CN112660381A - Laminar flow control technology-based wing body fusion layout passenger plane layout method - Google Patents
Laminar flow control technology-based wing body fusion layout passenger plane layout method Download PDFInfo
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Abstract
The invention belongs to the technical field of aviation aircraft design, and discloses a passenger plane layout method based on a wing body fusion layout of a laminar flow control technology, which comprises a fuselage, wings and an engine, wherein the fuselage and the wings adopt the wing body fusion layout, the wings are divided into a cabin section wing and an outer side wing, the cabin section wing is fused with the fuselage, the outer side wing is arranged at two sides of the cabin section wing, the engine is arranged at the rear part of the fuselage, and the rear edge of the cabin section wing is provided with a small V-shaped empennage; a passenger aircraft layout critical method is also included. The wing-body fusion passenger plane designed by the invention has the advantages that the frictional resistance is reduced by 46% compared with the passenger plane with the conventional layout, the frictional resistance is reduced by 32% compared with the passenger plane with the conventional wing-body fusion layout, the cruise lift-drag ratio reaches 28, the cruise lift-drag ratio is increased by 47% compared with the passenger plane with the conventional layout, the adverse effect of the increase of the attack angle and the speed on layer flow transition is also inhibited, and the drag reduction effect of the laminar flow control technology is fully exerted.
Description
Technical Field
The invention belongs to the technical field of aviation aircraft design, relates to a passenger plane layout method with a wing-body fusion layout, and particularly relates to a passenger plane layout method with a wing-body fusion layout based on a laminar flow control technology.
Background
The modern large subsonic airliner has high aerodynamic performance, the cruising lift-drag ratio reaches about 19, and the aerodynamic efficiency lifting space is limited. Wing body fusion technology and laminar flow control technology are two most effective drag reduction technologies at present. Although the friction resistance of the traditional wing body fusion layout aircraft can be reduced, the tailless layout causes the stability and the maneuverability of the aircraft body to be poor. The laminar flow control technology is restricted by a plurality of factors and is difficult to be applied to large-scale high-speed airplanes.
Disclosure of Invention
In order to solve the problems, the invention provides a passenger plane layout method of a wing body fusion layout based on a laminar flow control technology, which provides an efficient drag reduction technology for improving the aerodynamic efficiency of an airplane, obtains a better laminar flow control effect with the minimum energy loss by optimizing the wing body fusion layout and adopting an integrated laminar flow control technology, increases the cruise lift-drag ratio by 47 percent and effectively improves the performance of the airplane.
The technical scheme of the invention is as follows:
a passenger plane layout method based on laminar flow control technology and with wing body fusion layout comprises a passenger plane body, wings and an engine, wherein the passenger plane body and the wings adopt the wing body fusion layout, the wings are divided into a cabin section wing and an outer side wing, the cabin section wing is fused with the passenger plane body, the outer side wing is arranged on two sides of the cabin section wing, the engine is arranged on the rear part of the passenger plane body, and the rear edge of the cabin section wing is provided with a small V-shaped empennage; a passenger aircraft layout critical method is also included.
Further, the passenger plane layout key methods include a performance index design method, a top level parameter design method, a wing plane layout design method, a laminar flow control design method, a control system design method, and a power system design method.
Further, the method for designing the performance index specifically comprises the following steps: the cruising speed of the passenger plane is not more than 0.78Ma, and the cruising height is not less than 12000 m. The method can reduce the adverse effect of the large flight speed and the flight Reynolds number on the transition of the layer flow.
Further, the top-level parameter design method specifically comprises the following steps: the designed wing load is less than 300kg/m2The designed lift coefficient of cruise is reduced to about 0.3, and the thrust-weight ratio is compensated by power. Considering the energy loss of the wing leading edge air suction device used by the laminar flow control system, the thrust-weight ratio design needs to take the energy loss into account, and the method can inhibit the adverse effect of a large attack angle on the layer flow transition.
