CN210047618U - Variable-wing vertical take-off and landing aircraft - Google Patents
Variable-wing vertical take-off and landing aircraft Download PDFInfo
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- CN210047618U CN210047618U CN201920760790.1U CN201920760790U CN210047618U CN 210047618 U CN210047618 U CN 210047618U CN 201920760790 U CN201920760790 U CN 201920760790U CN 210047618 U CN210047618 U CN 210047618U
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Abstract
The utility model relates to a become wing formula VTOL aircraft, the utility model discloses an existing fixed wing aircraft's of aircraft characteristic also has rotor type aircraft's characteristic, is the aircraft of collecting fixed wing aircraft and rotor type aircraft advantage, the utility model discloses a rotor screw that the aircraft used when VTOL has become fixed wing or fixed wing's partly when flying or gliding, even the irrotational also can provide lift when continuing aircraft flight or gliding, this kind of aircraft not only can full load take off and land, also can full load VTOL, moreover can not be because of the former of having VTOL performance increases the energy consumption than ordinary aircraft, aircraft flight time long, can hover in the air, the flight process is steady, the flight is nimble, factor of safety is higher.
Description
Technical Field
The utility model relates to an aircraft technical field, concretely relates to become wing formula VTOL aircraft.
Background
At present, many airplanes in the world can not take off and land vertically, and need a very long runway or water surface to take off and land, but the airplanes which can take off and land vertically either have too large energy consumption in flying or have too large energy consumption in taking off and landing, even can not take off with full load, or are inflexible in flying, so that the airplanes are not safe and reliable enough, thereby restricting the popularization and application of the airplanes, therefore, the airplanes are always tall things since appearing in the market, and are difficult to purchase, park and maintain by common people.
Disclosure of Invention
The utility model aims at providing a become wing formula VTOL aircraft, the existing fixed wing aircraft's of this kind of aircraft characteristic also has the characteristic of rotor class aircraft.
The technical scheme of the utility model is that: the utility model provides a but change wing formula VTOL aircraft, component element includes main rotor, circular fixed wing, pulls screw, fuselage, controls fin, afterbody reaction torque screw and wheeled undercarriage, the concrete structure and the relation of connection of component element are:
the main rotor wing is composed of three or more than three blades, the deflection angle of the blades can be controlled like the main rotor wing of a common helicopter, or the blades can automatically deflect a certain angle by using the torsion of a shaft, in order to enable the blades to deflect, a certain gap is formed between the blades and a rotating head, a certain chamfer angle is formed between the blades and the blades, the main rotor wing is connected with a fuselage like the main rotor wing of a common single main rotor wing helicopter, a traction propeller is rotatably connected with the fuselage through the shaft, a left empennage and a right empennage are connected with two sides of the tail part of the fuselage like left and right main fixed wing aircrafts, a tail part anti-torque propeller is connected with the upper side of the tail part of the fuselage like a common single main rotor wing helicopter, a wheel type undercarriage is connected with the fuselage like the fixed wing aircrafts, when the deflection angle of the blades reaches 0 degree, the main rotor wing is changed into a disk shape or a round pot shape to be a part, the single main wing aircraft is called as a circular fixed wing, the operation control of the single main wing aircraft is the same as that of the common single main rotor aircraft during vertical takeoff and landing, the traction propellers and the left and right empennages are not moved at the moment, the operation control of the single main wing aircraft during running takeoff, flying and gliding landing is the same as that of the common single main fixed wing aircraft, the single main rotor is in a circular fixed wing state at the moment, and the tail part anti-torque propeller is in a braking state, so that the aircraft reaches a stable state.
