Multi-convex wing and multi-convex wing engine and control method thereof

Abstract

The present invention discloses a multi-convex wing and a multi-convex wing engine and a control method thereof. The multi-convex wing comprises a multi-convex wing base and a guide body. The multi-convex wing base is formed by connecting a plurality of single convex wings to form a plurality of continuous convex curved surfaces. The guide body is arranged between two convex curved surfaces of the multi-convex wing base. The multi-convex wing engine comprises a multi-convex wing, a flow channel, and a high-speed fluid generator. The multi-convex wing is arranged on the inner cavity surface of the flow channel. The high-speed fluid generator is a device capable of outputting high-speed fluid. When the fluid flows through the multi-convex wing base, the guide body guides the fluid flowing through the previous convex curved surface to the next convex curved surface, and guides the fluid to flow along the convex curved surface of the multi-convex wing base. The viscosity of the fluid and the inertia of the fluid work together to block the pressure of the fluid on the upper part of the multi-convex wing base and form a negative pressure area on the convex curved surface, thereby generating a plurality of corresponding lift areas on the multi-convex wing base, greatly improving the lift and force efficiency, and solving the problem of low efficiency of vehicles and equipment using traditional engines.

Description

Technical Field

[0001] The present invention relates to the technical field of engines and vehicles, and in particular to a multi-lobed wing and a multi-lobed wing engine and a control method thereof. Background Art

[0002] The existing wing has only one convex curved surface on its upper surface, which is called a single convex wing. It can only generate a large lift at the convex front end, and most of the wing area at the rear end generates a small lift. In addition, its utilization rate of high-speed fluid is low, resulting in a limited lift-to-drag ratio. The fuselage is not fully utilized to generate lift, so a long wing and a lift-enhancing device are needed to generate enough lift, resulting in a large appearance of common aircraft and low safety.

[0003] Traditional engines include turboprops, turbines, propfans, and propellers, but they have small power loads and low thrust-to-weight ratios, resulting in low efficiency in vehicles and equipment that use traditional engines to generate propulsion, and often experience insufficient power. Summary of the invention

[0004] The object of the present invention is to provide a multi-lobed wing and a multi-lobed wing engine and a control method thereof, aiming to solve the problem of low efficiency of vehicles and equipment using traditional engines to generate propulsion.

[0005] To achieve the above-mentioned object, in a first aspect, the present invention provides a multi-convex wing, comprising a multi-convex wing base and a drainage body, wherein the multi-convex wing base is formed by connecting a plurality of single convex wings, and forms a plurality of continuous convex curved surfaces along the flow direction of the fluid on the negative pressure lift surface, and the drainage body is arranged between two convex curved surfaces of the multi-convex wing base;

[0006] The fluid is any one of gas and liquid or a combination of several;

[0007] When the fluid flows through the multi-convex wing substrate, the guide body guides the fluid flowing through the previous convex curved surface to the next convex curved surface, and guides the fluid to flow along the convex curved surface of the multi-convex wing substrate. The viscosity of the fluid and the inertia of the fluid work together to block the pressure of the fluid on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex curved surface, thereby generating corresponding multiple lift areas on the multi-convex wing substrate. By adjusting the attitude and position of the guide body relative to the multi-convex wing substrate, the size, direction and distribution of the multi-convex wing lift can be regulated, thereby controlling the rise and fall and flight attitude of the entire aircraft.

[0008] Wherein, the drainage body includes any one or a combination of plate-shaped drainage bodies, cone-shaped drainage bodies, and streamlined drainage bodies;

[0009] The conical drainage body is a conical body with a sharp front and a blunt back, and the outer surface of the conical body includes any one of a straight surface and a curved surface or a combination of several of them;

[0010] The streamlined drainage body is a streamlined body with small ends and a large middle, and the outer surface of the streamlined body includes any one of a straight surface and a curved surface or a combination of several of them;

[0011] The multi-wing substrate and the guide body may be provided with any one of wing blades and vortex generators or a combination of several of them.

[0012] In a second aspect, the present invention provides a multi-convex wing engine, comprising the multi-convex wing described in the first aspect, and further comprising a flow channel and a fluid generator, wherein the multi-convex wing substrate is arranged on the inner cavity surface of the flow channel, and the fluid generator is a device for outputting high-speed fluid;

[0013] The flow channel includes any one of a unidirectional flow channel and a circulating flow channel or a combination of several thereof; the shape of the flow channel includes any one of an open cavity, a semi-closed cavity, and a closed cavity or a combination of several thereof;

[0014] The fluid generated by the fluid generator is sprayed toward the multi-convex wing substrate in the flow channel, and the guide body guides the fluid flowing through the previous convex curved surface to the next convex curved surface, guiding the fluid to flow along the convex curved surface of the multi-convex wing substrate. The viscosity of the fluid and the inertia of the fluid work together to block the pressure of the fluid on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex curved surface, thereby generating corresponding multiple lift areas on the multi-convex wing substrate.

[0015] Wherein, a plurality of convex curved surfaces are directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing base;

[0016] The drainage body can be directly integrated with the closed and semi-closed flow channels;

[0017] The fluid generator includes any one of an internal combustion engine and a steam engine or a combination of several of them;

[0018] The layout of the fluid generator includes any one of centralized, distributed, built-in, and external layouts, or a combination of several of them.

[0019] The nozzle of the fluid generator includes any one or a combination of fixed and movable types; the nozzle of the movable fluid generator is an adjustable structure, and the size of the nozzle and the relative angle and position with the multi-convex wing can be adjusted;

[0020] The multi-convex wing substrate includes any one or a combination of fixed multi-convex wings and movable multi-convex wings. The size, shape and number of the convex curved surfaces of the movable multi-convex wings can be adjusted according to the fluid flow rate.

