Fixed-wing aircraft

Abstract

The invention provides a fixed-wing aircraft, which takes a Karsi vertical coordinate system as a reference, takes a first plane formed by an X axis defined by the sailing direction of the fixed-wing aircraft and a Z axis defined by the gravity direction of the fixed-wing aircraft as a symmetry plane, and comprises an aircraft head, a fixed-wing aircraft body and a fixed-wing aircraft body, a fuselage; the main wing comprises a connecting part positioned at the rear part of the main wing, and the connecting part is used for connecting an air propulsion device; the air propulsion devices are connected with the main wings, each air propulsion device comprises an air guiding pipe, an air thruster and an air spraying pipe which are connected front and back in the X-axis direction, each air guiding pipe comprises an air inlet connected with the connecting part of the corresponding main wing, and the air inlets are used for guiding air into the air propulsion devices. According to the fixed-wing aircraft provided by the invention, the total lift force of the wings can be improved during cruising, and meanwhile, the maneuvering capability for supporting the fixed-wing aircraft to realize vertical / or short-distance take-off and landing and hovering is also provided.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft design, in particular to a fixed-wing aircraft. Background Art

[0002] Humans have been able to achieve powered manned flight for more than a hundred years, during which a variety of aircraft have emerged. From the perspective of overall structure, they can be divided into two categories: fixed-wing and rotary-wing. From the perspective of power, they range from the earliest steam power to mature fuel power, to today's electric and hybrid power, and to the future hydrogen fuel power and solar photovoltaic power. Thanks to humans' continuous research, understanding, and mastery of aerodynamics and the important targeted application of aircraft design, manufacturing, and control, the cruising and sprint flight speeds of aircraft can range from tens of kilometers per hour to thousands of kilometers per hour, the so-called supersonic flight, and the range can reach more than 10,000 kilometers, with a ceiling of 30,000 meters.

[0003] However, how to further improve the aircraft's powered flight efficiency, especially the range that can be achieved per unit of power consumption, and how to improve the adaptability and operability of aircraft takeoff and landing, especially to achieve short-moment or even vertical takeoff and landing, has always been one of the technical development goals that the aviation industry has been pursuing, especially under the current trend of electric power becoming more and more popular, and at the same time, drones, especially electric drones, are rapidly popularizing and their various applications are expanding.

[0004] In short, in addition to the specific requirements of special fields such as the military, which have an ever-increasing strategic demand for supersonic speed, super maneuverability and stealth, the fields dominated by electric aircraft and their applications in extensive civil airspace, especially in medium and low altitudes, continuously improving flight energy efficiency and achieving short-thrust takeoff and landing or even vertical takeoff and landing have become the unchanging core technology development direction and improvement goals.

[0005] Currently, fixed-wing aircraft are widely used in various application fields as the main powered aircraft. However, they still have problems such as large flight resistance, low flight speed and range, and low cost of short-takeoff and landing or even vertical takeoff and landing. Summary of the invention

[0006] In order to solve the problems existing in the prior art, the present invention provides a fixed-wing aircraft.

[0007] The invention provides a fixed-wing aircraft. With a Cartesian vertical coordinate system as a reference, the fixed-wing aircraft is constructed with a first plane formed by an X-axis defined by the navigation direction and a Z-axis defined by the gravity direction as a symmetry plane, and comprises: a nose; a fuselage, the fuselage is constructed along the X-axis with the first plane as the symmetry plane; a main wing, the main wing comprises a left main wing and a right main wing, the left main wing and the right main wing are respectively fixed on the left and right sides of the fuselage, the main wing comprises a connecting part located at the rear of the main wing and used for connecting an air propulsion device; at least one group of air propulsion devices connected to the main wing, the air propulsion device comprises an air bleed pipe, a gas thruster and an air jet pipe connected front and rear along the X-axis direction, and used for increasing the total lift of the wing, the air bleed pipe comprises an air inlet connected to the main wing connecting part, and the air inlet is used for introducing air into the air propulsion device.