But two main rotor crafts of left and right sides of variable-wing formula VTOL aircraft, constitute the component and include main rotor, circular fixed wing, pull screw, fuselage, control fin and wheeled undercarriage, main rotor is two, installs respectively in the fuselage both sides, the concrete structure and the joint relation system of component are:
the main rotor wing 1 is composed of three or more than three blades, the blades can control the deflection angle like the main rotor wing of the common helicopter, or the blades can automatically deflect a certain angle by using the torsion of a shaft, in order to enable the blades to deflect, a certain gap is formed between the blades and a rotating head, a certain chamfer is arranged between the blades and the blades, the main rotor wing is connected with a fuselage like the main rotor wing of the common left and right double main rotor wing helicopter, a traction propeller is rotatably connected with the fuselage through the shaft, a left empennage and a right empennage are connected with two sides of the fuselage like left and right main fixed wing aircrafts, a wheel type undercarriage is connected with the fuselage like a fixed wing aircraft, when the deflection angle of the blades reaches 0 degree, the main rotor wing is changed into a disk shape from a rotor wing in the shape of a propeller or a round pan shape to become a fixed wing or a part of a fixed wing of the aircraft, the operation control of the left and right main rotor aircraft is the same as that of the common left and right main rotor aircraft when the left and right main rotor aircraft vertically take off and land, the traction propeller is not moved at the moment, the operation control of the left and right main rotor aircraft during running take off, flying and gliding landing is the same as that of the common left and right main fixed wing aircraft and the movable wing aircraft, and the left and right main rotors are in a circular fixed wing state at the moment.
The circular fixed wing has two types, one is a circular fixed wing which automatically controls the deflection angle of the propeller wing by using the torsion of a shaft part, and the other is a circular fixed wing which can control the deflection angle like a common helicopter.
The specific structure and connection relationship of the circular fixed wing which automatically controls the deflection angle of the propeller wing by utilizing the torsion of the shaft part are as follows: the shaft part is loosely matched and connected with the rotating head, the propeller 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 at an accelerated speed, the gear disc also rotates along with the shaft part, the gear teeth of the wing roots and the propeller wings are driven to deflect for 0-45 degrees under the action of inertia and reverse torque, the circular fixed wings become propellers, and when the gear disc and the gear teeth of the wing roots reach a deflection limit and can not deflect any more, the propellers rotate along with the shaft part; the shaft part is connected with the lower end cover through the return spring, the lower end cover is connected with the rotating head in a tight fit mode, the lower end cover is connected with the shaft part in a loose fit mode, when the shaft part decelerates or stops rotating, due to the rotation inertia of the propeller or the action of the return spring, the propeller wing deflection transmission angle is reset to 0 degree through the force transmission of the gear disc and the gear teeth of the wing root, the propeller returns to the circular fixed wing in a disc or round pot shape, so that the automatic conversion between the propeller and the circular fixed wing can be achieved, namely, the propeller is rotated, and the circular fixed wing is stopped.
The specific structure and connection relation of the circular fixed wing which can control the deflection angle like a common helicopter are as follows: axle part close-fitting is connected with the rotating head close-fitting, the oar wing tip of rotating head is equipped with the pterygoid lamina ear, the oar wing stretches the inside and rotating head swing joint of rotating head through the pterygoid lamina root, pterygoid lamina root tip is equipped with the retainer plate in order to prevent the oar wing and rotating head because of the centrifugal action separation, the rotating head is equipped with the upper end cover so that the assembly, axle root portion is equipped with the bearing, the bearing outer lane has the outer lane connecting rod, the pterygoid lamina ear is through pterygoid lamina ear connecting rod and bearing outer lane connecting rod swing joint, the bearing inner circle does not contact with the axle part, so as long.
The circular fixed wing is in a shape of a cake or a round pot, the circular fixed wing consists of three or more than three blades and a rotor head, the blades are divided into odd blades and even blades, each blade of the odd blades has the same structure, shape, weight and size, the even blades are two blades which are symmetrical by taking the cake as the center, the two symmetrical propeller wings are identical in structure, shape, weight and size, in order to enable the propeller wings to deflect, a certain gap is reserved between the propeller wings and the rotating head, a certain chamfer angle is reserved between the propeller wings and the propeller wings, the rotor head comprises the rotating head, a lower end cover, a return 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 the rotor head are determined according to a circular fixed wing which automatically controls the deflection angle of the propeller wings by utilizing the torsion of the shaft part or a circular fixed wing which can control the deflection angle like a common helicopter.