[0021] Wherein, the flow channel includes any one or a combination of linear, spiral, annular, and disc shapes;

[0022] The ring shape includes any one or a combination of a circular ring, an elliptical ring, a polygonal ring, and an arc ring;

[0023] The disk shape includes any one or a combination of a circular disk shape, an elliptical disk shape, a polygonal disk shape, and an arc disk shape;

[0024] The annular multi-lobed wing engine comprises any one of a single annular multi-lobed wing engine or a multi-annular multi-lobed wing engine, and the multi-annular multi-lobed wing engine comprises a combination of a plurality of the single annular multi-lobed wing engines arranged in a nested manner.

[0025] In a third aspect, the present invention provides a multi-convex wing-body fusion aircraft, which adopts the multi-convex wing described in the first aspect and integrates the multi-convex wing with the body;

[0026] The multi-convex wings are arranged on the top, both sides or the tail of the body;

[0027] The multi-convex-wing wing-body fusion aircraft includes any one or a combination of multi-convex-wing aircraft, multi-convex-wing airship, multi-convex-wing flying car, multi-convex-wing flying ship, multi-convex-wing flying train, multi-convex-wing Airbus, multi-convex-wing space plane, and multi-convex-wing pneumatic rocket.

[0028] In a fourth aspect, the present invention provides a multi-convex wing engine equipment, which adopts the multi-convex wing engine described in the second aspect, uses the multi-convex wing engine to provide propulsion, and the multi-convex wing engine is installed in a manner including being independently installed on the equipment, or being integrated with the equipment to form a multi-convex wing engine equipment;

[0029] The multi-convex wing engine equipment includes any one or a combination of multiple convex wing engine vehicles, multiple convex wing engine airborne equipment, multiple convex wing engine space shuttles, multiple convex wing engine spacecrafts and multiple convex wing engine rockets;

[0030] The multi-convex wing engine vehicle includes any one or a combination of a multi-convex wing engine car, a multi-convex wing engine boat, a multi-convex wing engine submarine, a multi-convex wing engine aircraft, a multi-convex wing engine airship and a multi-convex wing engine flying saucer;

[0031] The multi-lobed wing engine aircraft includes any one or a combination of several of a multi-lobed wing engine airplane, a multi-lobed wing engine airship, a multi-lobed wing engine flying car, a multi-lobed wing engine flying ship, a multi-lobed wing engine flying train and a multi-lobed wing engine Airbus.

[0032] In a fifth aspect, the present invention provides a multi-convex wing engine control method, which is applied to the multi-convex wing engine equipment described in the fourth aspect, and comprises the following steps:

[0033] When it is necessary to start the multi-convex wing engine to provide propulsion, the fluid generator is turned on, and the fluid generated by the fluid generator is sprayed toward the multi-convex wing substrate in the flow channel at a preset angle. The fluid sprayed into the flow channel flows at a high speed in the flow channel, and repeatedly flows through the upper convex surface of the multi-convex wing substrate, so that the multi-convex wing substrate is in a relative fluid, so that the aerodynamic environment of the multi-convex wing substrate is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air. The viscosity and inertia of the fluid work together to block the fluid pressure on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex surface, and a pressure difference is generated between the convex surface and the flat surface of the multi-convex wing substrate, forming multiple lift areas, thereby causing the multi-convex wing engine to generate a propulsion force directed toward the convex surface;

[0034] The propulsion force generated by the multi-convex wing engine is used for the multi-convex wing engine vehicle to rise, descend, hover, advance, retreat, translate, and turn maneuvers. The throttle or switch of the multi-convex wing engine vehicle is controlled to control the flow rate and flow velocity of the fluid sprayed to the multi-convex wing substrate, thereby providing propulsion forces of different sizes; the size of the fluid generator nozzle and the relative angle and position with the multi-convex wing substrate are adjusted according to the needs to make the multi-convex wing engine generate propulsion forces of different sizes; the position and posture of the drainage body of the multi-convex wing substrate are adjusted by the posture adjustment device to generate propulsion forces of different sizes; the size and number of the convex surface with curvature arc are adjusted to generate propulsion forces of different sizes;

[0035] The steering power is obtained by changing the orientation of the multi-convex wing engine relative to the multi-convex wing engine equipment or the vehicle, and by changing the fluid flow rate at different positions of the multi-convex wing base. The part with fast flow rate has large lift, and the part with slow flow rate has small lift, which causes the lift force of the multi-convex wing base to be unbalanced, thereby generating a steering torque; the steering power is obtained by changing the different thrusts of each engine in the multi-convex wing engine group; and the power for forward, backward, translation and steering movements is provided by using rudders or jet fluid.

[0036] The beneficial effect of the present invention is that the multi-convex wing and multi-convex wing engine give full play to the principle that the viscosity of the fluid and the inertia of the high-speed fluid block the fluid pressure on the upper part of the multi-convex wing and form a negative pressure area on the convex curved surface to generate lift, and the lift is greatly increased by generating multiple lift areas through the multi-convex wing and the multi-convex wing engine, aiming to solve the problems of low power load, low thrust-to-weight ratio and insufficient lift of the existing aircraft and engine. The multi-convex wing engine controls the high-speed fluid to circulate in the flow channel, and repeatedly flows through the upper convex curved surface of the multi-convex wing, further improving the utilization rate of the high-speed airflow, making the lift-to-drag ratio extremely large, the ceiling high, the noise low, and the operation convenient and safe, so that the maximum take-off / landing weight of the multi-convex wing engine aircraft can exceed several times that of the same power fixed-wing aircraft, and exceed more than ten times that of the same power rotary helicopter, and take-off and landing are easy. The multi-convex wing engine aircraft has the advantages of extremely large power load, fast speed, long range, high ceiling, low noise, and convenient operation, especially it can also take off and land vertically, can hover in the air, has no special requirements for the take-off and landing site, can take off and land on a flat ground, and does not need to build a dedicated large airport.

