CN109850180A - Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft - Google Patents
Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft Download PDFInfo
- Publication number
- CN109850180A CN109850180A CN201910061640.6A CN201910061640A CN109850180A CN 109850180 A CN109850180 A CN 109850180A CN 201910061640 A CN201910061640 A CN 201910061640A CN 109850180 A CN109850180 A CN 109850180A
- Authority
- CN
- China
- Prior art keywords
- wing
- length
- leading edge
- mach number
- full
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Abstract
The invention provides a wide-speed-range sweepback-varying telescopic pneumatic layout design method for a full-waverider aircraft. The variable sweep telescopic wing can change the span length thereof through telescoping and can change the sweep angle thereof through rotating. When the flight Mach number is less than 0.6, the sweep angle of the leading edge of the wing is kept to be 0 degree, and the span length is extended; when the flying Mach number is between 0.6 and 0.8, the sweep angle of the leading edge of the wing is changed into 30 degrees, and the span length is shortened; when the flying Mach number is between 0.8 and 2.0, the sweep angle of the leading edge of the wing is changed into 60 degrees, and the span length is further shortened; when the flight Mach number is larger than 2.0, the wings are all retracted into the fuselage, and the aerodynamic layout is changed into a hypersonic cruise full-waverider aircraft. The lift-drag ratio performance of the wide-speed-range full-waverider aircraft variable sweepback telescopic pneumatic layout in the state of flight Mach number of 0.3-2.0 is obviously improved compared with that of the original full-waverider aircraft.
Description
Technical field
The present invention relates to hypersonic aircraft Design of Aerodynamic Configuration technical fields, are specifically related to a kind of width speed domain and multiply entirely
Wave aircraft becomes the flexible aerodynamic arrangement's design method of sweepback.
Background technique
Hypersonic aircraft refers to that flight Mach number is greater than 5, is main with airbreathing motor or combinations thereof engine
Power is unpowered, and the aircraft that can be flown in atmosphere and across atmosphere medium-long range.Its application of hypersonic aircraft
Form include hypersonic cruise missile, hypersonic glide vehicle, hypersonic someone/unmanned aerial vehicle, sky and space plane and
A variety of aircraft such as hypersonic wide fast domain aircraft.
Hypersonic aircraft aerodynamic configuration mainly has axial symmetry configuration, lifting body configuration and waverider-derived three categories,
Wherein, waverider-derived realizes high lift-drag ratio under the conditions of hypersonic flight using shock wave compression principle (rider principle)
It is pneumatic to require, so that Waverider becomes a kind of ideal configuration of hypersonic aircraft.
Publication date is on 07 14th, 2016, and the patent of invention of Patent No. ZL201610552526.X discloses one kind
Hypersonic inside and outside flow integrated full Waverider aircraft design method.It will be 2016 07 the applying date to describe hereinafter conveniently
Months 14 days, hypersonic inside and outside flow integrated full rider disclosed in the patent of invention of Patent No. ZL201610552526.X flew
Row device design method can be referred to as original full Waverider aircraft design method.As shown in Figure 1, because original full Waverider aircraft
Using rider design theory, so that its lift resistance ratio better performances in the case where designing 6 state of flight of Mach number, in close design horse
Under 3~6 state of flight of Mach number of conspicuous number 6 also preferably, but it is poor in 0.3~2.0 range lift resistance ratio performance of Mach number, i.e.,
Sub-, poor across, supersonic speed lift resistance ratio performance, which has limited original full Waverider aircraft design methods to be applied to wide fast domain aircraft
Aircraft when design is sub-, across, supersonic flight performance.
Summary of the invention
In view of the defects existing in the prior art, it is flexible pneumatic to provide a kind of wide fast full Waverider aircraft change sweepback in domain by the present invention
Layout design method can effectively provide aircraft using the fast full Waverider aircraft in domain of the width of method provided by the invention design and exist
It is sub-, across, supersonic flight when lift resistance ratio performance.
To realize the above-mentioned technical purpose, the technical scheme is that
A kind of wide fast complete flexible aerodynamic arrangement's design method of Waverider aircraft change sweepback in domain, is installed on full Waverider aircraft
Wing, wing are to become sweepback telescopic wing, and the change sweepback telescopic wing can change its length by flexible, and can lead to
Rotation is crossed to change its angle of sweep；When flight Mach number is less than 0.6, the leading edge sweep of wing remains 0 degree, and length is stretched
It is long, generate the aerodynamic configuration under low 0.3~0.6 state of subsonic flight Mach number；When flight Mach number is between 0.6 to 0.8,
The leading edge sweep of wing becomes 30 degree, and length shortens, and generates pneumatic under high 0.6~0.8 state of subsonic flight Mach number
Configuration；When flight Mach number is between 0.8 to 2.0, the leading edge sweep of wing becomes 60 degree, and length further shortens, and generates
Transonic speed with the aerodynamic configuration under 0.8~2.0 state of supersonic flight Mach number；When flight Mach number is greater than 2.0, wing is complete
Portion is retracted fuselage, and aerodynamic arrangement becomes the hypersonic full Waverider aircraft of cruise.
