CN113626934B - Multi-configuration coordination design method for unmanned aerial vehicle wing with flying wing layout - Google Patents
Multi-configuration coordination design method for unmanned aerial vehicle wing with flying wing layout Download PDFInfo
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Abstract
The invention relates to the field of unmanned aerial vehicle design, in particular to a multi-configuration coordination design method for an unmanned aerial vehicle wing with an all-wing layout, which comprises the following steps of firstly, performing coordination design on wing dimension parameters; step two, wing plane parameters are designed in a coordinated manner; step three, wing profile parameters are designed in a coordinated mode; step four, wing profile coordination design; fifthly, the high aspect ratio wing matched with the middle and small aspect ratio flying wing layout unmanned aerial vehicle platform is designed in a coordinated manner; and aiming at each group of profiles, a scheme with the maximum cruising lift-drag ratio and the minimum low head moment is selected through simulation and used as a final high aspect ratio wing scheme. The design method is simple, has good practicability, avoids repeated iteration of scheme design, solves the pneumatic design problem which is the key problem of multi-configuration wing design of the unmanned aerial vehicle with the flying wing layout, further promotes the configuration-changing technology of the unmanned aerial vehicle with the flying wing layout to land, and has high engineering application value.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicle design, in particular to a multi-configuration coordination design method for an unmanned aerial vehicle wing with an all-wing layout.
Background
The flying wing layout unmanned plane has the advantages of high aerodynamic efficiency, good stealth performance, light structural weight, large effective loading space and the like, and has become the main development direction of future airplanes recognized in the world and the current research and development hot spots of military strong countries in the world, such as a B2 bomber, an X47B unmanned plane, an RQ180 unmanned plane in the United states, neurons in France, thiens and Raushes in the United kingdom. Since the wing is the main component for generating the lift force of the whole aircraft, the layout form of the wing determines the purpose of the unmanned aerial vehicle, for example, the unmanned aerial vehicle is required to have higher lift-drag ratio in long distance and long voyage, the wing is generally designed to have large aspect ratio and small sweepback angle, and the unmanned aerial vehicle is required to have larger sweepback angle in high stealth. Therefore, unmanned aerial vehicles designed for high stealth cannot meet long-endurance flight requirements, and unmanned aerial vehicles designed for long-endurance flight cannot meet high stealth capability requirements, which would result in limitations of one type of unmanned aerial vehicle in performing tasks.
The multi-configuration wing is designed into a replaceable universal part, so that the purpose that the unmanned aerial vehicle configuration is quickly converted by exchanging different wings is achieved, the same type of aircraft can adapt to different task/function/field requirements is achieved, the number of unmanned aerial vehicles is greatly reduced, facilities are guaranteed, the cost is reduced, the utilization rate of the unmanned aerial vehicle is increased, and the use efficiency and the cost are higher.
The design of the multi-configuration wing of the unmanned aerial vehicle with the flying wing layout becomes a great technological change in the unmanned aerial vehicle design field in the future, but from the pneumatic design, different wings are assembled, the pneumatic performance of the whole unmanned aerial vehicle is completely different, and particularly, the longitudinal, transverse and course pneumatic characteristics of the unmanned aerial vehicle can be obviously changed aiming at the flying wing layout, and meanwhile, the pneumatic focus and the gravity center of the whole unmanned aerial vehicle can be changed, so that a series of matching and controlling problems of the unmanned aerial vehicle are brought. Therefore, a coordinated design between different configurations of wings is important for an flying wing layout drone for a multi-configuration wing. In the aspect of aerofoil layout unmanned aerial vehicle wing variable configuration research, the patent number of the aerofoil layout unmanned aerial vehicle wing research institute is CN201420760818.9, the name is modular aerofoil layout, only a scheme is disclosed, and a design method is not disclosed, so that for the aerofoil layout unmanned aerial vehicle wing variable configuration design, firstly, the difficulty in pneumatic design is solved, and the aerofoil variable configuration technology is further promoted to be applied to engineering.
Disclosure of Invention
The invention provides a method for the aerodynamic coordination design of a multi-configuration wing of an unmanned aerial vehicle in an airplane layout by using a medium-small aspect ratio to realize the basic configuration of the unmanned aerial vehicle.