The utility model has the advantages that:
1. the main rotor propeller used for taking off and landing the aircraft vertically becomes a fixed wing or a part of a fixed wing of the aircraft during flight or glide, and can provide lift even if not rotating during the flight or glide of the aircraft.
2. The main rotor propeller mainly comprises three or more than three blades, the blades can control the deflection angle like the main rotor of a common helicopter, when the deflection angle of the blades reaches 0 degree, the main rotor 1 is changed into a cake shape or a round pot shape from a rotor in the shape of a propeller to form a fixed wing or a part of a fixed wing of the helicopter, and the shape is called as a round fixed wing.
3. The utility model discloses an aircraft can be according to aircraft size, usage, designs into to adopt battery power drive or fuel power drive mode, also can adopt suitable rotation mode according to aircraft fuselage space.
6. The utility model discloses an aircraft can be with according to the required speed of aircraft and select suitable tractor.
The fixed wing is the wing that the shape changes little, deflection angle is little when the aircraft flies or glides.
Drawings
Fig. 1-1 is a perspective view of a single main rotor aircraft of a variable-wing vtol aircraft according to the present invention during takeoff.
Fig. 1-2 are right side views of a single main rotor aircraft of a variable wing vtol aircraft according to the present invention during takeoff.
Fig. 1-3 are perspective views of a single main rotor aircraft of a variable-wing vtol aircraft according to the present invention during flight or glide.
Fig. 1-4 are right side views of a single main rotor aircraft of a variable wing vtol aircraft of the present invention in flight or glide.
Fig. 2-1 is a top view of a dual main rotor aircraft about a variable wing vertical take-off and landing aircraft according to the present invention.
Fig. 2-2 is a right side view of the left and right dual main rotor aircraft of the variable-wing vertical take-off and landing aircraft of the present invention during takeoff.
Fig. 2-3 are top views of the left and right dual-main rotor aircraft of the variable-wing vtol aircraft according to the present invention during flying or gliding.
Fig. 2-4 are right side views of the left and right dual main rotor planes of the variable-wing vtol aircraft according to the present invention during flight or glide.
Fig. 3-1 is a top view of a circular stationary vane.
Fig. 3-2 is a schematic view of the structure of the central portion of a circular fixed wing for automatically controlling the deflection angle of the wing by using the shaft torsion.
Fig. 3-3 are schematic structural views showing the cooperation between the gear teeth at the root of the circular fixed wing and the gear plate at the shaft for automatically controlling the deflection angle of the wing by the torque force at the shaft.
Figures 3-4 are schematic structural views of a circular fixed wing rotor for controlling the rotor yaw angle as in a conventional helicopter.
Figures 3-5 are schematic views of the central portion of a circular fixed wing rotor for controlling the rotor yaw angle as in a conventional helicopter.
Labeled as: the aircraft comprises a main rotor wing 1, a circular fixed wing 2, a traction propeller 3, an airframe 4, left and right empennages 5, a tail part reactive torque propeller 6 and a wheel type undercarriage 7. 1-1 part of rotating head, 1-2 parts of paddle wing, 1-3 parts of lower end cover, 1-4 parts of return spring, 1-5 parts of gear disc, 1-6 parts of wing root gear teeth, 1-7 parts of shaft part, 1-8 parts of retainer ring, 1-9 parts of wing ear connecting rod, 1-10 parts of bearing outer ring connecting rod, 1-11 parts of bearing inner ring connecting rod, 1-12 parts of upper end cover, 1-2-1 parts of wing root and 1-2-2 parts of wing ear,
Detailed Description
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.