[0008] Optionally, the group of air propulsion devices is divided into a left air propulsion device and a right air propulsion device, the left air propulsion device is integrally configured with the connecting part of the left main wing, and the right air propulsion device is integrally configured with the connecting part of the right main wing; wherein the left air propulsion device includes a left bleed air pipe, a left gas thruster and a left jet pipe, which are connected in sequence front to back, and the right air propulsion device includes a right bleed air pipe, a right gas thruster and a right jet pipe, which are connected in sequence front to back.

[0009] Optionally, the left air duct includes a left air inlet connected to the left main wing, the left air inlet is a flat rectangular air inlet, the top of the left air inlet is parallelly arranged on the connecting part of the left main wing, and the bottom edge of the left air inlet is connected to the top surface of the connecting part of the left main wing.

[0010] Optionally, the right air duct includes a right air inlet connected to the right main wing, the right air inlet is a flat rectangular air inlet, the top of the right air inlet is parallelly arranged on the connecting part of the right main wing, and the bottom edge of the right air inlet is connected to the top surface of the connecting part of the right main wing.

[0011] Optionally, the left air duct includes a left air inlet connected to the left main wing, the top of the left air inlet is arranged in parallel above the connecting portion of the left main wing, the bottom of the left air inlet is arranged in parallel below the connecting portion of the left main wing, the left air inlet includes an upper air inlet and a lower air inlet, and the cross-section of the connecting portion between the upper air inlet and the lower air inlet of the left air inlet and the left main wing is a "human" shape.

[0012] Optionally, the right air duct includes a right air inlet connected to the right main wing, the top of the right air inlet is arranged in parallel above the connecting portion of the right main wing, the bottom of the right air inlet is arranged in parallel below the connecting portion of the right main wing, the right air inlet includes an upper air inlet and a lower air inlet, and the cross-section of the connecting portion between the upper air inlet and the lower air inlet of the right air inlet and the right main wing is a "human" shape.

[0013] Optionally, the left gas thruster and the right gas thruster are piston or engine driven propeller fans.

[0014] Optionally, the engine is a fuel engine, and the fuel includes one of fuel oil or hydrogen.

[0015] Optionally, the left air jet pipe and the right air jet pipe are bendable nozzles, and the bending angle range of the bendable nozzles on the first plane is 0-180°.

[0016] Optionally, the fixed-wing aircraft further includes: a third air thrust device constructed in the fuselage in front of or behind the main wing, the third air thrust device including: an air bleed top cover plate, a third gas thruster and an air outlet bottom cover plate, the air bleed top cover plate being arranged on the upper surface of the fuselage, the air outlet bottom cover plate being arranged on the lower surface of the fuselage at a position corresponding to the air bleed top cover plate, and the third gas thruster being arranged in a cavity jointly formed by the air bleed top cover plate, the air outlet bottom cover plate and the fuselage.

[0017] Optionally, the third air thrust device includes two states, open and closed; wherein, the air bleed top cover plate includes a first side close to the nose and a second side away from the nose, the second side of the air bleed top cover plate is rotatably connected to the fuselage, in the closed state, the first side of the air bleed top cover plate is connected to the upper surface of the fuselage, in the open state, the first side of the air bleed top cover plate is separated from the fuselage, the air bleed top cover plate rotates in a direction parallel to the first plane with the second side as the center, and forms a flat air bleed port together with the upper surface of the fuselage, and the rotation angle range is 0-90°; the air outlet bottom cover plate includes a first side close to the nose and a second side away from the nose, the first side of the air outlet bottom cover plate is rotatably connected to the fuselage, in the closed state, the second side of the air outlet bottom cover plate is connected to the lower surface of the fuselage, in the open state, the second side of the air outlet bottom cover plate is separated from the fuselage, the air outlet bottom cover plate rotates in a direction parallel to the first plane with the first side as the center, and forms an air outlet together with the lower surface of the fuselage, and the rotation angle range is 0-90°.

[0018] Optionally, the third gas thruster includes an upper fan and a lower fan which are symmetrically arranged with respect to the Z axis, and the upper fan and the lower fan rotate in opposite directions when turned on.

[0019] Optionally, at least one of the left gas thruster, the right gas thruster and the third gas thruster is an electric propeller fan.

[0020] Optionally, the fixed-wing aircraft further comprises: at least one set of auxiliary wings arranged in front of or behind the main wing, each set of auxiliary wings comprising a left auxiliary wing arranged on the left side of the fuselage and connected to the fuselage and a right auxiliary wing arranged on the right side of the fuselage and connected to the fuselage.