Further, the method for designing the plane layout of the wing specifically comprises the following steps:
the sweep angle of the wing leading edge is not more than 30 degrees, and the design can inhibit cross flow instability of CF waves caused by large sweep angle; the wing is evenly reduced along span-wise thickness, so that the wing body is highly integrated, and the design can reduce the adverse effect of the turbulence pollution of the contact line of the fuselage and the wing on the transition of the laminar flow of the wing surface.
Further, the method for designing the plane layout of the wing specifically comprises the following steps:
the span-wise width of the cabin segment machine is 35% of the span length of the wing, the length of the cabin segment machine is 63% of the chord length of the current machine, and a supercritical mixed laminar flow airfoil is adopted; the wing of the cabin section is divided into a middle cabin section wing and an outer cabin wing, the camber of the middle cabin section wing is 0, the wing profile design lift coefficient of the outer cabin wing is 0.12, and the thickness change is 0.16-0.15. The design method can reduce the cruise pneumatic trim loss;
the outer wing is divided into an inner wing part and an outer wing part, the inner wing part adopts a mixed laminar flow wing type, the wing type design lift coefficient is 0.33, the thickness variation is 0.15-0.13, the main function of the outer wing is to improve the lift characteristic of the airplane, and the arrangement and the appearance of a large integral oil tank are fused; the outer wing part adopts a natural laminar flow wing profile, the lift coefficient of the wing profile design is 0.33, the thickness change is 0.15-0.13, and the wing leading edge is provided with a micro-scale rough element matrix.
Further, the design method of laminar flow control specifically comprises:
the local Reynolds number of the wings of the passenger cabin section is the largest, the laminar flow control difficulty is high, the front edges of the wings and the inner side wings of the customer cabin section are uniformly provided with air suction holes, and the front beam space is provided with an air suction device; by adopting a mixed layer flow control technology and assisting the pumping action of an engine, the laminar flow transition point can be controlled to be behind 58% chord length; the outer wing part adopts a slender shape structure, because when the landmine is slightly curved, the passive laminar flow control technology is adopted, the layer flow transition can be effectively controlled, and the energy loss is reduced.
Further, the design method of the control system comprises the following specific steps:
the two small V-shaped empennages are symmetrical and are natural laminar flow airfoils, and the camber is 38 degrees; the trailing edge of the wing of the passenger cabin section is also provided with a power rudder and a high lift flap, and the jet flow of the engine is matched with the power rudder to realize thrust vector control; the rear edge of the inner side wing part is provided with a flaperon, the outer side wing part is provided with an aileron and a resistance rudder, and the stability and the maneuverability of the airplane can be improved by utilizing the cooperation of a flight control system, a V-shaped empennage control surface and each control surface of the rear edge of the wing.
Further, the design method of the power system specifically comprises the following steps:
3 turbofan engines with large bypass ratio are arranged between the small V-shaped empennages, one engine is arranged in the middle of the tail part, and one engine is arranged in front of each power rudder on two sides. The laminar flow control capability is improved by utilizing the pumping action of the engines in front of the power rudders at two sides, and the thrust vector control is realized by utilizing all engine jet flows.
The invention has the advantages that:
(1) the invention adopts the wing body with the V-shaped empennage to fuse the pneumatic layout, so that the frictional resistance is reduced by 46 percent compared with the passenger plane with the conventional layout, and the plane body has better three-axis stability and maneuverability;
(2) the invention applies the laminar flow control technology to the design of the airplane with the wing-body fusion layout for the first time, so that the frictional resistance is reduced by 32 percent compared with the conventional airplane with the wing-body fusion layout, the cruising lift-drag ratio reaches 28 percent, and the cruising lift-drag ratio is increased by 47 percent compared with the conventional airplane with the layout.
(3) The performance index design and the top parameter design of the invention inhibit the adverse effect of the angle of attack and the speed increase on the layer flow transition, so that the laminar flow control technology can be applied to the large wing body fusion layout passenger plane.