It should be noted that, unless explicitly stated or limited otherwise, the terms "connected" and "connected" in the description of the present invention are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Example 1
Become wing formula VTOL aircraft's structure the existing fixed wing aircraft's of characteristic, also have the characteristic of rotor class aircraft.
As shown in fig. 1-1 to fig. 3-5, in order to achieve the above object, the single main rotor aircraft of the variable-wing vtol aircraft of the present invention includes a main rotor 1, a circular fixed wing 2, a traction propeller 3, a fuselage 4, left and right empennages 5, a tail reaction torque propeller 6, and a wheel landing gear 7. The concrete structure and the connection relation of the components are as follows:
the main rotor wing 1 is connected with the fuselage 4 like a main rotor wing of a common single main rotor wing helicopter, the traction propellers 3 are rotatably connected with the fuselage 4 through a shaft, the left and right empennages 5 are connected with the two sides of the tail part of the fuselage 4 like left and right main fixed wing helicopters, the tail part reaction torque propellers 6 are connected with the upper side of the tail part of the fuselage 4 like a common single main rotor wing helicopter, and the wheel type undercarriage 7 is connected with the fuselage 4 like a fixed wing helicopter. When the deflection angle of the propeller wing reaches 0 degrees, the main rotor wing 1 is changed into a round cake shape or a round pan shape from a rotor wing in a propeller shape to be a fixed wing or a part of a fixed wing of the airplane, and is called as a round fixed wing 2.
The circular fixed wing is in a shape of a round cake or a round pot, the circular fixed wing consists of three or more than three blades and a rotor head, the blades are divided into odd blades and even blades, each blade of the odd blades has the same structure, shape, weight and size, the even blades are two symmetric blades taking the round cake as the center, the two symmetric blades have the same structure, shape, weight and size, in order to enable the blades to deflect, a certain gap is reserved between the blades and a rotating head, a certain chamfer angle 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 lug 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, the structure and connection relationship of the rotor head are determined according to a circular fixed wing which automatically controls the deflection angle of the rotor wing by using the torque force of the shaft part or a circular fixed wing which can control the deflection angle like a common helicopter.
The circular fixed wing has two types, one is a circular fixed wing which automatically controls the deflection angle of the propeller wing by using the torsion of a shaft part, and the other is a circular fixed wing which can control the deflection angle like a common helicopter.
The specific structure and connection relationship of the circular fixed wing which automatically controls the deflection angle of the propeller wing by utilizing the torsion of the shaft part are as follows: the shaft part 1-7 is loosely matched and connected with the rotating head 1-1, the paddle wing extends into the rotating head 1-1 through the wing root 1-2-1 and is movably connected with the rotating head, gear teeth 1-6 are arranged between the end parts of the wing root at 0-45 degrees, the gear teeth 1-6 are matched with a gear disc 1-5 arranged on the shaft part, when the shaft part starts to rotate or rotates at an accelerated speed, the gear disc 1-5 rotates along with the shaft part, the gear teeth 1-6 of the wing root and the paddle wing are driven to deflect for 0-45 degrees under the action of inertia and reverse torque, the circular fixed wing becomes a propeller, and when the gear disc 1-5 and the gear teeth 1-6 of the wing root reach a deflection limit and can not deflect any more, the propeller rotates along with the shaft part 1-7; the shaft part 1-7 is connected with the lower end cover 1-3 through the return spring 1-4, the lower end cover 1-3 is connected with the rotating head 1-1 in a tight fit mode, the lower end cover 1-3 is connected with the shaft part 1-7 in a loose fit mode, when the shaft part 1-7 decelerates or stops rotating, due to the rotating inertia of the propeller or the action of the return spring 1-4, force transmission of the gear disc 1-5 and the gear teeth 1-6 of the wing root is conducted, the deflection transmission angle of the propeller wing is reset to 0 degree, the propeller is changed back to the circular fixed wing in a disc or circular pot shape, namely, the propeller is rotated, and the circular fixed wing is stopped.