Further, the present invention generates full rider using hypersonic inside and outside flow integrated full Waverider aircraft design method
Aircraft.Hypersonic inside and outside flow integrated full Waverider aircraft design method is techniques known, for details, reference can be made to
" hypersonic inside and outside flow integrated full Waverider aircraft design method, Ding Feng, Liu Jun etc., Patent No.
ZL201610552526.X, the applying date are on 07 14th, 2016 ".
Wing includes left side wing and right side wing, and left side wing and right side wing axis are symmetricly set on the left and right two of fuselage
Side.Left side wing and right side wing choose NACA6 tie wings type wing.Known to installation site of the wing on fuselage.In full rider
In the short transverse of aircraft fuselage, distance H of the horizontal cross-section where wing installation site apart from fuselage highest point is determined, really
Fuselage width L of the fixed full Waverider aircraft in wing installed position1。
In the present invention, the determination method of the aerodynamic configuration under low 0.3~0.6 state of subsonic flight Mach number is:
The position for installing wing on its fuselage of full Waverider aircraft is given, determines full Waverider aircraft in installation wing position
The fuselage width L at place1；
Give under low 0.3~0.6 state of subsonic flight Mach number install wing after full Waverider aircraft length L and
Chord length b, left side leading edge of a wing length and right side leading edge of a wing equal length, length L2It indicates, L2As shown in formula (1)；Left side
Trailing edge length and right side trailing edge equal length, length L3It indicates, L3As shown in formula (2)；Left side wing wing root chord
Length and right side wing wing root chord length equal length, length b1It indicates, b1As shown in formula (3)；Left side wing wingtip chord length
Length and right side wing wingtip chord length equal length, length b2It indicates, b2As shown in formula (4)；The left side leading edge of a wing and left side
Trailing edge is vertical with left side wing wingtip and the holding of left side wing wing root, the right side leading edge of a wing and right side trailing edge with
Right side wing wingtip and right side wing wing root keep vertical.Left side wing and right side wing at this time is collectively as flight Mach number
Wing under 0.3~0.6 state, referred to as low Subsonic Wing.
b1=b (3)
b2=b (4)
When wing configuration on fuselage is low Subsonic Wing, the full Waverider aircraft for merging low Subsonic Wing is generated,
The configuration is as the aerodynamic configuration under low 0.3~0.6 state of subsonic flight Mach number.
In the present invention, the determination method of the aerodynamic configuration under high 0.6~0.8 state of subsonic flight Mach number is:
Left side wing in low Subsonic Wing is rotated 30 degree to inboard along the wing root leading edge point of left side wing,
Right side wing in low Subsonic Wing is rotated 30 degree to inboard along the wing root leading edge point of right side wing；
At this point, left side leading edge of a wing length and right side leading edge of a wing length, which remain unchanged, keeps L2It is constant, L2Still such as
Shown in formula (1)；Left side trailing edge length and right side trailing edge length shorten, the L after shortening3As shown in formula (5)；Left side machine
Thriving root long degree and right side wing wing root length increase, the b after growth1As shown in formula (6)；Left side wing wingtip length and right side
Wing wingtip length, which remains unchanged, keeps b2It is constant, b2Still as shown in formula (4)；At this point, the left side leading edge of a wing and left side machine
Wing rear is vertical with the holding of left side wing wingtip, and the right side leading edge of a wing and right side trailing edge are kept with right side wing wingtip
Vertically；Left side wing and right side wing at this time is collectively as the wing under 0.6~0.8 state of flight Mach number, referred to as Gao Ya
Velocity of sound wing；
When wing configuration on fuselage is high Subsonic Wing, the full Waverider aircraft for merging high Subsonic Wing is generated,
The configuration is as the aerodynamic configuration under high 0.6~0.8 state of subsonic flight Mach number.
In the present invention, transonic speed with the determination method of the aerodynamic configuration under 0.8~2.0 state of supersonic flight Mach number
It is:
The left side wing of high Subsonic Wing is rotated 30 degree to inboard along the wing root leading edge point of left side wing, it will
The left side wing of high Subsonic Wing rotates 30 degree to inboard along the wing root leading edge point of right side wing；
At this point, left side leading edge of a wing length and right side leading edge of a wing length, which remain unchanged, keeps L2It is constant, L2Still such as
Shown in formula (1)；Left side trailing edge length and right side trailing edge length further shorten, the L after further shortening3Such as formula
(5) shown in；Left side wing wing root length and right side wing wing root length increase, the b after further increasing1As shown in formula (8)；It is left
Side wing wingtip length and right side wing wingtip length remain unchanged, i.e., keep b2It is constant, b2Still as shown in formula (4)；This
When, the left side leading edge of a wing and left side trailing edge are vertical with the holding of left side wing wingtip, the right side leading edge of a wing and right side wing
Rear is vertical with the holding of right side wing wingtip.Left side wing and right side wing at this time is collectively as transonic speed winged with supersonic speed
Wing under 0.8~2.0 state of row Mach number, referred to as transonic speed/supersonic wing；
Wing configuration on fuselage be transonic speed/supersonic wing when, generate and merge the full rider of high Subsonic Wing and fly
Row device, the configuration as transonic speed with the aerodynamic configuration under 0.8~2.0 state of supersonic flight Mach number.