In order to achieve the technical effects, the invention is realized by the following technical scheme:
a multi-configuration coordination design method for an unmanned aerial vehicle wing with an all-wing layout comprises the following steps of
Step one, wing size parameters are designed in a coordinated mode;
step two, wing plane parameters are designed in a coordinated manner;
step three, wing profile parameters are designed in a coordinated mode;
step four, wing profile coordination design;
fifthly, the high aspect ratio wing matched with the middle and small aspect ratio flying wing layout unmanned aerial vehicle platform is designed in a coordinated manner;
and aiming at each group of profiles, a scheme with the maximum cruising lift-drag ratio and the minimum low head moment is selected through simulation and used as a final high aspect ratio wing scheme.
Further, the first step includes:
step a) determining the wing area S:
setting the cruising lift coefficient C L According to the use requirement, determining a cruise design parameter: cruise speed V, cruise altitude H, cruise weight G, balanced by lift L and gravity:
G＝L (1)
the combination of formulas (1) to (2) yields:
where ρ is the air density corresponding to cruise altitude H.
Step b) determination of the machine span length b R ：
The wing aspect ratio A is 15-20, and according to the relation between the aspect ratio and the wing area:
the calculated span length is as follows:
step c) determining the root chord length c r Tip chord length c t ：
The tip-root ratio lambda of the unmanned aerial vehicle is generally 0.3-0.5, namely:
the calculation formula of the trapezoid wing area is as follows:
the combination of formulas (5) to (6) yields:
further, the second step is specifically:
the wing plane parameters include wing sweep angle Λ ω And wing station h y Let the requirement of the control system on the stability margin of the unmanned aerial vehicle be C mCL Stability margin C mCL The design gravity center G of the unmanned plane platform ranges from-0.1 to-0.05 y Calculating the design focus position x of the new wing according to the conversion relation between the gravity center and the pneumatic focus to obtain a known value F The method comprises the following steps:
x F ＝G y -C mCL *b A (9)
in formula (9), b A For the average aerodynamic chord length of the wing, for a general trapezoidal wing, the average aerodynamic chord calculation formula is as follows:
in the formula (10), b Average of The specific calculation formula is as follows, wherein the geometric average chord length of the wing, eta is the root tip ratio:
the focal position of the large aspect ratio trapezoidal wing is calculated by adopting a lifting surface theory:
in the formula (13) of the present invention,b is A Is a spread station:
and (3) obtaining the joint solution formulas (9) - (14):
from equation (15), it can be seen that the wing sweep angle Λ ω And wing station h y In a linear one-to-one correspondence;
still further, according to fuselage constraints:
step a) wing sweep angle Λ w And a fuselage sweep angle lambda b The following relationship should be satisfied
46°≤Λ b -Λ w ≤54° (15)
Step b), the butt joint position of the wing front edge and the fuselage is selected at 90% -95% of the fuselage spanwise direction, and the wing station position range under a certain sweepback angle is obtained through a drawing judgment method;
wing sweep angle lambda is combined with formula (15) and fuselage constraints ω And wing station h y A finite data set may be composed:
further, the third step includes the following steps:
the aerofoil section parameters comprise the effective aerodynamic surface wing root span-wise station y ra Chord length c ra Wing-fuselage separation plane, wing tip section torsion angle tau t And the effective aerodynamic surface wing root torsion angle tau of the wing ra ，
Step a) determining wing root span-wise station y of effective aerodynamic surface of wing ra Chord length c ra ：
In equation (16), for each set of wing sweep angles Λ ω And wing station h y The plane shape and position of the whole wing are determined and unique, and the spanwise station position and chord length corresponding to the intersection point of the extension of the rear edge of the airplane body and the rear edge of the new wing are the effective aerodynamic surface wing root spanwise station position y of the wing ra Chord length c ra ；
Step b) determining the wing-fuselage separation surface:
the wing body is separated and selected at 85% -90% of the position of the fuselage spreading station;
step c) determining the wingtip section torsion angle τ t And the effective aerodynamic surface wing root torsion angle tau of the wing ra ：
Wing tip section torsion angle tau t Selecting a range from-2 degrees to-4 degrees;
in order to compensate the loss of lift force caused by the negative torsion angle of the wing tip section, the effective aerodynamic surface wing root section of the wing is not twisted or adopts a smaller positive torsion angle, tau ra Selected to be 0-2 degrees.