The specific structure and 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 tightly matched and connected with the shaft part 1-7, the end part of the paddle wing of the rotating head 1-1 is provided with a wing lug 1-2-2, the paddle wing extends into the rotating head 1-1 through the wing root to be movably connected with the rotating head 1-1, the end part of the wing root is provided with a fixed ring 1-8 to prevent the paddle wing from separating from the rotating head 1-1 due to centrifugal action, the rotating head 1-1 is provided with an upper end cover 1-12 for assembly, the shaft root part is provided with a bearing, the outer ring of the bearing is provided with a bearing outer ring connecting rod 1-10, the wing lug 1-2-2 is movably connected with a bearing outer ring connecting rod 1-10 through the wing lug connecting rod 1-9, and the, therefore, the conversion between the circular fixed wing and the propeller can be realized by only controlling the bearing inner rings 1-11 to move up and down.
The structure of the single main rotor aircraft during takeoff is the same as that of the common single main rotor aircraft, except that the aircraft is provided with a plurality of traction propellers 3 and left and right tail wings 5, which are set up for fast flight and change of flight direction after the aircraft is changed into a fixed wing aircraft, the shape of the single main rotor aircraft during flight or gliding is the same as that of the common single main fixed wing aircraft, and the difference is that the main wing of the single main rotor aircraft is changed into a circular fixed wing 2, as shown in figures 1-3. The single main wing aircraft has the same operation control as that of a common single main rotor aircraft during vertical takeoff and landing, the traction propeller 3 and the left and right empennages 5 are not moved at the moment, and the single main wing aircraft has the same operation control as that of a common single main fixed wing aircraft during running takeoff, flying and gliding landing, and is in a circular fixed wing state, and the tail anti-torque 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, in order to achieve the above object, the dual main rotor aircraft of the variable wing vtol aircraft of the present invention comprises a main rotor 1, a circular fixed wing 2, a towing propeller 3, a fuselage 4, a left empennage 5, a right empennage 5, and a wheel landing gear 7. Embodiment 2 differs from embodiment 1 in that there are two main rotors 1 installed on both sides of the fuselage; and the tail reaction torque propeller 6 is not arranged, and the specific structure and the connection relationship of the components are as follows:
the aircraft is characterized in that the number of the main rotors 1 is two, the two main rotors 1 are respectively arranged on the left side and the right side of the aircraft body 4 like a left main rotor aircraft and a right main rotor aircraft, the traction propellers 3 are rotatably connected with the aircraft body 4 through a shaft, the left empennage 5 and the right empennage 5 are connected with the two sides of the aircraft body 4 like a left main fixed wing aircraft and a right main fixed wing aircraft, and the wheel type undercarriage 7 is connected with the aircraft body 4. When the deflection angle of the propeller wing reaches 0 degrees, the main rotor wing 1 is changed into a round cake shape or a round pan shape from a rotor wing in a propeller shape to be a fixed wing or a part of a fixed wing of the airplane, and is called as a round fixed wing 2.
The circular fixed wing is in a shape of a round cake or a round pot, the circular fixed wing consists of three or more than three blades and a rotor head, the blades are divided into odd blades and even blades, each blade of the odd blades has the same structure, shape, weight and size, the even blades are two symmetric blades taking the round cake as the center, the two symmetric blades have the same structure, shape, weight and size, in order to enable the blades to deflect, a certain gap is reserved between the blades and a rotating head, a certain chamfer angle 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 lug 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, the structure and connection relationship of the rotor head are determined according to a circular fixed wing which automatically controls the deflection angle of the rotor wing by using the torque force of the shaft part or a circular fixed wing which can control the deflection angle like a common helicopter.
The circular fixed wing has two types, one is a circular fixed wing which automatically controls the deflection angle of the propeller wing by using the torsion of a shaft part, and the other is a circular fixed wing which can control the deflection angle like a common helicopter.