Compared with the prior art, technical effect of the invention:
Becoming sweepback telescopic wing is that wing design can be changed its length by flexible in retractable structure；And wing
It is fixed on fuselage by mechanical rotating mechanism (as driven wing rotation by rotating electric machine) and realizes that the rotation of wing changes
Become its angle of sweep.Present invention innovation is that will become sweepback telescopic wing and full Waverider aircraft carries out Combined design, and design generates
The full Waverider aircraft in wide speed domain becomes the flexible aerodynamic arrangement of sweepback, when flight Mach number is less than 0.6, after becoming sweepback telescopic wing
Sweep angle remains 0 degree, length elongation；When flight Mach number is between 0.6 to 0.8, the angle of sweep for becoming sweepback telescopic wing becomes
30 degree, length shortens；When flight Mach number is between 0.8 to 2.0, the angle of sweep for becoming sweepback telescopic wing becomes 60 degree, length
Further shorten；When flight Mach number is greater than 2.0, becomes sweepback telescopic wing and be fully retracted into fuselage, aerodynamic arrangement becomes superb
The full Waverider aircraft of velocity of sound cruise.The full Waverider aircraft in wide speed domain becomes sweepback and stretches aerodynamic arrangement in flight Mach number 0.3 to 2.0
Lift resistance ratio performance significantly improving than original full Waverider aircraft under state.
The present invention improve original full Waverider aircraft it is sub-, across, supersonic flight state under lift resistance ratio performance, more have
It is applied to wide fast domain Flight Vehicle Design conducive to such Waverider aircraft.
Detailed description of the invention
Fig. 1 shows the maximum lift-drag ratio of original full Waverider aircraft aerodynamic arrangement with flight Mach number changing rule (horse
Conspicuous number 0.3~6.0, resistance has deducted internal resistance)；
Fig. 2 shows the top views of full Waverider aircraft；
Fig. 3 shows the side view of full Waverider aircraft；
Fig. 4 shows NACA6 tie wings type schematic diagram；
Fig. 5 shows the low Subsonic Wing and fuselage edge line schematic diagram that leading edge sweep is 0 degree；
Fig. 6 shows the schematic diagram of the low Subsonic Wing in design left side；
Fig. 7 shows the top view for merging the full Waverider aircraft of low Subsonic Wing；
Fig. 8 shows the side view for merging the full Waverider aircraft of low Subsonic Wing；
Fig. 9 shows the schematic diagram of high Subsonic Wing and fuselage edge line that leading edge sweep is 30 degree；
Figure 10 shows the top view for merging the full Waverider aircraft of high Subsonic Wing；
Figure 11 shows the side view for merging the full Waverider aircraft of high Subsonic Wing；
Figure 12 shows the schematic diagram of transonic speed/supersonic wing and fuselage edge line that leading edge sweep is 60 degree；
Figure 13 shows the top view of the fusion full Waverider aircraft of transonic speed/supersonic wing；
Figure 14 shows the side view of the fusion full Waverider aircraft of transonic speed/supersonic wing；
Figure 15 shows the vertical view of transonic speed/supersonic wing retraction fuselage full Waverider aircraft of hypersonic cruise
Figure；
Figure 16 shows the side view of transonic speed/supersonic wing retraction fuselage full Waverider aircraft of hypersonic cruise
Become the flexible aerodynamic arrangement of sweepback Figure 17 shows the wide fast full Waverider aircraft in domain and original full Waverider aircraft is pneumatic
The maximum lift-drag ratios of two shapes is laid out with flight Mach number changing rule comparison (Mach number 0.3~6.0, in resistance has deducted
Resistance)；
Fig. 2 is into Figure 17: the starting point of 1 expression fuselage left side edge line, the distal point of 2 expression fuselage left side edge lines, and 3
Indicate the starting point of fuselage right side edge line, 4 indicate the distal point of fuselage right side edge line, and 5 indicate the machine of full Waverider aircraft
Body highest point, 6 indicate the benchmark molded line of NACA6 tie wings type, and 7 indicate the starting point of fuselage axis of symmetry, and 8 indicate fuselage axis of symmetry
Distal point, 9 indicate the leading edge point of left side wing wing root, and 10 indicate the leading edge point of left side wing wingtip, and 11 indicate the left side wing wing
The rear point of root, 12 indicate the rear point of left side wing wingtip, and 13 indicate the leading edge point of right side wing wing root, and 14 indicate right side machine
The leading edge point of the thriving tip, 15 indicate the rear point of right side wing wing root, and 16 indicate the rear point of right side wing wingtip, and 17 indicate the wing
Type benchmark molded line 15 amplifies the air-foil molded line after b times, and 18 indicate the spanwise direction perpendicular to air-foil molded line 16.