[0037] Because the multi-convex wing engine redefines the flow field in which it is located, the impact of the ambient airflow is reduced, and the self-control is greatly increased, so that multi-convex wing engine vehicles can fly stably under low-altitude complex airflow conditions, and the transition between vertical flight and level flight is smooth. It is suitable for both medium and high altitude flights and low and ultra-low altitude flights. It can achieve flight in the full range from low altitude to high altitude, and in the full range from high speed to low speed and even hovering. In addition, the closed circulation flow channel multi-convex wing engine can generate push and pull forces in the outer space environment and in the deep sea, so that it can achieve navigation, driving, and flying in the full range of sea, land, air, submarine, and space. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0039] Figure 1 The present invention provides a schematic diagram of an airfoil and airflow of a single convex wing and a multi-convex wing.

[0040] Figure 2 It is a schematic diagram of a multi-convex wing provided by the present invention.

[0041] Figure 3 It is a schematic cross-sectional view of a drainage body with multiple convex wings provided by the present invention.

[0042] Figure 4 It is a schematic cross-sectional view of a multi-convex wing and wing-body fusion aircraft provided by the present invention.

[0043] Figure 5 It is a schematic diagram of the cross section and airflow of an open unidirectional flow channel multi-convex wing engine provided by the present invention.

[0044] Figure 6 The present invention provides a schematic diagram of the cross section and airflow of a semi-enclosed unidirectional flow channel multi-convex wing engine.

[0045] Figure 7 The present invention provides an open disc-shaped circulating flow channel type multi-convex wing engine and an airflow schematic diagram.

[0046] Figure 8 The present invention provides a partial cross-sectional view and airflow schematic diagram of a closed disc-shaped circulating flow channel multi-convex wing engine.

[0047] Fig. 9 The present invention provides an open polygonal annular circulation channel type multi-convex wing engine and an airflow schematic diagram.

[0048] Fig.10 It is a partial cross-sectional view and airflow schematic diagram of a closed polygonal annular circulation flow channel type multi-convex wing engine provided by the present invention.

[0049] Fig.11 It is a schematic diagram of a multi-convex wing engine assembly provided by the present invention.

[0050] Fig.12 It is a schematic diagram of the cross section and airflow of an open unidirectional flow channel type multi-convex wing engine wing-body fusion aircraft in a vertical take-off and landing or hovering state provided by the present invention.

[0051] Fig.13 It is a schematic diagram of the cross section and airflow of an open unidirectional flow channel multi-convex wing engine wing-body fusion aircraft in level flight state provided by the present invention.

[0052] Fig.14 It is a schematic diagram of the cross section and airflow of a semi-closed unidirectional flow channel multi-convex wing engine wing-body fusion aircraft in a vertical take-off and landing or hovering state provided by the present invention.

[0053] Fig.15 It is a schematic diagram of the cross section and airflow of a semi-closed unidirectional flow channel multi-convex wing engine wing-body fusion aircraft in level flight state provided by the present invention. DETAILED DESCRIPTION

[0054] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0055] See also Figures 1 to 15 In a first aspect, the present invention provides a multi-convex wing, comprising a multi-convex wing base and a drainage body, wherein the multi-convex wing base is formed by connecting a plurality of single convex wings, and forms a plurality of continuous convex curved surfaces along the flow direction of the fluid on the negative pressure lift surface, and the drainage body is arranged between two convex curved surfaces of the multi-convex wing base;

[0056] The fluid is any one of gas and liquid or a combination of several;

[0057] When the fluid flows through the multi-convex wing substrate, the guide body guides the fluid flowing through the previous convex curved surface to the next convex curved surface, and guides the fluid to flow along the convex curved surface of the multi-convex wing substrate. The viscosity of the fluid and the inertia of the fluid work together to block the pressure of the fluid on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex curved surface, thereby generating corresponding multiple lift areas on the multi-convex wing substrate. By adjusting the attitude and position of the guide body relative to the multi-convex wing substrate, the size, direction and distribution of the multi-convex wing lift can be regulated, thereby controlling the rise and fall and flight attitude of the entire aircraft.

[0058] Furthermore, the drainage body includes any one or a combination of plate-shaped drainage bodies, cone-shaped drainage bodies, and streamlined drainage bodies;

[0059] The conical drainage body is a conical body with a sharp front and a blunt back, and the outer surface of the conical body includes any one of a straight surface and a curved surface or a combination of several of them;

[0060] The streamlined drainage body is a streamlined body with small ends and a large middle, and the outer surface of the streamlined body includes any one of a straight surface and a curved surface or a combination of several of them;

[0061] The multi-wing substrate and the guide body may be provided with any one of wing blades and vortex generators or a combination of several of them.

[0062] In a second aspect, the present invention provides a multi-convex wing engine, comprising the multi-convex wing described in the first aspect, and further comprising a flow channel and a fluid generator, wherein the multi-convex wing substrate is arranged on the inner cavity surface of the flow channel, and the fluid generator is arranged on one side of the fluid generator;

[0063] The flow channel includes any one of a unidirectional flow channel and a circulating flow channel, or a combination of several of them; the shape of the flow channel includes any one of an open cavity, a semi-closed cavity, and a closed cavity, or a combination of several of them; the fluid generated by the fluid generator is sprayed toward the multi-convex wing substrate in the flow channel, and the guide body guides the fluid flowing through the previous convex curved surface to the next convex curved surface, guiding the fluid to flow along the convex curved surface of the multi-convex wing substrate, and the viscosity of the fluid and the inertia of the fluid work together to block the pressure of the fluid on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex curved surface, thereby generating corresponding multiple lift areas on the multi-convex wing substrate.