[0021] Optionally, the left auxiliary wing and / or the right auxiliary wing are rotatable wings, and the left auxiliary wing and the right auxiliary wing can respectively rotate around the Y axis to independently adjust the installation angle with the fuselage.

[0022] Optionally, the left jet pipe, the right jet pipe and the air outlet bottom cover plate respectively include a left ground sub-component, a right ground sub-component and a middle ground sub-component, and the left ground sub-component, the right ground sub-component and the middle ground sub-component are used to form triangular endpoints when the fixed-wing aircraft lands to provide balance support.

[0023] Optionally, the left ground sub-component includes at least one rotatable pulley, the right ground sub-component includes at least one rotatable pulley, and the middle ground sub-component includes at least one rotatable pulley, and the rotation axis of the rotatable pulley is parallel to the Y axis.

[0024] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0025] A fixed-wing aircraft provided by the present invention comprises a pair of air propulsion devices respectively connected to the main wings, wherein the air propulsion devices have a continuously distributed air intake function, thereby providing longitudinal thrust for the entire aircraft through the wings and improving the boundary layer flow characteristics of the wing top surface to increase the total lift of the wing and reduce the total resistance. Furthermore, the air propulsion device also comprises a plurality of bendable nozzles that can be continuously rotated 90 degrees, which can cooperate with the upper and lower fans in the third gas thruster arranged at the front or rear of the fuselage to generate a three-point balanced normal thrust to support the vertical take-off and landing of the entire aircraft and hovering in the air. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 It is a longitudinal cross-sectional structure and airflow schematic diagram of a curved thin wing of an existing aircraft;

[0028] Figure 2It is a top view structural schematic diagram of a fixed-wing aircraft according to a first embodiment of the present disclosure;

[0029] Figure 3 It is a side structural schematic diagram of a fixed-wing aircraft according to a first embodiment of the present disclosure;

[0030] Figure 4 It is a front structural schematic diagram of the left main wing of the first embodiment of the present disclosure;

[0031] Figure 5 It is a schematic diagram of the cross-sectional structure of the left main wing of the first embodiment of the present disclosure;

[0032] Figure 6 It is a schematic diagram of the cross-sectional structure of the left main wing of the second embodiment of the present disclosure;

[0033] Figure 7 It is a rear view structural schematic diagram of the right main wing of the first embodiment of the present disclosure;

[0034] Figure 8 It is a schematic diagram of the cross-sectional structure and airflow introduction of the third air propulsion device of the first embodiment of the present disclosure. DETAILED DESCRIPTION

[0035] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited to the embodiments set forth herein.

[0036] In the present invention, unless otherwise specified, the directional words used, such as "upper and lower", generally refer to the upper and lower parts of the device in normal use, and "inside and outside" refer to the outline of the device. In addition, the terms "first, second, third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first, second, third" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined. Since the accompanying drawings are descriptions of the same device, the same reference numerals in the drawings represent the same components.

[0037] As described in the background technology, fixed-wing aircraft are the main powered aircraft and are widely used in various application fields, but they still have problems such as large flight resistance, low flight speed and range, and low cost of short-moment takeoff and landing or even vertical takeoff and landing.

[0038] Attached Figure 1The longitudinal cross-sectional structure and airflow diagram of the traditional aircraft thin curved wing. The main wing R100 is in nearly level flight or at a certain angle of attack. The airflow splitting and the splitting and vortex generation and flow field conditions above the rear part R130 of the main wing are shown in the figure. Figure 1 As is known to all, when the airflow speed corresponding to the flight speed of the aircraft reaches a certain critical point, the airflow R10 flowing through the top surface R110 of the main wing R100 will lose its laminar state, and generate a split flow above the rear part R130 of the main wing, accompanied by a vortex R90 above the tail, thereby causing a sudden change in the pressure distribution on the top surface R110 of the main wing and a sudden drop in the total lift of the wing, and even a sudden increase in the wing resistance caused by the vortex.