Specific embodiment
With reference to the accompanying drawing 2 to 17, specific implementation method of the invention is further detailed.Signal of the invention
Examples and descriptions thereof are used to explain the present invention for property, does not constitute improper limitations of the present invention.
A kind of wide fast complete flexible aerodynamic arrangement's design method of Waverider aircraft change sweepback in domain, comprising the following steps:
S1, using hypersonic inside and outside flow integrated full Waverider aircraft design method, generate full Waverider aircraft, and really
Fixed full Waverider aircraft becomes the fuselage width at sweepback telescopic wing position in installation.
As shown in Fig. 2, design generates full rider using hypersonic inside and outside flow integrated full Waverider aircraft design method
Aircraft.Hypersonic inside and outside flow integrated full Waverider aircraft design method is techniques known, for details, reference can be made to
" hypersonic inside and outside flow integrated full Waverider aircraft design method, Ding Feng, Liu Jun etc., Patent No.
ZL201610552526.X, the applying date are on 07 14th, 2016 ".
Wing is installed on full Waverider aircraft, wing is to become sweepback telescopic wing, and the change sweepback telescopic wing can
Change its length by flexible, and its angle of sweep can be changed by rotating.Wing includes left side wing and right side wing,
Left side wing and right side wing axis are symmetricly set on the left and right sides of fuselage.Left side wing and right side wing choose NACA6 tie wings
Type wing.Known to installation site of the wing on fuselage.As shown in figure 3, in the short transverse of full Waverider aircraft fuselage, really
Determine distance H of the horizontal cross-section where wing installation site apart from fuselage highest point 5.As shown in Fig. 2, fuselage left side edge line 1-
The 2 left side edge line to install horizontal cross-section locating for wing position on fuselage, fuselage right side edge line 3-4 are to install on fuselage
The right side edge line of horizontal cross-section locating for wing position.Determine full Waverider aircraft in the fuselage width of wing installed position
L1, 1 starting point for indicating fuselage left side edge line in figure, 2 indicate the distal point of fuselage left side edge lines, and 3 indicate on the right side of fuselages
The starting point of edge line, 4 indicate the distal point of fuselage right side edge line.
S2, it determines the i.e. low Subsonic Wing of wing configuration under low 0.3~0.6 state of subsonic flight Mach number, generates
Merge the full Waverider aircraft of low Subsonic Wing.
The aerofoil profile benchmark molded line 6 of NACA6 tie wings type is as shown in Figure 4.The chord length of the aerofoil profile benchmark molded line 6 of NACA6 tie wings type
For 1m.As shown in figure 5,7 indicate the starting point of fuselage axis of symmetry, 8 indicate fuselage axis of symmetry for straight wing and fuselage edge line
Distal point.Use L2It indicates left side leading edge of a wing 9-10 length and right side leading edge of a wing 13-14 length, uses L3After indicating left side wing
Edge 11-12 length and right side trailing edge 15-16 length, use b1Indicate left side wing wing root 9-11 length and right side wing wing root
13-15 length, uses b2Indicate left side wing wingtip 10-12 length and right side wing wingtip 14-16 length.
Under 0.3~0.6 state of flight Mach number, the leading edge sweep of wing is 0 degree.Give low subsonic flight Mach number
Under 0.3~0.6 state install wing after full Waverider aircraft length L and chord length b, the length of left side leading edge of a wing 9-10 and
The equal length of right side leading edge of a wing 13-14, length L2It indicates, L2As shown in formula (1).The length of left side trailing edge 11-12
The equal length of degree and right side trailing edge 15-16, length L3It indicates, L3As shown in formula (2).Left side wing wing root chord length
The length of 9-11 and the equal length of right side wing wing root chord length 13-15, length b1It indicates, b1As shown in formula (3).Left side
The length of wing wingtip chord length 10-12 and the equal length of right side wing wingtip chord length 14-16, length b2It indicates, b2Such as formula
(4) shown in.Further, left side leading edge of a wing 9-10 and left side trailing edge 11-12 with left side wing wingtip 10-12 and a left side
Side wing wing root 9-11 keeps vertical, right side leading edge of a wing 13-14 and right side trailing edge 15-16 with right side wing wingtip
14-16 and right side wing wing root 13-15 keeps vertical.Left side wing and right side wing at this time is collectively as flight Mach number
Wing under 0.3~0.6 state, referred to as low Subsonic Wing.
b1=b (3)
b2=b (4)
The design of left side wing is as shown in Figure 6.After aerofoil profile benchmark molded line 6 as shown in Figure 4 is amplified b times, left side is obtained
Air-foil molded line 17 stretches left side air-foil molded line 17 along the spanwise direction 18 perpendicular to left side air-foil molded line
The length of L2 obtains left side wing.The design method of right side wing is identical as left side wing.Left side wing and right side machine at this time
The wing is collectively as the wing under 0.3~0.6 state of flight Mach number, referred to as low Subsonic Wing.