[0064] Specifically, the closed circulation flow channel multi-lobed wing engine can generate push and pull forces in an outer space environment, and is particularly suitable for aerospace vehicles.

[0065] Furthermore, a plurality of raised curved surfaces are directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing substrate, thereby achieving fusion of the multi-convex wings and the flow channel, improving strength, and reducing volume and weight.

[0066] The drainage body can be directly integrated with the closed and semi-closed flow channels;

[0067] The fluid generator includes any one of an internal combustion engine and a steam engine or a combination of several of them;

[0068] The layout of the fluid generator includes any one of centralized, distributed, built-in, and external layouts, or a combination of several of them.

[0069] Specifically, arranging the high-speed fluid generator in the flow channel is called an internal layout form, and arranging the high-speed fluid generator outside the flow channel is called an external layout form; when the high-speed fluid generator is distributed between the two raised surfaces of the multi-convex wings, it can be arranged in combination with the drainage body, or it can be arranged alone instead of the drainage body.

[0070] Furthermore, the nozzle of the fluid generator includes any one or a combination of fixed and movable types; the nozzle of the movable fluid generator is an adjustable structure, and the size of the nozzle and the relative angle and position with the multi-convex wing can be adjusted;

[0071] The multi-convex wing substrate includes any one or a combination of fixed multi-convex wings and movable multi-convex wings. The size, shape and number of the convex curved surfaces of the movable multi-convex wings can be adjusted according to the fluid flow rate.

[0072] Furthermore, the flow channel includes any one or a combination of linear, spiral, annular, and disc shapes;

[0073] The ring shape includes any one or a combination of a circular ring, an elliptical ring, a polygonal ring, and an arc ring;

[0074] The disk shape includes any one or a combination of a circular disk shape, an elliptical disk shape, a polygonal disk shape, and an arc disk shape;

[0075] The annular multi-lobed wing engine comprises any one of a single annular multi-lobed wing engine or a multi-annular multi-lobed wing engine, and the multi-annular multi-lobed wing engine comprises a combination of a plurality of the single annular multi-lobed wing engines arranged in a nested manner.

[0076] In a third aspect, the present invention provides a multi-convex wing-body fusion aircraft, which adopts the multi-convex wing described in the first aspect and integrates the multi-convex wing with the body;

[0077] The multi-convex wings are arranged on the top, both sides or the tail of the body;

[0078] The multi-convex-wing wing-body fusion aircraft includes any one or a combination of multi-convex-wing aircraft, multi-convex-wing airship, multi-convex-wing flying car, multi-convex-wing flying ship, multi-convex-wing flying train, multi-convex-wing Airbus, multi-convex-wing space plane, and multi-convex-wing pneumatic rocket.

[0079] Specifically, the multi-convex wings are integrated with the fuselage to improve the strength of the multi-convex wings and reduce the size of the aircraft; the multi-convex wings arranged on the top of the fuselage provide lift and power for pitch maneuvers; multi-convex wings can be arranged on both sides of the fuselage to provide power for roll, yaw, steering and translation maneuvers; multi-convex wings can be arranged at the tail of the fuselage to provide air braking resistance.

[0080] In a fourth aspect, the present invention provides a multi-convex wing engine equipment, which adopts the multi-convex wing engine described in the second aspect, uses the multi-convex wing engine to provide propulsion, and the multi-convex wing engine is installed in a manner including being independently installed on the equipment, or being integrated with the equipment to form a multi-convex wing engine equipment;

[0081] The multi-convex wing engine equipment includes any one or a combination of multiple convex wing engine vehicles, multiple convex wing engine airborne equipment, multiple convex wing engine space shuttles, multiple convex wing engine spacecrafts and multiple convex wing engine rockets;

[0082] The multi-convex wing engine vehicle includes any one or a combination of a multi-convex wing engine car, a multi-convex wing engine boat, a multi-convex wing engine submarine, a multi-convex wing engine aircraft, a multi-convex wing engine airship and a multi-convex wing engine flying saucer;

[0083] The multi-lobed wing engine aircraft includes any one or a combination of several of a multi-lobed wing engine airplane, a multi-lobed wing engine airship, a multi-lobed wing engine flying car, a multi-lobed wing engine flying ship, a multi-lobed wing engine flying train and a multi-lobed wing engine Airbus.

[0084] In a fifth aspect, the present invention provides a multi-convex wing engine control method, which is applied to the multi-convex wing engine equipment described in the fourth aspect, and comprises the following steps:

[0085] When it is necessary to start the multi-convex wing engine to provide propulsion, the fluid generator is turned on, and the fluid generated by the fluid generator is sprayed toward the multi-convex wing substrate in the flow channel at a preset angle. The fluid sprayed into the flow channel flows at a high speed in the flow channel, and repeatedly flows through the upper convex surface of the multi-convex wing substrate, so that the multi-convex wing substrate is in a relative fluid, so that the aerodynamic environment of the multi-convex wing substrate is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air. The viscosity and inertia of the fluid work together to block the fluid pressure on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex surface, and a pressure difference is generated between the convex surface and the flat surface of the multi-convex wing substrate, forming multiple lift areas, thereby causing the multi-convex wing engine to generate a propulsion force directed toward the convex surface;