(4) The wing layout design of the invention is different from the traditional wing body fusion airplane, and the linear wing leading edge with the 30-degree sweepback angle is adopted, so that the adverse effect of the increase of the sweepback angle on the layer flow transition can be inhibited; each section of the wing adopts different wing profiles and laminar flow control technologies, and the drag reduction effect of the laminar flow control technology is fully exerted.
(5) According to the invention, according to the laminar flow control difficulty of each section of the wing, the wing design adopts a supercritical mixed laminar flow wing section, a mixed laminar flow wing section and a natural laminar flow wing section, and a mixed layer flow control technology and a passive laminar flow control technology which are matched with the supercritical mixed laminar flow wing section and the mixed laminar flow wing section are used, so that a better laminar flow control effect is obtained with minimum energy loss, and the performance of the airplane is effectively improved.
(6) The invention effectively improves the maneuverability and flight quality of the airplane by utilizing a flight control system, a V-shaped empennage control surface, a wing trailing edge maneuvering flaperon and a thrust vector technology.
Drawings
FIG. 1 is a top view of the pneumatic layout of the layout method of the present invention;
FIG. 2 is a front view of the pneumatic layout of the layout method of the present invention;
the airplane wing comprises 1 part of a middle cabin section wing, 2 parts of an outer cabin wing, 3 parts of an inner wing, 4 parts of the outer wing, 5 parts of the cabin, 6 parts of an air suction hole, 7 parts of a micro-scale rough element matrix, 8 parts of an air suction device, 9 parts of a drag rudder, 10 parts of an aileron, 11 parts of a flaperon, 12 parts of a small V-shaped empennage and 13 parts of a V-shaped empennage rudder surface.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
A passenger plane layout method based on laminar flow control technology and with wing body fusion layout comprises a fuselage, wings and an engine 16, wherein the fuselage and the wings adopt the wing body fusion layout, the wings are divided into a cabin section wing and an outer side wing, the cabin section wing is fused with the fuselage, the outer side wing is arranged on two sides of the cabin section wing, the engine 16 is arranged on the rear part of the fuselage, and the rear edge of the cabin section wing is provided with a small V-shaped empennage 12; a passenger aircraft layout critical method is also included.
The passenger plane layout key method comprises a performance index design method, a top parameter design method, a wing plane layout design method, a laminar flow control design method, a control system design method and a power system design method.
The method for designing the performance index specifically comprises the following steps: the cruising speed of the passenger plane is not more than 0.78Ma, and the cruising height is not less than 12000 m. The method can reduce the adverse effect of the large flight speed and the flight Reynolds number on the transition of the layer flow.
The top-level parameter design method specifically comprises the following steps: the designed wing load is less than 300kg/m2The designed lift coefficient of cruise is reduced to about 0.3, and the thrust-weight ratio is compensated by power. Considering the energy loss of the wing leading edge air suction device used by the laminar flow control system, the thrust-weight ratio design needs to take the energy loss into account, and the method can inhibit the adverse effect of a large attack angle on the layer flow transition.
The wing plane layout design method specifically comprises the following steps:
the sweep angle of the wing leading edge is not more than 30 degrees, and the design can inhibit cross flow instability of CF waves caused by large sweep angle; the wing is evenly reduced along span-wise thickness, so that the wing body is highly integrated, and the design can reduce the adverse effect of the turbulence pollution of the contact line of the fuselage and the wing on the transition of the laminar flow of the wing surface.