Further, the fifth step is specifically:
for each set of states in the finite dataset of equation (16), a fixed wingtip section torsion angle τ is set t And the effective aerodynamic surface wing root torsion angle tau of the wing ra The wingtip wing profile is configured on the wing profile, the wingroot wing profile is configured on the wing effective aerodynamic surface wingroot, and fusion transition repair is carried out between the wing-body separation surface and the wing effective aerodynamic surface wingroot, so that the sweepback angle lambda of each group of wings is finally formed ωi (i= … n) and wing position h i1 /h i2 (i= … n) opposing large chord fly layout drone profiles;
and aiming at each group of profiles, a scheme with the maximum cruising lift-drag ratio and the minimum low head moment is screened out through CFD flow field simulation to be used as a final high aspect ratio wing scheme.
The beneficial effects of the invention are as follows:
the design method is simple, has good practicability, avoids repeated iteration of scheme design, solves the key problem of multi-configuration wing design of the unmanned aerial vehicle with the flying wing layout, namely pneumatic design problem, fundamentally solves the pneumatic problem of multi-configuration design of the unmanned aerial vehicle with the flying wing layout, further promotes the configuration-changing technology of the unmanned aerial vehicle with the flying wing layout to land, and has higher engineering application value.
Drawings
FIG. 1 is a schematic illustration of a high aspect ratio wing configuration based on a medium to low aspect ratio flying wing layout unmanned aerial vehicle platform.
FIG. 2 is a parametric representation of an flying-wing layout unmanned aerial vehicle based on a high aspect ratio wing.
FIG. 3 is a schematic view of a high aspect ratio wing tip airfoil.
FIG. 4 is a schematic view of an effective aerodynamic surface root airfoil of a high aspect ratio wing.
FIG. 5 is a corresponding aerodynamic profile of a high aspect ratio flying wing layout unmanned with a swept wing angle.
FIG. 6 is a lift-drag curve comparison of a high aspect ratio wing configuration with a low aspect ratio wing configuration.
FIG. 7 is a pitching moment characteristic curve comparison of a high aspect ratio wing configuration with a medium and low aspect ratio wing configuration.
Detailed Description
The invention is described in detail below with reference to the attached drawing figures:
example 1
As shown in fig. 1 and 2, a specific description will be given of a matched high aspect ratio wing coordinated design process, taking a certain middle and low aspect ratio and a high maneuver type target aircraft as an example.
Setting flying wing layout unmanned aerial vehicle cruising speed V=177 m/s (i.e. Ma=0.6), cruising height H=13 km and cruising lift coefficient C based on large chord wing L =0.6, the cruising weight G is the weight of the middle-small aspect ratio flying wing layout unmanned aerial vehicle platform, and the wing area S is obtained by calculation of formula (1);
setting the aspect ratio A of the wing with the large aspect ratio to be 18, and calculating the span length b through a formula (4) R ；
Setting the tip root ratio lambda of the large span wing to be 0.36, and calculating according to formulas (7) - (8) to obtain c r 、c t ；
Setting stability margin C of unmanned aerial vehicle mCL = -0.1, design center of gravity G y The design gravity center of the unmanned plane platform is laid out for the middle and small aspect ratio flying wings, and the wing sweepback angle lambda is calculated through a formula (12) and a formula (15) ω And wing station h y Is a linear equation of (2);
according to equation (15), three discrete points, namely Λ, are selected b -Λ w =47 °, 50 °, 53 °, then the wing sweep sample point is Λ w ＝Λ b -47°、Λ w ＝Λ b -50°、Λ w ＝Λ b -53°(Λ b The sweepback angle of the body of the middle-small aspect ratio unmanned aerial vehicle platform is a known value); meanwhile, in order to reduce the range of sample points as far as possible, the joint position of the wing leading edge and the fuselage should be selected at 92% of the fuselage spanwise directionI.e. one wing position for each fuselage sweep. Establishing a wing sweep angle lambda according to equation (16) ω And wing station h y Is:
