Fig. 1 is the structural representation of the low-resistance preferred embodiment of the supersonic aircraft of quick-fried layout in a low voice according to the present invention
Figure；
Fig. 2 is the wing of the low-resistance embodiment illustrated in fig. 1 of the supersonic aircraft of quick-fried layout in a low voice according to the present invention
Aerofoil profile schematic diagram；
Fig. 3 is the embodiment illustrated in fig. 1 landing process of the low-resistance supersonic aircraft of quick-fried layout in a low voice according to the present invention
The aerofoil profile schematic diagram of middle wing；
Fig. 4 is that the embodiment illustrated in fig. 1 subsonic speed of the low-resistance supersonic aircraft of quick-fried layout in a low voice according to the present invention adds
The aerofoil profile schematic diagram of wing during speed and transonic speed；
Fig. 5 be according to the present invention low-resistance in a low voice the supersonic aircraft of quick-fried layout embodiment illustrated in fig. 1 supersonic speed fly
The aerofoil profile schematic diagram of wing during row.
Reference：
Rear body in 1- head, 2- canard, 3- air intake duct, 4- wing, the trapezoidal vertical fin of 5-, 6- rear body, 7-, 8- first can
Deflection trailing edge, the deflectable trailing edge of 8a- second, 9- end plate, 10- first can deviation leading edge, 10a- second can deviation leading edge, in 11-
Forebody, 13- jet engine, 21- upper limb, 22- bottom wing, 23- shock wave, 24- back wave, 27- first rotating shaft, 27a- second
Rotating shaft.
Specific embodiment
In order to more fully understand the supersonic aircraft of the low-resistance quick-fried layout in a low voice according to the present invention program, with reference to attached
Figure is further elaborated explanation to a preferred embodiment of the low-resistance of the present invention supersonic aircraft of quick-fried layout in a low voice.
As Figure 1-Figure 5, the supersonic aircraft of the low-resistance quick-fried layout in a low voice that the present invention is provided, using canard configuration and
High-fineness ratio fuselage, head 1 are overall slightly sagging, slightly upwarp at the lower edge of 1 tip of head；Nose-gear takes in forward head
The noselanding gear well of 1 bottom；After head 1, anterior the complete of arrangement moderate sweep of the middle forebody 11 of circular cross section is moved
Trapezoidal canard 2；It is the air intake duct 3 of dynamical system before 11 back of middle forebody, wing 4；Middle rear body 7 is designed using wasp waist,
And wasp waist part width is less, highly larger, to connect the root of the upper limb 21 of wing 4, bottom wing 22；The vertical cloth arranged side by side of rear body 6
Two jet engines 13 are put, highly swept trapezoidal vertical fin 5 is arranged on 6 top of rear body；The upper limb 21 of wing 4, bottom wing 22
Tip is connected by end plate 9.Wing 4 is double-vane airfoil structure, and upper limb 21 is isosceles triangle, upper limb with the aerofoil profile of bottom wing 22
21st, the drift angle of bottom wing 22 is inner side is relative, base is parallel to each other.Upper limb 21, the spacing of bottom wing 22, before triangle aerofoil profile
The design cruising speed of edge angle and aircraft is determining.Spacing between upper limb 21, bottom wing 22 is according to the leading edge of triangle aerofoil profile
The design cruising speed of angle and aircraft is determining.
Arrange on wing 4 first can deviation leading edge 10, the second deflectable leading edge 10a, first can deviation trailing edge 8, second
Deflectable trailing edge 8a, first can deviation leading edge 10, first can deviation trailing edge 8 27 position of first rotating shaft in 4 chord length of the wing
10%～35% between, the second deflectable leading edge 10a, the second rotating shaft 27a position of the second deflectable trailing edge 8a are in the machine
Between the 65%～75% of 4 chord length of the wing.Aircraft carries out subsonic speed and accelerates with during transonic flight, and first can deviation leading edge
10th, the second deflectable leading edge 10a is respectively while around first rotating shaft 27 and the inside deviation of the second rotating shaft 27a, and making first can be before deviation
Edge 10, the inner side edge of the second deflectable leading edge 10a are parallel to each other；First can deviation trailing edge 8, the second deflectable trailing edge 8a at the same to
Interior deviation, make first can deviation trailing edge 8, the inner side edge of the second deflectable trailing edge 8a be parallel to each other, form transonic speed configuration.
During aircraft carries out landing, first can deviation leading edge 10, the second deflectable leading edge 10a respectively while around the
Inclined certain angle under one rotating shaft 27, first can deviation trailing edge 8, the second deflectable trailing edge 8a respectively while under the second rotating shaft 27a
Certain angle, forms takeoff configuration partially.
When aircraft carries out subsonic speed acceleration and transonic flight, first can deviation leading edge 10, the second deflectable leading edge
10a while around 27 and 27a inside deviations, make first can deviation leading edge 10, the inner side edge of the second deflectable leading edge 10a mutually put down
OK；First can deviation trailing edge 8, the second deflectable trailing edge 8a also while inside deviation, makes the inner side edge of upper and lower two trailing edges mutual
Parallel, form transonic speed configuration
During aircraft carries out supersonic flight, first can deviation leading edge 10, the second deflectable leading edge 10a and first
Can deviation trailing edge 8, the second deflectable trailing edge 8a also and meanwhile recover normal condition, formed supersonic cruising configuration.