[0039] In order to solve the above problems, the present invention provides a fixed-wing aircraft. With a Cartesian vertical coordinate system as a reference, the fixed-wing aircraft is constructed with a first plane formed by an X-axis defined by its navigation direction and a Z-axis defined by its gravity direction as a symmetry plane, and comprises: a nose; a fuselage, the fuselage is constructed with the first plane as a symmetry plane and along the X-axis; a main wing, the main wing comprises a left main wing and a right main wing, the left main wing and the right main wing are respectively fixed to the left and right sides of the fuselage, the main wing comprises a connecting portion located at the rear of the main wing, and is used to connect an air propulsion device; at least one group of air propulsion devices connected to the main wing, the air propulsion device comprises an air bleed pipe, a gas thruster and an air jet pipe connected front and rear along the X-axis direction, and is used to increase the total lift of the wing, the air bleed pipe comprises an air inlet connected to the connecting portion of the main wing, and the air inlet is used to introduce air into the air propulsion device.

[0040] In order to provide a further understanding of the purpose, structure, features and functions of the present invention, specific examples of the present invention are further described in detail below in conjunction with the accompanying drawings.

[0041] Figure 2-3 This is a structural diagram of a fixed-wing aircraft of the first embodiment of the present disclosure. With reference to the Cartesian vertical coordinate system, the fixed-wing aircraft provided by the present invention is bilaterally symmetrically constructed with a first plane 21 formed by the X-axis defined by its navigation direction and the Z-axis defined by the gravity direction as a symmetry plane, wherein the first plane 21 is formed by the longitudinal X-axis and the normal Z-axis pointing downward from the aircraft and perpendicular to the longitudinal X-axis and the transverse Y-axis according to the right-hand rule. Therefore, each figure shows half of the structure if there are symmetrical parts, and the other half can be reasonably expanded with reference to the symmetry plane.

[0042] Specifically, the fixed-wing aircraft 999 includes: a nose, a fuselage 900 extending along the longitudinal X-axis direction, a left main wing 100 and a right main wing 200 respectively arranged on the left and right sides of the front of the fuselage and extending in the lateral Y-axis direction, the left main wing 100 is connected to the left air propulsion device 150, and the right main wing 200 is connected to the right air propulsion device 250.

[0043] In the first embodiment of the present disclosure, refer to Figure 4-5 The connection part at the rear of the left main wing 100 is connected to the left air propulsion device 150. The left air propulsion device 150 includes a left bleed pipe 160, a left gas thruster 170 and a left jet pipe 180 connected front and back along the longitudinal X-axis direction. The left bleed pipe 160 includes a left air inlet 161, which is arranged at the rear of the left main wing. The top 161A of the left air inlet 161 and the upper surface of the rear 130 of the left main wing together form an integrated left air inlet 161, which is used to introduce air into the air propulsion device 150.

[0044] In the second embodiment of the present disclosure, as shown in the attached Figure 6 As shown, the left air duct 160 includes a left air inlet 161 connected to the left main wing 100. The top of the left air inlet 161 is parallelly arranged on the connection part 130 of the left main wing, and the top of the left air inlet 161 and the upper surface of the connection part 130 of the left main wing constitute an upper air inlet; the bottom of the left air inlet 161 is parallelly arranged below the connection part 130 of the left main wing 100, and the bottom of the left air inlet 161 and the lower surface of the connection part 130 of the left main wing constitute a lower air inlet. The cross-section of the connection part between the upper air inlet and the lower air inlet of the left air inlet 161 and the left main wing is a "human" shape. The upper boundary laminar flow 91 on the upper surface of the left main wing 100 enters the left air propulsion device 150 through the upper air inlet, and the lower boundary laminar flow 92 on the lower surface of the left main wing 100 enters the left air propulsion device 150 through the lower air inlet, so that the boundary laminar flow of the left main wing 100 can be stabilized and the generation of diversion and vortex can be suppressed.

[0045] In the first embodiment of the present disclosure, refer to Figure 7 Similar to the left structure, the connection part at the rear of the right main wing 200 is connected to the right air propulsion device 250. The right air propulsion device 250 includes a right bleed pipe, a right gas thruster and a right jet pipe 280 connected front and back along the longitudinal X-axis direction. The right bleed pipe includes a right air inlet, which is arranged at the rear of the right main wing. The top 161A of the right air inlet and the upper surface of the rear of the right main wing together form an integrated right air inlet for introducing air into the right air propulsion device 250.

