CN114701640A - Jet wing type full-speed global vertical take-off and landing fixed wing aircraft and control method - Google Patents

Jet wing type full-speed global vertical take-off and landing fixed wing aircraft and control method Download PDF

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Publication number
CN114701640A
CN114701640A CN202210152867.3A CN202210152867A CN114701640A CN 114701640 A CN114701640 A CN 114701640A CN 202210152867 A CN202210152867 A CN 202210152867A CN 114701640 A CN114701640 A CN 114701640A
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wing
wings
aircraft
speed
convex
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田贵川
熊芳
陈盼盼
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/148—Aerofoil profile comprising protuberances, e.g. for modifying boundary layer flow

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention discloses a multi-convex wing, a multi-convex wing body fusion aircraft, a jet-wing type full-speed global vertical take-off and landing fixed-wing aircraft and a control method thereof. The upper surface of the multi-convex wing is provided with a plurality of convex curved surfaces along the airflow direction, so that larger lift force can be generated. The aircraft has the advantages of extremely large power load, high efficiency and long range, can realize global flight from low altitude to high altitude, can realize full-speed flight from high speed to low speed and even hovering, and can also take off and land vertically. The method is suitable for high-efficiency traffic in the air, space, city, countryside and city, and opens the three-dimensional traffic era.

Description

Jet wing type full-speed global vertical take-off and landing fixed wing aircraft and control method
Technical Field
The invention relates to an aircraft, in particular to a jet wing type full-speed global vertical take-off and landing fixed wing aircraft which has extremely high power load, can fly at high speed and low speed, and can take off, land and hover vertically and a control method thereof.
Background
Common aircrafts are of two main types, fixed wing and rotor wing. The fixed wing aircraft has the advantages of great weight, high speed, long voyage and high lift limit. However, the aircraft can take off only when a special large airport slides to a certain speed, even if the speed is slightly low, the aircraft can not hover in the air due to insufficient lift force to cause stalling accidents, the application range is limited, and the transportation in a distant city is only actively carried out at present.
The rotary wing aircraft can take off and land vertically, does not need a special large airport, can hover in the air, but has the advantages of small load, low speed, short voyage, low lifting limit, complex operation, high noise, poor safety and severely limited application range, and is only actively transported in the fields of military use, emergency, special use, edge and the like at present.
At present, some fixed-wing aircraft try to merge the fixed-wing aircraft and the rotary-wing aircraft in a manner of superposing a rotor or a lift fan on the fixed-wing aircraft, and the merged fixed-wing aircraft is represented by F35B aircraft, helicopter, hovercar and ever-appearing helicopter, and the loads of the vertical take-off and landing modes of the fixed-wing aircraft and the helicopter are low, and the noise is high. The technology can only be applied to ultra-light fixed-wing aircrafts, hovercrafts and unmanned planes, but the redundancy is increased, the structure is complex, and the safety is poor.
There are also some fixed-wing aircraft that attempt to merge the fixed-wing aircraft with the rotary-wing aircraft by tilting the rotors on a fixed-wing aircraft basis. The vertical take-off and landing modes of the three-dimensional space-saving ship have the advantages of less load, slower speed, shorter range, high noise, large pneumatic change during take-off, landing and flat flight conversion, complex structure and flight control and insecurity, so that the three-dimensional space-saving ship cannot be widely applied to the civil field all the time. The technology can only be applied to light fixed-wing aircrafts, electric helicopter fixed-wing aircrafts and unmanned planes, but is still a conceptual aircraft.
Disclosure of Invention
The invention aims to provide a multi-convex wing, a multi-convex wing body fusion aircraft, a jet wing type full-speed all-domain vertical take-off and landing fixed wing aircraft and a control method, which have the advantages of extremely high power load, great load, long range, high lift limit, low noise, convenience in operation and the like, and particularly can truly realize all-domain flight from low altitude to high altitude, and can also realize full-speed flight from high speed to low speed and even hovering, and can also vertically take off and land.
In a first aspect, the present invention provides an aircraft multi-winged wing, wherein the upper surface of the wing has a plurality of convex curved surfaces along the airflow direction, which is called a multi-winged wing, and the airflow flowing through the multi-winged wing generates a corresponding plurality of low pressure areas, thereby generating a corresponding plurality of aerodynamic lift areas on the wing.
The invention also provides a jet-wing type full-speed global vertical take-off and landing fixed-wing aircraft which consists of wings, a fuselage, a landing gear, an operating system and a power device, and is characterized in that airflow generated by the power device is jetted to the wings from the front of the wings through an air jet device, or airflow generated by the power device is directly jetted to the wings from the front of the wings, so that the wings are always in relative airflow, and a set aerodynamic lift force is generated on the wings; the wings are any one or combination of multi-convex wings, traditional single convex wings and flying wing layout wings; the upper surface of the traditional single convex wing only has one convex surface, and is an existing wing type.
The invention also provides a multi-convex wing body fusion aircraft which is characterized in that a plurality of convex wings and an aircraft body are integrated; the multi-convex wing is arranged at the top of the fuselage to provide power for lift force and pitching maneuvering, and the multi-convex wing is arranged at the two sides of the fuselage to provide power for rolling, yawing, steering and translating maneuvering; the multiple convex wings are arranged at the tail part and provide air brake resistance.
The wing blade device is added at the boundary of the airflow ejected by the air injection device on the wing, and is used for preventing the high-pressure airflow beside the wing from flowing to the low-pressure area of the airflow.
Wherein, the shape of the multi-convex wing can be set to be variable so as to realize different flight requirements.
The jet device can be composed of a duct, a nozzle and a valve, the number of the jet devices is one or more, the jet device is arranged in front of the wing and is movably connected with the wing, the airflow generated by the power device is transferred to the front of the wing through the duct, the relative position and the relative jet direction of the jet device and the wing are adjusted through an operating system, and the airflow is controlled to be jetted to the wing from the front of the wing through the nozzle according to flight control requirements.
Wherein the trailing edge flap of the wing is any one of a simple flap, a cracking flap, a slotted flap, a retreating flap or a retreating slotted flap; the retreating slotted flap is in any one of a retreating single slotted form, a retreating double slotted form, a retreating three slotted form or a retreating multi-slotted form.
Wherein, the power device is any one or the combination of a turbojet, a turbofan, a turboprop, a turboshaft engine or a piston propeller fan engine, an electric fan, an electric propeller fan and a high-pressure gas cylinder; the layout form of the power device is any one of a centralized power device and a distributed power device or the combination of the centralized power device and the distributed power device.
The jet-wing full-speed global vertical take-off and landing fixed-wing aircraft is any one of an airplane, a flying automobile, a flying ship, a flying device, a flying train, an airbus, an aerospace plane, a pneumatic take-off recovery rocket, a cruise missile or a cruise missile.
The fixed wing is arranged on the automobile, and the air injection device is arranged in front of the wing and is movably connected with the wing; the fixed wing is any one or combination of a traditional folding single-convex wing or a multi-convex wing; the thrust fan is provided with a switching valve, and the aerocar is provided with an operation system, so that the flying mode and the running mode can be switched.
The flying ship is formed by adding a fixed wing, a thrust fan and an air injection device on the basis of the ship, wherein the fixed wing is arranged on the ship, and the air injection device is arranged in front of a wing and is movably connected with the wing; the fixed wing is any one or combination of a traditional folding single-convex wing or a multi-convex wing; the thrust fan is provided with a switching valve, and the flight ship is provided with an operation and control system and has a flight mode and a running mode.
Wherein, a fixed wing, a thrust fan, an air jet device and a land driving system are added on the basis of the ship to form a flying device; the fixed wing is arranged on the ship, and the air injection device is arranged in front of the wing and is movably connected with the wing; the fixed wing is any one or combination of a traditional folding single-convex wing or a multi-convex wing; the thrust fan is provided with a switching valve, and the aircraft is provided with an operation system for controlling the aircraft to switch back and forth in a flying, running or sailing mode.
In a second aspect, the present invention provides a method for controlling a jet-wing full-speed global vertical take-off and landing fixed-wing aircraft according to the first aspect, including the following steps:
by adjusting a trailing edge flap, an aileron or a guide plate on the wing, airflow flowing through the wing is guided to the lower part of the aircraft, the forward reaction thrust generated by the power device or the air injection device when the airflow is ejected backwards to the aircraft is balanced while the aircraft is pushed to overcome gravity, and an accelerator or an electric door is operated to adjust the air injection speed and the air injection amount, so that the aircraft can take off and land vertically or hover;
the air current flowing through the wings is guided to the rear or the rear lower part by gradually retracting the trailing edge flaps, ailerons or guide plates on the wings, the aircraft is pushed to overcome the gravity, meanwhile, the power device or the air injection device is used for ejecting the air current backwards to generate forward reaction thrust to push the aircraft to fly forwards, and the throttle or the electric switch is operated to adjust the air injection speed and the air injection quantity, so that the aircraft can fly at low speed or high speed;
the trailing edge flaps, ailerons or guide plates on the wings are put down, airflow flowing through the wings is guided to the lower part or the front lower part of the aircraft, and an accelerator or an electric switch is operated to adjust the air injection speed and the air injection amount, so that the aircraft can be decelerated to a vertical take-off and landing or hovering state by means of air resistance or reverse air injection;
part of airflow provided by the power device is sprayed to the empennage or the second wing of the aircraft through the air spraying device, the airflow direction is adjusted through a flap, an aileron or a control surface, the aircraft is stabilized, and power for pitching, rolling, yawing, steering and translation maneuvering is provided for the aircraft;
the relative position and the relative air injection direction of the air injection device and the wing are adjusted through the control device, the included angle between the airflow direction and the wing is adjusted, and the air injection quantity ratio of the upper surface and the lower surface of the wing is adjusted, so that the adjustment of the attack angle and the optimal flight state are realized;
the multi-convex wing is fused with the machine body, the multi-convex wing is arranged at the top of the machine body to provide lift force, and the front and back air injection quantity, the air injection speed and the angle are controlled to realize pitching maneuver; the multi-convex wing is arranged at eight positions on two sides of the machine body, and is respectively provided with eight positions, namely left front upper position, left front lower position, left rear upper position, left rear lower position, right front upper position, right front lower position, right rear upper position and right rear lower position, and air injection devices are respectively and independently configured to control the air injection amount and the air injection speed of the eight air injection devices so as to realize rolling, yawing and translation maneuvering; the multiple convex wings are arranged at the tail part and provide air brake resistance.
When the fixed wing aircraft reaches a set speed, an integral flying mode can be selected, the air injection device is closed and retracted to be integrated with the wings, the fixed wing aircraft is pushed to fly forwards by directly injecting air backwards through the thrust fan, the wings and air move relatively, a set aerodynamic lift force is generated on the wings, and stable flying is realized.
The invention has the advantages that the power load of the jet-wing full-speed full-domain vertical take-off and landing fixed-wing aircraft is extremely large, the maximum take-off/landing weight can exceed several times of that of a fixed-wing aircraft with the same power, and exceeds ten times of that of a rotary-wing helicopter with the same power, and the take-off and landing are easy. The device has the advantages of large load, high speed, long range, high lifting limit, low noise, convenient operation and the like, and particularly can take off and land vertically, hover in the air, have no special requirements on a take-off and landing site, take off and land on a flat ground without building a special large airport.
The high-speed airflow generated by the aircraft power device is sprayed to the wings through the control of the air spraying device, namely, the flow field where the wings are located is redefined, the influence of environmental airflow is reduced, the self-control performance is greatly increased, stable flight can be realized under the low-altitude complex airflow condition, the vertical flight and the flat flight transition are stable, the aircraft power device is suitable for middle-high altitude flight, low-altitude flight and ultra-low altitude flight, the flight in the global range from the low altitude to the high altitude can be realized, and the flight in the full-speed range from the high speed to the low speed and even hovering can be realized.
The wing-spraying type full-speed global vertical take-off and landing fixed wing aircraft is convenient to use, high in safety and wide in application range, can be used for intercity traffic, urban air three-dimensional traffic, military use, emergency rescue, special, marginal and agricultural fields and the like, forms an air rapid traffic network, even realizes a new mode of multi-point to multi-point direct route between intercity, greatly relieves urban traffic jam, improves the traffic speed and efficiency by several times or even ten times compared with the existing plane traffic mode mainly comprising automobiles and subways, and obviously improves the traffic speed.
For example, the power device of the jet-wing full-speed global vertical take-off and landing fixed-wing aircraft mainly adopts an electric propulsion system, achieves the basic zero emission in the operation process, is very environment-friendly and low in consumption, and can be compared with the transportation cost of railways and even water transportation. The method promotes the efficient and environment-friendly development of traffic in the sky, city, intercity and city and particularly in remote areas, thoroughly improves the mode of traffic travel and opens a comprehensive three-dimensional traffic era.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of a conventional-layout jet-wing full-speed full-domain vertical take-off and landing fixed-wing aircraft provided by the present invention.
Fig. 2 is a schematic view of wing profiles and airflow of a jet-wing full-speed full-domain vertical take-off and landing fixed-wing aircraft provided by the invention during flat flight.
FIG. 3 is a schematic view of the airfoil profile and airflow of a jet-vane full-speed full-domain vertical take-off and landing fixed-wing aircraft in a vertical take-off and landing mode.
FIG. 4 is a schematic view of wing profiles and airflows of a jet-vane full-speed full-domain vertical take-off and landing fixed-wing aircraft in the transition stage from vertical take-off to flat flight provided by the invention.
FIG. 5 is a schematic view of conventional single and multiple wing airfoils and airflow provided by the present invention.
FIG. 6 is a longitudinal section and a schematic view of the flow of a binary vector jet apparatus according to the present invention.
Fig. 7 is a longitudinal section and a schematic view of the air flow when the air jet device provided by the invention is retracted and integrated with the wing.
FIG. 8 is a schematic view of a jet-wing full-speed full-domain vertical take-off and landing fixed-wing aircraft with a tailless distributed power layout according to the present invention.
Fig. 9 is a schematic diagram of a direct-injection wing type full-speed full-domain vertical take-off and landing fixed-wing aircraft with a distributed power layout according to the present invention.
Fig. 10 is a schematic view of a variable-attack-angle airfoil and airflow of a direct-injection wing type full-speed full-domain vertical take-off and landing fixed-wing aircraft with a distributed power layout provided by the invention.
FIG. 11 is a schematic view of a jet-wing full-speed full-domain vertical take-off and landing fixed-wing flying vehicle and airflow provided by the present invention.
Fig. 12 is an axonometric view of the jet-wing multi-convex-wing body fusion aircraft provided by the invention.
Fig. 13 is a vertical take-off and landing or hovering state front view of the jet-vane multi-winged body fusion aircraft provided by the invention.
Fig. 14 is a vertical take-off and landing or hovering state top view of the jet-vane multi-winged body fusion aircraft provided by the invention.
Fig. 15 is a front view of a jet-wing multi-convex-wing body fusion aircraft provided by the invention in a flat flight state.
Fig. 16 is a schematic step diagram of a method for controlling a jet-wing full-speed global vertical take-off and landing fixed-wing aircraft according to the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 5, the present invention provides a multi-lobe wing of an aircraft, which is characterized in that a plurality of convex curved surfaces are formed on the upper surface of the wing along the airflow direction, which is called a multi-lobe wing, and the airflow flowing through the multi-lobe wing generates a plurality of corresponding low pressure areas, thereby generating a plurality of corresponding aerodynamic lift areas on the wing.
Referring to fig. 1 to 15, the invention further provides a jet wing type full-speed all-domain vertical take-off and landing fixed wing aircraft, which comprises wings, a fuselage, a landing gear, an operating system and a power device, and is characterized in that airflow generated by the power device is jetted to the wings from the front of the wings through a jet device, or airflow generated by the power device is directly jetted to the wings from the front of the wings, so that the wings are always in relative airflow, and a set aerodynamic lift force is generated on the wings; the wings are any one or combination of multi-convex wings, traditional single-convex wings and flying wing layout wings; the upper surface of the traditional single convex wing only has one convex surface, and is an existing wing type.
Referring to fig. 12 to 15, the present invention further provides a multi-wing body fusion aircraft, which is characterized in that the multi-wing body is integrated with the aircraft body; the multi-convex wings are arranged at the top of the fuselage to provide power for lift force and pitching maneuvering, and the multi-convex wings are arranged at the two sides of the fuselage to provide power for rolling, yawing, steering and translating maneuvering; the multiple convex wings are arranged at the tail part and provide air brake resistance.
The airflow flowing through the wing is guided to the lower part of the aircraft by adjusting the trailing edge flap, the aileron or the guide plate on the wing, so that the lift force and the backward push-pull force of the aircraft are further increased, the forward reaction thrust generated by the power device or the air jet device when jetting high-speed airflow backward to the aircraft is balanced while the aircraft is pushed to overcome the gravity, and the air jet speed and the air jet volume are adjusted by operating an accelerator or an electric switch, so that the aircraft can take off and land vertically or hover.
When the aircraft climbs or flies flatly, trailing edge flaps, ailerons or guide plates on the wings are gradually retracted, high-speed airflow flowing through the wings is guided to the rear or the rear lower part, the aircraft is pushed to overcome gravity, meanwhile, the high-speed airflow is ejected backwards by a power device or an air injection device to generate forward reaction thrust to push the aircraft to fly forwards, the vertical flight is stably transited to the flat flight, and an accelerator or an electric door is operated to adjust the air injection speed and the air injection amount, so that the aircraft can fly at low speed or at high speed.
The wing with one or more convex surfaces on the upper surface is called a traditional single convex wing, the wing with a plurality of convex curved surfaces on the upper surface along the airflow direction is called a multi-convex wing, and high-speed airflow flowing through the multi-convex wing generates more low-pressure areas than the traditional single convex wing, so that more lifting force is generated.
And a power device or an air injection device or a flow guide rudder device is arranged between the two convex surfaces of the multiple convex wings and is used for controlling the air injection speed and angle according to flight control requirements.
The jet unit is typically mounted in front of and attached to the wing. The jet device can be a pipeline or a duct and a nozzle, the number of the jet device can be one or more, the jet device transfers the high-speed airflow generated by the power device to the front of the wing, the size, the shape and the angle of the nozzle can be adjusted so as to change the speed and the direction of the airflow, and the high-speed airflow is controlled to be jetted to the wing from the front of the wing at different flow speed, flow, direction and position according to the flight control requirement.
The jet device is movably connected with the wing, can move up and down and can rotate around a front support point, and the relative position and the relative jet direction of the jet device and the wing can be adjusted through the control device according to different flight speeds, environments and use requirements, so that the purposes of adjusting the included angle between the flow direction of high-speed airflow and the wing and adjusting the ratio of the air jet quantity on the upper surface and the lower surface of the wing are achieved, and the optimal flight effect is realized. The included angle between the air injection direction and the wing chord line is an attack angle, the attack angle is controlled within a range of +/-30 degrees, the attack angle is increased, and the lift force is improved. The angle of attack is adjusted to a large value during vertical take-off and landing, hovering and low-speed flight to obtain the optimal lift force, and the angle of attack is adjusted to a small value during high-speed flight to obtain enough lift force and simultaneously reduce flight resistance as much as possible.
The power device can be provided with a switching valve, when the aircraft reaches enough speed, the switching valve stops supplying air to the air injection device, the power device directly injects air backwards to push the aircraft, the air injection device is closed and retracts to be combined with the wing into a whole, and the wing and the air move relatively at high speed to generate aerodynamic lift force on the wing.
When the high-speed airflow sprayed by the air spraying device cannot cover all the wings, the winged knife device can be added at the boundary of the high-speed airflow sprayed by the air spraying device on the wings, namely, a baffle with a certain height is placed on the surface of the wings along the direction of the wing chord, and the high-pressure air beside the wing is prevented from running to the low-pressure area of the high-speed airflow to reduce the lifting force of the wings.
The direction-variable guide vanes can be arranged on the trailing edge flaps, ailerons or guide plates on the wings, and the direction of the guide vanes is adjusted to ensure that the gas flowing through the guide vanes flows to the left lower part or the right lower part of the aircraft, so that the aircraft obtains the power of moving left or right.
When the aircraft vertically takes off, the landing gear is gradually adjusted to enable the aircraft to be high in front and low in back, an included angle between the wing and the horizontal plane is gradually equal to a take-off attack angle, at the moment, the air injection direction is parallel to the horizontal plane, the influence of the forward reaction thrust generated by the high-speed airflow ejected backwards by the power device or the air injection device on the component of the vertical downward direction is eliminated, and the lift force is further improved.
If the power device is an internal combustion engine, hot air generated by the power device can be sprayed to the upper part of the wing through the air spraying device so as to further improve the lift force of the wing.
During flight, particularly during low-speed flight, vertical take-off and landing and hovering, part of high-speed airflow provided by the power device can be sprayed to the tail wing or the second wing of the aircraft through the air spraying device, the airflow direction can be adjusted through the flap, the aileron or the control surface, the aircraft is stabilized, and pitching, rolling, yawing, steering and translation maneuvering power is provided for the aircraft.
The wing may be a foldable fixed wing.
The aircraft can be provided with a tail wing or without a tail wing, such as a plurality of wings.
The trailing edge flap may be a simple flap, or a split flap, or a slotted flap, or a retreating slotted flap.
The retreating slotted flap can be in a retreating single-slotted mode, or a retreating double-slotted mode, or a retreating three-slotted mode, or a retreating multi-slotted mode.
The power device can be a turbojet engine, a turbofan engine, a turboprop engine, a turboshaft engine, a piston propeller fan engine, an electric fan, an electric propeller fan, a high-pressure gas cylinder or a combination thereof. The power device can be a single centralized power device or a plurality of centralized power devices, and can also be a plurality of distributed power devices.
The aircraft can be equipped with a high-pressure gas tank as an emergency power source. When the main power system has faults such as shutdown and the like and the generated high-speed airflow is insufficient, the high-speed airflow can be supplemented by the high-pressure gas tank in an emergency manner, so that emergency flight or forced landing is realized.
The jet-wing full-speed global vertical take-off and landing fixed-wing aircraft is any one of an airplane, a flying automobile, a flying ship, a flying device, a flying train, an airbus, an aerospace plane, a pneumatic take-off and recovery rocket, a cruise missile or a cruise missile. The unmanned air vehicle can be used as a manned passenger transport and freight transport platform and can also be used as an unmanned passenger transport and freight transport platform.
The aircraft can be fused with an automobile into a jet wing type full-speed global vertical take-off and landing fixed wing aerocar. A flying automobile is formed by adding fixed wings, a thrust fan and an air injection device on the automobile. The fixed wing is installed on the automobile, the thrust fan is preferably arranged at a place close to the power device and easy to suck and exhaust, and the air injection device is installed in front of the wing and movably connected with the wing. The fixed wing can be a traditional folding single-convex wing, a multi-convex wing or a combination thereof.
The aerocar is provided with a control system which can control the aerocar to vertically take off and land, can fly at low speed or high speed in the air, can also run on the ground, and can be switched back and forth in a flying or running mode at any time according to requirements. When the vehicle runs on the road, the vehicle can be driven by a power device of the vehicle to run, and the vehicle can also run by the counterforce generated by high-speed air injection of the thrust fan.
The aircraft can be integrated with a ship to form a jet wing type full-speed global vertical take-off and landing fixed wing flying ship. A flight ship is formed by adding fixed wings, a thrust fan and an air injection device on the basis of the ship. The fixed wing is arranged on the ship, the thrust fan is preferably arranged at a position close to the power device and easy for suction and exhaust, and the air injection device is arranged in front of the wing and movably connected with the wing. The fixed wing can be a traditional folding single-convex wing, a multi-convex wing or a combination thereof.
The flight ship is provided with an operation system, can vertically take off and land, can fly at low speed or high speed in the air, can run in water, and can be switched back and forth in a flight or navigation mode at any time according to requirements. When sailing in water, the ship can drive a propeller to run by a power device of the ship and can also run by the reaction force generated by high-speed air injection of a thrust fan.
The aircraft can be fused with an automobile and a ship into a jet wing type full-speed global vertical take-off and landing fixed wing aerocraft. A fixed wing, a thrust fan, an air jet device and a land driving system are added on the basis of a ship to form a flying device. The fixed wing is arranged on the ship, the thrust fan is preferably arranged at a position close to the power device and easy for suction and exhaust, and the air injection device is arranged in front of the wing and movably connected with the wing. The fixed wing can be a traditional folding single-convex wing, a multi-convex wing or a combination thereof. The aircraft is provided with an operation system, can be controlled to switch back and forth in flying, running or sailing modes, is made into a novel universal all-round vehicle, can fly in the sky, can run on the road and can sail in water.
Example 1 conventional layout spray wing type full speed all-domain vertical take-off and landing fixed wing aircraft example
As shown in fig. 1 and 2, a jet-wing type full-speed global vertical take-off and landing fixed-wing aircraft comprises a fuselage, wings, an empennage, a landing gear, an operating system, a power device, a jet device and the like, wherein the jet device is installed at the front end of the wings and is connected with the wings, high-speed airflow generated by the power device is transferred to the front of the wings through the jet device and is jetted backwards to the wings, as shown in fig. 2, the wings are always in relatively high-speed airflow, and the stress condition of the wings when the wings are in static or low-speed motion is similar to that of the fixed-wing aircraft when the fixed-wing aircraft flies at high speed, so that enough lift force is generated on the wings.
Lift formula of fixed wing
Figure BDA0003511284210000111
Knowing the wing lift FLifting of waterCoefficient of lift CyThe air density rho and the wing area S are in direct proportion, and the air density rho and the wing area S are in direct proportion to the square of the relative air flow velocity v. Therefore, under the condition of certain air density and wing area, the lift coefficient C can be improved by increasing the lift coefficient C most effectively and increasing the incidence angle by increasing the relative airflow velocity vyBut the maximum angle of attack should be less than the critical angle of attack. The maximum relative airflow speed of the scheme can exceed the maximum jet speed of the power device after being subjected to speed change by the jet device, the maximum flight speed of the aircraft is smaller than the maximum jet speed of the power device, and the take-off speed of the conventional fixed wing aircraft is only about 1/4 of the maximum flight speed, so that the maximum lifting/lowering lift force obtained by the scheme can exceed the fixed wing aircraft with the same power by several times and exceeds the rotor helicopter with the same power by ten times, and the maximum lifting/lowering lift force is greatly increasedThe lifting distance is shortened, and the lifting is easy.
And guiding the airflow flowing through the upper surface and the lower surface of the wing to the lower part of the aircraft by adjusting a trailing edge flap, an aileron or a guide plate on the wing of the aircraft, as shown in figure 3. According to the Newton's third law F ═ F', the acting force and the reacting force are equal in size and opposite in direction, the reacting force for guiding the high-speed airflow below the aircraft further increases the upward lift force and the backward push-pull force applied to the aircraft, the forward reacting thrust generated by the high-speed airflow ejected backwards by the power device or the air jet device is balanced while the aircraft is pushed to overcome the gravity, and the accelerator or the electric door is operated to enable the aircraft to vertically take off, land or hover. When the lift force is greater than the gravity, the lifting device rises, when the lift force is equal to the gravity, the lifting device hovers, and when the lift force is less than the gravity, the lifting device falls.
When the aircraft needs to climb or fly horizontally, the trailing edge flaps, ailerons or guide plates on the wings are gradually retracted, high-speed airflow flowing through the upper and lower surfaces of the wings is guided to the rear lower part or the rear part, as shown in fig. 4, the aircraft is pushed to overcome gravity, meanwhile, the aircraft is pushed to fly forwards or climb forwards by means of forward reaction thrust generated by high-speed airflow sprayed backwards by a power device or an air spraying device, and the accelerator or an electric door is operated to enable the aircraft to realize low-speed flight or high-speed flight.
The upper surface of the wing is one or more convex surfaces, the wing with one convex surface on the upper surface is called a traditional single convex wing, and the wing with a plurality of convex curved surfaces on the upper surface along the airflow direction is called a multi-convex wing, as shown in fig. 5; the multi-convex wings can be fused with the fuselage, the multi-convex wings are arranged at the top of the fuselage to provide power for lift force and pitching maneuver, the multi-convex wings are arranged at two sides of the fuselage to provide power for rolling, yawing, steering and translation maneuver, and the multi-convex wings are arranged at the tail to provide air braking resistance; and a power device or an air injection device is arranged between the two convex surfaces of the multi-convex wing, as shown in figure 12, and is used for controlling the air injection speed and angle according to flight control requirements.
The jet device can be a pipeline or a duct and comprises a nozzle, the jet device transfers the high-speed airflow generated by the power device to the front of the wing, the nozzle can be a binary vector structure, the direction and the sectional area of the air outlet can be adjusted to change the speed and the direction of the airflow, and the high-speed airflow is controlled to be sprayed to the wing according to the flight control requirement, as shown in figure 6;
the jet device is movably connected with the wings, when the aircraft reaches a sufficient speed, the jet device can be closed and retracted to be integrated with the wings, the power device directly jets air backwards to propel the aircraft, the wings and air move relatively at a high speed, and aerodynamic lift force is generated on the wings, as shown in figure 7.
During flying, especially during low-speed flying, vertical take-off and landing and hovering, partial high-speed airflow provided by the power device can be sprayed to the tail wing of the aircraft through the air spraying device, the airflow direction is adjusted through the aileron or the control surface, the aircraft is stabilized, and power for pitching, rolling, yawing, steering and translating maneuvering is provided for the aircraft.
Embodiment 2 non-tail wing distributed power layout spray wing type full-speed global vertical take-off and landing fixed wing aircraft embodiment
As shown in fig. 8, the fixed-wing aircraft with jet-wing type full-speed universe vertical take-off and landing consists of wings, a fuselage, a landing gear, an operating system, a power device, a jet device and the like, wherein the jet device is installed at the front end of the wings and connected with the wings, and high-speed airflow generated by the power device is jetted to the wings through the jet device, so that the wings are in high-speed relative airflow, and the stress condition of the wings in static or low-speed motion is similar to that of the fixed-wing aircraft in high-speed flight, thereby generating enough lift force on the wings.
Lift formula of fixed wing
Figure BDA0003511284210000131
Knowing the wing lift FLifting of wineCoefficient of lift CyThe air density rho and the wing area S are in direct proportion, and the air density rho and the wing area S are in direct proportion to the square of the relative air flow velocity v. Therefore, under the condition of certain air density and wing area, the lift coefficient C can be improved by increasing the relative airflow speed v most effectively and increasing the attack angleyBut the maximum angle of attack should be less than the critical angle of attack. The maximum relative air speed of the scheme can exceed the maximum air injection speed of the power device after being changed by the air injection device, and the maximum flight of the aircraftThe speed is less than the maximum jet speed of the power device, and the take-off speed of the conventional fixed wing aircraft is only about 1/4 of the maximum flight speed, so that the maximum take-off/landing lift force obtained by the scheme exceeds the fixed wing aircraft with the same power by multiple times and exceeds the rotor helicopter with the same power by tens of times, the take-off and landing distance is greatly shortened, and the take-off and landing are easy.
And then guiding the airflow flowing through the upper and lower surfaces of the wing to the lower part of the aircraft by adjusting a trailing edge flap, an aileron or a guide plate on the wing of the aircraft, wherein the acting force and the reacting force are equal and opposite according to a Newton's third law F', the reacting force guiding the high-speed airflow below the aircraft further increases the upward lifting force and the backward push-pull force applied to the aircraft, the forward reacting thrust generated by the high-speed airflow ejected backwards by a power device or an air injection device is balanced while the aircraft is pushed to overcome the gravity, and the air injection speed and the air injection amount are adjusted by operating an accelerator or an electric door, so that the aircraft can vertically take off and land or hover.
When the aircraft needs to climb or fly horizontally, the trailing edge flaps, ailerons or guide plates on the wings are gradually retracted, high-speed airflow flowing through the upper surface and the lower surface of the wings is guided to the rear lower part or the rear part, the aircraft is pushed to overcome gravity, meanwhile, the aircraft is pushed to fly forwards or climb forwards by means of forward reaction thrust generated by high-speed airflow sprayed backwards by a power device or an air spraying device, and an accelerator or an electric door is operated to adjust air spraying speed and air spraying amount, so that the aircraft can realize low-speed flight or high-speed flight.
The jet device can be a pipeline or a duct and comprises a nozzle, the jet device transfers high-speed airflow generated by the power device to the front of the wing, the nozzle can be a binary vector structure, the direction and the sectional area of the air outlet can be adjusted to change the speed and the direction of the airflow, and the high-speed airflow is controlled to be sprayed to the wing according to flight control requirements;
the jet device is movably connected with the wings, when the aircraft reaches enough speed, the jet device can be closed and retracted to be integrated with the wings, the power device directly jets air backwards to propel the aircraft, and the wings and air move relatively at high speed to generate aerodynamic lift on the wings.
During flying, particularly during low-speed flying, vertical take-off and landing and hovering, part of high-speed airflow provided by the power device can be sprayed to the second wing of the aircraft through the air injection device, the airflow direction is adjusted through the trailing edge flap, the aileron or the control surface, the aircraft is stabilized, the lift force is provided, and power for pitching, rolling, yawing, steering and translating maneuvering is provided for the aircraft.
Embodiment 3 distributed power layout direct-injection wing type full-speed global vertical take-off and landing fixed wing aircraft embodiment
As shown in fig. 9, a fixed-wing jet-wing aircraft with jet-wing type full-speed all-domain vertical take-off and landing comprises wings, a fuselage, an empennage, a landing gear, an operating system, a power device and the like, wherein the power device is distributed power arrangement and is installed at the front end of the wings and connected with the wings, and high-speed airflow generated by the power device is jetted to the wings, so that the wings are always in relative high-speed airflow, and the stress condition of the wings during static or low-speed movement is similar to that of the fixed-wing aircraft during high-speed flight, thereby generating enough lift force on the wings.
Lift formula of fixed wing
Figure BDA0003511284210000141
Knowing the wing lift FLifting of wineCoefficient of lift CyThe air density rho and the wing area S are in direct proportion, and the air density rho and the wing area S are in direct proportion to the square of the relative air flow velocity v. Therefore, under the condition of certain air density and wing area, the lift coefficient C can be improved by increasing the relative airflow speed v most effectively and increasing the attack angleyBut the maximum angle of attack should be less than the critical angle of attack. The maximum relative airflow speed of the scheme can exceed the maximum jet speed of the power device after being subjected to speed change by the jet device, the maximum flight speed of the jet wing type airplane is smaller than the maximum jet speed of the power device, and the takeoff speed of the conventional fixed wing airplane is only about 1/4 of the maximum flight speed, so that the maximum takeoff/landing lift force obtained by the scheme can exceed that of the fixed wing airplane with the same power, and the takeoff and landing distance is shortened.
And guiding the airflow flowing through the upper and lower surfaces of the wing to the lower part of the jet wing aircraft by adjusting a trailing edge flap, an aileron or a guide plate on the whole wing, wherein the acting force and the reacting force are equal and opposite according to a Newton's third law F', the reacting force of the high-speed airflow guided to the lower part of the jet wing aircraft further increases the upward lifting force and the backward push-pull force applied to the jet wing aircraft, the forward reacting thrust generated by the high-speed airflow ejected backwards by a power device or an air jet device is balanced while the jet wing aircraft is pushed to overcome the gravity, and an accelerator or an electric door is operated to adjust the air jet speed and the air jet quantity, so that the jet wing aircraft can vertically take off, land or hover.
When the jet wing aircraft climbs or flies flatly, the trailing edge flaps, ailerons or guide plates on the wings are gradually retracted, high-speed airflow flowing through the upper surface and the lower surface of the wings is guided to the rear lower part or the rear part, the jet wing aircraft is pushed to overcome gravity, meanwhile, the jet wing aircraft is pushed to fly forwards or climb forwards by means of forward reaction thrust generated by high-speed airflow sprayed backwards by a power device or an air spraying device, and an accelerator or an electric door is operated to adjust air spraying speed and air spraying amount, so that the jet wing aircraft can realize low-speed flight or high-speed flight.
The bypass can be arranged on the fan of the power device, so that the flow field is standardized, the air injection speed is increased, and the contribution to the lift force of the airplane is increased.
The power device is movably connected with the wing, the relative position and the relative air injection direction of the power device and the wing can be adjusted through the control device, the included angle between the air injection direction and the wing chord line, namely the attack angle, is controlled within the range of +/-30 degrees, the attack angle is increased, and the lift force is improved. The angle of attack is adjusted to a large value to obtain the optimal lift force during vertical take-off and landing, hovering and low-speed flight, and the angle of attack is adjusted to a small value during high-speed flight, so that the resistance is reduced as much as possible while enough lift force is obtained, as shown in fig. 10.
During flying, especially during low-speed flying, vertical take-off and landing and hovering, high-speed airflow provided by part of the power device can be sprayed to the tail wing or the second wing of the jet wing aircraft, the airflow direction is adjusted through the trailing edge flap, the aileron or the control surface, the jet wing aircraft is stabilized, lift force is provided, and power for pitching, rolling, yawing, steering and translation maneuvering is provided for the jet wing aircraft.
Embodiment 4 jet-wing type full-speed global vertical take-off and landing fixed-wing aerocar embodiment
The jet wing type aircraft can be fused with an automobile into a jet wing type full-speed global vertical take-off and landing fixed wing aerocar. A flying automobile is formed by adding fixed wings, a thrust fan and an air injection device on the automobile. The fixed wing can be a traditional folding single-convex wing, as shown in fig. 11, or a multi-convex wing, as shown in fig. 12. The fixed wing is arranged on the automobile, the thrust fan is preferably arranged at a position close to the power device, and the air injection device is arranged in front of the wing and is movably connected with the wing.
The upper surface of the fixed wing is one or more convex surfaces, the wing with one convex surface on the upper surface is called a traditional single convex wing, and the wing with a plurality of convex curved surfaces on the upper surface along the airflow direction is called a multi-convex wing; the multiple ailerons can be integrated with the body, placed on top of the body to provide power for lift and pitch maneuvers, as shown in fig. 12, and placed on both sides of the body to provide power for roll, yaw, steering, and pan maneuvers.
And a power device or an air injection device or a flow guide rudder device is arranged between the two convex surfaces of the multiple convex wings and is used for controlling the air injection speed and angle according to flight control requirements.
The wing knife device is added at the boundary of the air flow ejected by the air injection device on the wing and is used for preventing the high-pressure air beside from flowing to the low-pressure area of the air flow.
The aerocar can take off and land vertically, can fly at low speed or high speed in the air, can also run on the ground, and can be switched back and forth in a flying or running mode at any time according to requirements. When the vehicle runs on the road, the vehicle can be driven by a power device of the vehicle to run, and the vehicle can also run by the counterforce generated by high-speed air injection of the thrust fan.
When the airplane needs to fly in the air, the fixed wing is unfolded and folded firstly, and then the high-speed airflow generated by the thrust fan is sprayed to the wing from the front of the wing through the air spraying device, so that the wing is always in the relatively high-speed airflow, the stress condition of the wing in the static or low-speed motion is similar to that of the fixed wing airplane in the high-speed flight, and therefore, enough lift force is generated on the wing.
The thrust fan may be provided with a switching damper. When the aerocar needs the thrust fan to provide driving force during running, the air valve is opened, and high-speed airflow generated by the thrust fan is directly sprayed to the rear to provide reaction thrust for the aerocar; when the flying automobile flies, the air valve is closed, the high-speed airflow generated by the thrust fan is guided to the air injection device, and the high-speed airflow is injected to the wings from the front of the wings through the air injection device, so that the lift force and the forward flying thrust are provided for the flying automobile.
By adjusting the trailing edge flaps, ailerons or guide plates on the wings of the flying automobile, airflow flowing through the wings is guided to the lower part of the flying automobile, so that the lifting force and the backward push-pull force of the flying automobile are further increased, the flying automobile is pushed to overcome gravity, and meanwhile, the forward reaction thrust generated by the air jet device when high-speed airflow is ejected backwards to the airplane is balanced. The accelerator or the electric switch is operated to adjust the air injection speed and the air injection quantity, so that the flying automobile can take off and land vertically or hover.
When the aerocar climbs or flies flatly, the trailing edge flaps, ailerons or guide plates on the wings are gradually retracted, the high-speed airflow flowing through the wings is guided to the rear or the rear lower part, the aerocar is pushed to overcome the gravity, and meanwhile, the high-speed airflow is ejected backwards by the air injection device to generate forward reaction thrust to push the aerocar to fly forwards. The throttle or electric switch is operated to adjust the air injection speed and the air injection quantity, so that the flying automobile can fly at low speed or high speed. When the flying automobile reaches a high enough speed, the air injection device can be closed and retracted to be integrated with the wings, the thrust fan directly injects air backwards to push the flying automobile to fly forwards at a high speed, and the wings and air move relatively at a high speed to generate enough lift force on the wings.
Embodiment 5 jet-fin type full-speed global vertical take-off and landing fixed-fin flying ship embodiment
The jet-wing aircraft can be fused with a ship to form a jet-wing full-speed global vertical take-off and landing fixed-wing flying ship. A flight ship is formed by adding fixed wings, a thrust fan and an air injection device on the basis of the ship. The fixed wing can be a traditional folding single-convex wing or a multi-convex wing. The fixed wing is fixed at the top or the bottom of the ship, the thrust fan is preferably arranged at a position close to the power device, and the air injection device is arranged in front of the wing and is movably connected with the wing.
The upper surface of the fixed wing is one or more convex surfaces, the wing with one convex surface on the upper surface is called a traditional single convex wing, and the wing with a plurality of convex curved surfaces on the upper surface along the airflow direction is called a multi-convex wing; the multi-convex wing can be fused with a ship body, the multi-convex wing is arranged at the top of the ship body to provide power for lift force and pitching maneuvering, and the multi-convex wing is arranged at two sides of a vehicle body to provide power for rolling, yawing, steering and translating maneuvering; a power device or an air injection device is arranged between the two convex surfaces of the multi-convex wing and is used for controlling the air injection speed and angle according to flight control requirements; the wing knife device is added at the boundary of the air flow ejected by the air injection device on the wing and is used for preventing the high-pressure air beside from flowing to the low-pressure area of the air flow.
The flying ship can take off and land vertically, can fly at low speed or high speed in the air, can also run in water, and can be switched back and forth in a flying or sailing mode at any time according to requirements. When sailing in water, the ship can drive a propeller to run by a power device of the ship and can also run by the reaction force generated by high-speed air injection of a thrust fan.
When the aircraft needs to fly in the air, the fixed wing is unfolded firstly, and then the high-speed airflow generated by the thrust fan is sprayed to the wing from the front of the wing through the air spraying device, so that the wing is always in the relatively high-speed airflow, the stress condition of the wing in the static or low-speed motion is similar to that of the fixed wing aircraft in the high-speed flight, and sufficient lift force is generated on the wing.
The thrust fan may be provided with a switching damper. When the flight ship needs the thrust fan to provide driving force during running, the air valve is opened, and high-speed airflow generated by the thrust fan is directly sprayed to the rear part to provide reaction thrust for the flight ship; when the flying ship flies, the air valve is closed, the high-speed airflow generated by the thrust fan is guided to the air injection device, and the high-speed airflow is injected to the wing from the front of the wing through the air injection device, so that the lift force and the forward flying thrust are provided for the flying automobile.
By adjusting the trailing edge flaps, ailerons or guide plates on the wings, the airflow flowing through the wings is guided to the lower part of the flight ship, so that the lift force and the backward push-pull force of the flight ship are further increased, the flight ship is pushed to overcome the gravity, and the forward reaction thrust generated by the jet device when jetting high-speed airflow backwards to the airplane is balanced. The throttle or the electric valve is operated to adjust the air injection speed and the air injection amount, so that the flight ship can take off and land vertically or hover.
When the flying ship climbs or flies flatly, trailing edge flaps, ailerons or guide plates on the wings are gradually retracted, high-speed airflow flowing through the wings is guided to the rear or the rear lower part, the flying ship is pushed to overcome gravity, and meanwhile, the high-speed airflow is ejected backwards by the air injection device to generate forward reaction thrust to push the flying ship to fly forwards. The throttle or electric switch is operated to adjust the air injection speed and the air injection amount, so that the flying ship can fly at low speed or high speed. When the flying ship reaches a high enough speed, the air injection device can be closed and retracted to be integrated with the wings, the thrust fan directly injects air backwards to push the flying ship to fly forwards at a high speed, the wings and air move relatively at a high speed, and sufficient lift force is generated on the wings.
Embodiment 6 jet wing type full speed all-domain vertical take-off and landing fixed wing aircraft embodiment
The jet-wing aircraft can be fused with an automobile and a ship into a jet-wing full-speed global vertical take-off and landing fixed-wing aircraft. A fixed wing, a thrust fan, an air jet device and a land driving system are added on the basis of a ship to form a flying device. The fixed wing is installed on the ship, the thrust fan is preferably arranged at a place close to the power device and easy for suction and exhaust, and the air injection device is installed in front of the wing and movably connected with the wing. The fixed wing can be a traditional folding single-convex wing or a multi-convex wing. The aircraft is provided with an operation system which controls the aircraft to switch back and forth in flying, running or navigation modes, so that a novel global all-round vehicle is made, can fly in the sky, can run on the road and can also run in the water.
The upper surface of the fixed wing is one or more convex surfaces, the wing with one convex surface on the upper surface is called a traditional single convex wing, and the wing with a plurality of convex curved surfaces on the upper surface along the airflow direction is called a multi-convex wing; the multi-convex wings can be integrated with the ship body, the multi-convex wings are arranged at the top of the ship body to provide power for lift force and pitching maneuvering, and the multi-convex wings are arranged at two sides of the ship body to provide power for rolling, yawing, steering and translating maneuvering; a power device or an air injection device is arranged between the two convex surfaces of the multi-convex wing and is used for controlling the air injection speed and angle according to flight control requirements; the wing knife device is added at the boundary of the air flow ejected by the air injection device on the wing and is used for preventing the high-pressure air beside from flowing to the low-pressure area of the air flow.
Example 7 jet wing type full speed all-domain vertical take-off and landing multi-wing body fusion aircraft example
The upper surface of the wing has a plurality of convex curved surfaces along the airflow direction, which is called a multi-convex wing, and the airflow flowing through the multi-convex wing generates a plurality of corresponding low-pressure areas, thereby generating a plurality of corresponding aerodynamic lift areas on the wing, as shown in fig. 5.
Fusing multiple convex wings with a fuselage, wherein the multiple convex wings are arranged at the top of the fuselage to provide power for lift force and pitching maneuvering, and the multiple convex wings are arranged at two sides of the fuselage to provide power for rolling, yawing, steering and translating maneuvering; the multiple convex wings are arranged at the tail part and provide air brake resistance. FIGS. 12 to 15.
A power device or an air injection device can be arranged between the two convex surfaces of the multi-convex wing and is used for controlling the air injection speed and angle according to flight control requirements.
A wing knife device can be added at the boundary of the airflow ejected by the air injection device on the wing, and is used for preventing the high-pressure airflow beside the wing from flowing to the low-pressure area of the airflow.
By adjusting the trailing edge flaps, ailerons or guide plates on the wings, the airflow flowing through the wings is guided to the lower part of the multi-convex wing body fusion aircraft, as shown in fig. 13, the lift force and the backward push-pull force of the multi-convex wing body fusion aircraft are further increased, the multi-convex wing body fusion aircraft is pushed to overcome the gravity, and meanwhile, the forward reaction thrust generated by the air jet device when high-speed airflow is ejected backwards to the aircraft is balanced. The throttle or the electric switch is operated to adjust the air injection speed and the air injection quantity, so that the multi-convex-wing body fusion aircraft can take off and land vertically or hover.
When the multi-winged-wing body fusion aircraft climbs or flies flatly, the trailing edge flaps, ailerons or guide plates on the wings are gradually retracted, and the high-speed airflow flowing through the wings is guided to the rear or the rear lower part, as shown in fig. 15, the multi-winged-wing body fusion aircraft is pushed to overcome the gravity, and meanwhile, the multi-winged-wing body fusion aircraft is pushed to fly forwards by means of the forward reaction thrust generated by the high-speed airflow ejected backwards by the air injection device. The throttle or the electric door is operated to adjust the air injection speed and the air injection quantity, so that the multi-convex-wing body fusion aircraft can realize low-speed flight or high-speed flight.
The multi-convex wing is integrated with the machine body, the multi-convex wing is arranged at the top of the machine body to provide lift force, and the front and back air injection quantity, the air injection speed and the angle are controlled to realize pitching maneuver.
The multi-convex wing is arranged at eight positions on two sides of the machine body, and is respectively arranged at eight positions of left front upper position, left front lower position, left rear upper position, left rear lower position, right front upper position, right front lower position, right rear upper position and right rear lower position, and the air injection devices are respectively and independently configured to control the air injection amount and the air injection speed of the eight air injection devices, so that the maneuvering such as rolling, yawing, translation and the like is realized. FIGS. 12 to 15.
When the air injection devices in the four directions of the upper left direction and the lower right direction inject air simultaneously, left rolling is realized; when the air injection devices in the four directions of the upper right and the lower left inject air simultaneously, the right rolling is realized.
When the air injection devices in the four directions of the left front part and the right rear part simultaneously inject air, left steering is realized; when the air injection devices in the four directions of the right front part and the left back part simultaneously inject air, the right steering is realized.
Of course, the left and right air injection amount and speed at the top can be adjusted to realize the yaw of the steering engine.
When the air injection devices in the four directions on the left inject air simultaneously, left translation is realized; when the air injection devices in the four directions on the right simultaneously inject air, the right translation is realized.
The multiple convex wings are arranged at the tail part and provide air brake resistance when air is sprayed to the multiple convex wings.
Based on the fusion technology of the jet wings, the multi-convex wings and the multi-convex wing fuselage of the embodiment, combined with the reality of airplanes, automobiles, steamships, trains, passenger cars, aerospace planes, rockets, cruise missiles and the like, novel aircrafts such as jet wing type full-speed all-domain vertical take-off and landing multi-convex wing fuselage fusion airplanes, flying automobiles, flying steamships, aerocrafts, flying trains, air passenger cars, aerospace planes, pneumatic take-off and recovery rockets, cruise missile-level cruise missiles and the like can be developed.
Example 8 pneumatic rocket example
The existing rocket is mainly pushed to the sky by the reverse thrust of an engine, aerodynamics are not fully utilized in the atmosphere to improve efficiency, in addition, the existing rocket is mostly disposable, only Mask falcon rocket can be partially recycled, but the existing rocket is recovered by the reverse thrust of the engine and also does not fully utilize aerodynamics to improve efficiency, so that the efficiency is low, the cost is high, and the space economy and exploration activities of human are severely limited.
The multi-convex wings are fused with the rocket body, the multi-convex wings are arranged along the axial direction of the rocket body, the multi-convex wings at the upper part provide power for lift force and pitching maneuver, and the multi-convex wings at the two sides of the rocket body or the deflection nozzle direction or the pneumatic control surface provide power for rolling, yawing, steering and translation maneuver, so that the rocket has pneumatic performance. The aerodynamic lift can be generated by means of high-speed airflow flowing through the multiple convex wings, and high-speed airflow sprayed out of an engine is guided to the multiple convex wings to generate aerodynamic lift, so that the aerodynamic lift can play a role efficiently and flexibly in the take-off and recovery processes, the efficiency is improved, and the cost is reduced.
The jet-wing full-speed global vertical take-off and landing aircraft can be built into an aerial launching platform, rocket is supported to the high altitude of about 2-3 ten thousand meters, and then the rocket is accelerated to the maximum speed and separated and launched, so that launching fuel can be greatly saved, effective load is greatly improved, and manned lunar landing mars and other deep space exploration are realized. And a high-voltage cable direct power supply mode can be adopted to provide power for the air launching platform of the jet wing type full-speed global vertical take-off and landing aircraft, so that the jet wing type full-speed global vertical take-off and landing aircraft is environment-friendly.
Referring to fig. 16, the present invention provides a method for controlling a jet-wing full-speed global vertical take-off and landing fixed-wing aircraft, comprising the steps of:
s101, guiding airflow flowing through the wing to the lower part of the aircraft by adjusting a trailing edge flap, an aileron or a guide plate on the wing, pushing the aircraft to overcome gravity, balancing forward reaction thrust generated by a power device or an air injection device when the airflow is ejected backwards to the aircraft, and operating an accelerator or an electric door to adjust air injection speed and air injection amount so that the aircraft can take off and land vertically or hover;
s102, by gradually retracting a trailing edge flap, an aileron or a guide plate on the wing, guiding airflow flowing through the wing to the rear or the rear lower part, pushing the aircraft to overcome gravity, meanwhile, ejecting the airflow backwards by virtue of a power device or an air jet device to generate forward reaction thrust to push the aircraft to fly forwards, and operating an accelerator or a switch to adjust the air jet speed and the air jet quantity so as to enable the aircraft to realize low-speed flight or high-speed flight;
s103, guiding airflow flowing through the wing to the lower part or the front lower part of the aircraft by putting down a trailing edge flap, an aileron or a guide plate on the wing, and operating an accelerator or a switch to adjust the air injection speed and the air injection amount to enable the aircraft to decelerate to a vertical take-off and landing or hovering state by means of air resistance or reverse air injection;
s104, spraying partial airflow provided by the power device to an empennage or a second wing of the aircraft through the air injection device, adjusting the airflow direction through a flap, an aileron or a control surface, stabilizing the aircraft, and providing power for pitching, rolling, yawing, steering and translating maneuvering for the aircraft;
s105, adjusting the relative position and the relative air injection direction of the air injection device and the wing through the control device, adjusting the included angle between the airflow direction and the wing, and adjusting the ratio of the air injection amount of the upper surface and the lower surface of the wing to realize the adjustment of the attack angle and the optimal flight state;
s106, fusing a plurality of convex wings and the airframe, wherein the plurality of convex wings are arranged at the top of the airframe to provide lift force, and simultaneously controlling the front and back jet flow, the jet speed and the jet angle to realize pitching maneuvering; the multi-convex wing is arranged at eight positions at two sides of the machine body, and is respectively provided with eight positions, namely a left front upper position, a left front lower position, a left rear upper position, a left rear lower position, a right front upper position, a right front lower position, a right rear upper position and a right rear lower position, and is respectively and independently provided with an air injection device or a flow guide device, so that the air injection amount and the air injection speed of the eight air injection devices are controlled, and the rolling, yawing and translating maneuvers are realized;
s107, when the fixed wing aircraft reaches a set speed, a whole-body flight mode can be selected, the air injection device is closed and retracted to be integrated with the wings, the fixed wing aircraft is directly pushed to fly forwards by injecting air backwards through the thrust fan, the wings and the air move relatively, aerodynamic lift is set on the wings, and stable flight is achieved.
In this embodiment, the operation flow of the control method for the jet-wing full-speed all-domain vertical take-off and landing fixed-wing aircraft is the same as the flow of the jet-wing full-speed all-domain vertical take-off and landing fixed-wing aircraft provided by the present invention, and therefore, the description thereof is omitted here.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

Claims (10)

1. An aircraft multi-convex wing is characterized in that the upper surface of the wing is provided with a plurality of convex curved surfaces along the airflow direction, namely the multi-convex wing, and airflow flowing through the multi-convex wing generates a plurality of corresponding low-pressure areas so as to generate a plurality of corresponding aerodynamic lift areas on the wing.
2. A multi-convex wing body fusion aircraft is characterized in that a plurality of convex wings and an aircraft body are fused into a whole; the multi-convex wings arranged at the top of the machine body provide power for lift force and pitching maneuvering, and the multi-convex wings arranged at the two sides of the machine body provide power for rolling, yawing, steering and translating maneuvering; the multiple convex wings are arranged at the tail part and provide air brake resistance.
3. A jet wing type full-speed global vertical take-off and landing fixed wing aircraft comprises wings, a fuselage, a landing gear, an operating system and a power device, and is characterized in that airflow generated by the power device is jetted to the wings from the front of the wings through a jet device, or airflow generated by the power device is directly jetted to the wings from the front of the wings, so that the wings are always in opposite airflow, and a set aerodynamic lift force is generated on the wings; the wings are any one or combination of multi-convex wings, traditional single-convex wings and flying wing layout wings; the upper surface of the traditional single convex wing only has one convex curved surface, and is a common wing type.
4. The wing-spraying type full-speed all-domain vertical take-off and landing fixed-wing aircraft as claimed in claim 3, wherein the air spraying device comprises a duct, a nozzle and a valve, the number of the air spraying devices is one or more, the air spraying devices are installed in front of the wings and movably connected with the wings, the airflow generated by the power device is transferred to the front of the wings through the duct, the relative positions and the relative air spraying directions of the air spraying devices and the wings are adjusted through an operating system, and the airflow is controlled to be sprayed to the wings from the front of the wings through the nozzle according to flight control requirements; the wing knife device is added at the boundary of the air flow ejected by the air injection device on the wing and is used for preventing the high-pressure air beside from flowing to the low-pressure area of the air flow.
5. The jet-wing full-speed global vertical take-off and landing fixed wing aircraft according to claim 3, wherein the power device is any one of or a combination of a turbojet, a turbofan, a turboprop, a turboshaft engine or a piston-propeller fan engine, an electric fan, an electric propeller fan and a high-pressure gas cylinder; the layout form of the power device is any one of a centralized power device and a distributed power device or the combination of the centralized power device and the distributed power device.
6. The jet-wing full-speed global vertical take-off and landing fixed-wing aircraft according to claim 3, wherein the aircraft is any one of an airplane, a flying automobile, a flying ship, a flying device, a flying train, an airbus, an aerospace plane, a pneumatic take-off and recovery rocket, a cruise missile or a cruise missile.
7. The jet-wing full-speed global vertical take-off and landing fixed-wing aircraft as claimed in claim 6, wherein a flying automobile is formed by adding fixed wings, a thrust fan and a jet device on the automobile, the fixed wings are installed on the automobile, and the jet device is installed in front of the wings and movably connected with the wings; the fixed wing is any one or combination of a traditional folding single-convex wing or a multi-convex wing; the thrust fan is provided with a switching valve, and the aerocar is provided with an operation system, so that the flying mode and the running mode can be switched.
8. The jet-vane type full-speed global vertical take-off and landing fixed-wing aircraft as claimed in claim 6, wherein a flight ship is formed by adding fixed wings, a thrust fan and an air jet device on the basis of the ship, the fixed wings are installed on the ship, and the air jet device is installed in front of the wings and movably connected with the wings; the fixed wing is any one or combination of a traditional folding single-convex wing or a multi-convex wing; the thrust fan is provided with a switching valve, and the flight ship is provided with an operation and control system and has a flight mode and a running mode.
9. The jet-wing full-speed all-domain vertical take-off and landing fixed-wing aircraft as claimed in claim 6, wherein a fixed wing, a thrust fan, an air jet device and a land driving system are added on the basis of a ship to form a flying device; the fixed wing is arranged on the ship, and the air injection device is arranged in front of the wing and is movably connected with the wing; the fixed wing is any one or combination of a traditional folding single-convex wing or a multi-convex wing; the thrust fan is provided with a switching valve, and the aircraft is provided with an operation system for controlling the aircraft to switch back and forth in a flying, running or sailing mode.
10. A method for controlling a jet-wing full-speed all-domain vertical take-off and landing fixed-wing aircraft according to any one of claims 3 to 9, comprising the steps of:
by adjusting a trailing edge flap, an aileron or a guide plate on the wing, airflow flowing through the wing is guided to the lower part of the aircraft, the forward reaction thrust generated by the power device or the air injection device when the airflow is ejected backwards to the aircraft is balanced while the aircraft is pushed to overcome gravity, and an accelerator or an electric door is operated to adjust the air injection speed and the air injection amount, so that the aircraft can take off and land vertically or hover;
the air current flowing through the wings is guided to the rear or the rear lower part by gradually retracting the trailing edge flaps, ailerons or guide plates on the wings, the aircraft is pushed to overcome the gravity, meanwhile, the power device or the air injection device is used for ejecting the air current backwards to generate forward reaction thrust to push the aircraft to fly forwards, and the throttle or the electric switch is operated to adjust the air injection speed and the air injection quantity, so that the aircraft can fly at low speed or high speed;
the trailing edge flaps, ailerons or guide plates on the wings are put down, airflow flowing through the wings is guided to the lower part or the front lower part of the aircraft, and an accelerator or an electric switch is operated to adjust the air injection speed and the air injection amount, so that the aircraft can be decelerated to a vertical take-off and landing or hovering state by means of air resistance or reverse air injection;
part of airflow provided by the power device is sprayed to the empennage or the second wing of the aircraft through the air spraying device, the airflow direction is adjusted through a flap, an aileron or a control surface, the aircraft is stabilized, and power for pitching, rolling, yawing, steering and translation maneuvering is provided for the aircraft;
the relative position and the relative air injection direction of the air injection device and the wing are adjusted through the control device, the included angle between the airflow direction and the wing is adjusted, and the air injection quantity ratio of the upper surface and the lower surface of the wing is adjusted, so that the adjustment of the attack angle and the optimal flight state are realized;
the multi-convex wing is fused with the machine body, the multi-convex wing is arranged at the top of the machine body to provide lift force, and the front and back air injection quantity, the air injection speed and the angle are controlled to realize pitching maneuver; the multi-convex wing is arranged at eight positions on two sides of the machine body, and is respectively provided with eight positions, namely a left front upper position, a left front lower position, a left rear upper position, a left rear lower position, a right front upper position, a right front lower position, a right rear upper position and a right rear lower position, and is respectively and independently provided with an air injection device or a flow guide device, so that the air injection quantity and the air injection speed of the eight air injection devices are controlled, and the rolling, yawing and translation maneuvering is realized; the multiple convex wings are arranged at the tail part and provide air brake resistance.
When the fixed wing aircraft reaches a set speed, an integral flying mode can be selected, the air injection device is closed and retracted to be integrated with the wings, the fixed wing aircraft is pushed to fly forwards by directly injecting air backwards through the thrust fan, the wings and air move relatively, a set aerodynamic lift force is generated on the wings, and stable flying is realized.
CN202210152867.3A 2022-02-18 2022-02-18 Jet wing type full-speed global vertical take-off and landing fixed wing aircraft and control method Pending CN114701640A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116186904A (en) * 2023-04-14 2023-05-30 北京舯迦科技有限公司 Mechanical overall aerodynamic layout method with lifting surface moving in fluid

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116186904A (en) * 2023-04-14 2023-05-30 北京舯迦科技有限公司 Mechanical overall aerodynamic layout method with lifting surface moving in fluid

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