for each group of states in the formula (17), carrying out extension on the tail edge of the middle-low aspect ratio flying wing layout unmanned aerial vehicle body to intersect with the tail edge of the large aspect ratio wing, and drawing to obtain the spanwise standing position and chord length of the focal point position, namely the spanwise standing position and chord length of the effective aerodynamic surface wing root of the wing
The wing body separating surface is set at 87% of the machine body in the expanding direction, and the torsion angle tau of the wing tip section is selected t The section torsion angle of the wing root of the effective aerodynamic surface of the wing is-2.5 degrees and is 0 degree;
for each group of parameters, respectively configuring high lift-drag ratio and small low-head moment wing profiles (see fig. 3 and 4) designed for the large-aspect-ratio aircraft layout unmanned aerial vehicle at the wing tip and the effective aerodynamic surface wing root, performing transition modification between the wing-body separation surface and the wing effective aerodynamic surface wing root, and finally forming the aerodynamic profile of the large-aspect-ratio aircraft layout unmanned aerial vehicle corresponding to each group of parameters, wherein fig. 5 is the wing sweepback angle lambda w ＝Λ b -53 ° of the corresponding aerodynamic profile of the high aspect ratio flying wing layout unmanned aerial vehicle;
and comparing simulation by CFD flow fields for each aerodynamic shape, wherein the grid topology structure and the grid quantity adopted by each aerodynamic shape are consistent in order to ensure the rationality of simulation results. The results show that: wing sweep angle lambda w ＝Λ b The scheme corresponding to-53 ° is chosen as the final optimization scheme, with the highest cruise lift-drag ratio and the lowest heading torque.
Fig. 6 is a comparison of lift-drag ratio curves of a high aspect ratio wing configuration and a low aspect ratio wing configuration, and it can be seen that the lift-drag ratio of a cruise point of the aerodynamic scheme of the high aspect ratio flying wing layout designed by the invention is near the maximum lift-drag ratio, and the lift-drag ratio of the cruise point reaches 28, which is beneficial to long-distance flight.
Fig. 7 is a pitch moment characteristic curve comparison of a high aspect ratio wing configuration and a middle and small aspect ratio wing configuration, and can be seen that the low head moment of the high aspect ratio flying wing layout unmanned aerial vehicle is smaller, and after the correction of the air inlet effect, the pitch moment coefficient of the cruising point is close to self-balancing, so that the problem that the cruising low head moment of the conventional high aspect ratio flying wing layout unmanned aerial vehicle is large is solved, and the design of the multi-wing configuration of the same unmanned aerial vehicle platform is realized.
Example 2
A multi-configuration coordination design method for an unmanned aerial vehicle wing with an all-wing layout comprises the following steps of
Step one, wing size parameters are designed in a coordinated mode;
step a) determining the wing area S:
the high aspect ratio flying wing layout is generally used as a stealth long-endurance unmanned plane, the cruising design point is near the maximum lift-drag ratio, the corresponding lift coefficient range is generally 0.55-0.7, and the cruising lift coefficient C is assumed L According to the use requirement, determining a cruise design parameter: cruise speed V, cruise altitude H, cruise weight G, balanced by lift L and gravity:
G＝L (1)
the combination of formulas (1) to (2) yields:
where ρ is the air density corresponding to cruise altitude H.
Step b) determination of the machine span length b R ：
The wing aspect ratio A of the large aspect ratio and long-endurance unmanned aerial vehicle is generally 15-20, and the relation between the aspect ratio and the wing area is as follows:
the calculated span length is as follows:
step c) determining the root chord length c r Tip chord length c t ：
The wing tip root ratio lambda of the unmanned aerial vehicle with large aspect ratio and long voyage is generally 0.3-0.5, namely:
the calculation formula of the trapezoid wing area is as follows:
the combination of formulas (5) to (6) yields:
step two, wing plane parameters are designed in a coordinated manner;
the wing plane parameters include wing sweep angle Λ ω And wing station h y These two parameters are also the main parameters for determining the aerodynamic focus position F.