As shown in Figure 7 and Figure 8, it when the wing configuration on fuselage is low Subsonic Wing, generates and merges low Subsonic Wing
Full Waverider aircraft, the configuration is as the aerodynamic configuration under low 0.3~0.6 state of subsonic flight Mach number.
S3, it determines the i.e. high Subsonic Wing of wing configuration under high 0.6~0.8 state of subsonic flight Mach number, generates
Merge the full Waverider aircraft of high Subsonic Wing.
As shown in figure 9, leading edge sweep is 30 degree under 0.6~0.8 state of flight Mach number.The left side that step S2 is generated
Side wing rotates 30 degree to inboard along the wing root leading edge point of left side wing, and the right side wing that step S2 is generated is along the right side
The wing root leading edge point of side wing rotates 30 degree to inboard.
As shown in figure 9, the length of left side leading edge of a wing 9-10 and the length of right side leading edge of a wing 13-14 remain unchanged at this time
Keep L2It is constant, L2Still as shown in formula (1).The length of left side trailing edge 11-12 and right side trailing edge 15-16's
Length L3Shorten, the L after shortening3As shown in formula (5).The length of left side wing wing root 9-11 and the length of right side wing wing root 13-15
Degree increases, the b after growth1As shown in formula (6).Left side wing wingtip 10-12 length and right side wing wingtip 14-16 length are protected
Hold constant i.e. holding b2It is constant, b2Still as shown in formula (4).Further, left side leading edge of a wing 9-10 and left side trailing edge
11-12 is vertical with left side wing wingtip 10-12 holding, right side leading edge of a wing 13-14 and right side trailing edge 15-16 with the right side
Side wing wingtip 14-16 keeps vertical.Left side wing and right side wing at this time is collectively as 0.6~0.8 shape of flight Mach number
Wing under state, referred to as high Subsonic Wing.
As shown in Figure 10 and Figure 11, it when the wing configuration on fuselage is high Subsonic Wing, generates and merges high subsonic speed machine
The full Waverider aircraft of the wing, the configuration is as the aerodynamic configuration under high 0.6~0.8 state of subsonic flight Mach number.
S4, determine transonic speed be transonic speed/ultrasound with the wing configuration under 0.8~2.0 state of supersonic flight Mach number
Fast wing generates the fusion full Waverider aircraft of transonic speed/supersonic wing；
Under 0.8~2.0 state of flight Mach number, leading edge sweep is 60 degree.As shown in figure 12, high step S3 generated
Left side wing in Subsonic Wing rotates 30 degree to inboard along wing root leading edge point 7, the high infrasound that step S3 is generated
Right side wing in fast wing rotates 30 degree to inboard along wing root leading edge point 11.
At this point, the length of left side leading edge of a wing 9-10 and the length of right side leading edge of a wing 13-14 are remained unchanged and are kept
L2It is constant, L2Still as shown in formula (1)；The length of left side trailing edge 11-12 and the length of right side trailing edge 15-16 are into one
Step shortens, the L after further shortening3As shown in formula (5)；The length and right side wing wing root 13-15 of left side wing wing root 9-11
Length b1Increase, the b after further increasing1As shown in formula (8).The length and right side wing wingtip of left side wing wingtip 10-12
The length of 14-16, which remains unchanged, remains b2It is constant, b2Still as shown in formula (4).At this point, left side leading edge of a wing 9-10 and
Left side trailing edge 11-12 is vertical with left side wing wingtip 10-12 holding, after right side leading edge of a wing 13-14 and right side wing
Edge 15-16 is vertical with right side wing wingtip 14-16 holding.Left side wing and right side wing at this time collectively as transonic speed and
Wing under 0.8~2.0 state of supersonic flight Mach number, referred to as transonic speed/supersonic wing.
As shown in Figure 13 and Figure 14, the wing configuration on fuselage be transonic speed/supersonic wing when, generate and merge high infrasound
The full Waverider aircraft of fast wing, the configuration as transonic speed with the pneumatic structure under 0.8~2.0 state of supersonic flight Mach number
Type.
Under S5,2.0~6.0 state of flight Mach number, left side wing and right side wing are fully retracted full Waverider aircraft
Fuselage in, generate hypersonic cruise aerodynamic arrangement, the aerodynamic arrangement is as 2.0~6.0 shape of hypersonic flight Mach number
The full Waverider aircraft of hypersonic cruise under state.
As shown in Figure 15 and Figure 16, transonic speed/supersonic wing is retracted fuselage, generates the full rider flight of hypersonic cruise
Device.