[0086] The propulsion force generated by the multi-convex wing engine is used for the multi-convex wing engine vehicle to rise, descend, hover, advance, retreat, translate, and turn maneuvers. The throttle or switch of the multi-convex wing engine vehicle is controlled to control the flow rate and flow velocity of the fluid sprayed to the multi-convex wing substrate, thereby providing propulsion forces of different sizes; the size of the fluid generator nozzle and the relative angle and position with the multi-convex wing substrate are adjusted according to the needs to make the multi-convex wing engine generate propulsion forces of different sizes; the position and posture of the drainage body of the multi-convex wing substrate are adjusted by the posture adjustment device to generate propulsion forces of different sizes; the size and number of the convex surface with curvature arc are adjusted to generate propulsion forces of different sizes;

[0087] The steering power is obtained by changing the orientation of the multi-convex wing engine relative to the multi-convex wing engine equipment or the vehicle, and by changing the fluid flow rate at different positions of the multi-convex wing base. The part with fast flow rate has large lift, and the part with slow flow rate has small lift, which causes the lift force of the multi-convex wing base to be unbalanced, thereby generating a steering torque; the steering power is obtained by changing the different thrusts of each engine in the multi-convex wing engine group; and the power for forward, backward, translation and steering movements is provided by using rudders or jet fluid.

[0088] Example 1: Multi-convex wing-body fusion aircraft example

[0089] To overcome the problem that the wings and fuselage of existing aircraft are not fully integrated, resulting in a large appearance and low safety, please refer to Figures 1 to 4 The present embodiment provides a multi-convex wing-body fusion aircraft, which is characterized in that the multi-convex wings are fused with the body into one, thereby improving the strength of the multi-convex wings and reducing the size of the aircraft.

[0090] The multi-convex wing comprises a multi-convex wing base and a drainage body, wherein the drainage body is arranged between two convex curved surfaces of the multi-convex wing base, and the posture and position of the drainage body relative to the multi-convex wing base are adjustable.

[0091] The guide body is arranged between the two convex curved surfaces of the multi-convex wing base, and is used to guide the high-speed fluid flowing through the previous convex curved surface to the next convex curved surface; the guide body is in the shape of a cone, and the conical guide body is a cone with a sharp front and a blunt back, and the outer surface of the cone is any one or a combination of a straight surface and a curved surface.

[0092] When the fluid flows through the multi-convex wing at high speed, the guide body guides the high-speed fluid flowing through the previous convex surface to the next convex surface, and guides the high-speed fluid to flow along the convex surface of the multi-convex wing base. The viscosity of the fluid and the inertia of the high-speed fluid work together to block the fluid pressure on the upper part of the multi-convex wing and form a negative pressure area on the convex surface, thereby generating multiple corresponding lift areas on the multi-convex wing, forming a lift greater than that of a single convex wing. By adjusting the attitude and position of the guide body relative to the multi-convex wing base, the size, direction and distribution of the lift of the multi-convex wing can be regulated, thereby controlling the rise and fall and flight attitude of the entire aircraft.

[0093] The multi-convex wings set on the top of the fuselage provide lift and power for pitch maneuvers.

[0094] Multiple convex wings can be set on both sides of the fuselage to provide power for rolling, yaw, steering and translation maneuvers.

[0095] Multiple convex wings can be set at the tail of the fuselage to provide air braking resistance.

[0096] Embodiment 2 Open circulation flow channel multi-convex wing engine embodiment

[0097] like Figure 7 As shown, this embodiment provides a multi-lobed wing engine, specifically an open circulating flow channel type multi-lobed wing engine, characterized in that it mainly comprises multi-lobed wings, a flow channel, a high-speed fluid generator, and a control device, the multi-lobed wings are arranged on the inner cavity surface of the flow channel, and the high-speed fluid generator is a device that can output high-speed fluid.

[0098] The flow channel is a circulating flow channel, and the flow channel is a disc-shaped open semi-cavity. A plurality of convex curved surfaces can be directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing substrate, so as to realize the fusion of the multi-convex wing and the flow channel, improve the strength, reduce the volume and weight, further simplify the design and manufacturing, and improve the efficiency, performance, reliability and safety. The high-speed fluid generator is a rotor or a fan, which is installed above the multi-convex wing and can generate and output a high-speed airflow along the circumferential direction. When the rotor or the fan is started, the circumferential high-speed airflow generated by it can circulate in the flow channel and repeatedly flow through the upper convex surface of the multi-convex wing, so that the multi-convex wing is in a relatively high-speed fluid, so that the aerodynamic environment of the multi-convex wing is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air, the viscosity of the fluid and the inertia of the high-speed fluid work together to block the fluid pressure on the upper part of the multi-convex wing and form a negative pressure area on the convex surface, and the pressure difference between the upper and lower surfaces generates corresponding multiple lift areas on the multi-convex wing, so that its maximum lift-to-drag ratio can be several times higher than the lift-to-drag ratio of the existing single-convex wing aircraft.

[0099] A plurality of disc-shaped multi-lobed wing engines can be combined together in a certain structural form to form a multi-disc-shaped multi-lobed wing engine group, which is convenient for controlling flight.

[0100] Example 3 Closed circulation flow channel multi-convex wing engine example

[0101] like Figure 8 As shown, this embodiment provides a multi-lobed wing engine, specifically a closed circulation flow channel type multi-lobed wing engine, characterized in that it mainly includes multi-lobed wings, a flow channel, a high-speed fluid generator, and a control device, the multi-lobed wings are arranged on the inner cavity surface of the flow channel, and the high-speed fluid generator is a device that can output high-speed fluid.