Assume that the control system has a C requirement for the stability margin of the unmanned aerial vehicle mCL ，C mCL With known values, the flying-wing layout unmanned aerial vehicle generally adopts weak stability control, stability margin C mCL The design gravity center G of the unmanned plane platform ranges from-0.1 to-0.05 y Calculating the design focus position x of the new wing according to the conversion relation between the gravity center and the pneumatic focus to obtain a known value F The method comprises the following steps:
x F ＝G y -C mCL *b A (9)
in formula (9), b A For the average aerodynamic chord length of the wing, for a general trapezoidal wing, the average aerodynamic chord calculation formula is as follows:
in the formula (10), b Average of The specific calculation formula is as follows, wherein the geometric average chord length of the wing, eta is the root tip ratio:
to sweep the wing back angle lambda w And wing station h y The focal position of the large aspect ratio trapezoidal wing is calculated by adopting a lifting surface theory in association with the aerodynamic focal position:
in the formula (13) of the present invention,b is A Is a spread station:
and (3) obtaining the joint solution formulas (9) - (14):
from equation (15), it can be seen that the wing sweep angle Λ ω And wing station h y In a linear one-to-one correspondence;
according to the fuselage constraint conditions:
step a) the unmanned aerial vehicle body with the flying wing layout is a trapezoid wing with similar small aspect ratio and large sweepback angle, in order to simulate the airflow separation of the connection position of the wing body under the medium attack angle, the subsonic cruising performance of the wing with the large aspect ratio is ensured, so that the sweepback angle of the wing must be reasonably selected, and the sweepback angle lambda of the wing is required to be reasonably selected w And a fuselage sweep angle lambda b The following relationship should be satisfied
46°≤Λ b -Λ w ≤54° (15)
Step b), the butt joint position of the wing leading edge and the fuselage should be reasonably selected, the closer to the inner side, the space utilization of the fuselage is affected, the closer to the outer side, the fusion transition profile of the wing body is poor, the butt joint position of the wing leading edge and the fuselage should be selected at the position of 90% -95% of the spanwise direction of the fuselage, and the butt joint position and the wing station h y Directly related. The wing station range under a certain sweepback angle can be obtained by a drawing judgment method;
wing sweep angle lambda is combined with formula (15) and fuselage constraints ω And wing station h y A finite data set may be composed:
step three, wing profile parameters are designed in a coordinated mode;
the aerofoil section parameters comprise the effective aerodynamic surface wing root span-wise station y ra Chord length c ra Wing-body separation plane and wing tip section torsion angleτ t And the effective aerodynamic surface wing root torsion angle tau of the wing ra ，
Step a) determining wing root span-wise station y of effective aerodynamic surface of wing ra Chord length c ra ：
In equation (16), for each set of wing sweep angles Λ ω And wing station h y The plane shape and position of the whole wing are determined and unique, and the spanwise station position and chord length corresponding to the intersection point of the extension of the rear edge of the airplane body and the rear edge of the new wing are the effective aerodynamic surface wing root spanwise station position y of the wing ra Chord length c ra ；
Step b) determining the wing-fuselage separation surface:
for the multi-configuration wing unmanned aerial vehicle, the shadow separating surface is a fixed value, the selection of the wing separating surface is reasonable, the closer the wing separating surface is to the symmetrical plane of the vehicle body, the laser loading space is affected, the smaller the wing separating surface is to one side of the wing, the smaller the wing transition space is, the design of the multi-configuration wing is difficult to consider, and the wing separating surface is generally selected at the position of 85% -90% of the extending station position of the vehicle body;
step c) determining the wingtip section torsion angle τ t And the effective aerodynamic surface wing root torsion angle tau of the wing ra ：
For a trapezoid wing with a sweepback angle, the wing surface has three-dimensional flow, the wing surface is easily accumulated on the wing tip to cause the wing tip separation, in order to delay the phenomenon, negative torsion is generally designed on the section of the wing tip, meanwhile, the negative torsion of the wing tip can also solve the problem that the moment of the low head of the wing with a large aspect ratio is overlarge, but the overlarge negative torsion can cause overlarge loss of the lift-drag ratio of the whole aircraft, so that the flight performance of the unmanned aerial vehicle is influenced, and the torsion angle tau of the section of the wing tip is based on the wing with the large aspect ratio of the unmanned aerial vehicle platform with the wingwing layout t Selecting a range from-2 degrees to-4 degrees;
in order to compensate the loss of lift force caused by the negative torsion angle of the wing tip section, the effective aerodynamic surface wing root section of the wing is not twisted or adopts a smaller positive torsion angle, which is generally tau ra The specific torsion angle value is selected to be 0-2 degrees, and also depends on the fusion transition condition of the wing root of the effective aerodynamic surface of the wing and the wing-body separation surface.