The present invention installs wing on full Waverider aircraft, and wing is to become sweepback telescopic wing, the change sweepback telescopic machine
The wing can change its length by flexible, and can change its angle of sweep by rotating.When flight Mach number between 0.3 to
When 0.6, the leading edge sweep of wing remains 0 degree, and length reaches longest, generates low 0.3~0.6 shape of subsonic flight Mach number
Aerodynamic configuration under state is deformed into the full Waverider aircraft for merging low Subsonic Wing；When flight Mach number is between 0.6 to 0.8
When, the leading edge sweep of wing becomes 30 degree, and length shortens, and generates the gas under high 0.6~0.8 state of subsonic flight Mach number
Dynamic configuration is deformed into the full Waverider aircraft for merging high Subsonic Wing；When flight Mach number is between 0.8 to 2.0, wing
Leading edge sweep become 60 degree, length further shortens, generate transonic speed with 0.8~2.0 state of supersonic flight Mach number
Under aerodynamic configuration i.e. be deformed into fusion the full Waverider aircraft of transonic speed/supersonic wing；When flight Mach number is greater than 2.0
When, wing is fully retracted into fuselage, and aerodynamic arrangement becomes the hypersonic full Waverider aircraft of cruise.
Below with reference to specific implementation case to the original full rider mentioned in method provided by the present invention and background technique
Flight Vehicle Design method is compared:
In Mach number 6 as design Mach number, original full Waverider aircraft aerodynamic arrangement is generated, in identical design item
The wide fast full Waverider aircraft in domain is generated under part becomes the flexible aerodynamic arrangement of sweepback.It calculates and rises Figure 17 shows the numerical value of two shapes
It hinders than performance with the comparison of flight Mach number, full solid line indicates that wide fast domain Waverider aircraft becomes the flexible aerodynamic arrangement of sweepback in figure
Lift resistance ratio performance curve, dotted line indicate the lift resistance ratio performance curve of original full Waverider aircraft aerodynamic arrangement.As seen from Figure 17, exist
Subsonic speed, transonic speed with (Ma0.3~2.0) under the conditions of supersonic flight Mach number, the full Waverider aircraft in wide speed domain becomes sweepback and stretches
The lift resistance ratio of contracting aerodynamic arrangement is significantly improved compared to the lift resistance ratio of original full Waverider aircraft aerodynamic arrangement.Which improve originals
Shi Quan Waverider aircraft aerodynamic arrangement in subsonic speed, transonic speed with lift resistance ratio performance when supersonic flight.
Although right those skilled in the art will be clear that this hair in conclusion the present invention has been disclosed as a preferred embodiment
Bright range is not limited to example discussed above, it is possible to several changes and modification is carried out to it, without departing from appended right
The scope of the present invention that claim limits.Although oneself is through illustrating and describing the present invention in detail in the accompanying drawings and the description, this
Illustrating and describing for sample is only explanation or schematical, and not restrictive.The present invention is not limited to the disclosed embodiments.
By to attached drawing, the research of specification and claims, those skilled in the art can be in carrying out the present invention
Understand and realize the deformation of the disclosed embodiments.In detail in the claims, term " includes " is not excluded for other steps or element,
And indefinite article "one" or "an" be not excluded for it is multiple.The certain measures quoted in mutually different dependent claims
The fact does not mean that the combination of these measures cannot be advantageously used.Any reference marker in claims is not constituted pair
The limitation of the scope of the present invention.
Claims (6)
1. a kind of wide fast full Waverider aircraft in domain becomes the flexible aerodynamic arrangement's design method of sweepback, which is characterized in that fly in full rider
Wing is installed on row device, wing is to become sweepback telescopic wing, and the change sweepback telescopic wing can change its length by flexible,
And its angle of sweep can be changed by rotating；When flight Mach number is less than 0.6, the leading edge sweep of wing remains 0
Degree, length elongation, generates the aerodynamic configuration under low 0.3~0.6 state of subsonic flight Mach number；When flight Mach number between
When 0.6 to 0.8, the leading edge sweep of wing becomes 30 degree, and length shortens, and generates high 0.6~0.8 shape of subsonic flight Mach number
Aerodynamic configuration under state；When flight Mach number is between 0.8 to 2.0, the leading edge sweep of wing becomes 60 degree, and length is further
Shorten, generate transonic speed with the aerodynamic configuration under 0.8~2.0 state of supersonic flight Mach number；When flight Mach number is greater than 2.0
When, wing is fully retracted into fuselage, and aerodynamic arrangement becomes the hypersonic full Waverider aircraft of cruise.
2. the wide fast full Waverider aircraft in domain according to claim 1 becomes the flexible aerodynamic arrangement's design method of sweepback, feature
It is, wing includes left side wing and right side wing, and left side wing and right side wing axis are symmetricly set on the left and right sides of fuselage.
3. the wide fast full Waverider aircraft in domain according to claim 2 becomes the flexible aerodynamic arrangement's design method of sweepback, feature
It is, left side wing and right side wing choose NACA6 tie wings type wing.