[0046] In the second embodiment of the present disclosure, similar to the left structure, the right air duct includes a right air inlet connected to the right main wing. The top of the right air inlet is parallelly arranged above the connecting portion of the right main wing, and the top of the right air inlet and the upper surface of the connecting portion of the right main wing constitute an upper air inlet; the bottom of the right air inlet is parallelly arranged below the connecting portion of the right main wing, and the bottom of the right air inlet and the lower surface of the connecting portion of the right main wing constitute a lower air inlet. The right air inlet includes an upper air inlet and a lower air inlet, and the cross-section of the connecting portion of the upper air inlet and the lower air inlet of the right air inlet and the right main wing is a "human" shape. The upper boundary laminar flow on the upper surface of the right main wing enters the right air propulsion device through the upper air inlet, and the lower boundary laminar flow on the lower surface of the right main wing enters the right air propulsion device through the lower air inlet, which can stabilize the boundary laminar flow of the right main wing and suppress the generation of diversion and vortex.

[0047] In some embodiments, the left gas thruster and the right gas thruster are piston or engine driven propeller fans. In a specific embodiment, the left gas thruster and / or the right gas thruster are electric propeller fans.

[0048] In some embodiments, the left gas thruster and the right gas thruster are both composed of fuel engines, and the propulsion fuel used may be fuel oil or hydrogen.

[0049] In the disclosed embodiment, the left jet pipe 180 of the left air propulsion device and the right jet pipe 280 of the right air propulsion device are both multi-section bendable nozzles, and the bending angle range of the bendable nozzles on the first plane 21 is 0-180°. The rotatable nozzles can independently and continuously rotate at least 90 degrees between the longitudinal X-axis and the normal Z-axis. By rotating at different angles, a 90-degree continuous conversion of air propulsion is achieved, from jetting backward along the longitudinal X-axis required for level flight to jetting vertically along the normal Z-axis.

[0050] In the embodiments of the present disclosure, refer to Figure 4 and Figure 6 The left jet pipe component 180 includes a left grounding sub-component 189 , and the right jet pipe component 280 includes a right grounding sub-component 289 .

[0051] In some embodiments, the left ground sub-element and the right ground sub-element each include at least one rotatable pulley, and a rotation axis of the rotatable pulley is parallel to the Y-axis.

[0052] In some embodiments, the geometric dimensions of the cross-section of the air inlet, including the length of the main wing, the thickness of the air inlet, the geometric design of the main wing, the type of gas thruster, the power and import requirements, and other related components are considered in a coordinated manner, and ultimately depend on the design requirements of the fixed-wing aircraft, such as cruising speed, altitude, and load. The embodiments of the present disclosure are not limited to this.

[0053] In the disclosed embodiment, the left main wing 100 and the right main wing 200 both have wing tips 110 and 210 with the same inclination angle to reduce the wind resistance caused by vortices above the wing tips. At the same time, the cross section of the entire fuselage 900 adopts a V-shaped polygonal design to improve its stealth performance.

[0054] In the disclosed embodiment, the left and right bleed air pipes are respectively provided with a left aile flap 190 and a right aile flap (not shown) at the rear of the main wing between the fuselage. In some embodiments, the left aile flap and the right aile flap can rotate with the lateral Y axis as the axis to support the left main wing or the right main wing to complete lateral rolling, i.e., lateral rolling and overall pitch aerodynamic attitude adjustment and control, on one side or on both sides.

[0055] In the disclosed embodiment, the fixed-wing aircraft 999 further includes a left auxiliary wing 300 and a right auxiliary wing 400, which are respectively arranged on the left and right sides of the tail of the fuselage 900 and extend in the Y-axis direction. The left auxiliary wing 300 and the right auxiliary wing 400 are both rotatable wings, and the left auxiliary wing 300 and the right auxiliary wing 400 can be rotated around the Y-axis direction respectively, so as to independently adjust the installation angle between the auxiliary wing and the fuselage.

[0056] In some embodiments, the auxiliary wings may also be arranged on both sides of the fuselage in front of the main wings.