Step four, wing profile coordination design;
because the high aspect ratio flying wing layout is generally used as a stealth long-endurance unmanned aerial vehicle, the high lift-drag ratio is one of the main aerodynamic design indexes for measuring the performance of the whole aircraft. The wing with large aspect ratio has no tail wing, and the wing profile adopted by the wing with large aspect ratio in the general conventional layout can cause the low head moment of the wing to be very large, thereby causing larger trimming resistance of the whole aircraft. Therefore, a unique high lift-to-drag ratio, low tip torque tip airfoil and root airfoil must be designed for this type of layout wing. After optimization, the wing tip airfoil parameters are determined as follows:
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the wing root airfoil parameters are:
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fifthly, the high aspect ratio wing matched with the middle and small aspect ratio flying wing layout unmanned aerial vehicle platform is designed in a coordinated manner;
and aiming at each group of profiles, a scheme with the maximum cruising lift-drag ratio and the minimum low head moment is selected through simulation and used as a final high aspect ratio wing scheme.
For each set of states in the finite dataset of equation (16), a fixed wingtip section torsion angle τ is set t And the effective aerodynamic surface wing root torsion angle tau of the wing ra The wingtip wing profile is configured on the wing profile, the wingroot wing profile is configured on the wing effective aerodynamic surface wingroot, and fusion transition repair is carried out between the wing-body separation surface and the wing effective aerodynamic surface wingroot, so that the sweepback angle lambda of each group of wings is finally formed ωi (i= … n) and wing position h i1 /h i2 (i= … n) opposing large chord fly layout drone profiles;
and aiming at each group of profiles, a scheme with the maximum cruising lift-drag ratio and the minimum low head moment is screened out through CFD flow field simulation to be used as a final high aspect ratio wing scheme.
Claims (3)
1. A multi-configuration coordination design method for an unmanned aerial vehicle wing with an all-wing layout is characterized by comprising the following steps of: comprising
Step one, wing size parameters are designed in a coordinated mode;
step two, wing plane parameters are designed in a coordinated manner;
step three, wing profile parameters are designed in a coordinated mode;
step four, wing profile coordination design;
fifthly, the high aspect ratio wing matched with the middle and small aspect ratio flying wing layout unmanned aerial vehicle platform is designed in a coordinated manner;
aiming at each group of profiles, a scheme with the maximum cruising lift-drag ratio and the minimum low head moment is selected through simulation and used as a final high aspect ratio wing scheme;
the first step comprises the following steps:
step a) determining the wing area S:
setting the cruising lift coefficient C L According to the use requirement, determining a cruise design parameter: cruise speed V, cruise altitudeH. Cruising weight G, balanced by lift L and gravity:
G＝L (1)
the combination of formulas (1) to (2) yields:
wherein ρ is the air density corresponding to the cruise altitude H;
step b) determination of the machine span length b R ：
The wing aspect ratio A is 15-20, and according to the relation between the aspect ratio and the wing area:
the calculated span length is as follows:
step c) determining the root chord length c r Tip chord length c t ：
The tip-root ratio lambda of the unmanned aerial vehicle is 0.3-0.5, namely:
the calculation formula of the trapezoid wing area is as follows:
the combination of formulas (5) to (6) yields:
the second step is specifically as follows:
the wing plane parameters include wing sweep angle Λ ω And wing station h y Let the requirement of the control system on the stability margin of the unmanned aerial vehicle be C mCL Stability margin C mCL The design gravity center G of the unmanned plane platform ranges from-0.1 to-0.05 y Calculating the design focus position x of the new wing according to the conversion relation between the gravity center and the pneumatic focus to obtain a known value F The method comprises the following steps:
x F ＝G y -C mCL *b A (9)