4. the wide fast full Waverider aircraft in domain according to claim 3 becomes the flexible aerodynamic arrangement's design method of sweepback, feature
It is, the determination method of the aerodynamic configuration under low 0.3~0.6 state of subsonic flight Mach number is:
The position for installing wing on its fuselage of full Waverider aircraft is given, determines full Waverider aircraft at installation wing position
Fuselage width L1；
Give the length L and chord length that the full Waverider aircraft after wing is installed under low 0.3~0.6 state of subsonic flight Mach number
B, left side leading edge of a wing length and right side leading edge of a wing equal length, length L2It indicates, L2As shown in formula (1)；Left side wing
Trailing edge length and right side trailing edge equal length, length L3It indicates, L3As shown in formula (2)；Left side wing wing root chord length is long
Degree and right side wing wing root chord length equal length, length b1It indicates, b1As shown in formula (3)；Left side wing wingtip chord length length
With right side wing wingtip chord length equal length, length b2It indicates, b2As shown in formula (4)；The left side leading edge of a wing and left side wing
Rear is vertical with left side wing wingtip and the holding of left side wing wing root, the right side leading edge of a wing and right side trailing edge with right side
Wing wingtip and right side wing wing root keep vertical；Left side wing and right side wing at this time is collectively as flight Mach number 0.3
Wing under~0.6 state, referred to as low Subsonic Wing；
b1=b (3)
b2=b (4)
When wing configuration on fuselage is low Subsonic Wing, the full Waverider aircraft for merging low Subsonic Wing, the structure are generated
Type is as the aerodynamic configuration under low 0.3~0.6 state of subsonic flight Mach number.
5. the wide fast full Waverider aircraft in domain according to claim 4 becomes the flexible aerodynamic arrangement's design method of sweepback, feature
It is, the determination method of the aerodynamic configuration under high 0.6~0.8 state of subsonic flight Mach number is:
Left side wing in low Subsonic Wing is rotated 30 degree to inboard along the wing root leading edge point of left side wing, it will be low
Right side wing in Subsonic Wing rotates 30 degree to inboard along the wing root leading edge point of right side wing；
At this point, left side leading edge of a wing length and right side leading edge of a wing length, which remain unchanged, keeps L2It is constant, L2Still such as formula
(1) shown in；Left side trailing edge length and right side trailing edge length shorten, the L after shortening3As shown in formula (5)；Left side wing
Wing root length and right side wing wing root length increase, the b after growth1As shown in formula (6)；Left side wing wingtip length and right side machine
Thriving tip length, which remains unchanged, keeps b2It is constant, b2Still as shown in formula (4)；At this point, the left side leading edge of a wing and left side wing
Rear is vertical with the holding of left side wing wingtip, and the right side leading edge of a wing and right side trailing edge keep hanging down with right side wing wingtip
Directly；Left side wing and right side wing at this time is collectively as the wing under 0.6~0.8 state of flight Mach number, referred to as high infrasound
Fast wing；
When wing configuration on fuselage is high Subsonic Wing, the full Waverider aircraft for merging high Subsonic Wing, the structure are generated
Type is as the aerodynamic configuration under high 0.6~0.8 state of subsonic flight Mach number.
6. the wide fast full Waverider aircraft in domain according to claim 5 becomes the flexible aerodynamic arrangement's design method of sweepback, feature
It is, transonic speed the determination method with the aerodynamic configuration under 0.8~2.0 state of supersonic flight Mach number is:
The left side wing of high Subsonic Wing is rotated 30 degree to inboard along the wing root leading edge point of left side wing, by Gao Ya
The left side wing of velocity of sound wing rotates 30 degree to inboard along the wing root leading edge point of right side wing；
At this point, left side leading edge of a wing length and right side leading edge of a wing length, which remain unchanged, keeps L2It is constant, L2Still such as formula
(1) shown in；Left side trailing edge length and right side trailing edge length further shorten, the L after further shortening3Such as formula (5)
It is shown；Left side wing wing root length and right side wing wing root length increase, the b after further increasing1As shown in formula (8)；Left side
Wing wingtip length and right side wing wingtip length remain unchanged, i.e., keep b2It is constant, b2Still as shown in formula (4)；At this point,
The left side leading edge of a wing and left side trailing edge are vertical with the holding of left side wing wingtip, the right side leading edge of a wing and right side trailing edge
It is vertical with the holding of right side wing wingtip；Left side wing and right side wing at this time collectively as transonic speed with supersonic flight horse
Wing under conspicuous 0.8~2.0 state of number, referred to as transonic speed/supersonic wing；
Wing configuration on fuselage be transonic speed/supersonic wing when, generate the full Waverider aircraft for merging high Subsonic Wing,
The configuration as transonic speed with the aerodynamic configuration under 0.8~2.0 state of supersonic flight Mach number.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910061640.6A CN109850180B (en) | 2019-01-23 | 2019-01-23 | Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910061640.6A CN109850180B (en) | 2019-01-23 | 2019-01-23 | Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109850180A true CN109850180A (en) | 2019-06-07 |