The specific structure and connection relationship of the circular fixed wing which automatically controls the deflection angle of the propeller wing by utilizing the torsion of the shaft part are as follows: the shaft part 1-7 is loosely matched and connected with the rotating head 1-1, the paddle wing extends into the rotating head 1-1 through the wing root 1-2-1 and is movably connected with the rotating head, gear teeth 1-6 are arranged between the end parts of the wing root at 0-45 degrees, the gear teeth 1-6 are matched with a gear disc 1-5 arranged on the shaft part, when the shaft part starts to rotate or rotates at an accelerated speed, the gear disc 1-5 rotates along with the shaft part, the gear teeth 1-6 of the wing root and the paddle wing are driven to deflect for 0-45 degrees under the action of inertia and reverse torque, the circular fixed wing becomes a propeller, and when the gear disc 1-5 and the gear teeth 1-6 of the wing root reach a deflection limit and can not deflect any more, the propeller rotates along with the shaft part 1-7; the shaft part 1-7 is connected with the lower end cover 1-3 through the return spring 1-4, the lower end cover 1-3 is connected with the rotating head 1-1 in a tight fit mode, the lower end cover 1-3 is connected with the shaft part 1-7 in a loose fit mode, when the shaft part 1-7 decelerates or stops rotating, due to the rotating inertia of the propeller or the action of the return spring 1-4, force transmission of the gear disc 1-5 and the gear teeth 1-6 of the wing root is conducted, the deflection transmission angle of the propeller wing is reset to 0 degree, the propeller is changed back to the circular fixed wing in a disc or circular pot shape, namely, the propeller is rotated, and the circular fixed wing is stopped.
The specific structure and 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 tightly matched and connected with the shaft part 1-7, the end part of the paddle wing of the rotating head 1-1 is provided with a wing lug 1-2-2, the paddle wing extends into the rotating head 1-1 through the wing root to be movably connected with the rotating head 1-1, the end part of the wing root is provided with a fixed ring 1-8 to prevent the paddle wing from separating from the rotating head 1-1 due to centrifugal action, the rotating head 1-1 is provided with an upper end cover 1-12 for assembly, the shaft root part is provided with a bearing, the outer ring of the bearing is provided with a bearing outer ring connecting rod 1-10, the wing lug 1-2-2 is movably connected with a bearing outer ring connecting rod 1-10 through the wing lug connecting rod 1-9, and the, therefore, the conversion between the circular fixed wing and the propeller can be realized by only controlling the bearing inner rings 1-11 to move up and down.
The left and right dual main rotor aircraft has the same shape when taking off as the common left and right dual main rotor aircraft, except that the aircraft is provided with a plurality of traction propellers 3, which are set up for the purpose of fast flying and changing the flying direction after the aircraft is converted into a fixed wing aircraft, and the left and right dual main rotor aircraft has the same shape when flying or gliding as the common left and right main fixed wings, except that the main wings are changed from the left and right dual main rotors 1 into double circular fixed wings 2, as shown in fig. 2-3.
The operation control of the left and right main rotor aircraft is the same as that of the common left and right main rotor aircraft when the left and right main rotor aircraft vertically take off and land, the traction propeller 3 is not moved at the moment, the operation control of the left and right main rotor aircraft during running take off, flying and gliding landing is the same as that of the common left and right main fixed wing aircraft and the movable wing aircraft, and the left and right main rotors are in the state of the circular fixed wing 2 at the moment.
The working principle and the process are as follows:
when the airplane is ready to take off vertically, under the control action of a control system, the main rotor wing 1 is in a propeller state, under the action of power, the main rotor wing 1 rotates in an accelerating way to enable the airplane to obtain lift force, the paddle wing angle or rotating speed of the main rotor wing 1, the rotating speed of the tail part reaction torque propeller 6 and the angles of the left tail wing and the right tail wing 5 are controlled to enable the airplane to ascend stably, when the airplane ascends to a proper height, the traction propeller 3 is started, the airplane flies forwards under power, and simultaneously, under the control action, the main rotor wing 1 gradually slows down the rotating speed and gradually changes into a round cake or round pot state, namely a round fixed wing 2, then the round fixed wing 2 can stop rotating, as the round fixed wing 2 stops rotating at any angle, the cross section is the same and is similar to the wing cross section of a common fixed wing, in the forward flying process of the airplane, the lift force is continuously obtained under the, when the aircraft lands vertically, the circular fixed wing 2 is controlled to start rotating and be in a propeller state, the traction propeller 3 is closed, and the angle or the rotating speed of the propeller wing of the main rotor wing 1, the rotating speed of the tail part reaction torque propeller 6 and the angles of the left tail wing and the right tail wing 5 are controlled to enable the aircraft to land stably. Because the weight ratio of main rotor 1 pulls screw 3 and is much greater, can also provide lift moreover after it becomes circular stationary vane 2, so make the utility model discloses an inoperative component weight all is much less than tilting rotor aircraft when the aircraft from VTOL to flight, glide, so light more during the flight, more energy-conserving.
Claims (6)
1. The utility model provides a but change wing formula VTOL aircraft, component element includes main rotor, circular fixed wing, pulls screw, fuselage, controls fin, afterbody reaction torque screw and wheeled undercarriage, its characterized in that, the concrete structure and the relation of connection of component element are:
the main rotor wing is composed of three or more than three blades, the deflection angle of the blades can be controlled like the main rotor wing of a common helicopter, or the blades can automatically deflect a certain angle by using the torsion of a shaft, in order to enable the blades to deflect, a certain gap is formed between the blades and a rotating head, a certain chamfer angle is formed between the blades and the blades, the main rotor wing is connected with a fuselage like the main rotor wing of the common single main rotor helicopter, a traction propeller is rotatably connected with the fuselage through the shaft, a left empennage and a right empennage are connected with two sides of the tail part of the fuselage like left and right main fixed wing aircrafts, a tail part anti-torque propeller is connected with the upper side of the tail part of the fuselage like the common single main rotor wing helicopter, a wheel type undercarriage is connected with the fuselage like the fixed wing aircrafts, when the deflection angle of the blades reaches 0 degree, the main rotor wing is changed into a disk shape or a round pot shape to be a part of, the single main wing aircraft is called as a circular fixed wing, the operation control of the single main wing aircraft is the same as that of the common single main rotor aircraft during vertical takeoff and landing, the traction propellers and the left and right empennages are not moved at the moment, the operation control of the single main wing aircraft during running takeoff, flying and gliding landing is the same as that of the common single main fixed wing aircraft, the single main rotor is in a circular fixed wing state at the moment, and the tail part anti-torque propeller is in a braking state, so that the aircraft reaches a stable state.
2. The variable-wing vertical take-off and landing aircraft according to claim 1, wherein the number of the main rotors is two, and the main rotors are respectively mounted on two sides of the aircraft body, and the specific structures and connection relations of the components are as follows:
the main rotor wing is composed of three or more than three blades, the deflection angle of the blades can be controlled like the main rotor wing of a common helicopter, or the blades can automatically deflect a certain angle by using the torsion of a shaft, in order to enable the blades to deflect, a certain gap is formed between the blades and a rotating head, a certain chamfer angle is formed between the blades and the blades, the main rotor wing is connected with a fuselage like the main rotor wing of the common left and right double main rotor wing helicopter, a traction propeller is rotatably connected with the fuselage through the shaft, a left empennage and a right empennage are connected with two sides of the fuselage like a left and right main fixed wing aircrafts, a wheel type undercarriage is connected with the fuselage like a fixed wing aircraft, when the deflection angle of the blades reaches 0 degree, the main rotor wing is changed into a disk shape or a round pan shape to be a part of a fixed wing or a fixed wing of the aircraft, and is called as a round, the operation control of the left and right main rotor aircraft is the same as that of the common left and right main rotor aircraft when the left and right main rotor aircraft vertically take off and land, the traction propeller is not moved at the moment, the operation control of the left and right main rotor aircraft during running take off, flying and gliding landing is the same as that of the common left and right main fixed wing aircraft and the movable wing aircraft, and the left and right main rotors are in a circular fixed wing state at the moment.