[0102] The flow channel is a circulating flow channel, and the flow channel is a disc-shaped closed cavity. A plurality of convex curved surfaces can be directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing substrate, and the guide body can be integrated with the flow channel to achieve the fusion of the multi-convex wing and the flow channel, thereby improving the strength, reducing the volume and weight, further simplifying the design and manufacturing, and improving the efficiency, performance, reliability and safety. The high-speed fluid generator is a rotor or a fan, which is installed above the multi-convex wing and can generate and output a high-speed airflow along the circumferential direction. When the rotor or the fan is started, the circumferential high-speed airflow generated by it can circulate in the flow channel and repeatedly flow through the upper convex surface of the multi-convex wing, so that the multi-convex wing is in a relatively high-speed fluid, so that the aerodynamic environment of the multi-convex wing is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air, and the viscosity of the fluid and the inertia of the high-speed fluid work together to block the fluid pressure on the upper part of the multi-convex wing and form a negative pressure area on the convex surface, and the pressure difference between the upper and lower surfaces generates corresponding multiple lift areas on the multi-convex wing, so that its maximum lift-to-drag ratio can be several times higher than the lift-to-drag ratio of the existing single-convex wing aircraft.

[0103] Because the closed circulation flow channel multi-convex wing engine completely encloses the high-speed fluid, it can be used in all space environments, even in outer space and deep sea environments without atmosphere, and can generate sufficient push and pull forces, thereby providing powerful and lasting propulsion for various aircraft and vehicles. It is particularly suitable for aerospace vehicles and is of revolutionary significance.

[0104] Example 4: Open Polygonal Annular Circulation Channel Type Multi-convex Wing Engine Example

[0105] like Figure 4 As shown, this embodiment provides a multi-convex wing engine, specifically an open polygonal annular circulating flow channel type multi-convex wing engine, characterized in that it mainly includes multi-convex wings, a flow channel, a high-speed fluid generator, and a control device, the multi-convex wings are arranged on the inner cavity surface of the flow channel, and the high-speed fluid generator is a device that can output high-speed fluid.

[0106] The flow channel is an annular open semi-cavity, and a plurality of convex curved surfaces can be directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing substrate, so as to realize the fusion of the multi-convex wing and the flow channel, improve the strength, reduce the volume and weight, further simplify the design and manufacturing, and improve the efficiency, performance, reliability and safety. The high-speed fluid generator is an axial flow fan built in the flow channel, which can generate and output a high-speed airflow along the circumferential direction. After starting the axial flow fan, the circumferential high-speed airflow generated by it can circulate in the flow channel and repeatedly flow through the upper convex surface of the multi-convex wing, so that the multi-convex wing is in a relatively high-speed airflow, so that the aerodynamic environment of the multi-convex wing is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air, and the viscosity of the fluid and the inertia of the high-speed fluid work together to block the fluid pressure on the upper part of the multi-convex wing and form a negative pressure area on the convex surface, and the pressure difference between the upper and lower surfaces generates corresponding multiple lift areas on the multi-convex wing, so that its maximum lift-to-drag ratio can be several times higher than the lift-to-drag ratio of the existing single-convex wing aircraft.

[0107] like Fig.11 As shown, multiple annular multi-convex wing engines of different sizes can be assembled together to form a multi-convex wing engine group. Multiple annular multi-convex wing engines can also be combined together in a certain structural form to form a multi-convex wing engine multi-ring group, which is convenient for controlling flight.

[0108] Example 5: Open Unidirectional Flow Channel Multi-convex Wing Engine Wing-body Blended Aircraft Example

[0109] See also Figure 12 to Figure 13 The present embodiment provides a multi-convex wing engine aircraft, specifically an open unidirectional flow channel multi-convex wing engine wing-body fusion aircraft, characterized in that the multi-convex wing engine and the body are integrated into one, thereby improving the strength of the multi-convex wing engine and reducing the size of the aircraft.

[0110] The multi-convex wing engine mainly comprises multi-convex wings, a flow channel, a high-speed fluid generator, and a control device. The multi-convex wings are arranged on the inner cavity surface of the flow channel, and the high-speed fluid generator is a device that can output high-speed fluid.

[0111] The flow channel is a one-way flow channel, and the flow channel is a linear open half cavity. A plurality of convex curved surfaces can be directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing substrate, so as to realize the fusion of the multi-convex wing and the flow channel, improve the strength, reduce the volume and weight, further simplify the design and manufacturing, and improve the efficiency, performance, reliability and safety. The high-speed fluid generator is a ducted fan, which is installed in front of the multi-convex wing and between its two convex curved surfaces, and can generate and output a high-speed airflow along the one-way flow channel. When the ducted fan is started, the high-speed airflow generated by it flows along the flow channel and repeatedly flows through the upper convex surface of the multi-convex wing, so that the multi-convex wing is in a relatively high-speed fluid, so that the aerodynamic environment of the multi-convex wing is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air, the viscosity of the fluid and the inertia of the high-speed fluid work together to block the fluid pressure on the upper part of the multi-convex wing and form a negative pressure area on the convex curved surface, and the pressure difference between the upper and lower surfaces generates corresponding multiple lift areas on the multi-convex wing, so that its maximum lift-to-drag ratio can be higher than the lift-to-drag ratio of the existing single-convex wing aircraft.

[0112] The multi-convex wing engines mounted on top of the fuselage provide lift and power for pitch maneuvers;

[0113] Multiple convex wing engines can be installed on both sides of the fuselage to provide power for rolling, yaw, turning and translation maneuvers;

[0114] Multiple convex wing engines can be installed at the tail of the fuselage to provide air braking resistance.