in formula (9), b A For the average aerodynamic chord length of the wing, for a trapezoidal wing, the average aerodynamic chord calculation formula is:
in the formula (10), b Average of The specific calculation formula is as follows, wherein the geometric average chord length of the wing, eta is the root tip ratio:
the focal position of the large aspect ratio trapezoidal wing is calculated by adopting a lifting surface theory:
in the formula (13) of the present invention,b is A Is a spread station:
and (3) obtaining the joint solution formulas (9) - (14):
from equation (15), it can be seen that the wing sweep angle Λ ω And wing station h y In a linear one-to-one correspondence;
according to the fuselage constraint conditions:
step a) wing sweep angle Λ w And a fuselage sweep angle lambda b The following relationship should be satisfied
46°≤Λ b -Λ w ≤54° (16)
Step b), the butt joint position of the wing front edge and the fuselage is selected at 90% -95% of the fuselage spanwise direction, and the wing station position range under a certain sweepback angle is obtained through a drawing judgment method;
wing sweep angle lambda is combined with formula (16) and fuselage constraints ω And wing station h y A finite data set may be composed:
the third step comprises the following steps:
wing profileThe surface parameters comprise the effective pneumatic surface wing root direction-spreading station y of the wing ra Chord length c ra Wing-fuselage separation plane, wing tip section torsion angle tau t And the effective aerodynamic surface wing root torsion angle tau of the wing ra ，
Step a) determining wing root span-wise station y of effective aerodynamic surface of wing ra Chord length c ra ：
In equation (16), for each set of wing sweep angles Λ ω And wing station h y The plane shape and position of the whole wing are determined and unique, and the spanwise station position and chord length corresponding to the intersection point of the extension of the rear edge of the airplane body and the rear edge of the new wing are the effective aerodynamic surface wing root spanwise station position y of the wing ra Chord length c ra ；
Step b) determining the wing-fuselage separation surface:
the wing body is separated and selected at 85% -90% of the position of the fuselage spreading station;
step c) determining the wingtip section torsion angle τ t And the effective aerodynamic surface wing root torsion angle tau of the wing ra ：
Wing tip section torsion angle tau t Selecting a range from-2 degrees to-4 degrees;
in order to compensate the lift loss caused by the negative torsion angle of the wing tip section, tau ra Selected to be 0-2 degrees.
2. The method for the multi-configuration coordinated design of an unmanned aerial vehicle wing with an all-wing layout according to claim 1, wherein the method comprises the following steps: the fourth step is specifically as follows:
the wingtip airfoil parameters were determined as:
the wing root airfoil parameters are:
3. the method for the multi-configuration coordinated design of an unmanned aerial vehicle wing with an all-wing layout according to claim 2, wherein the method comprises the following steps: the fifth step is specifically as follows:
for each set of states in the finite dataset of equation (16), a fixed wingtip section torsion angle τ is set t And the effective aerodynamic surface wing root torsion angle tau of the wing ra The wingtip wing profile is configured on the wing profile, the wingroot wing profile is configured on the wing effective aerodynamic surface wingroot, and fusion transition repair is carried out between the wing-body separation surface and the wing effective aerodynamic surface wingroot, so that the sweepback angle lambda of each group of wings is finally formed ω And wing station h y The shape of the unmanned plane is distributed on the opposite large-chord flying wing;
and aiming at each group of profiles, a scheme with the maximum cruising lift-drag ratio and the minimum low head moment is screened out through CFD flow field simulation to be used as a final high aspect ratio wing scheme.
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| CN106672260A (en) * | 2015-11-11 | 2017-05-17 | 成都飞机工业（集团）有限责任公司 | High-aspect-ratio wing frame architecture design method |
| CN111959816A (en) * | 2020-07-15 | 2020-11-20 | 成都飞机工业（集团）有限责任公司 | Pneumatic design method for improving high-low speed performance of flying wing layout aircraft |
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