An aircraft based on the combination of fan wings and fixed wings and a design method thereof

Abstract

The application belongs to the technical field of aircrafts, and particularly discloses an aircraft based on a combination of fan wings and fixed wings and a design method thereof, which comprises: a fuselage, a wing plate is arranged on the fuselage, the wing plate comprises a fan wing plate and a fixed wing plate; a fan wing, an installation surface for installing the fan wing is arranged on the fan wing plate, and the fan wing is used for cooperating with the fan wing plate; a power part, which is arranged on the fan wing plate and connected with an input shaft of the fan wing; wherein, a preset range of proportional relationship is arranged between the fan wing plate and the fixed wing plate, the proportional relationship is used for adjusting the flight stability of the aircraft under the same air speed change, so that the aircraft can stably fly under the combined action of gliding lift and flight lift; the aircraft has the following advantages: the aerodynamic complementary characteristics of the fixed wing and the fan wing are utilized for integrated design, so that the aircraft as a whole has the advantages of short take-off and landing distance, good low-speed performance, sufficient lift when the air speed is small or large, and the ability of unpowered gliding.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a kind of aircraft based on fan wing fixed wing combination and design method thereof. BACKGROUND

[0002] With the continuous development of aviation technology, there are many new concept aircrafts using new flight principles, and fan wing aircraft is a new concept aircraft developed in recent years. Fan wing aircraft is different from the structure and principle of fixed wing and rotary wing aircraft. It embeds cross-flow fan in the wing, rotates the fan at high speed, accelerates the airflow speed on the upper surface of the wing, and generates low pressure eccentric vortex in the fan to provide lift for the aircraft. Fan wing aircraft has the advantages of short take-off distance, good low-speed performance and stall at large angle of attack.

[0003] The lift of fixed wing increases with the increase of airspeed, and generally can achieve unpowered gliding. However, fixed wing aircraft needs a long runway to take off, and must always maintain a high speed during flight.

[0004] Fixed wing aircraft needs a long runway to take off, and must always maintain a high speed during flight. When the angle of attack of the wing of fixed wing aircraft increases, the airflow will gradually separate from the upper surface of the wing, so that when the angle of attack is too large, the wing lift will drop sharply, causing stall and crash.

[0005] Fan wing aircraft will have a decrease in lift at high airspeed, and the lift of fan wing aircraft is related to the speed of fan wing blades, so the lift of fan wing aircraft will decrease rapidly when fan wing is unpowered, which makes fan wing aircraft unable to achieve unpowered gliding.

[0006] Therefore, a kind of aircraft based on fan wing fixed wing combination and design method thereof is proposed to solve the above problems. SUMMARY

[0007] The present application aims to provide an aircraft based on fan wing fixed wing combination and design method thereof to solve or improve at least one of the above technical problems.

[0008] Therefore, the first aspect of the present application provides an aircraft based on fan wing fixed wing combination.

[0009] The second aspect of the present application provides a design method of an aircraft based on fan wing fixed wing combination.

[0010] The first aspect of the present application provides a fan wing and fixed wing combined aircraft, comprising: a fuselage, the fuselage is provided with a wing plate, the wing plate comprises a fan wing plate and a fixed wing plate, the fixed wing plate is used to provide gliding lift when the aircraft flies; a fan wing, the fan wing plate is provided with a mounting surface for mounting the fan wing, the fan wing is used to cooperate with the fan wing plate to provide flight lift for the aircraft; a power part is arranged on the fan wing plate and connected with the input shaft of the fan wing; wherein the area of the fan wing plate and the fixed wing plate is provided with a preset range of proportional relationship, the change of the proportional relationship is used to adjust the flight stability of the aircraft under the same air speed change, so that the aircraft can fly stably under the combined action of gliding lift and flight lift.