[0115] A level flight / hover conversion device is provided at the tail of the aircraft to guide the high-speed airflow flowing out of the multi-convex wing engine. When the high-speed airflow is guided to flow downward, the aircraft can achieve vertical take-off and landing or hover; when the high-speed airflow is guided to flow rearward and downward, the aircraft can achieve transition flight; when the high-speed airflow is guided to flow backward, the aircraft can achieve level flight.

[0116] Example 6: Semi-enclosed unidirectional flow channel multi-convex wing engine wing-body fusion aircraft example

[0117] See also Figure 14 to Figure 15 The present embodiment provides a multi-convex wing engine aircraft, specifically a semi-closed unidirectional flow channel multi-convex wing engine wing-body fusion aircraft, characterized in that the multi-convex wing engine and the body are integrated into one, thereby improving the strength of the multi-convex wing engine and reducing the size of the aircraft.

[0118] The multi-convex wing engine mainly comprises multi-convex wings, a flow channel, a high-speed fluid generator, and a control device. The multi-convex wings are arranged on the inner cavity surface of the flow channel, and the high-speed fluid generator is a device that can output high-speed fluid.

[0119] The flow channel is a one-way flow channel, and the flow channel is a tubular semi-enclosed cavity with only two ends open. A plurality of raised curved surfaces can be directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing substrate, and the guide body can be integrated with the flow channel to achieve the fusion of the multi-convex wings and the flow channel, thereby improving the strength, reducing the volume and weight, further simplifying the design and manufacturing, and improving the efficiency, performance, reliability and safety. The high-speed fluid generator is a ducted fan, which is installed in front of the multi-convex wings or between its two raised curved surfaces, and can generate and output high-speed airflow along the one-way flow channel. When the ducted fan is started, the high-speed airflow it generates flows along the flow channel and repeatedly flows through the upper convex surface of the multi-convex wing, so that the multi-convex wing is in a relatively high-speed fluid. The aerodynamic environment of the multi-convex wing is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air. The viscosity of the fluid and the inertia of the high-speed fluid work together to block the fluid pressure on the upper part of the multi-convex wing and form a negative pressure area on the convex surface. The pressure difference between the upper and lower surfaces generates multiple corresponding lift areas on the multi-convex wing, so that its maximum lift-to-drag ratio can be higher than the lift-to-drag ratio of existing single-convex wing aircraft.

[0120] The multi-convex wing engines mounted on top of the fuselage provide lift and power for pitch maneuvers;

[0121] Multiple convex wing engines can be installed on both sides of the fuselage to provide power for rolling, yaw, turning and translation maneuvers;

[0122] Multiple convex wing engines can be installed at the tail of the fuselage to provide air braking resistance.

[0123] A level flight / hover conversion device is provided at the tail of the aircraft to guide the high-speed airflow flowing out of the multi-convex wing engine. When the high-speed airflow is guided to flow downward, the aircraft can achieve vertical take-off and landing or hover; when the high-speed airflow is guided to flow rearward and downward, the aircraft can achieve transition flight; when the high-speed airflow is guided to flow backward, the aircraft can achieve level flight.

[0124] What is disclosed above is only a preferred embodiment of a multi-lobed wing and a multi-lobed wing engine and a control method thereof of the present invention. Of course, this cannot be used to limit the scope of rights of the present invention. Ordinary technicians in this field can understand that all or part of the processes of the above embodiments and equivalent changes made according to the claims of the present invention still fall within the scope of the invention.

Claims

1. A multi-convex wing, characterized in that: It comprises a multi-convex wing base and a drainage body, wherein the multi-convex wing base is formed by connecting a plurality of single convex wings, forming a plurality of continuous convex curved surfaces along the flow direction of the fluid on the negative pressure lift surface, and the drainage body is arranged between two convex curved surfaces of the multi-convex wing base; The fluid is any one of gas and liquid or a combination of several; When the fluid flows through the multi-convex wing substrate, the guide body guides the fluid flowing through the previous convex curved surface to the next convex curved surface, and guides the fluid to flow along the convex curved surface of the multi-convex wing substrate. The viscosity of the fluid and the inertia of the fluid work together to block the pressure of the fluid on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex curved surface, thereby generating corresponding multiple lift areas on the multi-convex wing substrate. By adjusting the attitude and position of the guide body relative to the multi-convex wing substrate, the size, direction and distribution of the multi-convex wing lift can be regulated, thereby controlling the rise and fall and flight attitude of the entire aircraft.

2. The multi-convex wing according to claim 1, characterized in that: The drainage body includes any one or a combination of plate-shaped drainage bodies, cone-shaped drainage bodies, and streamlined drainage bodies; The conical drainage body is a conical body with a sharp front and a blunt back, and the outer surface of the conical body includes any one of a straight surface and a curved surface or a combination of several of them; The streamlined drainage body is a streamlined body with small ends and a large middle, and the outer surface of the streamlined body includes any one of a straight surface and a curved surface or a combination of several of them; The multi-wing substrate and the guide body may be provided with any one of wing blades and vortex generators or a combination of several of them.

3. A multi-convex wing engine, comprising the multi-convex wing according to any one of claims 1 to 2, characterized in that: It also includes a flow channel and a fluid generator, wherein the multi-convex wing substrate is arranged on the inner cavity surface of the flow channel, and the fluid generator is a device for outputting high-speed fluid; The flow channel includes any one of a unidirectional flow channel and a circulating flow channel or a combination of several thereof; the shape of the flow channel includes any one of an open cavity, a semi-closed cavity, and a closed cavity or a combination of several thereof; The fluid generated by the fluid generator is sprayed toward the multi-convex wing substrate in the flow channel, and the guide body guides the fluid flowing through the previous convex curved surface to the next convex curved surface, guiding the fluid to flow along the convex curved surface of the multi-convex wing substrate. The viscosity of the fluid and the inertia of the fluid work together to block the pressure of the fluid on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex curved surface, thereby generating corresponding multiple lift areas on the multi-convex wing substrate.