The wing plane layout design method specifically comprises the following steps:
the span-wise width of the cabin segment machine is 35% of the span length of the wing, the length of the cabin segment machine is 63% of the chord length of the current machine, and a supercritical mixed laminar flow airfoil is adopted; the wing of the cabin section is divided into a middle cabin section wing 1 and an outer cabin wing 2, the camber of the middle cabin section wing 1 is 0, the wing profile design lift coefficient of the outer cabin wing 1 is 0.12, and the thickness change is 0.16-0.15. The design method can reduce the cruise pneumatic trim loss;
the outer wing is divided into an inner wing part 3 and an outer wing part 4, the inner wing part 3 adopts a mixed laminar flow wing type, the design lift coefficient of the wing type is 0.33, the thickness change is 0.15-0.13, the main function of the outer wing is to improve the lift characteristic of the airplane, and the arrangement and the appearance of a large-scale integral oil tank are fused; the outer wing part 4 adopts a natural laminar flow wing shape, the lift coefficient of the wing shape design is 0.33, the thickness change is 0.15-0.13, and the wing leading edge is provided with a micro-scale rough element matrix 7.
The laminar flow control design method specifically comprises the following steps:
the local Reynolds number of the wings of the passenger cabin section is the largest, the laminar flow control difficulty is high, the front edges of the wings of the customer cabin section and the inner side wing part 3 are uniformly provided with air suction holes 6, and the front beam space is provided with an air suction device 8; by adopting a mixed layer flow control technology and assisting the pumping action of an engine, the laminar flow transition point can be controlled to be behind 58% chord length; the outer wing part 4 adopts a slender shape structure, because when the landmine is slightly curved, the passive laminar flow control technology is adopted, the layer flow transition can be effectively controlled, and the energy loss is reduced.
The design method of the control system comprises the following steps:
the two small V-shaped empennages 12 are symmetrical and are natural laminar flow airfoils, and the camber is 38 degrees; the trailing edge of the wing of the passenger cabin section is also provided with a power rudder 14 and a high lift flap 15, and the jet flow of an engine 16 is matched with the power rudder to realize thrust vector control; the rear edge of the inner side wing part 3 is provided with a flaperon 11, the outer side wing part 4 is provided with an aileron 10 and a resistance rudder 9, and the stability and the maneuverability of the airplane can be improved by utilizing the cooperation of a flight control system, a V-shaped empennage control surface 13 and each control surface of the rear edge of the wing.
The design method of the power system comprises the following steps:
3 turbofan engines 16 with large bypass ratio are arranged between the small V-shaped empennages 12, one engine is arranged in the middle of the tail part, and one engine is arranged in front of each power rudder 14 on two sides. The laminar flow control capability is improved by utilizing the pumping action of the engines in front of the power rudders at two sides, and the thrust vector control is realized by utilizing all engine jet flows.
Another embodiment of the present invention is described below with reference to the drawings.
The structure of the present invention is shown in fig. 1 and 2.
Step 1, designing performance indexes: the airplane has passenger carrying capacity of 360 people, voyage of 11000km, lift limit of 13500m or more, maximum flying weight of 172t or less, take-off field length of 1200m or less and landing approach speed of 55m/s or less. According to the requirements of laminar flow control, the cruise design lift coefficient is 0.28, the cruise speed is 0.78Ma, the cruise height is 12000m, and the lift limit is 13500 m.
Step 2, designing top layer parameters: according to the cruise design lift coefficient and the long performance requirement of a take-off and landing field, the load of an example airplane wing is 278kg/m 2; the energy loss of a wing leading edge air suction device used by a laminar flow control system is controlled to be below 10%, and the thrust-weight ratio of an object airplane after power compensation is adopted is 0.23.
Step 3, designing the plane layout of the wings: the wing area is 630m2, the wingspan is 65m, the wing aspect ratio is 6.71, and the wing leading edge sweepback angle is 30 degrees for inhibiting the cross flow instability of the CF wave caused by the large sweepback angle; the thickness of each section of the wing is uniformly reduced, so that the height of the wing body is fused, and the adverse effect of turbulent pollution of a contact line of the wing body and the wing on the transition of the laminar flow of the wing surface is reduced; in order to improve aerodynamic efficiency, the local span-chord ratio of the trapezoidal outer wing on the outer side of the airplane is larger, and the local chord length is reduced, so that the local fender number is reduced, and the laminar transition of the wings is favorably controlled.
