CN108945481B

CN108945481B - Method for enhancing lift force and realizing vertical take-off and landing by installing driving mechanism below plate wing

Info

Publication number: CN108945481B
Application number: CN201811080568.3A
Authority: CN
Inventors: 杨卫华
Original assignee: Kunming Qiaoyi Technology Co ltd
Current assignee: Kunming Qiaoyi Technology Co ltd
Priority date: 2018-09-17
Filing date: 2018-09-17
Publication date: 2021-05-11
Anticipated expiration: 2038-09-17
Also published as: CN108945481A

Abstract

The invention discloses a method for enhancing lift force and realizing vertical take-off and landing by installing a driving mechanism below a plate wing, and belongs to the technical field of aviation. For the aircraft with large-area plate-shaped wings, a driving device is arranged at the front lower part of the front edge of each plate wing, high-speed airflow is blown to the lower parts of the plate wings along the chord direction through the driving device, and the driving device sucks air from the upper parts of the plate wings and exhausts the air to the lower parts of the plate wings, so that a negative pressure area is formed above the plate wings, a positive pressure area is formed below the plate wings, and vertical take-off and landing are realized by utilizing differential pressure lift force formed by the negative pressure area and the positive pressure area; meanwhile, the plate wings can be designed into a combined type to further improve the vertical take-off and landing capacity and the flying efficiency, the plate wings are folded into a fixed wing shape with small resistance in horizontal flight, the left side, the right side and the rear part of the combined type plate wings are downward and forcibly reflect the airflow direction from the horizontal direction to the vertical direction, the lift-increasing and drag-reducing effects are obviously enhanced, and different requirements of horizontal flight and vertical take-off and landing are well met.

Description

Method for enhancing lift force and realizing vertical take-off and landing by installing driving mechanism below plate wing

Technical Field

The invention relates to a method for realizing vertical take-off, landing and flying of an aircraft, in particular to a method for enhancing lift force and realizing vertical take-off and landing by installing a driving mechanism below a plate wing, and belongs to the technical field of aviation.

Background

Manned aircraft can be divided into two broad categories, fixed wing, which is common in horizontal take-off and landing aircraft (e.g., jet airliners), and rotating wing, which is common in vertical take-off and landing aircraft (e.g., helicopters). In the prior art, the fixed wing aircraft can fly at high speed, is simple and convenient to operate, and needs to take off and land by means of a runway. The rotary wing aircraft can take off and land vertically without depending on a runway, has strong adaptability, but has the disadvantages of disordered mechanism, complex control, slow flight speed and low fuel efficiency.

At present, the vertical take-off and landing aircraft has inherent defects which cannot be overcome. Firstly, the efficiency is low, the thrust-weight ratios of the existing vertical take-off and landing aircrafts are all smaller than 1, the flight efficiency is low, and the difference is very obvious compared with the thrust-weight ratio generally larger than 5 of a fixed wing aircraft; secondly, the theoretical speed of the rotary wing aircraft cannot exceed 420 km/h and the flight speed is limited due to the fact that the absolute speed of the wing tip is necessarily smaller than the sonic speed; thirdly, the flapping of the rotor blades generates mechanical vibration, the abrasion of the hinge is increased, and the reliability is low; fourthly, the rotary wing aircraft can roll over due to uneven lifting force of the rotors on the two sides, and the rolling stability is poor; fifthly, the rotor wing of the helicopter not only provides maneuverability of flight, but also causes complexity of flight control, and the control is complex, so that the control load is far greater than that of a fixed-wing aircraft, and the probability of human error is increased; sixthly, the diameter and the rotating speed of the rotor wing are limited by the fact that the speed of the wing tip cannot exceed the sonic speed, the diameter of the rotor wing is generally dozens of meters at the maximum, and the size of the aircraft is limited and cannot be enlarged; seventhly, the helicopter has poor coordination in the flight mechanism, is full of congenital contradiction and has disordered flight mechanism; eighthly, many novel combined vertical take-off and landing aircrafts try to adopt fixed wings, but face the contradiction that the effect of small-area fixed wings is limited, and large-area fixed wings can shield the downwash airflow during vertical take-off and landing.

In summary, the above-mentioned drawbacks of the vertical take-off and landing aircraft result from the contradiction that the wings must satisfy both the vertical take-off and landing and the horizontal flight modes. The method for realizing vertical take-off and landing by using the wing surface chord direction air blowing method can be well compatible with two flight modes of vertical take-off and landing and horizontal flight, is a new development direction of the vertical take-off and landing aircraft, and the method for installing the driving mechanism below the plate wing to enhance the lift force and realize vertical take-off and landing can ensure that the plate wing aircraft runs more efficiently, flies more safely, has a more reasonable structure and has more stable performance.

Disclosure of Invention

The invention aims to solve the technical problems that the existing vertical take-off and landing aircraft is low in flight efficiency, the thrust-weight ratio is generally less than 1, the operation is complex, the safety is poor, the conversion between a horizontal flight mode and a vertical take-off and landing mode is not smooth and natural, the wing resistance of the existing plate-wing aircraft is overlarge, the vertical lift force is insufficient, the chord direction blowing airflow is dispersed, and the like.

In order to solve the technical problems, the invention provides a method for installing a driving mechanism below a plate wing to enhance lift force and realize vertical take-off and landing, for an aircraft adopting a large-area plate wing as a wing, a driving device is arranged at the lower part in front of the front edge of the plate wing, high-speed airflow is blown to the lower part of the plate wing along the chord direction through the driving device, a negative pressure area is formed above the plate wing by an air inlet of the driving device, a positive pressure area is formed below the plate wing by an air nozzle, and the flight efficiency and the thrust-weight ratio of the plate wing machine can be greatly improved by utilizing the differential pressure lift force formed by the negative pressure area above the plate wing and the positive pressure area below the plate; meanwhile, the plate wing is designed into a combined type and is divided into four parts, the front part is a fixed main wing, the left side and the right side are wingtip winglets capable of being turned downwards and flattened, the rear part is a lower counter wing capable of being turned downwards and flattened, and the tail part is a fixed rectifying wing; when the combined plate wing vertically takes off and lands, the left side, the right side and the rear part of the combined plate wing are downward-reversed to change the airflow direction of the slipstream of the propeller from the horizontal direction to the vertical direction, so that the effects of increasing lift and reducing drag are achieved, and the lift force and the flight control capability of the vertical take off and land are further improved; when the aircraft flies horizontally, the plate wings are folded into a shape of a fixed wing with small resistance, and besides the differential pressure lift force, the wing-shaped lift force is further generated; in the process of interconversion flight mode between VTOL and horizontal flight, control mechanism's the mode transition of controlling is natural, and it is smooth-going to control the parameter variation, controls the effect and does not produce the sudden change, has compromise the different requirements of horizontal flight and VTOL, has effectively solved the problem of the mode conversion difficulty of ubiquitous flight mode among the current mode conversion VTOL airborne vehicle, greatly reduced VTOL airborne vehicle control the degree of difficulty.

The plate wing is combined and divided into four parts, the front part is a fixed main wing, the left side and the right side are wingtip winglets capable of being turned downwards and leveled, the rear part is a lower counter wing capable of being turned downwards and leveled, and the tail part is a fixed rectifying wing; wingtip winglets on the left side and the right side are in a pull-down type; the rear lower reverse wing is any one of a pull-down type, a bisection type, a folding type, a sliding type and a surrounding type (which can be selected according to actual requirements); the pull-down type lower anti-wing is characterized in that a rotating shaft is additionally arranged between the lower anti-wing and the main wing to manufacture a flexible or rigid thin-shell structure for pulling the lower anti-wing to be downward-inverse and loosening the upper anti-wing to be upward-inverse, the lower anti-wing is pulled to be downward-inverse or upward-inverse by a pulling rope or a pulling mechanism, the pulling rope is directly used for pulling the lower anti-wing to be downward-inverse when downward inverse is needed, and the pulling rope is released to enable the lower anti-wing to be upward-inverse under the pushing of the slipstream pressure of the propeller when; the bisection type lower reverse wing divides the main wing into two parts along the horizontal direction and is divided into an upper board wing and a lower board wing, the upper board wing is a movable wing, the lower board wing is a fixed wing, the upper board wing is connected with the machine body through a rocker, the operating mechanism drives the rocker to enable the upper board wing to swing back and forth around the lower board wing, during horizontal flight, the upper board wing swings forwards and is combined with the lower board wing into a complete upper-convex lower-flat-wing-type board wing to reduce resistance to achieve high-speed flight, during vertical take-off and landing, the upper board wing is lifted to swing greatly towards the rear lower part, and the upper board wing and the lower board wing are staggered into the lower reverse board wing connected end to end; the folding lower reverse wing is made of flexible cloth, and the lower reverse wing is collected into the plate wing or unfolded through a folding mechanism; the sliding lower counter wing is made of rigid materials, the lower counter wing is divided into a plurality of sections which can be mutually overlapped, and the plurality of sections of lower counter wings are folded into a section which is collected in the main wing or unfolded through a sliding mechanism; the enclosure type lower counter wing utilizes the left vertical surface and the right vertical surface of the flaky fuselage to store the lower counter wing, the rotating shaft of the lower counter wing is positioned in the plane of the flaky fuselage, the left lower counter wing and the right lower counter wing are folded in the plane of the flaky fuselage in a backward unfolding mode during horizontal flight to reduce resistance, the left lower counter wing and the right lower counter wing are unfolded forward to be perpendicular to the plane of the flaky fuselage during vertical take-off and landing to enclose horizontal airflow downwards to play a role in increasing lift, and the enclosure type lower counter wing also plays a role in regulating and controlling a vertical tail wing.

The plate wing is of a thin-shell structure and is made of a high-strength composite material or a high-strength light metal frame and nylon cloth, for example, the plate wing is made of a composite material such as carbon fiber cloth sandwiched honeycomb or an aluminum alloy or titanium alloy frame and nylon cloth; the contour line of the slat wing is an upper surface curve of a low-speed wing profile, when the slat wing horizontally flies, the upper surface of the slat wing can also wash down the air flow through the wing profile to generate lift force, and meanwhile, the lower surface of the slat wing can also wash down the slipstream of the propeller to generate lift force forcibly, so that the lift force generated by the slat wing is larger than that generated by a common fixed wing; the thrust-weight ratio of vertical take-off and landing is more than 1, and the thrust-weight ratio of horizontal flight is more than 5.

The wingtip of the plate wing is provided with wingtip winglets capable of being reversed and flattened, the wingtip winglets are thin plate winglets or wingtip winglets which are outwards convex and flat, the front edges of the wingtip winglets are close to the driving device, the lower edges of the wingtip winglets exceed the lower edges of the driving device, the rear edges of the wingtip winglets are close to or exceed the rear edges of the plate wing, and the width of the rear edge contour lines of the wingtip winglets is gradually reduced to zero according to the streamline shape; when the wingtip winglet is of a wing shape which is convex outwards and flat inwards, the longitudinal hinge is arranged between the wingtip winglet and the plate wing to be connected, so that the downward wingtip winglet can be automatically reversely flattened upwards under the pushing of wing profile lifting force generated by horizontal flight airflow and is changed into a wing shape which is convex upwards and flat downwards, and the flattened wingtip winglet can increase the lifting force of the plate wing aircraft, increase the light receiving area of the wing and reduce the wing load to the maximum extent; in both horizontal flight state and vertical take-off and landing state, when the lower dihedral angles of wingtip winglets on the left side and the right side are different, a yaw moment is generated on the plate wing, and the yaw control can be realized by adjusting the lower dihedral angles of the wingtip winglets on the left side and the right side; when the dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, the slat type wing aircraft yaws leftwards; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; the larger the declination deviation of wingtip winglets on the left side and the right side is, the larger the yawing moment of the plate-wing aircraft is.

The front lower part of the front edge of the plate wing is provided with a driving device, the front lower part of the driving device is provided with an aileron, the aileron is provided with an upper convex wing shape and a lower flat wing shape and is connected with the fuselage through a transverse hinge at the rear part of the aileron, and the aileron rotates around the transverse hinge to change an attack angle; during horizontal flight, the wing profile of the aileron can generate wing profile lift force, and the lift force and the resistance of the slat wing are changed by changing the attack angle of the aileron, so that the pitching of the slat wing aircraft is controlled; when the ailerons turn to the positive attack angle, the ailerons can generate impact lift force, the slat plane tilts upwards, and the larger the positive attack angle is, the larger the elevation angle of the slat plane is; when the aileron turns to the negative attack angle, the aileron can produce impact pressure, and the board wing machine dives, and the negative attack angle is bigger, and the board wing machine dive angle is bigger. In addition, the airflow generated when the air inlet of the driving device inhales flows through the upper wing surface of the aileron, the airflow speed of the lower wing surface of the aileron is the same as the flying speed of the aircraft, and negative pressure lift can still be formed on the aileron even if the airflow speed of the lower wing surface of the aileron is zero when the aircraft hovers.

The driving device is positioned in a box body formed by enclosing the plate wings, the ailerons and the wingtip winglets to form a ducted fan; the driving device is any one of a propeller, a ducted propeller, a turbojet engine, a turbofan engine and a turboprop engine (which can be selected according to actual needs), and the flow speed of airflow blown onto the wings is in direct proportion to the power of the driving device.

The flight control of the plate-wing aircraft is realized by adjusting the dihedral angle of the lower inverse wing, the dihedral angle of the winglet, the attack angle of the aileron and the power of the driving device through the control mechanism; during horizontal flight, the pitching of the slat type wing aircraft is realized by adjusting the attack angle of the ailerons or the lower dihedral angle of the rear lower inverse wing, the yawing of the slat type wing aircraft is realized by differentially adjusting the lower dihedral angles of the wingtip winglets on the left side and the right side, the lower dihedral angle of the wingtip winglets on the left side is larger than the lower dihedral angle of the wingtip winglets on the right side when yawing is carried out to the left side, and the lower dihedral angle of the wingtip winglets on the right side is larger than the lower dihedral angle of the wingtip winglets; when the slat type wing aircraft vertically rises and falls, the up-and-down motion of the slat type wing aircraft is regulated and controlled through the power, the forward motion of the slat type wing aircraft is realized by reducing the lower dihedral angle through the lower anti-wing, the backward motion of the slat type wing aircraft is realized by increasing the lower dihedral angle to 100 DEG and 120 DEG (about 110 DEG) through the lower anti-wing, the yaw of the slat type wing aircraft is realized by differentially regulating the lower dihedral angles of wingtip winglets on the left side and the right side, the lower dihedral angle of the wingtip winglets on the left side is larger than the lower dihedral angle of the wingtip wingtips on the right side when the wingtip wingtips on the right side are deviated, and; because the gravity center of the plate-wing aircraft is lower, the pitching moment and the rolling moment in the vertical take-off and landing flight are automatically balanced and compensated through the deflection angle of the gravity center of the plate-wing aircraft, and special mechanism control is not needed.

The width of the plate wing is 1.1-1.5 times (can be determined according to actual conditions) that all the propellers are arranged side by side according to the diameter D, and is slightly larger than the width of all the propellers arranged side by side according to the diameter D; the length of the fixed main wing is greater than or equal to 3 times of propeller diameter D, and the length of the lower counter wing is greater than or equal to 2 times of propeller diameter D.

The take-off, landing and forced landing of the plate-wing aircraft are all vertical modes, and a suspension type cylinder spring undercarriage can be directly adopted.

The number of the plate wings can be increased, the number of the plate wings can be one overhead type wing or a plurality of bilaterally symmetrical transverse type wings, and for a medium-sized or large-sized manned aircraft, the number of the plate wings can be increased in a mode that the left and right transverse type wings of the transverse type wings are connected in series in pairs.

In the invention, the body of the plate-wing aircraft is a flaky body, a larger box body is defined by the plate wings, the ailerons and the wingtip winglets, the stability can be increased during horizontal flight, the plate wings which are turned downwards during vertical take-off and landing and the box body form an airflow duct to guide the jet airflow of the driving device downwards, the ground effect is obvious, the elasticity of air can be increased during take-off and landing, and the take-off and landing impact can be alleviated; when the forced landing is in failure, the box body surrounded by the plate wings is like a parachute, so that the plate wing machine can slowly land; in addition, the vertical taking-off and landing mode of front air intake and rear air exhaust straightens the motion path of the air flow, compared with the taking-off and landing mode of vertical downward air exhaust (such as a helicopter), the motion path of the air flow is more scientific and reasonable, and the shielding of ground sand blown dust on sight and the damage to a machine are avoided.

The bottom-drive plate-wing aircraft can completely have two flight working conditions of vertical take-off and landing and high-speed flight, and has the advantages of natural mode conversion, high flight efficiency, low wing load of the wings, safety, stability, simple structure, simplicity and convenience in operation and control, low cost, easiness in popularization and the like.

Drawings

FIG. 1 is a schematic side view of the bottom-drive slat-wing aircraft in a horizontal flight state.

FIG. 2 is a schematic top view of the bottom-drive slat-wing aircraft in a horizontal flight state.

FIG. 3 is a rear view of the bottom-drive slat-wing aircraft in a horizontal flight state.

FIG. 4 is a schematic side view of the bottom-drive slat-type aircraft in a vertical take-off and landing state.

FIG. 5 is a schematic top view of the bottom-drive slat-type aircraft in a vertical take-off and landing state.

FIG. 6 is a schematic rear view of the bottom-drive slat-type aircraft in a vertical take-off and landing state.

FIG. 7 is a schematic view of a thin-shell structure plate wing of the bottom-drive plate wing machine of the present invention.

Fig. 8 is a schematic diagram of the relationship between the diameter D of the bottom-drive plate-wing aircraft propeller and the lengths of the fixed main wing and the lower counter wing.

FIG. 9 is a schematic view of the principle of controlling the horizontal flying upward movement of the bottom-drive slat-wing aircraft according to the present invention.

FIG. 10 is a schematic view of the principle of the control of the horizontal flying downward motion of the bottom-drive slat-wing aircraft according to the present invention.

FIG. 11 is a schematic diagram of the control principle of the horizontal flying right movement of the bottom-drive slat-type aircraft.

FIG. 12 is a schematic view of the principle of controlling the horizontal flying leftward movement of the bottom-drive slat-type aircraft according to the present invention.

FIG. 13 is a schematic view of the control principle of the vertical take-off and landing forward motion of the bottom-drive plate-wing aircraft.

FIG. 14 is a schematic view of the control principle of the vertical take-off, landing and backward movement of the bottom-drive plate-wing aircraft.

FIG. 15 is a schematic view of the control principle of vertical take-off and landing and right movement of the bottom-drive plate-wing aircraft.

FIG. 16 is a schematic view of the control principle of the vertical take-off and landing leftward movement of the bottom-drive plate-wing aircraft according to the present invention.

Fig. 17 is a schematic view of the landing principle of the suspended cylinder spring landing gear of the bottom-drive plate-wing aircraft of the invention.

Fig. 18 is a schematic view of the takeoff principle of the suspended cylinder spring landing gear of the bottom-drive plate-wing aircraft.

In the figure: 1-aileron, 2-aileron hinge, 3-drive device, 4-slat wing, 5-winglet, 6-winglet lower stay cord, 7-winglet lower stay cord buckle, 8-lower fly hinge, 9-lower fly, 10-lower fly pull cord, 11-lower fly stay cord buckle, 12-rectifying empennage, 13-fuselage, 14-left and right winglet differential lower control lever, 15-cabin, 16-undercarriage, 17-winglet hinge, 18-NACA4412 wing profile horizontal tension wing profile parameter.

Detailed Description

The following detailed description of the embodiments of the present invention will be described in detail with reference to the accompanying drawings, wherein the technology and products not shown in the embodiments are all conventional products available in the art or commercially.

Example 1: as shown in fig. 1-18, in the method for enhancing lift force and realizing vertical take-off and landing by installing a driving mechanism below a plate wing, an aircraft adopting the plate wing as a wing is provided with a driving device at the lower part in front of the front edge of the plate wing, high-speed airflow is blown to the lower part of the plate wing along the chord direction by the driving device, a negative pressure region is formed above the plate wing by an air inlet of the driving device, a positive pressure region is formed below the plate wing by an air nozzle, and differential pressure lift force is formed between the negative pressure region above the plate wing and the positive pressure region below the plate wing; meanwhile, the plate wings are combined, and when the plate wings vertically take off and land, the left sides, the right sides and the rear part of the combined plate wings are downward-reversed, so that the airflow direction of the slipstream of the propeller is changed from the horizontal direction to the vertical direction, the effects of increasing lift and reducing drag are achieved, and the lift force and the flight control capability of vertical take off and land are further improved; when the aircraft flies horizontally, the plate wings are folded into a shape of fixed wings with small resistance, and wing-shaped lift force is generated besides the differential pressure lift force; in the process of interconversion flight mode between VTOL and horizontal flight, control mechanism's the mode transition of controlling is natural, and it is smooth-going to control the parameter variation, controls the effect and does not produce the sudden change, has compromise the different requirements of horizontal flight and VTOL, has effectively solved the problem of the mode conversion difficulty of ubiquitous flight mode among the current mode conversion VTOL airborne vehicle, greatly reduced VTOL airborne vehicle control the degree of difficulty.

The plate wings are combined, the front part is a fixed wing, the left side and the right side are wingtip winglets, the rear part is a lower reverse wing, and the tail part is a rectifying wing; wingtip winglets on the left side and the right side are in a pull-down type; the rear lower reverse wing is of a pull-down type, a rotating shaft is additionally arranged between the lower reverse wing and the main wing to manufacture a flexible or rigid thin-shell structure for pulling the lower reverse wing and loosening the upper reverse wing, when the lower reverse wing needs to be reversed, the lower reverse wing is directly pulled to be reversed by using the traction rope, and when the upper reverse wing needs to be reversed, the traction rope is released to enable the lower reverse wing to be reversed under the pushing of the sliding flow pressure of the propeller.

The plate wings are of a thin-shell structure and are made of carbon fiber cloth sandwiched honeycomb composite materials; the contour line of the slat wing is an upper surface curve of a low-speed wing profile, when the slat wing flies horizontally, the upper surface of the slat wing can wash down the air flow through the wing profile to generate lift force while the propeller slipstream is forced to wash down the lower surface of the slat wing to generate lift force, and the lift force of the slat wing is larger than that of a common fixed wing; the thrust-weight ratio of vertical take-off and landing is more than 1, and the thrust-weight ratio of horizontal flight is more than 5.

The front lower part of the front edge of the plate wing is provided with a driving device, the front lower part of the driving device is provided with an aileron, the aileron is provided with an upper convex wing shape and a lower flat wing shape and is connected with the fuselage through a transverse hinge at the rear part of the aileron, and the aileron rotates around the transverse hinge to change an attack angle; during horizontal flight, the wing profile of the aileron can generate wing profile lift force, and the lift force and the resistance of the slat wing are changed by changing the attack angle of the aileron, so that the pitching of the slat wing aircraft is controlled; when the ailerons turn to the positive attack angle, the ailerons can generate impact lift force, the slat plane tilts upwards, and the larger the positive attack angle is, the larger the elevation angle of the slat plane is; when the ailerons turn to the negative attack angle, the ailerons can generate impact pressure, the plate-wing aircraft bends downwards, and the larger the negative attack angle is, the larger the downward bending angle of the plate-wing aircraft is; in addition, the airflow generated when the air inlet of the driving device inhales flows through the upper wing surface of the aileron, the airflow speed of the lower wing surface of the aileron is the same as the flight speed of the aircraft, and the airflow speed is zero at the vertical take-off and landing, so that the negative pressure lift force can be formed on the aileron even if the flight speed is equal to zero when the aircraft hovers.

The wingtip of the plate wing is provided with wingtip winglets capable of being reversed and flattened, the wingtip winglets are thin plate wing profiles, the front edges of the wingtip winglets are close to the driving device, the lower edges of the wingtip winglets exceed the lower edges of the driving device, the rear edges of the wingtip winglets are close to the rear edges of the plate wing, and the width of the rear edge contour lines of the wingtip winglets is gradually reduced to zero according to the streamline shape; in both horizontal flight state and vertical take-off and landing state, when the lower dihedral angles of wingtip winglets on the left side and the right side are different, a yaw moment is generated on the plate wing to control the lower dihedral angles of the wingtip winglets on the left side and the right side to control yaw; when the dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, the slat type wing aircraft yaws leftwards; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; the larger the lower dihedral angle deviation of wingtips winglets on the left side and the right side is, the larger the yawing moment of the plate-wing aircraft is; the flattened winglet also has the effects of increasing the lift force of the slat plane, increasing the light receiving area of the wing and reducing the wing load to the maximum extent.

The flight control of the plate wing aircraft is realized by adjusting the dihedral angle of the lower inverse wing, the dihedral angle of the winglet, the attack angle of the aileron and the power of the driving device through the control mechanism; during horizontal flight, pitching of the slat-type wing aircraft is realized by adjusting the attack angle of the ailerons, yawing of the slat-type wing aircraft is realized by differentially adjusting the lower dihedral angles of wingtip winglets on the left side and the right side, the left lower contravariant deviates from the midpoint and slightly reverses downwards while the right lower contravariant deviates from the midpoint and slightly reverses upwards; when the wing is vertically lifted, the up-and-down movement of the plate-wing aircraft is regulated and controlled according to the power, the forward movement of the plate-wing aircraft is realized by the upward reflection of the tail wing, the backward movement of the plate-wing aircraft is realized by the downward reflection of the tail wing by 105 degrees, and the yaw of the plate-wing aircraft is realized by the differential adjustment of the downward reflection angles of wingtips on the left side and the right side; because the gravity center of the plate-wing aircraft is lower, the pitching moment and the rolling moment in the vertical take-off and landing flight are automatically balanced and compensated by the deflection angle of the gravity center of the plate-wing aircraft, and a special mechanism is not needed for control.

The driving device is a propeller and is positioned in a box body formed by enclosing the plate wing, the aileron and the wingtip winglet to form a ducted fan, and the flow velocity of airflow blown onto the wings is in direct proportion to the power of the driving device.

The width of the plate wing is slightly larger than the width of all the propellers which are arranged side by side according to the diameter D, and is 1.15 times of the width of all the propellers which are arranged side by side according to the diameter D; the length of the fixed main wing is 3 times of the diameter D of the propeller, and the length of the lower reverse wing is 2 times of the diameter D of the propeller.

The take-off, landing and forced landing of the plate-wing aircraft are all vertical modes, and a suspension type cylinder spring landing gear is adopted.

Example 2: as shown in fig. 1-18, in the method for enhancing lift force and realizing vertical take-off and landing by installing a driving mechanism below a plate wing, an aircraft adopting the plate wing as a wing is provided with a driving device at the lower part in front of the front edge of the plate wing, high-speed airflow is blown to the lower part of the plate wing along the chord direction by the driving device, a negative pressure region is formed above the plate wing by an air inlet of the driving device, a positive pressure region is formed below the plate wing by an air nozzle, and differential pressure lift force formed by the negative pressure region above the plate wing and the positive pressure region below the plate wing is utilized; meanwhile, the plate wings are combined, and when the plate wings vertically take off and land, the left sides, the right sides and the rear part of the combined plate wings are downward-reversed, so that the airflow direction of the slipstream of the propeller is changed from the horizontal direction to the vertical direction, the effects of increasing lift and reducing drag are achieved, and the lift force and the flight control capability of vertical take off and land are further improved; when the aircraft flies horizontally, the plate wings are folded into a shape of fixed wings with small resistance, and wing-shaped lift force is generated besides the differential pressure lift force; in the process of interconversion flight mode between VTOL and horizontal flight, control mechanism's the mode transition of controlling is natural, and it is smooth-going to control the parameter variation, controls the effect and does not produce the sudden change, has compromise the different requirements of horizontal flight and VTOL, has effectively solved the problem of the mode conversion difficulty of ubiquitous flight mode among the current mode conversion VTOL airborne vehicle, greatly reduced VTOL airborne vehicle control the degree of difficulty.

The plate wings are combined, the front part is a fixed main wing, the left side and the right side are wingtip winglets, the rear part is a lower reverse wing, and the tail part is a rectifying wing; the left lower reverse wing and the right lower reverse wing are in a pull-down type; the rear lower reverse wing is divided into two parts along the horizontal direction, the two parts are divided into an upper board wing and a lower board wing, the upper board wing is a movable wing, the lower board wing is a fixed wing, the upper board wing is connected with the fuselage through a rocker, an operating mechanism drives the rocker to enable the upper board wing to swing back and forth around the lower board wing, during horizontal flight, the upper board wing swings forwards and is combined with the lower board wing into a complete upper convex lower flat wing type board wing to reduce resistance to realize high-speed flight, during vertical takeoff and landing, the upper board wing is lifted to swing backwards and downwards greatly, and the upper board wing and the lower board wing are staggered into the lower reverse board wings connected end to end.

The plate wing is of a thin-shell structure and is made of an aluminum alloy frame and nylon cloth; the contour line of the slat wing is an upper surface curve of a low-speed wing profile, when the slat wing flies horizontally, the upper surface of the slat wing can wash down the air flow through the wing profile to generate lift force while the propeller slipstream is forced to wash down the lower surface of the slat wing to generate lift force, and the lift force of the slat wing is larger than that of a common fixed wing; the thrust-weight ratio of vertical take-off and landing is more than 1, and the thrust-weight ratio of horizontal flight is more than 5.

The wingtip of the plate wing is provided with a wingtip winglet capable of reversing and flattening downwards, the wingtip winglet is a wing type with a convex outer surface and a flat inner surface, the front edge of the wingtip winglet is close to the driving device, the lower edge of the wingtip winglet exceeds the lower edge of the driving device, the rear edge of the wingtip winglet exceeds the rear edge of the plate wing, the width of the rear edge contour line of the wingtip winglet is gradually reduced to zero according to the streamline shape, and a longitudinal hinge is arranged between the wingtip winglet and the plate wing to be connected, so that the drooped wingtip winglet with the convex outer surface and the flat inner surface can be pushed by wing lift force generated by horizontal flight airflow to be reversely flattened upwards and become a; in both horizontal flight state and vertical take-off and landing state, when the lower dihedral angles of wingtip winglets on the left side and the right side are different, a yaw moment is generated on the plate wing to control the lower dihedral angles of the wingtip winglets on the left side and the right side to control yaw; when the dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, the slat type wing aircraft yaws leftwards; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; the larger the lower dihedral angle deviation of wingtips winglets on the left side and the right side is, the larger the yawing moment of the plate-wing aircraft is; the flattened winglet also has the effects of increasing the lift force of the slat plane, increasing the light receiving area of the wing and reducing the wing load to the maximum extent.

The flight control of the plate wing aircraft is realized by adjusting the dihedral angle of the lower inverse wing, the dihedral angle of the winglet, the attack angle of the aileron and the power of the driving device through the control mechanism; when the wing is in horizontal flight, the pitching of the plate-wing aircraft is realized by adjusting the dihedral angle of the rear lower contra wing, the yawing of the plate-wing aircraft is also realized by differentially adjusting the dihedral angles of the wingtips winglets on the left side and the right side, and when the dihedral angle of the wingtip winglets on the left side is larger than the dihedral angle of the wingtips winglets on the right side, the plate-wing aircraft drifts to the left; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; when the wing is vertically lifted, the up-and-down movement of the plate-wing machine is regulated and controlled by the power, the forward movement of the plate-wing machine is realized by reducing the dihedral angle by the lower counter wing, the backward movement of the plate-wing machine is realized by increasing the dihedral angle to 108 degrees by the lower counter wing, and the yaw of the plate-wing machine is realized by differentially adjusting the dihedral angles of wingtips winglets at the left side and the right side; because the gravity center of the plate-wing aircraft is lower, the pitching moment and the rolling moment in the vertical take-off and landing flight are automatically balanced and compensated by the deflection angle of the gravity center of the plate-wing aircraft, and a special mechanism is not needed for control.

The driving device is a ducted propeller and is positioned in a box body formed by enclosing the plate wing, the aileron and the wingtip winglet to form a ducted fan, and the flow velocity of airflow blown onto the wings is in direct proportion to the power of the driving device.

The width of the plate wing is slightly larger than the width of all the propellers which are arranged side by side according to the diameter D, and is 1.25 times of the width of all the propellers which are arranged side by side according to the diameter D; the length of the fixed main wing is 3.5 times of the diameter D of the propeller, and the length of the lower reverse wing is 3 times of the diameter D of the propeller.

The number of the plate wings can be increased, and for medium-sized or large-sized manned aircrafts, the number of the wings can be increased in a mode that left and right wings of transverse type wings are connected in series in pairs.

Example 3: as shown in fig. 1-18, in the method for enhancing lift force and realizing vertical take-off and landing by installing a driving mechanism below a plate wing, an aircraft adopting the plate wing as a wing is provided with a driving device at the lower part in front of the front edge of the plate wing, high-speed airflow is blown to the lower part of the plate wing along the chord direction by the driving device, a negative pressure region is formed above the plate wing by an air inlet of the driving device, a positive pressure region is formed below the plate wing by an air nozzle, and differential pressure lift force formed by the negative pressure region above the plate wing and the positive pressure region below the plate wing is utilized; meanwhile, the plate wings are combined, and when the plate wings vertically take off and land, the left sides, the right sides and the rear part of the combined plate wings are downward-reversed, so that the airflow direction of the slipstream of the propeller is changed from the horizontal direction to the vertical direction, the effects of increasing lift and reducing drag are achieved, and the lift force and the flight control capability of vertical take off and land are further improved; when the aircraft flies horizontally, the plate wings are folded into a shape of fixed wings with small resistance, and wing-shaped lift force is generated besides the differential pressure lift force; in the process of interconversion flight mode between VTOL and horizontal flight, control mechanism's the mode transition of controlling is natural, and it is smooth-going to control the parameter variation, controls the effect and does not produce the sudden change, has compromise the different requirements of horizontal flight and VTOL, has effectively solved the problem of the mode conversion difficulty of ubiquitous flight mode among the current mode conversion VTOL airborne vehicle, greatly reduced VTOL airborne vehicle control the degree of difficulty.

The plate wings are combined, the front part is a fixed wing, the left side and the right side are wingtip winglets capable of being turned downwards and flattened, the rear part is a lower reverse wing capable of being turned downwards and flattened, and the tail part is a rectifying wing; wingtip winglets on the left side and the right side are in a pull-down type; the lower back reverse wing is foldable; the folding lower reverse wing is made of flexible cloth and is collected into the plate wing through a folding mechanism.

The plate wing is of a thin-shell structure and is made of a titanium alloy frame and nylon cloth; the contour line of the slat wing is an upper surface curve of a low-speed wing profile, when the slat wing flies horizontally, the upper surface of the slat wing can wash down the air flow through the wing profile to generate lift force while the propeller slipstream is forced to wash down the lower surface of the slat wing to generate lift force, and the lift force of the slat wing is larger than that of a common fixed wing; the thrust-weight ratio of vertical take-off and landing is more than 1, and the thrust-weight ratio of horizontal flight is more than 5.

The wingtip of the plate wing is provided with a downward-reversed wingtip winglet, the wingtip winglet is a thin plate wing type, the front edge of the wingtip winglet is close to the driving device, the lower edge of the wingtip winglet exceeds the lower edge of the driving device, the rear edge of the wingtip winglet is close to the rear edge of the plate wing, and the width of the rear edge contour line of the wingtip winglet is gradually reduced to zero according to the streamline shape; in both horizontal flight state and vertical take-off and landing state, when the lower dihedral angles of wingtip winglets on the left side and the right side are different, a yaw moment is generated on the plate wing to control the lower dihedral angles of the wingtip winglets on the left side and the right side to control yaw; when the dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, the slat type wing aircraft yaws leftwards; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; the larger the lower dihedral angle deviation of wingtips winglets on the left side and the right side is, the larger the yawing moment of the plate-wing aircraft is; the flattened winglet also has the effects of increasing the lift force of the slat plane, increasing the light receiving area of the wing and reducing the wing load to the maximum extent.

The flight control of the plate wing aircraft is realized by adjusting the dihedral angle of the lower inverse wing, the dihedral angle of the winglet, the attack angle of the aileron and the power of the driving device through the control mechanism; during horizontal flight, pitching of the slat-type wing aircraft is realized by adjusting the attack angle of the ailerons, yawing of the slat-type wing aircraft is realized by differentially adjusting the lower dihedral angles of wingtip winglets on the left side and the right side, the left lower contravariant deviates from the midpoint and slightly reverses downwards while the right lower contravariant deviates from the midpoint and slightly reverses upwards; when the wing is vertically lifted, the up-and-down movement of the plate-wing machine is regulated and controlled by the power, the forward movement of the plate-wing machine is realized by reducing the dihedral angle by the lower counter wing, the backward movement of the plate-wing machine is realized by increasing the dihedral angle to 115 degrees by the lower counter wing, and the yaw of the plate-wing machine is realized by differentially adjusting the dihedral angles of wingtips winglets at the left side and the right side; because the gravity center of the plate-wing aircraft is lower, the pitching moment and the rolling moment in the vertical take-off and landing flight are automatically balanced and compensated by the deflection angle of the gravity center of the plate-wing aircraft, and a special mechanism is not needed for control.

The driving device is a turbojet engine and is positioned in a box body formed by enclosing the plate wing, the aileron and the wingtip winglet to form a ducted fan, and the flow velocity of airflow blown onto the wings is in direct proportion to the power of the driving device.

The width of the plate wing is slightly larger than the width of all the propellers which are arranged side by side according to the diameter D, and is 1.1 times of the width of all the propellers which are arranged side by side according to the diameter D; the length of the fixed main wing is 4 times of the diameter D of the propeller, and the length of the lower reverse wing is 2.5 times of the diameter D of the propeller.

Example 4: as shown in fig. 1-18, in the method for enhancing lift force and realizing vertical take-off and landing by installing a driving mechanism below a plate wing, an aircraft adopting the plate wing as a wing is provided with a driving device at the lower part in front of the front edge of the plate wing, high-speed airflow is blown to the lower part of the plate wing along the chord direction by the driving device, a negative pressure region is formed above the plate wing by an air inlet of the driving device, a positive pressure region is formed below the plate wing by an air nozzle, and differential pressure lift force formed by the negative pressure region above the plate wing and the positive pressure region below the plate wing is utilized; meanwhile, the plate wings are combined, and when the plate wings vertically take off and land, the left sides, the right sides and the rear part of the combined plate wings are downward-reversed, so that the airflow direction of the slipstream of the propeller is changed from the horizontal direction to the vertical direction, the effects of increasing lift and reducing drag are achieved, and the lift force and the flight control capability of vertical take off and land are further improved; when the aircraft flies horizontally, the plate wings are folded into a shape of fixed wings with small resistance, and wing-shaped lift force is generated besides the differential pressure lift force; in the process of interconversion flight mode between VTOL and horizontal flight, control mechanism's the mode transition of controlling is natural, and it is smooth-going to control the parameter variation, controls the effect and does not produce the sudden change, has compromise the different requirements of horizontal flight and VTOL, has effectively solved the problem of the mode conversion difficulty of ubiquitous flight mode among the current mode conversion VTOL airborne vehicle, greatly reduced VTOL airborne vehicle control the degree of difficulty.

The plate wings are combined, the front part is a fixed wing, the left side and the right side are wingtip winglets capable of being turned downwards and flattened, the rear part is a lower reverse wing capable of being turned downwards and flattened, and the tail part is a rectifying wing; the left lower reverse wing and the right lower reverse wing are in a pull-down type; the rear lower reverse wing is in a sliding mode; the sliding lower reverse wing is made of rigid materials, the lower reverse wing is divided into a plurality of sections which can be mutually overlapped, and the plurality of sections of lower reverse wings are folded into a section which is collected in the main wing through a sliding mechanism.

The wing tip of the plate wing is provided with a downward-inverted wingtip winglet, the wingtip winglet is a wing shape which is convex and flat, the front edge of the wingtip winglet is close to the driving device, the lower edge of the wingtip winglet exceeds the lower edge of the driving device, the rear edge of the wingtip winglet exceeds the rear edge of the plate wing, the width of the rear edge contour line of the wingtip winglet is gradually reduced to zero according to the streamline shape, and a longitudinal hinge is arranged between the wingtip winglet and the plate wing to be connected, so that the drooping wingtip winglet can be pushed to be inverted and flat under the wing lift force generated by horizontal flight airflow and becomes a wing shape which is convex and flat; in both horizontal flight state and vertical take-off and landing state, when the lower dihedral angles of wingtip winglets on the left side and the right side are different, a yaw moment is generated on the plate wing to control the lower dihedral angles of the wingtip winglets on the left side and the right side to control yaw; when the dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, the slat type wing aircraft yaws leftwards; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; the larger the lower dihedral angle deviation of wingtips winglets on the left side and the right side is, the larger the yawing moment of the plate-wing aircraft is; the flattened winglet also has the effects of increasing the lift force of the slat plane, increasing the light receiving area of the wing and reducing the wing load to the maximum extent.

The flight control of the plate wing aircraft is realized by adjusting the dihedral angle of the lower inverse wing, the dihedral angle of the winglet, the attack angle of the aileron and the power of the driving device through the control mechanism; during horizontal flight, the pitching of the plate-wing aircraft is realized by adjusting the lower dihedral angle of the rear lower inverse wing, the yawing of the plate-wing aircraft is realized by adjusting the lower dihedral angles of wingtips winglets on the left side and the right side by differential motion, the left lower inverse wing deviates from the midpoint and slightly reverses downwards while the right lower inverse wing deviates from the midpoint and slightly reverses upwards; when the wing is vertically lifted, the up-and-down movement of the plate-wing machine is regulated and controlled by the power, the forward movement of the plate-wing machine is realized by reducing the dihedral angle by the lower counter wing, the backward movement of the plate-wing machine is realized by increasing the dihedral angle to 120 degrees by the lower counter wing, and the yaw of the plate-wing machine is realized by differentially adjusting the dihedral angles of wingtip winglets at the left side and the right side; because the gravity center of the plate-wing aircraft is lower, the pitching moment and the rolling moment in the vertical take-off and landing flight are automatically balanced and compensated by the deflection angle of the gravity center of the plate-wing aircraft, and a special mechanism is not needed for control.

The driving device is a turbofan engine and is positioned in a box body formed by enclosing the plate wing, the aileron and the wingtip winglet to form a ducted fan, and the flow velocity of airflow blown onto the wings is in direct proportion to the power of the driving device.

The width of the plate wing is slightly larger than the width of all the propellers which are arranged side by side according to the diameter D, and is 1.15 times of the width of all the propellers which are arranged side by side according to the diameter D; the length of the fixed main wing is 3.5 times of the diameter D of the propeller, and the length of the lower reverse wing is 3.5 times of the diameter D of the propeller.

Example 5: as shown in fig. 1-18, in the method for enhancing lift force and realizing vertical take-off and landing by installing a driving mechanism below a plate wing, an aircraft adopting the plate wing as a wing is provided with a driving device at the lower part in front of the front edge of the plate wing, high-speed airflow is blown to the lower part of the plate wing along the chord direction by the driving device, a negative pressure region is formed above the plate wing by an air inlet of the driving device, a positive pressure region is formed below the plate wing by an air nozzle, and differential pressure lift force formed by the negative pressure region above the plate wing and the positive pressure region below the plate wing is utilized; meanwhile, the plate wings are combined, and when the plate wings vertically take off and land, the left sides, the right sides and the rear part of the combined plate wings are downward-reversed, so that the airflow direction of the slipstream of the propeller is changed from the horizontal direction to the vertical direction, the effects of increasing lift and reducing drag are achieved, and the lift force and the flight control capability of vertical take off and land are further improved; when the aircraft flies horizontally, the plate wings are folded into a shape of fixed wings with small resistance, and wing-shaped lift force is generated besides the differential pressure lift force; in the process of interconversion flight mode between VTOL and horizontal flight, control mechanism's the mode transition of controlling is natural, and it is smooth-going to control the parameter variation, controls the effect and does not produce the sudden change, has compromise the different requirements of horizontal flight and VTOL, has effectively solved the problem of the mode conversion difficulty of ubiquitous flight mode among the current mode conversion VTOL airborne vehicle, greatly reduced VTOL airborne vehicle control the degree of difficulty.

The plate wings are combined, the front part is a fixed wing, the left side, the right side and the rear part are lower reverse wings, and the tail part is a rectifying wing; the left lower reverse wing and the right lower reverse wing are in a pull-down type; the rear lower reverse wing is in a surrounding baffle type; the enclosure type lower counter wing is collected by utilizing the left vertical face and the right vertical face of the flaky fuselage, the rotating shaft of the lower counter wing is positioned in the plane of the flaky fuselage, the left lower counter wing and the right lower counter wing are unfolded backwards and folded in the plane of the flaky fuselage during horizontal flight so as to reduce resistance, the left lower counter wing and the right lower counter wing are unfolded forwards and are vertical to the plane of the flaky fuselage during vertical take-off and landing, horizontal airflow is enclosed downwards to play a role in increasing lift, and the enclosure type lower counter wing also plays a role in regulating and controlling the vertical tail wing.

The wingtip of the plate wing is provided with a wingtip winglet capable of reversing and flattening downwards, the wingtip winglet is a wing type with a convex outer surface and a flat inner surface, the front edge of the wingtip winglet is close to the driving device, the lower edge of the wingtip winglet exceeds the lower edge of the driving device, the rear edge of the wingtip winglet is close to the rear edge of the plate wing, the width of the rear edge contour line of the wingtip winglet is gradually reduced to zero according to the streamline shape, and a longitudinal hinge is arranged between the wingtip winglet and the plate wing to be connected, so that the drooped wingtip winglet with the convex outer surface and the flat inner surface can be pushed by wing lift force generated by horizontal flying airflow to be reversely flattened upwards and; in both horizontal flight state and vertical take-off and landing state, when the lower dihedral angles of wingtip winglets on the left side and the right side are different, a yaw moment is generated on the plate wing to control the lower dihedral angles of the wingtip winglets on the left side and the right side to control yaw; when the dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, the slat type wing aircraft yaws leftwards; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; the larger the lower dihedral angle deviation of wingtips winglets on the left side and the right side is, the larger the yawing moment of the plate-wing aircraft is; the flattened winglet also has the effects of increasing the lift force of the slat plane, increasing the light receiving area of the wing and reducing the wing load to the maximum extent.

The flight control of the plate wing aircraft is realized by adjusting the dihedral angle of the lower inverse wing, the dihedral angle of the winglet, the attack angle of the aileron and the power of the driving device through the control mechanism; during horizontal flight, pitching of the slat-type wing aircraft is realized by adjusting the attack angle of the ailerons, yawing of the slat-type wing aircraft is realized by differentially adjusting the lower dihedral angles of wingtip winglets on the left side and the right side, the left lower contravariant deviates from the midpoint and slightly reverses downwards while the right lower contravariant deviates from the midpoint and slightly reverses upwards; when the wing is vertically lifted, the up-and-down movement of the plate-wing machine is regulated and controlled by the power, the forward movement of the plate-wing machine is realized by reducing the dihedral angle by the lower counter wing, the backward movement of the plate-wing machine is realized by increasing the dihedral angle to 118 degrees by the lower counter wing, and the yaw of the plate-wing machine is realized by differentially adjusting the dihedral angles of wingtip winglets at the left side and the right side; because the gravity center of the plate-wing aircraft is lower, the pitching moment and the rolling moment in the vertical take-off and landing flight are automatically balanced and compensated by the deflection angle of the gravity center of the plate-wing aircraft, and a special mechanism is not needed for control.

The driving device is a turboprop engine which is positioned in a box body formed by enclosing a plate wing, an aileron and a wingtip winglet to form a ducted fan, and the flow velocity of airflow blown onto the wings is in direct proportion to the power of the driving device.

The width of the plate wing is slightly larger than the width of all the propellers which are arranged side by side according to the diameter D, and is 1.2 times of the width of all the propellers which are arranged side by side according to the diameter D; the length of the fixed main wing is 4 times of the diameter D of the propeller, and the length of the lower reverse wing is 4 times of the diameter D of the propeller.

While the present invention has been described with reference to the accompanying drawings, it is to be understood that the invention is not limited thereto, and that various changes and modifications may be made without departing from the spirit and scope of the invention as defined by the appended claims.

Claims

1. A method for installing a driving mechanism below a plate wing to enhance lift force and realize vertical take-off and landing is characterized in that: the driving device is arranged at the lower part in front of the front edge of the plate wing machine, high-speed airflow is blown to the lower part of the plate wing along the chord direction through the driving device, a negative pressure area is formed above the plate wing by an air inlet of the driving device, a positive pressure area is formed below the plate wing by an air jet, and the flying efficiency and the thrust-weight ratio of the plate wing machine are greatly improved by utilizing the differential pressure lift force formed by the negative pressure area above the plate wing and the positive pressure area below the plate wing; meanwhile, the plate wing is designed into a combined type and is divided into four parts, the front part is a fixed main wing, the left side and the right side are wingtip winglets capable of being turned downwards and flattened, the rear part is a lower counter wing capable of being turned downwards and flattened, and the tail part is a fixed rectifying wing; when the combined plate wing vertically takes off and lands, the left side, the right side and the rear part of the combined plate wing are downward-reversed to change the air flow direction of the slipstream of the driving device from the horizontal direction to the vertical direction, so that the effects of increasing lift and reducing drag are achieved, and the lift force and the flight control capability of the vertical take off and landing are further improved; during horizontal flight, the plate wings are folded into a fixed wing shape, and wing-shaped lift force is further generated besides the differential pressure lift force; in the process of mutually converting the flight mode between vertical take-off and landing and horizontal flight, the control mode of the control mechanism is naturally transited, the control parameter change is smooth, and the control effect does not generate sudden change.

2. The method for enhancing lift and achieving VTOL by installing a driving mechanism under a plate wing according to claim 1, wherein: the wingtip winglets at the left side and the right side are downward pulled, and the downward reverse wings at the rear part are any one of folding type, sliding type and enclosure type; the folding lower reverse wing is made of flexible cloth and is collected into the plate wing or unfolded through a folding mechanism; the sliding lower counter wing is made of rigid materials and is divided into a plurality of sections which can be mutually overlapped, and the plurality of sections of lower counter wings are folded into a section which is collected in the fixed main wing or unfolded through a sliding mechanism; the enclosure type lower counter wing utilizes the left vertical surface and the right vertical surface of the flaky fuselage to store the lower counter wing, the rotating shaft of the lower counter wing is positioned in the plane of the flaky fuselage, the left lower counter wing and the right lower counter wing are folded in the plane of the flaky fuselage in a backward unfolding mode during horizontal flight to reduce resistance, the left lower counter wing and the right lower counter wing are unfolded forward to be perpendicular to the plane of the flaky fuselage during vertical take-off and landing to enclose horizontal airflow downwards to play a role in increasing lift, and the enclosure type lower counter wing also plays a role in regulating and controlling a vertical tail wing.

3. The method for enhancing the lift force and realizing the vertical take-off and landing by installing the driving mechanism below the plate wing according to claim 1 or 2, wherein the method comprises the following steps: the plate wing is of a thin-shell structure and is made of a high-strength composite material or a high-strength light metal frame and nylon cloth; the contour line of the slat wing is an upper surface curve of a low-speed wing, when the slat wing horizontally flies, the air flow is washed downwards through the wing on the upper surface of the slat wing to generate lift force, meanwhile, the slipstream of the driving device is forcibly washed downwards on the lower surface of the slat wing to generate lift force, the lift force is larger than that of a common fixed wing, the thrust-weight ratio of vertical take-off and landing is larger than 1, and the thrust-weight ratio of horizontal flying is larger than 5.

4. The method for enhancing lift and achieving VTOL by installing a driving mechanism under a plate wing according to claim 1, wherein: the flattening of the wingtip winglet and the lower counter wing of the plate wing is realized by means of wing profile lifting force, and/or the pressure of slipstream of a driving device, and/or the pressure of ascending airflow during forced landing and falling; the wing profile of the lower counter wing is a thin plate wing profile, the upper surface and the lower surface of the lower counter wing are connected with the upper surface and the lower surface of the fixed main wing and the rectifying wing according to the shape of a pneumatic streamline, and the shape of the lower counter wing is rectangular, triangular, trapezoidal or arc; the slip flow direction of the driving device can be changed by adjusting the lower dihedral angle of the lower inverse wing, so that the lift force in the vertical direction and the thrust force in the horizontal direction of the plate wing machine are changed, and the flight direction of the plate wing machine is changed; the wing profile of the wingtip winglet is a thin plate wing profile or a wing profile with a convex inner plane, the front edge of the wingtip winglet shape is close to the driving device, the lower edge exceeds the lower edge of the driving device, the rear edge is close to or exceeds the rear edge of the plate wing, and the width of the rear edge contour line of the wingtip winglet shape is gradually reduced to zero according to the streamline shape; when the wingtip winglet is of a wing shape with an outward convex inner plane, a longitudinal hinge is arranged between the wingtip winglet and the plate wing for connection, so that the drooping wingtip winglet with the outward convex inner plane can be automatically unfolded upwards and reversely under the pushing of wing profile lifting force generated by horizontal flight airflow and the pressure of slipstream of a driving device to be changed into a wing shape with an upward convex lower plane, and the unfolded wingtip winglet can increase the lifting force of the plate wing aircraft, increase the light receiving area of the wing and reduce the wing load to the maximum extent; adjusting the dihedral angles of the wingtip winglets on the left side and the right side to enable the dihedral angles of the wingtip winglets on the left side and the right side to be different so as to generate a yaw moment on the plate wing and realize yaw control; when the dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, the slat type wing aircraft yaws leftwards; when the dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet, the slat wing aircraft yaws rightwards; the larger the declination deviation of wingtip winglets on the left side and the right side is, the larger the yawing moment of the plate-wing aircraft is.

5. The method for enhancing the lift force and realizing the vertical take-off and landing by installing the driving mechanism below the plate wing according to any one of claims 1, 2 and 4, wherein the method comprises the following steps: the front lower part of the front edge of the plate wing is provided with a driving device, the front lower part of the driving device is provided with an aileron, the aileron is provided with an upper convex wing shape and a lower flat wing shape and is connected with the fuselage through a transverse hinge at the rear part of the aileron, and the aileron rotates around the transverse hinge to change an attack angle; during horizontal flight, the wing profile of the aileron can generate wing profile lift force, and the lift force and the resistance of the slat plane are changed by changing the attack angle of the aileron, so that the pitching of the slat plane is controlled; when the ailerons turn to the positive attack angle, the ailerons can generate impact lift force, the slat plane tilts upwards, and the larger the positive attack angle is, the larger the elevation angle of the slat plane is; when the ailerons turn to the negative attack angle, the ailerons generate impact pressure, the plate-wing aircraft bends downwards, and the larger the negative attack angle is, the larger the downward bending angle of the plate-wing aircraft is; the airflow generated by the air inlet of the driving device flows through the upper wing surface of the aileron, the airflow speed of the lower wing surface of the aileron is the same as the flying speed of the aircraft, the airflow speed of the lower wing surface of the aileron is zero when the aircraft is vertically lifted and landed and suspended, and negative pressure lift force can still be formed on the aileron.

6. The method for enhancing lift and achieving VTOL by installing a driving mechanism under a plate wing according to claim 5, wherein: the driving device is positioned in a box body formed by enclosing the plate wings, the ailerons and the wingtip winglets to form a ducted fan; the driving device is any one of a propeller, a ducted propeller, a turbojet engine, a turbofan engine and a turboprop engine, and the flow speed of airflow blown onto the wings is in direct proportion to the power of the driving device.

7. The method for enhancing lift and achieving VTOL by installing a driving mechanism under a plate wing according to claim 5, wherein: the flight control of the plate-wing aircraft is realized by adjusting the dihedral angle of the lower inverse wing, the dihedral angle of the winglet, the attack angle of the aileron and the power of the driving device through the control mechanism; during horizontal flight, the pitching of the plate-wing aircraft is realized by adjusting the lower dihedral angle of the lower back wing of the rear part, and the yawing of the plate-wing aircraft is realized by differentially adjusting the lower dihedral angles of the wingtips winglets at the left side and the right side: when the left wingtip winglet flies horizontally, the slat-type wing aircraft drifts leftwards when the lower dihedral angle of the left wingtip winglet is larger than that of the right wingtip winglet, and drifts rightwards when the lower dihedral angle of the right wingtip winglet is larger than that of the left wingtip winglet; when the wing is vertically lifted, the up-and-down movement of the plate-wing machine is regulated and controlled through the power of the driving device, the forward movement of the plate-wing machine is realized by reducing the lower dihedral angle through the lower contravariant, the backward movement of the plate-wing machine is realized by increasing the lower dihedral angle to 120 degrees through the lower contravariant, the yaw of the plate-wing machine is realized by differentially adjusting the lower dihedral angles of the wingtip winglets on the left side and the right side, the plate-wing machine yaws leftwards when the lower dihedral angle of the wingtip winglets on the left side is larger than the lower dihedral angle of the wingtip wingtips on the right side, and the plate-wing machine yaws rightwards when; because the gravity center of the plate-wing aircraft is lower, the pitching moment and the rolling moment of the plate-wing aircraft can be automatically balanced and compensated through the deflection angle of the gravity center of the plate-wing aircraft during vertical take-off, landing and flying.

8. The method for enhancing the lift force and realizing the vertical take-off and landing by installing the driving mechanism below the plate wing according to claim 1 or 2, wherein the method comprises the following steps: the driving device is a propeller, the width of the plate wing is 1.1-1.5 times of the width of all the propellers arranged side by side according to the diameter D, the length of the fixed main wing is more than or equal to 3 times of the diameter D of the propeller, and the length of the lower reverse wing is more than or equal to 2 times of the diameter D of the propeller.

9. The method for enhancing the lift force and realizing the vertical take-off and landing by installing the driving mechanism below the plate wing according to any one of claims 1, 2 and 4, wherein the method comprises the following steps: the take-off, landing and forced landing of the plate-wing aircraft are all vertical modes, and a suspension type cylinder spring undercarriage is directly adopted.

10. The method for enhancing the lift force and realizing the vertical take-off and landing by installing the driving mechanism below the plate wing according to any one of claims 1 or 2, wherein the method comprises the following steps: the number of the plate wings is one wing in an overhead type.

11. The method for enhancing the lift force and realizing the vertical take-off and landing by installing the driving mechanism below the plate wing according to any one of claims 1 or 2, wherein the method comprises the following steps: the number of the plate wings is a plurality of wings which are transversely arranged in a left-right symmetrical mode, and for a medium-sized or large-sized manned aircraft, the number of the wings is increased in a mode that the left wing and the right wing of the transversely arranged wings are connected in series in pairs in a front-back mode.