[0057] In the disclosed embodiment, both the left auxiliary wing 300 and the right auxiliary wing 400 have V-shaped inclined wing tips 310 and 410 to improve the rolling stability of the whole aircraft, while having certain stealth characteristics.

[0058] In the disclosed embodiment, Figure 8 The third air thrust device 950 is shown, which is arranged in the fuselage behind the main wing, and includes: an air bleed top cover plate 960, a third gas thruster 970 and an air outlet bottom cover plate 980. The air bleed top cover plate 960 is arranged on the upper surface 910 of the fuselage, and the air outlet bottom cover plate 980 is arranged on the lower surface 920 of the fuselage, and corresponds to the position of the air bleed top cover plate 960 up and down. The third gas thruster 970 is arranged in a cavity formed by the air bleed top cover plate 960, the air outlet bottom cover plate 980 and the fuselage 900. The third gas thruster 970 includes an upper fan and a lower fan symmetrically arranged with the Z axis as the axis, and the upper fan and the lower fan rotate in opposite directions when turned on. The second end of the air outlet bottom cover plate 980 is also provided with a middle ground sub-component 989.

[0059] In some embodiments, the third air thrust device may be constructed in the fuselage in front of the main wing.

[0060] In some embodiments, the third gas thruster is an electric propeller fan.

[0061] In some embodiments, the grounding sub-component at the second end of the air outlet bottom cover plate includes at least one rotatable pulley.

[0062] In the embodiment of the present disclosure, the third air thrust device includes two states: open and closed; wherein the air bleed top cover plate includes a first end close to the nose and a second end away from the nose, in the closed state, the air bleed top cover plate is connected to the upper surface of the fuselage, in the open state, the first end of the air bleed top cover plate is separated from the fuselage, the air bleed top cover plate rotates around the second end with the Y axis as the axis in the direction away from the upper surface of the fuselage, the rotation angle range is 0-90°, and together with the upper surface of the fuselage, a flat air bleed port is formed; the air outlet bottom cover plate includes a first end close to the nose and a second end away from the nose, in the closed state, the air outlet bottom cover plate is connected to the lower surface of the fuselage, in the open state, the second end of the air outlet bottom cover plate is separated from the fuselage, the air outlet bottom cover plate rotates around the first end with the Y axis as the axis in the direction away from the lower surface of the fuselage, the rotation angle range is 0-90°, and together with the lower surface of the fuselage, an air outlet is formed, generating aerodynamic thrust below the normal Z axis.

[0063] In the disclosed embodiment, the air bleed top cover plate 960 and the air outlet bottom cover plate 980 are respectively flush with the upper surface of the fuselage 900 and the lower surface of the fuselage 900 when the aircraft is cruising in level flight and the third gas thruster is in the closed state, so as to reduce resistance; and when the third air thruster is in the open state, the front edge 961 of the air bleed top cover plate 960 forms a flat air bleed port with the upper surface of the fuselage 900, while promoting the stability of the adjacent boundary layer flow and the positive pressure gradient, so as to promote the increase of the aerodynamic lift of the fuselage; the air outlet bottom cover plate 980 can be continuously and adjustable with the Y axis as the axis, and the rotation angle range is 0-90°, which can not only adjust the exhaust direction, that is, the aerodynamic thrust direction, but also can be attached with a ground sub-component, the top of which provides a support point required for take-off and landing. In order to achieve three-point support balance, the middle ground sub-component 989, the left ground sub-component 189 at the rear of the left wing, and the right ground sub-component 289 at the rear of the right wing provide three-point ground support for the fuselage 900.

[0064] In some embodiments, the third gas thruster, i.e., the normal gas thruster, is only started during takeoff, landing, and hovering of the aircraft. The third gas thruster is a fuel lift fan engine, and for small and medium-sized aircraft, a dual electric coaxial fan with reversed directions can be used. The left gas thruster and the right gas thruster, the main flight power unit of the aircraft, should use turbine engines for large and medium-sized aircraft, piston-driven ducted fans can be considered for medium-sized aircraft, and electric ducted fans can be used for small aircraft.

[0065] In some embodiments, the type, power and model of the rotatable pulley of the third gas thruster ultimately depend on the design requirements of the fixed-wing aircraft, such as cruising speed, altitude, load, etc., and the embodiments of the present disclosure do not impose any restrictions on this.