Step 4, designing wings of the passenger cabin section: the width of the wing of the cabin section is 35% of the span length of the wing, the length of the wing is 63% of the local chord length, and a supercritical mixed laminar flow wing type is adopted. In order to reduce the cruise aerodynamic trim loss, the wing camber of the middle passenger cabin section is 0, the wing profile design lift coefficient of the outer passenger cabin wing is 0.12, and the thickness is changed by 0.16-0.15. The front edge of the wing is uniformly provided with air suction holes, and the front beam space is provided with an air suction device.
Step 5, layout design of the outer wing: the outer wing is divided into an inner part and an outer part, the inner part adopts a mixed laminar flow wing type, the wing type design lift coefficient is 0.33, the thickness variation is 0.15-0.13, the main function of the aircraft is to improve the lift characteristic of the aircraft, and the arrangement and the appearance of a large-scale integral oil tank are fused; the outer side part adopts a natural laminar flow airfoil profile, the design lift coefficient of the airfoil profile is 0.33, the thickness change is 0.15-0.13, and the wing leading edge is provided with a micro-scale rough element matrix.
Step 6, laminar flow control design: the wing in the passenger cabin section has the largest local Reynolds number and large laminar flow control difficulty, a suction device with higher power is installed at the front edge of the wing, a mixed layer flow control technology is adopted, and the pumping action of an engine is assisted, so that the laminar flow transition point can be controlled to be behind 58% chord length; the inner side part of the outer wing adopts a mixed layer flow control technology, a wing leading edge is provided with a low-power air suction device, the outer side part of the slender shape is provided with a small local fender number, and a passive laminar flow control technology is adopted, so that the layer flow transition can be effectively controlled, and the energy loss is reduced.
And 7, designing a control system: the rear edge of the wing of the cabin section is provided with a small V-shaped empennage which adopts a natural laminar flow wing type, the thickness of the empennage is 0.11, and the empennage is camber of 38 degrees. The trailing edge of the wing is also provided with a power rudder and a high lift flap, and the jet flow of the engine is matched with the power rudder to realize thrust vector control; the rear edge of the inner side part of the outer wing is provided with a flaperon, the outer side part is provided with an aileron and a resistance rudder, and the stability and the maneuverability of the airplane can be improved by matching the flight control system, the V-shaped empennage control surface and each control surface of the rear edge of the wing.
Step 8, designing a power system: 3 high-bypass-ratio turbofan engines with the thrust of 132KN are installed between the V-shaped empennages to improve the reliability of a power system, improve the laminar flow control capability by utilizing the suction action of the engines, and realize thrust vector control by utilizing jet flow and power rudders behind the jet flow.
And 9, calculating the performance of the airplane according to the design data.
The aerodynamic characteristics are as follows: the zero lift drag coefficient is 0.0058, the cruise lift drag ratio is 28, the cruise speed is 0.78Ma, the lift limit is 13800m, and the voyage is 11362km, so that the design requirement is met.
Claims (9)
1. A passenger plane layout method based on laminar flow control technology and with wing body fusion layout is characterized by comprising a passenger plane body, wings and an engine (16), wherein the passenger plane body and the wings adopt the wing body fusion layout, the wings are divided into a cabin section wing and an outer side wing, the cabin section wing is fused with the passenger plane body, the outer side wing is arranged on two sides of the cabin section wing, the engine (16) is arranged on the rear part of the passenger plane body, and the rear edge of the cabin section wing is provided with a small V-shaped empennage (12); a passenger aircraft layout critical method is also included.
2. The passenger plane layout method of the wing-body fusion layout based on the laminar flow control technology as claimed in claim 1, wherein the passenger plane layout key methods include a performance index design method, a top-level parameter design method, a wing plane layout design method, a laminar flow control design method, a control system design method, and a power system design method.
3. The passenger plane layout method of the wing body fusion layout based on the laminar flow control technology as claimed in claim 2, wherein the performance index design method specifically comprises: the cruising speed of the passenger plane is not more than 0.78Ma, and the cruising height is not less than 12000 m. The method can reduce the adverse effect of the large flight speed and the flight Reynolds number on the transition of the layer flow.
4. The passenger plane layout method of the wing-body fusion layout based on the laminar flow control technology as claimed in claim 2, wherein the top parameter design method specifically comprises: the designed wing load is less than 300kg/m2The designed lift coefficient of cruise is reduced to about 0.3, and the thrust-weight ratio is compensated by power. Considering the energy loss of the wing leading edge air suction device used by the laminar flow control system, the thrust-weight ratio design needs to take the energy loss into account, and the method can inhibit the adverse effect of a large attack angle on the layer flow transition.
5. The passenger plane layout method of the wing body fusion layout based on the laminar flow control technology according to claim 2, wherein the wing plane layout design method specifically comprises the following steps:
the sweep angle of the front edge of the wing is not more than 30 degrees; the wing has even thickness reduction along the spanwise direction, so that the height of the wing body is fused.
6. The passenger plane layout method of wing body fusion layout based on laminar flow control technology according to claim 5, wherein the wing plane layout design method specifically comprises the following steps:
the span-wise width of the cabin segment machine is 35% of the span length of the wing, the length of the cabin segment machine is 63% of the chord length of the current machine, and a supercritical mixed laminar flow airfoil is adopted; the cabin section wing is divided into a middle cabin section wing (1) and an outer cabin wing (2), the camber of the middle cabin section wing (1) is 0, the wing profile design lift coefficient of the outer cabin wing (1) is 0.12, and the thickness change is 0.16-0.15;
the outer wing is divided into an inner wing part (3) and an outer wing part (4), the inner wing part (3) adopts a mixed laminar flow wing type, the wing type design lift coefficient is 0.33, and the thickness variation is 0.15-0.13; the side wing part (4) adopts a natural laminar flow wing shape, the lift coefficient of the wing shape design is 0.33, the thickness variation is 0.15-0.13, and the wing leading edge is provided with a micro-scale rough element matrix (7).
7. The passenger plane layout method of the wing body fusion layout based on the laminar flow control technology as claimed in claim 2, wherein the laminar flow control design method is specifically as follows:
the front edges of the wings and the inner side wing parts (3) of the cabin section are uniformly provided with air suction holes (6), and the front beam space is provided with an air suction device (8); the outboard wing part (4) adopts a slender profile structure.
8. The passenger aircraft layout method of the wing-body fusion layout based on the laminar flow control technology as claimed in claim 2, wherein the design method of the control system is specifically as follows:
the two small V-shaped tail wings (12) are symmetrical and are natural laminar flow wing profiles, and the camber is 38 degrees; the trailing edge of the wing of the passenger cabin section is also provided with a power rudder (14) and a high lift flap (15); the rear edge of the inner wing part (3) is provided with a flaperon (11), and the outer wing part (4) is provided with an aileron (10) and a resistance rudder (9).
9. The passenger plane layout method of the wing-body fusion layout based on the laminar flow control technology according to claim 8, characterized in that the power system design method specifically comprises:
the engine (16) is a high bypass ratio turbofan engine (16); 3 turbofan engines (16) with large bypass ratio are arranged between the small V-shaped empennages (12), one engine is arranged in the middle of the tail part, and one engine is arranged in front of each power rudder (14) at two sides.
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| CN113232831A (en) * | 2021-06-25 | 2021-08-10 | 西北工业大学 | Wing body fuses single wing structure on civil aircraft run-through formula of overall arrangement |
| CN113978697A (en) * | 2021-11-18 | 2022-01-28 | 中国航空研究院 | Liquid hydrogen fuel ultra-remote wing body fusion layout transport airplane and operation method |
| CN113978697B (en) * | 2021-11-18 | 2024-04-09 | 中国航空研究院 | Liquid hydrogen fuel ultra-remote wing body fusion layout transportation aircraft and operation method |
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Application publication date: 20210416 |