[0011] The fan wing and fixed wing combined aircraft provided by the present application adopts the combination of fan wing and fixed wing for the wing of the aircraft, realizes the aerodynamic complementary characteristics of the two, can achieve short take-off and landing distance, good low-speed performance, sufficient lift when the air speed is small or large, and can glide without power;

[0012] For the fan wing and fixed wing combined aircraft wing, the proportional relationship of the two is considered, the flight instability after combination can be optimized, and the aircraft combined with the fan wing and the fixed wing can maintain stability under different types of lift in actual flight, that is, the gliding lift and flight lift provided by different structures.

[0013] In addition, the technical scheme provided by the embodiment of the present application can also have the following additional technical features:

[0014] In any of the above technical solutions, the fan wing is provided with two, and the input shafts of the two fan wings are coaxially arranged, and the power part comprises: a motor installed in the middle of the fan wing plate; a transmission mechanism for connecting the input shaft and the output shaft of the motor to transmit the power of the motor to the fan wing.

[0015] In this technical solution, two fan wings are arranged, and the input shafts of the two fan wings are coaxially arranged to be driven by the same power part, which ensures synchronization;

[0016] Due to the weight of the motor, the motor is arranged in the middle of the fan wing plate to avoid uneven weight causing unstable flight of the aircraft.

[0017] In any of the above technical solutions, the transmission mechanism comprises: a transmission shaft for connecting the two input shafts; a driven wheel installed on the transmission shaft; a driving wheel installed on the output shaft of the motor and connected with the driven wheel.

[0018] In the technical scheme, the input shafts of the two fan wings are coaxially connected through the transmission shaft, and the driven wheel matched with the main drive wheel is installed on the transmission shaft, so that the motor drives the two input shafts to rotate through the output wheel, the input wheel and the transmission shaft in sequence.

[0019] In any of the above technical solutions, the aircraft based on the combination of the fan wing and the fixed wing further comprises a mounting frame for mounting the fan wing on the fan wing plate, wherein the mounting frame is provided with a fairing edge for connecting the top of the fan wing and the root of the fan wing plate, and / or the transmission mechanism further comprises a limiting bearing for connecting the transmission shaft and the mounting frame.

[0020] In the technical scheme, the mounting frame is used for mounting between the fan wing and the fan wing plate, and the fairing edge is arranged on the mounting frame, so that the airflow can flow more smoothly when passing through the outer top of the fan wing and the rear edge of the fan wing plate, and the fairing edge plays a role of guiding the airflow.

[0021] The first aspect of the application provides a design method of an aircraft based on the combination of a fan wing and a fixed wing, comprising the following steps: arranging the fan wing on the mounting surface of the wing plate, and dividing the wing plate along the fuselage axis to obtain a fan wing plate corresponding to the fan wing and providing flight lift; arranging the remaining part of the wing plate after removing the fan wing plate as a fixed wing plate for providing gliding lift; considering the influence of the proportion of the wing plate and the fixed wing plate on the total lift, respectively, on the wing plate, the preset range of the proportional relationship between the area of the wing plate and the fixed wing plate is determined; based on the simulation experiment environment, the flight experiment of the aircraft with different proportional relationships of the fan wing plate and the fixed wing plate is carried out in the preset range, and the total lift change data of the wing plate under different proportional relationships in the same airspeed range is obtained; the difference between the maximum total lift and the minimum total lift under different proportional relationships is obtained respectively, and the proportional relationship corresponding to the minimum difference is obtained, which is used as the optimal result of the fan wing plate and the fixed wing plate and used for aircraft design; wherein the design method of the aircraft based on the combination of the fan wing and the fixed wing is used for designing the aircraft as described in any one of the first aspect.

[0022] The design method of the aircraft based on the combination of the fan wing and the fixed wing provided by the application considers the stability of the aircraft after the combination, and therefore proposes a design method to improve the flight stability of the aircraft in a certain airspeed range after the combination, so as to ensure the smooth flight of the aircraft. The total lift of the aircraft with different proportional relationships of the fan wing and the fixed wing plate is tested and data is obtained in the simulation experiment, and the proportional relationship corresponding to the minimum total lift change is taken as the optimal result.

[0023] In any of the above technical solutions, the difference between the maximum total lift and the minimum total lift is used to represent the flight stability of the aircraft in a range of airspeeds; the total lift is composed of gliding lift and flight lift; wherein the smaller the difference, the more stable the aircraft flies in the range of airspeeds.

[0024] In this technical solution, the aircraft in flight state in the air is mainly affected by the total lift, so the difference between the maximum total lift and the minimum total lift is used to represent the flight stability, and the smaller the difference, the more stable the aircraft with the wing panel in the proportional relationship flies.

[0025] In the measurement, the gliding lift and the flight lift are jointly considered as the total lift, so that the experimental means considers the combination of the fan wing and the fixed wing, and the experimental results are more consistent with the combination of the fan wing and the fixed wing.

[0026] In any of the above technical solutions, the fixed wing panel includes two single panels, the two single panels are symmetrically located at the end of the fan wing panel along the fuselage axis direction; and the area of the fixed wing panel is S1, the area of the fan wing panel is S2, and the preset range is: S1 / S2=0.2-5.

[0027] In this technical solution, in order to avoid extreme wing panel allocation and ensure that the fan wing and the fixed wing can normally provide lift in the flight of the aircraft, the preset range is: S1 / S2=0.2-5.

[0028] The fan wing is a power-driven structure for flight, which is arranged in the middle of the wing panel and divides the fixed wing into two parts arranged at both ends of the fan wing panel, further ensuring the stability of the flight.

[0029] In any of the above technical solutions, based on the difference value under different proportional relationships in the simulation experiment environment, the optimal result is S1 / S2=0.875; the area ratio of a single single panel to a fan wing panel is 7:16.

[0030] In this technical solution, by comparing the differences under different proportional relationships in the simulation experiment environment, the optimal result can be selected, that is, S1 / S2=0.875, and the area ratio of the single panel to the fan wing panel is 7:16, which is set at the end of the fan wing panel as the design result of the wing part of the aircraft.

[0031] In any of the above technical solutions, in the continuous change of airspeed in the simulation experiment environment, the total area of the wing panel and the rotating speed of the fan wing remain unchanged.

[0032] In the technical solution, for different proportional relationships, simulation experiments are carried out in a unified airspeed range, specifically, the airspeed changes in the range of 0-40 m / s; the total area of the wing plate is kept unchanged, and the lift provided by the fan blades in the fan wing is not changed, so as to eliminate the interference of irrelevant factors.

[0033] Compared with the prior art, the present application has the following beneficial effects:

[0034] The wing of the aircraft is combined in the form of fan wing and fixed wing, the aerodynamic complementary characteristics of the two are realized, the short take-off and landing distance, good low-speed performance, sufficient lift when the airspeed is small or large, and the ability of unpowered gliding are achieved;

[0035] For the aircraft wing combined by the fan wing and the fixed wing, the proportional relationship of the two is considered, the flight instability caused after the combination can be optimized, and it is ensured that the aircraft combined with the fan wing and the fixed wing can maintain stability under different types of lift in actual flight, that is, the gliding lift and flight lift provided by different structures.

[0036] Additional aspects and advantages of embodiments according to the present application will become apparent from the following description, or will be learned by practice of embodiments according to the present application. BRIEF DESCRIPTION OF DRAWINGS

[0037] The accompanying drawings are included to provide a further understanding of the embodiments and are incorporated in and constitute a part of this specification, illustrate embodiments and explain their principles.

[0038] Figure 1 The wing lift curve when the fixed wing area of the present application is too small;

[0039] Figure 2 The wing lift curve when the fixed wing area of the present application is too large;

[0040] Figure 3 The wing lift curve when the fixed wing area of the present application is designed;

[0041] Figure 4 The three-view of the aircraft of the present application;

[0042] Figure 5 The structure schematic diagram of the wing fan fixed wing of the present application;

[0043] Figure 6 The structure schematic diagram of the power group of the present application;

[0044] Figure 7 The local structure schematic diagram of the main wing of the present application;

[0045] Figure 8 The structure schematic diagram of the fan wing segment of the present application;

[0046] Figure 9 Structure diagram of the aircraft of the present application;

[0047] Figure 10 Flow chart of the design method of the present application.

[0048] wherein, Figures 1-10 The correspondence between the reference signs and the component names in the accompanying drawings is as follows:

[0049] 1 fan wing, 2 fuselage, 3 main landing gear, 4 wing panel, 401 fan wing panel, 402 fixed wing panel, 403 mounting surface, 404 aileron, 5 large gear, 6 limit bearing, 7 transmission shaft, 8 motor, 9 small gear, 10 carbon tube, 11 paulownia beam, 12 sub beam, 13 wing rib, 14 trailing edge, 15 wall. DETAILED DESCRIPTION

[0050] In order to make the above object, features and advantages of the present application more clearly understood, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict.

[0051] In the following description, a large number of specific details are set forth in order to facilitate a thorough understanding of the present application, however, the present application can also be implemented in other ways different from those described herein, therefore, the protection scope of the present application is not limited by the specific embodiments disclosed below.

[0052] Please refer to Figures 1-10 , the following describes some embodiments of the present application, a fan wing fixed wing combined aircraft and its design method.

[0053] The embodiments of the first aspect of the present application propose a fan wing fixed wing combined aircraft. In some embodiments of the present application, as shown in Figures 4-9 , a fan wing fixed wing combined aircraft is provided, the fan wing fixed wing combined aircraft comprising:

[0054] A fuselage 2, the fuselage 2 is provided with a wing panel 4, the wing panel 4 comprises a fan wing panel 401 and a fixed wing panel 402, the fixed wing panel 402 is used to provide gliding lift when the aircraft is flying;

[0055] A fan wing 1, the fan wing panel 401 is provided with a mounting surface 403 for mounting the fan wing 1, the fan wing 1 is used to cooperate with the fan wing panel 401 to provide flight lift for the aircraft;

[0056] A power part, provided on the fan wing panel 401 and connected with the input shaft of the fan wing 1;

[0057] The area of the fan wing plate 401 and the fixed wing plate 402 is arranged in a proportional relationship with a preset range, and the change of the proportional relationship is used to adjust the flight stability of the aircraft under the same airspeed change, so that the aircraft can fly stably under the combined action of the gliding lift and the flight lift.

[0058] The aircraft provided by the application combines the fan wing 1 and the fixed wing, realizes the aerodynamic complementary characteristics of the two, has a short take-off and landing distance, good low-speed performance, sufficient lift when the airspeed is small or large, and can glide without power;

[0059] For the aircraft wing combined by the fan wing 1 and the fixed wing, the proportional relationship of the two can be considered to optimize the flight instability after combination, so that the aircraft combined with the fan wing 1 and the fixed wing can maintain stability under different types of lift in actual flight, that is, the gliding lift and the flight lift provided by different structures.

[0060] Further, the aileron 404 is rotatably installed at the end of the fixed wing plate away from the mounting surface along the axis of the fuselage, which is used to adjust the airflow direction on the fixed wing plate; and the aileron 404 is arranged at the end of the fixed wing plate away from the mounting surface along the axis of the fuselage, which can reduce the disturbance to the airflow flowing on the fan wing and the fan wing plate, and reduce the generation of turbulence on the wing plate.

[0061] Further, the main landing gear 3 is installed on the side of the fan wing plate away from the fan wing, so as to support the relatively heavy part of the wing plate with the fan wing.

[0062] In some embodiments, two fan wings 1 are provided, and the input shafts of the two fan wings 1 are coaxially arranged, and the power part includes: a motor 8 installed in the middle of the fan wing plate 401; a transmission mechanism for connecting the input shaft and the output shaft of the motor 8 to transmit the power of the motor 8 to the fan wing 1.

[0063] In this embodiment, two fan wings 1 are arranged on the fan wing 1, and the input shafts of the two fan wings 1 are coaxially arranged, so as to be driven by the same power part, thereby ensuring synchronization.

[0064] Due to the weight of the motor 8, the motor 8 is arranged in the middle of the fan wing plate 401 to avoid the instability of the aircraft caused by uneven weight.

[0065] In some embodiments, the transmission mechanism includes: a transmission shaft 7 for connecting the two input shafts; a driven wheel installed on the transmission shaft 7; and a driving wheel installed on the output shaft of the motor 8 and connected to the driven wheel.

[0066] In this embodiment, the input shafts of the two fan wings 1 are coaxially connected by the transmission shaft 7, and a driven gear matched with the driving gear is installed on the transmission shaft 7, so that the motor 8 drives the two input shafts to rotate in turn through the driving gear, the driven gear and the transmission shaft 7.

[0067] Further, the driving gear is a pinion 9, and the driven gear is a gear wheel 5 which is engaged with the pinion 9 to realize power transmission.

[0068] In some embodiments, the aircraft based on the combination of the fan wing and the fixed wing further comprises a mounting frame for mounting the fan wing 1 on the fan wing plate 401; wherein the mounting frame is provided with a fairing edge for connecting the top of the fan wing 1 and the root of the fan wing plate 401, and / or the transmission mechanism further comprises a limit bearing 6 for connecting the transmission shaft 7 and the mounting frame.

[0069] In this embodiment, the mounting frame is used for mounting between the fan wing 1 and the fan wing plate 401, and the fairing edge is arranged on the mounting frame, which can make the airflow more smoothly when passing through the outer top of the fan wing 1 and the rear edge of the fan wing plate 401, and play a role in guiding the flow.

[0070] Further, the mounting frame comprises a plurality of wing ribs 13 arranged along the wing plate and equidistantly arranged along the direction perpendicular to the fuselage axis, and the part of the wing rib 13 in contact with the fan wing is arranged in a circular arc to adapt to the installation of the fan wing, and the fairing edge is arranged on the wing rib 13.

[0071] Specifically, the limit bearing is fixedly assembled with the wing rib 13 closest to it.

[0072] Further, the adjacent wing ribs are positioned by inserting the secondary beam 12 therebetween to prevent the movement of the wing ribs along the fuselage axis.

[0073] Further, the wing rib is provided with a trailing edge 14 at the end away from the fan wing, and the trailing edge 14 is fixedly assembled with the rear part of the fixed wing plate.

[0074] Further, the two ends of the fairing edge correspond to the top end of the wing rib in contact with the fan wing and the rear part of the fan wing plate respectively, so as to ensure that the airflow flowing on the outer surface of the fan wing smoothly transitions to the rear end of the fan wing plate.

[0075] Further, a carbon tube is inserted on the top end of the wing rib in contact with the fan wing and perpendicular to the axis of the fuselage.

[0076] Further, a paulownia beam 11 is inserted on the wing rib, and a wall 15 connected with the paulownia beam is arranged between the adjacent wing ribs for fixedly mounting the plurality of wing ribs.

[0077] A second aspect of the present invention provides a method for designing an aircraft based on a combination of fan-wing and fixed-wing architecture. In some embodiments of the present invention, such as... Figures 1-3 As shown in Figure 10, a design method for an aircraft based on a fan-wing fixed-wing combination is provided. This method includes the following steps: The fan-wing 1 is mounted on the mounting surface 403 of the wingplate 4; the wingplate 4 is axially divided along the fuselage 2 to form a fan-wing plate 401 corresponding to the fan-wing 1 and providing lift; the remaining portion of the wingplate 4 after removing the fan-wing plate 401 is designated as a fixed-wing plate 402 providing gliding lift; considering the influence of the proportions of the wingplate 4 and the fixed-wing plate 402 on the total lift, the proportions of the wingplate 4 and the fixed-wing plate 402 are defined. A preset range for the proportional relationship between areas; based on the simulation experimental environment, flight experiments are conducted on aircraft with fan-wing plates and fixed-wing plates with different proportional relationships within the preset range to obtain the total lift change data on the wing plate 4 under different proportional relationships within the same airspeed range; the difference between the maximum and minimum total lift under different proportional relationships is obtained respectively, and the proportional relationship corresponding to the minimum difference is obtained. This proportional relationship is used as the optimal result of the fan-wing plate 401 and the fixed-wing plate 402 and used for aircraft design; wherein, an aircraft design method based on the combination of fan-wing and fixed-wing is used to design an aircraft as described in any of the first aspects.

[0078] This invention provides a design method for an aircraft based on the combination of a fan-wing and a fixed wing. When combining the fan-wing 1 and the fixed wing, the stability of the aircraft after the structure is considered. Therefore, a design method is proposed to improve the flight stability of the combined aircraft within a certain airspeed range, ensuring smooth flight of the aircraft. The total lift of the aircraft is tested and the data probability is obtained by conducting simulation experiments on the fan-wing 1 and the fixed wing plate 402 with different proportions. The proportion with the smallest change in total lift is taken as the optimal result.

[0079] In some embodiments, the difference between the maximum and minimum total lift is used to characterize the flight stability of an aircraft within a certain airspeed range; the total lift consists of gliding lift and flight lift; wherein, the smaller the difference, the more stable the flight of the aircraft is within that airspeed range.

[0080] In this embodiment, the aircraft's flight status is mainly affected by the total lift. Therefore, the difference between the maximum and minimum total lift is used to characterize flight stability, and the smaller the difference, the more stable the aircraft with the wing plate 4 under this ratio is.

[0081] In the measurement, gliding lift and flight lift were combined as the total lift, so that the experimental method took into account the combination of fan wing 1 and fixed wing, and the experimental results were more consistent with the case of fan wing 1 and fixed wing combined.

[0082] In some embodiments, the fixed wing plate 402 includes two single plates, which are symmetrically located at the ends of the fan wing plate 401 along the fuselage axis direction, and the area of the fixed wing plate 402 is S1, the area of the fan wing plate 401 is S2, and the preset range is S1 / S2=0.2-5.

[0083] In this embodiment, in order to avoid extreme wing plate 4 allocation, ensure that the fan wing 1 and the fixed wing can normally play a role in providing lift during flight, and therefore the preset range is S1 / S2=0.2-5.

[0084] The fan wing 1 is set in the middle of the wing plate 4 as a flight power driven structure, which divides the fixed wing into two and is set at the two ends of the fan wing plate 401, further ensuring the stability of flight.

[0085] In some embodiments, based on the difference value data under different proportional relationships in the simulation experiment environment, the optimal result is S1 / S2=0.875; the area ratio of a single plate to the fan wing plate 401 is 7:16.

[0086] In this embodiment, by comparing the differences under different proportional relationships in the simulation experiment environment, the optimal result can be selected, that is, S1 / S2=0.875, and the area ratio of a single plate to the fan wing plate 401 is 7:16, which is set at the end of the fan wing plate 401, as the design result of the aircraft wing part.

[0087] In some embodiments, in the continuous change of airspeed in the simulation experiment environment, the total area of the wing plate 4 and the rotating speed of the fan wing 1 remain unchanged.

[0088] In this embodiment, for different proportional relationships, simulation experiments are carried out in a unified airspeed range, specifically, the airspeed changes in the range of 0-40 m / s; and the total area of the wing plate is kept unchanged, and the lift provided by the fan blade in the fan wing does not change, eliminating the interference of irrelevant factors.

[0089] In the description of the present application, it should be understood that the terms "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation of the present application.

[0090] The above described embodiments are only to illustrate the preferred modes of the present application, and are not intended to limit the scope of the present application. Any modification and improvement made by those skilled in the art to the technical solutions of the present application without departing from the design spirit of the present application shall fall within the protection scope of the present application as defined by the claims.

Claims

1. An aircraft based on a combination of a fan wing and a fixed wing, characterized in that, The utility model relates to a kind of aircraft, including: Machine body, wing plate is provided on the machine body, the wing plate includes fan wing plate and fixed wing plate, the fixed wing plate is used to provide gliding lift when the aircraft flies; Fan wing, the mounting surface for installing the fan wing is provided on the fan wing plate, the fan wing is used to cooperate with fan wing plate to provide flight lift for the aircraft; Power part, the input shaft of fan wing is connected with the fan wing plate and is arranged; Wherein, the area of the fan wing plate and the fixed wing plate is provided with the proportion relationship of preset range, the change of the proportion relationship is used to adjust the flight stability of aircraft under the same airspeed variation, so that the aircraft is stably flown under the joint action of gliding lift and flight lift; Two fan wings are provided, and the input shafts of the two fan wings are coaxially arranged, and the power part includes: Motor, installed in the middle of fan wing plate; Transmission mechanism, for connecting input shaft and the output shaft of the motor, to transmit the power of the motor to the fan wing; The transmission mechanism includes: Transmission shaft, for connecting two input shafts; Driven wheel, installed on the transmission shaft; Driving wheel, installed on the output shaft of the motor, and connected with the driven wheel; Also including: Mounting bracket, for mounting the fan wing on the fan wing plate; Wherein, the mounting bracket is provided with fairing edge for connecting the top of fan wing and the root of fan wing plate, and / or the transmission mechanism further includes limit bearing for connecting the transmission shaft and mounting bracket.

2. A method for designing a flying machine based on a combination of a fixed wing and a fan wing, for designing a flying machine as claimed in claim 1, characterized in that, The following steps: Fan wing is set on mounting surface, and wing plate is divided into fan wing plate for corresponding with the fan wing and providing flight lift along the machine body axis;The remaining part of the end of the wing plate after removing the fan wing plate is set as the fixed wing plate for providing gliding lift; The proportion relationship between the area of the wing plate and the fixed wing plate is determined in the preset range considering the influence of the proportion of the wing plate and the fixed wing plate on the total lift respectively; Based on simulation experiment environment, flight experiment is carried out on the aircraft with different proportion relationship between fan wing plate and fixed wing plate in the preset range, and total lift change data on wing plate under different proportion relationship in the same airspeed range is obtained; The difference value of maximum total lift and minimum total lift under different proportion relationship is obtained respectively, and the proportion relationship corresponding to the minimum difference value is obtained, which is used as the optimal result of fan wing plate and fixed wing plate and used for aircraft design.

3. The method of claim 2, wherein, The difference value of maximum total lift and minimum total lift is used to represent the flight stability of the aircraft in a certain airspeed range; The total lift is composed of gliding lift and flight lift; Wherein, the smaller the difference value is, the more stable the aircraft flies in the airspeed range.

4. The method of claim 2, wherein, The fixed wing plate includes two single plates, and the two single plates are symmetrically located at the end of the fan wing plate along the machine body axis direction;And The area of the fixed wing plate is S1, the area of the fan wing plate is S2, and the preset range is S1 / S2=0.2-5.

5. The method of designing a fan wing fixed wing combined aircraft according to claim 4, wherein, Based on the difference value data under different proportion relationship in the simulation experiment environment, the optimal result is S1 / S2=0.875; The area ratio of a single single plate to fan wing plate is 7:

16.

6. The method of designing a fan wing fixed wing combined aircraft according to claim 2, wherein, In the simulation experiment environment, the total area of the wing plate and the rotating speed of the fan wing remain unchanged.

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