| CN109850180B CN109850180B (en) | 2020-06-30 |
Family
ID=66895698
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910061640.6A Active CN109850180B (en) | 2019-01-23 | 2019-01-23 | Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109850180B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110341932A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of high-speed aircraft based on high pressure capture contour of flange |
| CN110341933A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of air suction type high-speed aircraft with the high pressure capture wing |
| CN110406671A (en) * | 2019-07-29 | 2019-11-05 | 中国科学院力学研究所 | A kind of side air inlet high-speed aircraft |
| 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 |
| CN115924104A (en) * | 2023-02-08 | 2023-04-07 | 北方工业大学 | Aircraft aerodynamic design method based on multi-section telescopic wing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1073222A (en) * | 1963-04-16 | 1967-06-21 | British Aircraft Corp Opperati | Improvements in aeroplanes |
| US20100264260A1 (en) * | 2009-04-17 | 2010-10-21 | Itt Manufacturing Enterprises, Inc. | Mechanism for folding, sweeping, and locking vehicle wings about a single pivot |
| CN102673774A (en) * | 2012-05-18 | 2012-09-19 | 北京理工大学 | Deforming wing mechanism |
| CN103593524A (en) * | 2013-11-13 | 2014-02-19 | 北京航空航天大学 | Dynamics modeling and analyzing method for aerospace vehicle |
| CN106005475A (en) * | 2016-07-14 | 2016-10-12 | 中国人民解放军国防科学技术大学 | Design method for hypersonic speed inner and outer flow integrated full wave rider flight vehicle |
| CN106672205A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-size variable sweep supersonic aircraft layout |
-
2019
- 2019-01-23 CN CN201910061640.6A patent/CN109850180B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1073222A (en) * | 1963-04-16 | 1967-06-21 | British Aircraft Corp Opperati | Improvements in aeroplanes |
| US20100264260A1 (en) * | 2009-04-17 | 2010-10-21 | Itt Manufacturing Enterprises, Inc. | Mechanism for folding, sweeping, and locking vehicle wings about a single pivot |
| CN102673774A (en) * | 2012-05-18 | 2012-09-19 | 北京理工大学 | Deforming wing mechanism |
| CN103593524A (en) * | 2013-11-13 | 2014-02-19 | 北京航空航天大学 | Dynamics modeling and analyzing method for aerospace vehicle |
| CN106005475A (en) * | 2016-07-14 | 2016-10-12 | 中国人民解放军国防科学技术大学 | Design method for hypersonic speed inner and outer flow integrated full wave rider flight vehicle |
| CN106672205A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-size variable sweep supersonic aircraft layout |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110341932A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of high-speed aircraft based on high pressure capture contour of flange |
| CN110341933A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of air suction type high-speed aircraft with the high pressure capture wing |
| CN110406671A (en) * | 2019-07-29 | 2019-11-05 | 中国科学院力学研究所 | A kind of side air inlet high-speed aircraft |
| 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 |
| CN115924104A (en) * | 2023-02-08 | 2023-04-07 | 北方工业大学 | Aircraft aerodynamic design method based on multi-section telescopic wing |
| CN115924104B (en) * | 2023-02-08 | 2024-01-26 | 北方工业大学 | Pneumatic design method of aircraft based on multi-section type telescopic wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109850180B (en) | 2020-06-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109850180A (en) | Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft | |
| CN108995803B (en) | Foldable wave rider pneumatic layout structure and method of supersonic passenger plane | |
| JP4703638B2 (en) | Aircraft leading edge system and corresponding sizing method | |
| US10625847B2 (en) | Split winglet | |
| US20070262205A1 (en) | Retractable multiple winglet | |
| US20170073062A1 (en) | Variable Geometry Wingtip | |
| CN202320772U (en) | High lift device of double-aisle large-type passenger plane | |
| Anyoji et al. | Planetary atmosphere wind tunnel tests on aerodynamic characteristics of a Mars airplane scale model | |
| Dwivedi et al. | Effect of surface roughness on aerodynamic performance of the wing with NACA 4412 airfoil at Reynolds number 1.7× 105 | |
| Ahmed et al. | Non-planarity to improve subsonic performance of delta wing at low angles of attack | |
| CN108502138A (en) | A kind of buzzard-type wing expanded letter high subsonic flight device aerodynamic arrangement using leading edge braced wing | |
| RU113238U1 (en) | LOW-MIXED UNMANNED AIRCRAFT | |
| CN204507270U (en) | Novel high lift joined wing configuration aircraft | |
| US9382000B1 (en) | Aircraft design | |
| Linehan et al. | Aerodynamics and lateral stability of low-aspect-ratio wings with dihedral at low Reynolds numbers | |
| Chowdhury et al. | The lift force produced by an unsteady translating plate with a rotating tip | |
| CN100513256C (en) | Sail wing for increasing lift force and stalling attack angle | |
| Watkins | Development of a micro air vehicle | |
| Radestock et al. | Deformation measurement in the wind tunnel for an UAV leading edge with a morphing mechanism | |
| Maqsood et al. | Propeller-induced effects on the aerodynamics of a small unmanned aerial vehicle | |
| CN106553749B (en) | Low speed airfoil design for aerodynamic improved performance of UAVs | |
| Rinoie et al. | Experimental studies of a 70-degree delta wing with vortex flaps | |
| Leng et al. | Comparisons of different propeller wake models for a propeller-wing combination | |
| M Jaffal et al. | Theoretical and Experimental Study of a Forward Swept Wing | |
| JP2002173093A (en) | Wing tip device of aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |