CN110053767B - Variable-wing type vertical take-off and landing aircraft - Google Patents
Variable-wing type vertical take-off and landing aircraft Download PDFInfo
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- CN110053767B CN110053767B CN201910442031.5A CN201910442031A CN110053767B CN 110053767 B CN110053767 B CN 110053767B CN 201910442031 A CN201910442031 A CN 201910442031A CN 110053767 B CN110053767 B CN 110053767B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/32—Blade pitch-changing mechanisms mechanical
- B64C11/34—Blade pitch-changing mechanisms mechanical automatic
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
Abstract
The invention relates to a variable-wing type vertical take-off and landing aircraft, which has the characteristics of both fixed-wing aircraft and rotor-type aircraft, and integrates the advantages of the fixed-wing aircraft and the rotor-type aircraft.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a variable-wing type vertical take-off and landing aircraft.
Background
Many airplanes in the world can not take off and land vertically, long runway or water surface are needed for taking off and landing, but the airplanes capable of taking off and land vertically have too large energy consumption in the process of taking off and landing, even can not take off under full load or are inflexible in the process of taking off and landing, so that the airplanes are not safe and reliable enough, popularization and application of the airplanes are restricted, and therefore, the airplanes are always high things in the market, and the ordinary people are difficult to purchase, park and maintain.
Disclosure of Invention
The invention aims to provide a variable-wing type vertical take-off and landing aircraft, which has the characteristics of both a fixed-wing aircraft and a rotor-wing type aircraft.
The technical scheme of the invention is as follows: the utility model provides a but become wing type vertical take-off and landing aircraft, but, component element includes main rotor, circular fixed wing, traction screw, fuselage, left and right fin, afterbody anti-moment of torsion screw and wheeled undercarriage, component element's concrete structure and relation of connection are:
the main rotor is formed by three or more than three blades of wings, the wings can control deflection angles like a main rotor of a common helicopter, or the wings can deflect automatically by utilizing torsion of a shaft to a certain angle, in order to enable the wings to deflect, certain gaps are formed between the wings and the rotating head, certain chamfers are formed between the wings, the main rotor is connected with a fuselage like a main rotor of the common single main rotor helicopter, the traction screw is rotatably connected with the fuselage through a shaft, the left tail wing and the right tail wing are connected with the two sides of the tail of the fuselage like a left main rotor helicopter, the tail anti-torque screw is connected with the upper side of the tail of the fuselage like a common single main rotor helicopter, the wheel type landing gear is connected with the fuselage like a fixed wing helicopter, when the deflection angle of the wings reaches 0 DEG, the main rotor is changed into a round cake shape or a round pot shape into a part of the fixed wing or a fixed wing of the helicopter, at the moment, the round fixed wing is called round fixed wing, the round helicopter can vertically take off, land and land like the common single main rotor, the operation control is the same when the traction screw is in a state of a round helicopter, the left tail of the aircraft and the single helicopter is in a stable state, and the state when the traction screw is in a stable state when the traction screw is in a state, and the single helicopter is in a stable state, and the state when the single helicopter is in a stable state, and the state is in a stable state, and in a state.
The variable-wing type vertical take-off and landing aircraft comprises a left main rotor wing and a right main rotor wing, wherein the constituent elements comprise main rotors, round fixed wings, a traction propeller, a machine body, left tail wings, right tail wings and wheel type landing gear, the number of the main rotors is two, the main rotors are respectively arranged on two sides of the machine body, and the concrete structures and the connection relations of the constituent elements are as follows:
the main rotor 1 is composed of three or more blades, the deflection angle of the blades can be controlled like a main rotor of a common helicopter, or the blades can be deflected automatically by a certain angle by utilizing the torsion of a shaft, in order to enable the blades to deflect, a certain gap is formed between the blades and the rotating head, a certain chamfer is formed between the blades, the main rotor is connected with a fuselage like the main rotor of the common left and right double-main rotor helicopter, the traction rotor is rotatably connected with the fuselage through a shaft, the left and right tail wings are connected with both sides of the fuselage like a left and right main fixed wing aircraft, the wheel landing gear is connected with the fuselage like a fixed wing aircraft, when the deflection angle of the blades reaches 0 ℃, the main rotor is changed into a round cake shape or a round pot shape into a part of the fixed wing or the fixed wing of the aircraft, the round fixed wing is called round fixed wing, the left and right double-main rotor aircraft vertically takes off, and when the round double-main rotor is in the same operation control with the common left and right double-main rotor aircraft, the traction rotor is not moved, and takes off, flies, slides, and runs on the left and right main wings and is in the same operation control state when the round main wing is in the round state.
The circular fixed wings are two types, one is a circular fixed wing which utilizes the torsion force of the shaft part to automatically control the deflection angle of the propeller wing, and the other is a circular fixed wing which can control the deflection angle like a common helicopter.
The specific structure and connection relation of the circular fixed wing for automatically controlling the deflection angle of the paddle wing by utilizing the torsion of the shaft part are as follows: the shaft part is in loose fit connection with the rotating head, the paddle wings extend into the rotating head through the wing roots and are movably connected with the rotating head, gear teeth are arranged between 0-45 degrees at the end parts of the wing roots and are matched with a gear disc arranged on the shaft part, when the shaft part starts or rotates in an accelerating mode, the gear disc rotates along with the gear disc, the wing roots and the paddle wings are driven to deflect for 0-45 degrees together under the action of inertia and reverse torque, the circular fixed wings become propellers, and when the gear disc and the wing roots reach the deflection limit, the propellers rotate along with the shaft part; the shaft part is connected with the lower end cover through the reset spring, the lower end cover is in tight fit connection with the rotating head, the lower end cover is in loose fit connection with the shaft part, when the shaft part is decelerated or stopped to rotate, the inclined transmission angle of the propeller wing is reset to 0 degree through the force transmission of the gear disc and the gear teeth of the wing root under the action of the reset spring, and the propeller is changed to a circular fixed wing in a disc or circular pot shape, so that automatic conversion between the propeller and the circular fixed wing can be realized, namely the propeller rotates and the circular fixed wing stops rotating.
The specific structure and the connection relation of the circular fixed wing which can control the deflection angle like a common helicopter are as follows: the shaft part tight fit is connected with the rotating head tight fit, the oar wing end part of the rotating head is provided with a wing lug, the oar wing extends into the rotating head through a wing root and is movably connected with the rotating head, the wing root end part is provided with a fixed ring so as to prevent the oar wing from being separated from the rotating head due to centrifugal action, the rotating head is provided with an upper end cover so as to be assembled, the shaft root is provided with a bearing, the bearing outer ring is provided with an outer ring connecting rod, the wing lug is movably connected with the bearing outer ring connecting rod through the wing lug connecting rod, and the bearing inner ring is not contacted with the shaft part, so that the transformation between the circular fixed wing and the propeller can be realized only by controlling the bearing inner ring to move up and down.
The circular fixed wings are round cakes or round pot shapes, the circular fixed wings are composed of three or more leaves of wings and rotor heads, each wing is divided into an odd wing and an even wing, the structure, the shape, the weight and the size of each wing of the odd wing are the same, each wing of the even wing is two wings which are symmetrical by taking the round cakes as the center, the two symmetrical wings are the same in structure, the shape, the weight and the size, in order to enable the wings to deflect, a certain gap is reserved between each wing and each rotating head, a certain chamfer is reserved between each wing and each wing, each rotor head comprises a rotating head, a lower end cover, a reset spring, a gear disc, gear teeth, a shaft part, a fixed ring, a wing ear connecting rod, an outer ring connecting rod, a bearing inner ring connecting rod and an upper end cover, and the structure and the connection relation of each rotor head are determined according to the circular fixed wings which can control the deflection angle of the wings by utilizing the torsion of the shaft part or the circular fixed wings which can control the deflection angle like a common helicopter.
The invention has the outstanding advantages that:
1. a main rotor propeller used for vertical take-off and landing of an aircraft becomes a fixed wing or a part of a fixed wing of the aircraft during flight or gliding, and can provide lift even if the main rotor propeller does not rotate during flight or gliding of the aircraft.
2. The main rotor propeller mainly comprises three or more than three blades, the deflection angle of the blades can be controlled like a main rotor of a common helicopter, when the deflection angle of the blades reaches 0 DEG, the main rotor 1 is changed from a rotor in a propeller shape into a cake shape or a round pot shape into a fixed wing or a part of a fixed wing of the plane, and the round fixed wing is called a round fixed wing.
3. The aircraft can be designed to adopt a battery electric drive or fuel power drive mode according to the size and the application of the aircraft, and can also adopt a proper rotation mode according to the aircraft body space.
6. The aircraft of the invention can select a proper tractor according to the speed required by the aircraft.
The fixed wing refers to a wing with small shape change and small deflection angle during the flight or gliding of an airplane.
Drawings
Fig. 1-1 is a perspective view of a single main rotor aircraft of a variable wing vertical takeoff and landing aircraft according to the present invention.
Fig. 1-2 are right side views of a single main rotor aircraft of a variable wing vertical takeoff and landing aircraft according to the present invention.
Fig. 1-3 are perspective views of a single main rotor aircraft of a variable wing vertical takeoff and landing aircraft according to the present invention in flight or glide.
Fig. 1-4 are right side views of a single main rotor aircraft of a variable wing vertical take-off and landing aircraft according to the present invention in flight or glide.
Fig. 2-1 is a top view of a wing-variable type vertical takeoff and landing aircraft of the present invention when the wing-variable type vertical takeoff and landing aircraft is taking off.
Fig. 2-2 is a right side view of a wing-variable type vertical take-off and landing aircraft of the present invention when the wing-variable type vertical take-off and landing aircraft is taking off.
Fig. 2-3 are top views of a variable-wing vertical takeoff and landing aircraft of the present invention when the aircraft is flying or gliding.
Fig. 2-4 are right side views of a variable-wing vertical takeoff and landing aircraft of the present invention when the aircraft is flying or gliding.
Fig. 3-1 is a top view of a circular fixed wing.
Fig. 3-2 is a schematic view of the central portion of a circular fixed wing with the deflection angle of the wing automatically controlled by the torsion of the shaft portion.
Fig. 3-3 are schematic diagrams of the configuration of the blade root gear teeth of the circular fixed blade and the shaft gear disc in cooperation with each other by utilizing the shaft torsion to automatically control the deflection angle of the blade.
Fig. 3-4 are schematic structural views of a circular fixed wing airfoil for controlling the angle of deflection of the airfoil as in a conventional helicopter.
Fig. 3-5 are schematic illustrations of the central portion of a circular fixed wing airfoil for controlling the angle of deflection of the airfoil as in a conventional helicopter.
Marked in the figure as: the main rotor wing 1, the circular fixed wing 2, the traction propeller 3, the fuselage 4, the left tail wing 5, the right tail wing 5, the tail anti-torque propeller 6 and the wheel landing gear 7. The rotating head 1-1, the paddle wing 1-2, the lower end cover 1-3, the reset spring 1-4, the gear disc 1-5, the wing root gear teeth 1-6, the shaft part 1-7, the fixed ring 1-8, the wing ear connecting rod 1-9, the bearing outer ring connecting rod 1-10, the bearing inner ring connecting rod 1-11, the upper end cover 1-12, the wing root 1-2-1 and the wing ear 1-2-2,
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings and examples. The following examples are illustrative of the invention but are not intended to limit the scope of the invention.
It should be noted that, in the description of the present invention, unless explicitly specified and limited otherwise, the terms "connected" and "connected" are to be construed broadly, and for example, they may be fixedly connected, or they may be detachably connected, or they may be integrally connected, or they may be mechanically connected, or they may be electrically connected; either directly or indirectly via an intermediary. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
Example 1
The variable-wing type vertical take-off and landing aircraft structure has the characteristics of both fixed-wing aircraft and rotor wing type aircraft.
As shown in fig. 1-1 to 3-5, the single main rotor aircraft of the variable wing type vertical take-off and landing aircraft according to the present invention comprises main rotor 1, circular fixed wing 2, traction propeller 3, fuselage 4, left and right tail wing 5, tail anti-torque propeller 6 and wheel landing gear 7. The specific structure and connection relation of the component elements are as follows:
the main rotor 1 is connected with the fuselage 4 like a main rotor of a common single main rotor helicopter, the traction screw 3 is rotatably connected with the fuselage 4 through a shaft, the left tail wing 5 and the right tail wing 5 are connected on two sides of the tail of the fuselage 4 like a left main fixed wing helicopter, the tail anti-torque screw 6 is connected with the upper side of the tail of the fuselage 4 like a common single main rotor helicopter, and the wheel landing gear 7 is connected with the fuselage 4 like a fixed wing helicopter. When the rotor deflection angle reaches 0 °, the main rotor 1 is changed from a rotor with a propeller shape into a cake shape or a round pot shape into a fixed wing or a part of a fixed wing of an aircraft, which is called a round fixed wing 2.
The circular fixed wing is in a round cake or round pot shape, the circular fixed wing consists of three or more blades and a rotor head, the blades are divided into odd blades and even blades, the structure, the shape, the weight and the size of each blade of the odd blades are the same, the even blades are two blades which are symmetrical by taking the round cake as the center, the symmetrical two blades are the same in structure, the shape, the weight and the size, in order to enable the blades to deflect, a certain gap is reserved between the blades and the rotating head, a certain chamfer is reserved between the blades and the blades, the rotor head comprises a rotating head 1-1, a lower end cover 1-3, a reset spring 1-4, a gear disc 1-5, gear teeth 1-6, a shaft part 1-7, a fixed ring 1-8, a wing ear connecting rod 1-9, an outer ring connecting rod 1-10, a bearing inner ring connecting rod 1-11 and an upper end cover 1-12, and the structure and the connection relation of the rotor head are the circular fixed wing which can automatically control the deflection angle of the blades according to the torsion of the shaft part or the circular fixed wing which can control the deflection angle like a common helicopter.
The circular fixed wings are two types, one is a circular fixed wing which utilizes the torsion force of the shaft part to automatically control the deflection angle of the propeller wing, and the other is a circular fixed wing which can control the deflection angle like a common helicopter.
The specific structure and connection relation of the circular fixed wing for automatically controlling the deflection angle of the paddle wing by utilizing the torsion of the shaft part are as follows: the shaft part 1-7 is in loose fit connection with the rotating head 1-1, the paddle wings extend into the rotating head 1-1 through the wing roots 1-2-1 and are movably connected with the rotating head, gear teeth 1-6 are arranged between 0-45 degrees at the end parts of the wing roots, the gear teeth 1-6 are matched with a gear disc 1-5 arranged on the shaft part, when the shaft part starts or accelerates to rotate, the gear disc 1-5 also rotates, the wing roots gear teeth 1-6 and the paddle wings are driven to deflect by 0-45 degrees together due to the action of inertia and reverse torque, the circular fixed wings become propellers, and when the gear disc 1-5 and the wing roots gear teeth 1-6 reach the deflection limit and can not deflect any more, the propellers rotate along with the shaft part 1-7; the shaft part 1-7 is connected with the lower end cover 1-3 through the reset spring 1-4, the lower end cover 1-3 is in tight fit connection with the rotating head 1-1, the lower end cover 1-3 is in loose fit connection with the shaft part 1-7, when the shaft part 1-7 is decelerated or stops rotating, the propeller is turned back to 0 degree through the force conduction between the gear disc 1-5 and the wing root gear teeth 1-6 due to the rotation inertia of the propeller or the effect of the reset spring 1-4, and the propeller turns back to a circular fixed wing in a disc shape or a round pot shape, namely the propeller is turned, and the circular fixed wing is turned down.
The specific structure and the connection relation of the circular fixed wing which can control the deflection angle like a common helicopter are as follows: the rotating head 1-1 is in tight fit connection with the shaft part 1-7, the blade end part of the rotating head 1-1 is provided with a blade lug 1-2-2, the blade lug extends into the rotating head 1-1 through a blade root and is movably connected with the rotating head 1-1, the end part of the blade root is provided with a fixed ring 1-8 so as to prevent the blade lug from being separated from the rotating head 1-1 due to centrifugal action, the rotating head 1-1 is provided with an upper end cover 1-12 so as to be assembled, the shaft root is provided with a bearing, the bearing outer ring is provided with a bearing outer ring connecting rod 1-10, the blade lug 1-2-2 is movably connected with the bearing outer ring connecting rod 1-10 through a blade lug connecting rod 1-9, and the bearing inner ring 1-11 is not contacted with the shaft part, so that the transformation between the circular fixed blade and the propeller can be realized only by controlling the bearing inner ring 1-11 to move up and down.
The structure of the single-main-rotor aircraft is basically the same as that of a common single-main-rotor aircraft when taking off, except that the aircraft is provided with a plurality of traction propellers 3 and left and right tail wings 5, which are arranged for enabling the aircraft to fly quickly after being converted into a fixed-wing aircraft, and the shape of the single-main-rotor aircraft when flying or gliding is basically the same as that of the common single-main-rotor aircraft, except that the main wings of the single-main-rotor aircraft are changed from the single main-rotor aircraft to form circular fixed wings 2, as shown in figures 1 to 3. The operation control of the single main wing aircraft is the same as that of a common single main wing aircraft during vertical take-off and landing, at the moment, the traction screw propeller 3 and the left and right tail wings 5 are not moved, and the operation control of the single main wing aircraft is the same as that of a common single main fixed wing aircraft during running take-off, flying and gliding landing, at the moment, the single main wing is in a circular fixed wing state, and the tail anti-torque screw propeller 6 is in a braking state, so that the aircraft reaches a stable state.
Example 2
As shown in fig. 2-1 to 3-5, the left and right double main rotor wing aircraft of the variable wing type vertical take-off and landing aircraft according to the present invention comprises main rotor wings 1, circular fixed wings 2, traction propellers 3, a fuselage 4, left and right tail wings 5 and wheel landing gear 7. Embodiment 2 differs from embodiment 1 in that the number of main rotors 1 in this embodiment is two, and the main rotors are respectively installed on two sides of the fuselage; and no tail anti-torque propeller 6, the specific structure and connection relation of the component elements are as follows:
the two main rotor wings 1 are arranged, the two main rotor wings 1 are respectively arranged at the left side and the right side of the machine body 4 like a left main rotor wing airplane and a right main rotor wing airplane, the traction screw propeller 3 is rotatably connected with the machine body 4 through a shaft, the left tail wing 5 and the right tail wing 5 are connected at the two sides of the machine body 4 like a left main fixed wing airplane and a right main fixed wing airplane, and the wheel type landing gear 7 is connected with the machine body 4 like a fixed wing airplane. When the rotor deflection angle reaches 0 °, the main rotor 1 is changed from a rotor with a propeller shape into a cake shape or a round pot shape into a fixed wing or a part of a fixed wing of an aircraft, which is called a round fixed wing 2.
The circular fixed wing is in a round cake or round pot shape, the circular fixed wing consists of three or more blades and a rotor head, the blades are divided into odd blades and even blades, the structure, the shape, the weight and the size of each blade of the odd blades are the same, the even blades are two blades which are symmetrical by taking the round cake as the center, the symmetrical two blades are the same in structure, the shape, the weight and the size, in order to enable the blades to deflect, a certain gap is reserved between the blades and the rotating head, a certain chamfer is reserved between the blades and the blades, the rotor head comprises a rotating head 1-1, a lower end cover 1-3, a reset spring 1-4, a gear disc 1-5, gear teeth 1-6, a shaft part 1-7, a fixed ring 1-8, a wing ear connecting rod 1-9, an outer ring connecting rod 1-10, a bearing inner ring connecting rod 1-11 and an upper end cover 1-12, and the structure and the connection relation of the rotor head are the circular fixed wing which can automatically control the deflection angle of the blades according to the torsion of the shaft part or the circular fixed wing which can control the deflection angle like a common helicopter.
The circular fixed wings are two types, one is a circular fixed wing which utilizes the torsion force of the shaft part to automatically control the deflection angle of the propeller wing, and the other is a circular fixed wing which can control the deflection angle like a common helicopter.
The specific structure and connection relation of the circular fixed wing for automatically controlling the deflection angle of the paddle wing by utilizing the torsion of the shaft part are as follows: the shaft part 1-7 is in loose fit connection with the rotating head 1-1, the paddle wings extend into the rotating head 1-1 through the wing roots 1-2-1 and are movably connected with the rotating head, gear teeth 1-6 are arranged between 0-45 degrees at the end parts of the wing roots, the gear teeth 1-6 are matched with a gear disc 1-5 arranged on the shaft part, when the shaft part starts or accelerates to rotate, the gear disc 1-5 also rotates, the wing roots gear teeth 1-6 and the paddle wings are driven to deflect by 0-45 degrees together due to the action of inertia and reverse torque, the circular fixed wings become propellers, and when the gear disc 1-5 and the wing roots gear teeth 1-6 reach the deflection limit and can not deflect any more, the propellers rotate along with the shaft part 1-7; the shaft part 1-7 is connected with the lower end cover 1-3 through the reset spring 1-4, the lower end cover 1-3 is in tight fit connection with the rotating head 1-1, the lower end cover 1-3 is in loose fit connection with the shaft part 1-7, when the shaft part 1-7 is decelerated or stops rotating, the propeller is turned back to 0 degree through the force conduction between the gear disc 1-5 and the wing root gear teeth 1-6 due to the rotation inertia of the propeller or the effect of the reset spring 1-4, and the propeller turns back to a circular fixed wing in a disc shape or a round pot shape, namely the propeller is turned, and the circular fixed wing is turned down.
The specific structure and the connection relation of the circular fixed wing which can control the deflection angle like a common helicopter are as follows: the rotating head 1-1 is in tight fit connection with the shaft part 1-7, the blade end part of the rotating head 1-1 is provided with a blade lug 1-2-2, the blade lug extends into the rotating head 1-1 through a blade root and is movably connected with the rotating head 1-1, the end part of the blade root is provided with a fixed ring 1-8 so as to prevent the blade lug from being separated from the rotating head 1-1 due to centrifugal action, the rotating head 1-1 is provided with an upper end cover 1-12 so as to be assembled, the shaft root is provided with a bearing, the bearing outer ring is provided with a bearing outer ring connecting rod 1-10, the blade lug 1-2-2 is movably connected with the bearing outer ring connecting rod 1-10 through a blade lug connecting rod 1-9, and the bearing inner ring 1-11 is not contacted with the shaft part, so that the transformation between the circular fixed blade and the propeller can be realized only by controlling the bearing inner ring 1-11 to move up and down.
The shape of the left and right double-main rotor aircraft is the same as that of the common left and right double-main rotor aircraft when taking off, except that the aircraft is provided with a plurality of traction propellers 3, which are arranged for the purpose of fast flight and change of the flight direction after the aircraft is converted into the fixed-wing aircraft, and the shape of the left and right double-main rotor aircraft when flying or gliding is the same as that of the common left and right main fixed-wing, except that the main wings are changed by the left and right double-main rotor 1 to form the double-circular fixed wing 2, as shown in figures 2-3.
The operation control of the left and right double main rotor wing aircrafts is the same as that of a common left and right double main rotor wing aircrafts during vertical take-off and landing, at the moment, the traction screw propeller 3 is not moved, and the operation control of the left and right double main rotor wing aircrafts is the same as that of a common left and right main fixed wing aircrafts during running take-off, flying and gliding landing, at the moment, the left and right double main rotor wings are in a circular fixed wing 2 state.
Working principle and process:
when the aircraft is ready for vertical take-off, under the control action of the control system, the main rotor 1 is in a propeller state, the aircraft obtains lift force by accelerating rotation of the main rotor 1 under the power action, the angle or rotation speed of the wings of the main rotor 1, the rotation speed of the tail anti-torque propeller 6 and the angles of the left tail wing 5 are controlled to enable the aircraft to stably rise, when the aircraft rises to a proper height, the traction propeller 3 is started, the aircraft obtains power to fly forward, simultaneously, the main rotor 1 gradually slows down the rotation speed under the control action and gradually becomes a cake or round pot state, namely the round fixed wing 2, then the round fixed wing 2 can be stopped rotating, and as the round fixed wing 2 stops rotating at that angle, the section is the same as the section of the wing of the common fixed wing, and is similar to the section of the wing of the common fixed wing, so that in the forward flight of the aircraft, the angle of the left tail wing 5 is controlled to enable the aircraft to stably fly under the action of the air, the round fixed wing 2 starts to rotate and is started to be in a propeller state when the aircraft is lifted vertically, the traction propeller 3 is turned off, and the angle or the wings of the main rotor 1 is controlled to enable the wings of the aircraft to stably land. Since the main rotor 1 is much heavier than the traction propeller 3 and can provide lift after it becomes a circular fixed wing 2, the weight of the components of the aircraft which are not active when the aircraft of the invention is lifted from vertical to fly and glide is much smaller than that of the tilting rotor aircraft, so that the aircraft is lighter and more energy-saving when flying.
Claims (6)
1. The utility model provides a but become wing type vertical take-off and landing aircraft, component element includes main rotor, circular fixed wing, traction screw, fuselage, left and right fin, afterbody anti-torque screw and wheeled undercarriage, its characterized in that, the concrete structure and the relation of connection of component element are:
the main rotor is formed by three or more than three blades of wings, the wings can control deflection angles like a main rotor of a common helicopter, or the wings can deflect automatically by utilizing torsion of a shaft to a certain angle, in order to enable the wings to deflect, certain gaps are formed between the wings and the rotating head, certain chamfers are formed between the wings, the main rotor is connected with a fuselage like a main rotor of the common single main rotor helicopter, the traction screw is rotatably connected with the fuselage through a shaft, the left tail wing and the right tail wing are connected with the two sides of the tail of the fuselage like a left main rotor helicopter, the tail anti-torque screw is connected with the upper side of the tail of the fuselage like a common single main rotor helicopter, the wheel type landing gear is connected with the fuselage like a fixed wing helicopter, when the deflection angle of the wings reaches 0 DEG, the main rotor is changed into a round cake shape or a round pot shape into a part of the fixed wing or a fixed wing of the helicopter, at the moment, the round fixed wing is called round fixed wing, the round helicopter can vertically take off, land and land like the common single main rotor, the operation control is the same when the traction screw is in a state of a round helicopter, the left tail of the aircraft and the single helicopter is in a stable state, and the state when the traction screw is in a stable state when the traction screw is in a state, and the single helicopter is in a stable state, and the state when the single helicopter is in a stable state, and the state is in a stable state, and in a state.
2. The variable-wing type vertical take-off and landing aircraft left and right double-main-rotor aircraft according to claim 1, wherein the constituent elements comprise main rotors 1, circular fixed wings, traction propellers, a fuselage, left and right tail wings and wheel landing gear, and the variable-wing type vertical take-off and landing aircraft is characterized in that the number of the main rotors is two, the main rotors are respectively arranged at two sides of the fuselage, and the specific structures and connection relations of the constituent elements are as follows:
the main rotor (1) is composed of three or more blades, the deflection angle of the blades can be controlled like a main rotor of a common helicopter, or the blades can be deflected automatically by a certain angle by utilizing the torsion of a shaft, in order to enable the blades to deflect, a certain gap is formed between the blades and the rotating head, a certain chamfer is formed between the blades, the main rotor is connected with a fuselage like the main rotor of the common left and right double-main rotor helicopter, the traction screw is rotatably connected with the fuselage through a shaft, the left and right tail wings are connected with both sides of the fuselage like a left and right main fixed wing aircraft, the wheel landing gear is connected with the fuselage like a fixed wing aircraft, when the deflection angle of the blades reaches 0 ℃, the main rotor is changed into a round cake shape or a round pot shape into a part of the fixed wing or the fixed wing of the aircraft, so-called round fixed wing, the left and right double-main rotor aircraft vertically takes off, and when the operation control is the same as that of the common left and right double-main rotor aircraft, the traction screw is not moving, and when the left and right main rotors and the aircraft are in the round running state and the same when the flying and the common left and right main rotor are in the round operation and the fixed state.
3. The variable wing type vertical take-off and landing aircraft according to claim 1, wherein the two kinds of circular fixed wings are circular fixed wings, one of which is a deflection angle of the propeller wing is automatically controlled by torsion of the shaft part, and the other is a circular fixed wing, which can control the deflection angle like a general helicopter.
4. The variable wing type vertical take-off and landing aircraft according to claim 3, wherein the specific structure and connection relation of the circular fixed wing for automatically controlling the deflection angle of the propeller wing by using the torsion force of the shaft part are as follows: the shaft part is in loose fit connection with the rotating head, the paddle wings extend into the rotating head through the wing roots and are movably connected with the rotating head, gear teeth are arranged between 0-45 degrees at the end parts of the wing roots and are matched with a gear disc arranged on the shaft part, when the shaft part starts or rotates in an accelerating mode, the gear disc rotates along with the gear disc, the wing roots and the paddle wings are driven to deflect for 0-45 degrees together under the action of inertia and reverse torque, the circular fixed wings become propellers, and when the gear disc and the wing roots reach the deflection limit, the propellers rotate along with the shaft part; the shaft part is connected with the lower end cover through the reset spring, the lower end cover is in tight fit connection with the rotating head, the lower end cover is in loose fit connection with the shaft part, when the shaft part is decelerated or stopped to rotate, the inclined transmission angle of the propeller wing is reset to 0 degree through the force transmission of the gear disc and the gear teeth of the wing root under the action of the reset spring, and the propeller is changed to a circular fixed wing in a disc or circular pot shape, so that automatic conversion between the propeller and the circular fixed wing can be realized, namely the propeller rotates and the circular fixed wing stops rotating.
5. A variable wing type vertical take-off and landing aircraft according to claim 3, wherein the specific structure and connection relation of the circular fixed wing capable of controlling the deflection angle like a common helicopter are as follows: the shaft part tight fit is connected with the rotating head tight fit, the oar wing end part of the rotating head is provided with a wing lug, the oar wing extends into the rotating head through a wing root and is movably connected with the rotating head, the wing root end part is provided with a fixed ring so as to prevent the oar wing from being separated from the rotating head due to centrifugal action, the rotating head is provided with an upper end cover so as to be assembled, the shaft root is provided with a bearing, the bearing outer ring is provided with an outer ring connecting rod, the wing lug is movably connected with the bearing outer ring connecting rod through the wing lug connecting rod, and the bearing inner ring is not contacted with the shaft part, so that the transformation between the circular fixed wing and the propeller can be realized only by controlling the bearing inner ring to move up and down.
6. The variable wing type vertical take-off and landing aircraft according to claim 1, wherein the circular fixed wing is in a shape of a cake or a round pot, the circular fixed wing is composed of three or more blades and a rotor head, the blades are divided into an odd blade and an even blade, the structure, the shape, the weight and the size of each blade of the odd blade are identical, the even blade is two blades symmetrical about the cake, the symmetrical two blades are identical in structure, shape, weight and size, in order to enable the blades to deflect, a certain gap is formed between the blades and the rotor head, a certain chamfer is formed between the blades and the rotor head, the rotor head comprises a rotating head, a lower end cover, a reset spring, a gear disc, gear teeth, a shaft part, a fixed ring, a lug connecting rod, an outer ring connecting rod, a bearing inner ring connecting rod and an upper end cover, and the structure and the connection relation of the rotor head are fixed according to the circular fixed wing which can automatically control the deflection angle of the blades by utilizing the torsion of the shaft part or the circular fixed wing which can control the deflection angle like a common helicopter.
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| CN201910442031.5A CN110053767B (en) | 2019-05-24 | 2019-05-24 | Variable-wing type vertical take-off and landing aircraft |
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|---|---|---|---|---|
| CN1105942A (en) * | 1994-01-25 | 1995-08-02 | 张会山 | Magic wing plane |
| CN1440906A (en) * | 2003-04-08 | 2003-09-10 | 赵志贤 | Vertical and short-distance take-off and landing aircraft |
| US6669137B1 (en) * | 2002-08-26 | 2003-12-30 | Zhuo Chen | Air vehicle having rotor/scissors wing |
| CN2734622Y (en) * | 2004-06-24 | 2005-10-19 | 张志坚 | Flight device with disc wing |
| CN210047618U (en) * | 2019-05-24 | 2020-02-11 | 杨德合 | Variable-wing vertical take-off and landing aircraft |
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2019
- 2019-05-24 CN CN201910442031.5A patent/CN110053767B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1105942A (en) * | 1994-01-25 | 1995-08-02 | 张会山 | Magic wing plane |
| US6669137B1 (en) * | 2002-08-26 | 2003-12-30 | Zhuo Chen | Air vehicle having rotor/scissors wing |
| CN1440906A (en) * | 2003-04-08 | 2003-09-10 | 赵志贤 | Vertical and short-distance take-off and landing aircraft |
| CN2734622Y (en) * | 2004-06-24 | 2005-10-19 | 张志坚 | Flight device with disc wing |
| CN210047618U (en) * | 2019-05-24 | 2020-02-11 | 杨德合 | Variable-wing vertical take-off and landing aircraft |
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| CN110053767A (en) | 2019-07-26 |
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