4. The multi-lobed wing engine according to claim 3, characterized in that: A plurality of convex curved surfaces are directly arranged on the inner cavity surface of the flow channel to replace the multi-convex wing base; The drainage body can be directly integrated with the closed and semi-closed flow channels; The fluid generator includes any one of an internal combustion engine and a steam engine or a combination of several of them; The layout of the fluid generator includes any one of centralized, distributed, built-in, and external layouts, or a combination of several of them.

5. The multi-lobed wing engine according to claim 3, characterized in that: The nozzle of the fluid generator includes any one or a combination of fixed and movable types; the nozzle of the movable fluid generator is an adjustable structure, and the size of the nozzle and the relative angle and position with the multi-convex wing can be adjusted; The multi-convex wing substrate includes any one or a combination of fixed multi-convex wings and movable multi-convex wings. The size, shape and number of the convex curved surfaces of the movable multi-convex wings can be adjusted according to the fluid flow rate.

6. The multi-lobed wing engine according to claim 3, characterized in that: The flow channel includes any one or a combination of linear, spiral, annular, and disc shapes; The ring shape includes any one or a combination of a circular ring, an elliptical ring, a polygonal ring, and an arc ring; The disk shape includes any one or a combination of a circular disk shape, an elliptical disk shape, a polygonal disk shape, and an arc disk shape; The annular multi-lobed wing engine comprises any one of a single annular multi-lobed wing engine or a multi-annular multi-lobed wing engine, and the multi-annular multi-lobed wing engine comprises a combination of a plurality of the single annular multi-lobed wing engines arranged in a nested manner.

7. A multi-convex wing-body fusion aircraft, using the multi-convex wing according to claim 1, characterized in that: The multi-convex wings are integrated with the body; The multi-convex wings are arranged on the top, both sides or the tail of the body; The multi-convex-wing wing-body fusion aircraft includes any one or a combination of multi-convex-wing aircraft, multi-convex-wing airship, multi-convex-wing flying car, multi-convex-wing flying ship, multi-convex-wing flying train, multi-convex-wing Airbus, multi-convex-wing space plane, and multi-convex-wing pneumatic rocket.

8. A multi-lobed wing engine equipment, using the multi-lobed wing engine according to claim 3, characterized in that: The multi-convex wing engine is used to provide propulsion, and the multi-convex wing engine is installed in a manner including being independently installed on equipment, or being integrated with equipment to form a multi-convex wing engine equipment; The multi-convex wing engine equipment includes any one or a combination of multiple convex wing engine vehicles, multiple convex wing engine airborne equipment, multiple convex wing engine space shuttles, multiple convex wing engine spacecrafts and multiple convex wing engine rockets; The multi-convex wing engine vehicle includes any one or a combination of a multi-convex wing engine car, a multi-convex wing engine boat, a multi-convex wing engine submarine, a multi-convex wing engine aircraft, a multi-convex wing engine airship and a multi-convex wing engine flying saucer; The multi-lobed wing engine aircraft includes any one or a combination of several of a multi-lobed wing engine airplane, a multi-lobed wing engine airship, a multi-lobed wing engine flying car, a multi-lobed wing engine flying ship, a multi-lobed wing engine flying train and a multi-lobed wing engine Airbus.

9. A multi-convex wing engine control method, applied to the multi-convex wing engine according to claim 3 or the multi-convex wing engine equipment according to claim 8, characterized in that: The following steps are involved: When it is necessary to start the multi-convex wing engine to provide propulsion, the fluid generator is turned on, and the fluid generated by the fluid generator is sprayed toward the multi-convex wing substrate in the flow channel at a preset angle. The fluid sprayed into the flow channel flows at a high speed in the flow channel, and repeatedly flows through the upper convex surface of the multi-convex wing substrate, so that the multi-convex wing substrate is in a relative fluid, so that the aerodynamic environment of the multi-convex wing substrate is similar to that of the wing of a fixed-wing aircraft flying at high speed in the air. The viscosity and inertia of the fluid work together to block the fluid pressure on the upper part of the multi-convex wing substrate and form a negative pressure area on the convex surface, and a pressure difference is generated between the convex surface and the flat surface of the multi-convex wing substrate, forming multiple lift areas, thereby causing the multi-convex wing engine to generate a propulsion force directed toward the convex surface; The propulsion force generated by the multi-convex wing engine is used for the multi-convex wing engine vehicle to ascend, descend, hover, advance, retreat, translate, and turn maneuvers. The throttle or switch of the multi-convex wing engine vehicle is controlled to control the flow rate and flow velocity of the fluid sprayed to the multi-convex wing matrix, thereby providing propulsion forces of different sizes. According to the demand, the size of the flow generator nozzle and the relative angle and position with the multi-convex wing base are adjusted to make the multi-convex wing engine generate different thrusts; the position and posture of the drainage body of the multi-convex wing base are adjusted by the posture adjustment device to generate different thrusts; the size and number of the convex surface with curvature arc are adjusted to generate different thrusts; The steering power is obtained by changing the orientation of the multi-convex wing engine relative to the multi-convex wing engine equipment or the vehicle, and by changing the fluid flow rate at different positions of the multi-convex wing base. The part with fast flow rate has large lift, and the part with slow flow rate has small lift, which causes the lift force of the multi-convex wing base to be unbalanced, thereby generating a steering torque; the steering power is obtained by changing the different thrusts of each engine in the multi-convex wing engine group; and the power for forward, backward, translation and steering movements is provided by using rudders or jet fluid.

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