The supersonic aircraft aerodynamic arrangement of the low-resistance quick-fried layout in a low voice that the present invention is provided is symmetrical.Wing 4 is using double
Thriving type, upper aerofoil profile 21 are isosceles triangle with Airfoil 22, and relative thickness is 4%-6%.The drift angle of upper Airfoil exists
Inner side is relative, and base is parallel to each other.The spacing of upper Airfoil, according to the toe angle of triangle aerofoil profile and the design cruise of aircraft
Speed is determining.Under design cruising speed, the shock wave 23 of generation, the right up to top of bottom wing 22 at 21 leading edge cusp of upper limb
Point.Shock wave 23 produces back wave 24 through summit, and back wave 24 is right up to the trailing edge cusp of upper limb.The shock wave that bottom wing 22 is produced
Identical with the situation of upper limb 21 with back wave.Under design cruising speed, the mutual shock wave reflection between aerofoil profile causes swashing for aerofoil profile
Wave resistance is greatly lowered.
Supersonic aircraft specific embodiment above in association with the low-resistance quick-fried layout in a low voice of the present invention is described in detail, but
It is not limitation of the present invention, every technical spirit according to the present invention is equal to any simple modification made for any of the above embodiments
Belong to the technical scope of the present invention, in addition it is also necessary to explanation, according to the supersonic aircraft of the low-resistance quick-fried layout in a low voice of the present invention
The category of technical scheme includes any combination between each part mentioned above.
Claims (7)
1. the supersonic aircraft of a kind of low-resistance quick-fried layout in a low voice, it is characterised in that：Using canard configuration and high-fineness ratio fuselage,
Head (1) is overall sagging, upwarps in the lower edge of head (1) tip；Nose-gear takes in forward the nose-gear of head (1) bottom
Cabin；After head (1), entirely dynamic trapezoidal canard (2) of the anterior arrangement moderate sweep of the middle forebody (11) of circular cross section；
It is the air intake duct (3) of dynamical system before middle forebody (11) back, wing (4)；Middle rear body (7) are designed using wasp waist, and
Wasp waist part width is less, highly larger, to connect the root of the upper limb (21) of wing (4), bottom wing (22)；Rear body (6) is vertical
Two jet engines (13) are arranged in juxtaposition, highly swept trapezoidal vertical fin (5) are arranged on rear body (6) top；Wing (4)
Upper limb (21), bottom wing (22) tip are connected by end plate (9).
2. the supersonic aircraft of low-resistance as claimed in claim 1 quick-fried layout in a low voice, it is characterised in that：Wing (4) are
Double-vane airfoil structure, upper limb (21) are isosceles triangle with the aerofoil profile of the bottom wing (22), upper limb (21), described
The drift angle of bottom wing (22) is inner side is relative, base is parallel to each other.
3. the supersonic aircraft of low-resistance as claimed in claim 2 quick-fried layout in a low voice, it is characterised in that：Upper limb (21),
Bottom wing (22) spacing is determined according to the toe angle of triangle aerofoil profile and the design cruising speed of aircraft.
4. the supersonic aircraft of low-resistance as claimed in claim 2 quick-fried layout in a low voice, it is characterised in that：In the wing (4)
Upper arrange first can deviation leading edge (10), second deflectable leading edge (10a), first can deviation trailing edge (8), the second deflectable trailing edge
(8a), first can deviation leading edge (10), first can deviation trailing edge (8) first rotating shaft (27) position in the wing (4) chord length
10%-35% between, the second rotating shaft (27a) position of second deflectable leading edge (10a) second deflectable trailing edge (8a) is in institute
State between the 65%-75% of wing (4) chord length.
5. the supersonic aircraft of low-resistance as claimed in claim 4 quick-fried layout in a low voice, it is characterised in that：Aircraft carries out subsonics
Speed accelerate and transonic flight during, first can deviation leading edge (10), second deflectable leading edge (10a) respectively simultaneously around first
The inside deviation of rotating shaft (27) and the second rotating shaft (27a), make first can deviation leading edge (10), second deflectable leading edge (10a) interior
Side is parallel to each other；First can deviation trailing edge (8), second deflectable trailing edge (8a) while inside deviation, making first can be after deviation
Edge (8), the inner side edge of second deflectable trailing edge (8a) are parallel to each other, and form transonic speed configuration.
6. the supersonic aircraft of low-resistance as claimed in claim 4 quick-fried layout in a low voice, it is characterised in that：Carry out in aircraft
During drop, first can deviation leading edge (10), second deflectable leading edge (10a) respectively while under first rotating shaft (27) partially, the
One can deviation trailing edge (8), second deflectable trailing edge (8a) respectively while under the second rotating shaft (27a) partially, form takeoff configuration.
7. the supersonic aircraft of low-resistance as claimed in claim 4 quick-fried layout in a low voice, it is characterised in that：Add subsonic speed is carried out
Speed and transonic flight during, first can deviation leading edge (10), second deflectable leading edge (10a) and first can deviation trailing edge
(8), second deflectable trailing edge (8a) is also while recovery normal condition, forms supersonic cruising configuration.
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| US6857599B2 (en) * | 2002-12-30 | 2005-02-22 | Aerion Corporation | Highly swept canard with low sweep wing supersonic aircraft configuration |
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