[0066] The fixed-wing aircraft provided by the disclosed embodiment can not only effectively suppress the generation of upper boundary layer airflow and vortex, but also enhance the total lift of the main wing. Taking the left main wing as an example, from the aerodynamic point of view, through the "suction force" of the left air propulsion device 150, especially the left gas thruster 170, the "boundary layer flow suction" flat rectangular air inlet 161 can reduce the "boundary layer flow" pressure of a certain thickness on the upper surface of the left main wing 100 along with the flow. If it is a turbo electric fan or a turbo engine, the left bleed air pipe will be "sucked" into the left gas thruster 170 at a higher laminar flow rate. The left gas thruster 170 further pressurizes the airflow and ejects it through the rear left jet pipe 180, while generating a longitudinal X-axis forward thrust to the left main wing 100 and the fuselage 900.

[0067] The continuously distributed "boundary layer airflow introduction" design along the wing span provided by the embodiments of the present disclosure can achieve maximum laminar modulation, lift enhancement, drag reduction and extended cruising range for civil low-speed aircraft with a speed range of 0 to 0.3 Mach and 0.3 to 0.8 Mach subsonic aircraft.

[0068] The above descriptions are merely embodiments of the present application and are not intended to limit the patent scope of the present application. Any equivalent structural or equivalent process transformations made using the contents of the specification and drawings of the present application, such as the mutual combination of technical features between the embodiments, or direct or indirect application in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A fixed-wing aircraft, with a Cartesian vertical coordinate system as a reference, wherein the first plane formed by the X-axis defined by the navigation direction and the Z-axis defined by the gravity direction of the fixed-wing aircraft is constructed as a symmetry plane, characterized in that: include: Machine head; A fuselage, wherein the fuselage is arranged along the X-axis with the first plane as a symmetric plane; A main wing, wherein the main wing comprises a left main wing and a right main wing, wherein the left main wing and the right main wing are respectively fixed to the left and right sides of the fuselage, and the main wing comprises a connecting portion located at the rear of the main wing for connecting to an air propulsion device; At least one set of air propulsion devices connected to the main wing, the air propulsion device includes an air bleed pipe, a gas thruster and an air jet pipe connected front and back along the X-axis direction, which is used to increase the total lift of the wing, and the air bleed pipe includes an air inlet connected to the main wing connection part, and the air inlet is used to introduce air into the air propulsion device.

2. The fixed-wing aircraft according to claim 1, characterized in that: The group of air propulsion devices is divided into a left air propulsion device and a right air propulsion device, the left air propulsion device is integrally configured with the connection portion of the left main wing, and the right air propulsion device is integrally configured with the connection portion of the right main wing; Among them, the left air propulsion device includes a left bleed air pipe, a left gas thruster and a left jet pipe connected in sequence front and back, and the right air propulsion device includes a right bleed air pipe, a right gas thruster and a right jet pipe connected in sequence front and back.

3. The fixed-wing aircraft according to claim 2, characterized in that: The left air duct comprises a left air inlet connected to the left main wing, wherein the left air inlet is a flat rectangular air inlet, the top of the left air inlet is arranged parallel to the connecting portion of the left main wing, and the bottom edge of the left air inlet is connected to the top surface of the connecting portion of the left main wing.

4. The fixed-wing aircraft according to claim 2, characterized in that: The right air duct comprises a right air inlet connected to the right main wing, wherein the right air inlet is a flat rectangular air inlet, the top of the right air inlet is arranged parallel to the connecting portion of the right main wing, and the bottom edge of the right air inlet is connected to the top surface of the connecting portion of the right main wing.

5. The fixed-wing aircraft according to claim 2, characterized in that: The left air duct comprises a left air inlet connected to the left main wing, the top of the left air inlet is arranged parallel to the connecting portion of the left main wing, the bottom of the left air inlet is arranged parallel to the connecting portion of the left main wing, the left air inlet comprises an upper air inlet and a lower air inlet, and the cross-section of the connecting portion of the upper air inlet and the lower air inlet of the left air inlet and the left main wing is a "human" shape.

6. The fixed-wing aircraft according to claim 2, characterized in that: The right air duct comprises a right air inlet connected to the right main wing, the top of the right air inlet is arranged parallel to the connecting portion of the right main wing, the bottom of the right air inlet is arranged parallel to the connecting portion of the right main wing, the right air inlet comprises an upper air inlet and a lower air inlet, and the cross-section of the connecting portion between the upper air inlet and the lower air inlet of the right air inlet and the right main wing is a "human" shape.

7. The fixed-wing aircraft according to claim 2, characterized in that: The left gas thruster and the right gas thruster are piston or engine driven propeller fans.

8. The fixed-wing aircraft according to claim 7, characterized in that: The engine is a fuel engine, and the fuel includes one of fuel oil or hydrogen.

9. The fixed-wing aircraft according to claim 2, characterized in that: The left air-injection pipe and the right air-injection pipe are bendable nozzles, and the bending angle range of the bendable nozzles on the first plane is 0-180°.

10. The fixed-wing aircraft according to claim 2, characterized in that: Also includes: A third air thrust device is arranged in the fuselage in front of or behind the main wing, and the third air thrust device comprises: an air bleed top cover plate, a third gas thruster and an air outlet bottom cover plate, wherein the air bleed top cover plate is arranged on the upper surface of the fuselage, the air outlet bottom cover plate is arranged on the lower surface of the fuselage at a position corresponding to the air bleed top cover plate, and the third gas thruster is arranged in a cavity formed by the air bleed top cover plate, the air outlet bottom cover plate and the fuselage.

11. The fixed-wing aircraft according to claim 10, characterized in that: The third air thrust device includes two states: open and closed; wherein, The air bleed top cover plate comprises a first side close to the nose and a second side away from the nose, the second side of the air bleed top cover plate is rotatably connected to the fuselage, in a closed state, the first side of the air bleed top cover plate is connected to the upper surface of the fuselage, in an open state, the first side of the air bleed top cover plate is separated from the fuselage, the air bleed top cover plate rotates in a direction parallel to the first plane with the second side as the center of a circle, and forms a flat air bleed port together with the upper surface of the fuselage, and the rotation angle range is 0-90°; The air outlet bottom cover plate includes a first side close to the machine head and a second side away from the machine head. The first side of the air outlet bottom cover plate is rotatably connected to the fuselage. In a closed state, the second side of the air outlet bottom cover plate is connected to the lower surface of the fuselage. In an open state, the second side of the air outlet bottom cover plate is separated from the fuselage. The air outlet bottom cover plate rotates in a direction parallel to the first plane with the first side as the center of the circle to form an air outlet together with the lower surface of the fuselage. The rotation angle range is 0-90°.

12. The fixed-wing aircraft according to claim 10, characterized in that: The third gas thruster comprises an upper fan and a lower fan which are symmetrically arranged with the Z axis as the axis, and the upper fan and the lower fan rotate in opposite directions when turned on.

13. The fixed-wing aircraft according to claim 10, characterized in that: At least one of the left gas thruster, the right gas thruster and the third gas thruster is an electric propeller fan.

14. The fixed-wing aircraft according to claim 1, characterized in that: Also includes: At least one set of auxiliary wings is arranged in front of or behind the main wing, and each set of auxiliary wings includes a left auxiliary wing arranged on the left side of the fuselage and connected to the fuselage, and a right auxiliary wing arranged on the right side of the fuselage and connected to the fuselage.

15. The fixed-wing aircraft according to claim 14, characterized in that: The left auxiliary wing and / or the right auxiliary wing are rotatable wings. The left auxiliary wing and the right auxiliary wing can rotate around the Y axis respectively to independently adjust the installation angle with the fuselage.

16. The fixed-wing aircraft according to claim 10, characterized in that: The left jet pipe, the right jet pipe and the air outlet bottom cover plate respectively include a left ground sub-component, a right ground sub-component and a middle ground sub-component, and the left ground sub-component, the right ground sub-component and the middle ground sub-component are used to form triangular endpoints when the fixed-wing aircraft lands to provide balance support.

17. The fixed-wing aircraft according to claim 16, characterized in that: The left ground sub-component includes at least one rotatable pulley, the right ground sub-component includes at least one rotatable pulley, and the middle ground sub-component includes at least one rotatable pulley, and the rotation axis of the rotatable pulley is parallel to the Y axis.

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