3. The variable-wing vtol aircraft as claimed in claim 1, wherein the circular fixed wing is a circular fixed wing which automatically controls the deflection angle of the wing by the torque of the shaft, and a circular fixed wing which can control the deflection angle like a general helicopter.
4. The variable-wing vtol aircraft as claimed in claim 3, wherein the circular fixed wing for automatically controlling the deflection angle of the wing by the torque of the shaft has the following specific structure and connection relationship: the shaft part is loosely matched and connected with the rotating head, the propeller 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 at an accelerated speed, the gear disc also rotates along with the shaft part, the gear teeth of the wing roots and the propeller wings are driven to deflect for 0-45 degrees under the action of inertia and reverse torque, the circular fixed wings become propellers, and when the gear disc and the gear teeth of the wing roots reach a deflection limit and can not deflect any more, the propellers rotate along with the shaft part; the shaft part is connected with the lower end cover through the return spring, the lower end cover is connected with the rotating head in a tight fit mode, the lower end cover is connected with the shaft part in a loose fit mode, when the shaft part decelerates or stops rotating, due to the rotation inertia of the propeller or the action of the return spring, the propeller wing deflection transmission angle is reset to 0 degree through the force transmission of the gear disc and the gear teeth of the wing root, the propeller returns to the circular fixed wing in a disc or round pot shape, so that the automatic conversion between the propeller and the circular fixed wing can be achieved, namely, the propeller is rotated, and the circular fixed wing is stopped.
5. The variable-wing VTOL airplane according to claim 3, wherein the specific structure and connection relationship of the circular fixed wing capable of controlling the deflection angle like the ordinary helicopter are: axle part close-fitting is connected with the rotating head close-fitting, the oar wing tip of rotating head is equipped with the pterygoid lamina ear, the oar wing stretches the inside and rotating head swing joint of rotating head through the pterygoid lamina root, pterygoid lamina root tip is equipped with the retainer plate in order to prevent the oar wing and rotating head because of the centrifugal action separation, the rotating head is equipped with the upper end cover so that the assembly, axle root portion is equipped with the bearing, the bearing outer lane has the outer lane connecting rod, the pterygoid lamina ear is through pterygoid lamina ear connecting rod and bearing outer lane connecting rod swing joint, the bearing inner circle does not contact with the axle part, so as long.
6. The variable-wing vertical take-off and landing aircraft according to claim 1, wherein the circular fixed wing is in a shape of a disk or a pot, the circular fixed wing is composed of three or more blades and a rotor head, the blades are divided into odd-numbered blades and even-numbered blades, each blade of the odd-numbered blades has the same structure, shape, weight and size, the even-numbered blades are two blades symmetric about the disk, the two symmetric blades have the same structure, shape, weight and size, the blades have a certain gap with the rotating head in order to enable the blades to deflect, a certain chamfer is formed between the blades and the blades, the rotor head comprises a rotating head, a lower end cover, a return 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 relationship of the rotor head are controlled according to the circular fixed wing which automatically controls the angle of the blades by using the torsion of the rotation or like a normal helicopter The deflection angle depends on the circular fixed wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920760790.1U CN210047618U (en) | 2019-05-24 | 2019-05-24 | Variable-wing vertical take-off and landing aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920760790.1U CN210047618U (en) | 2019-05-24 | 2019-05-24 | Variable-wing vertical take-off and landing aircraft |
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| CN210047618U true CN210047618U (en) | 2020-02-11 |
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| CN201920760790.1U Withdrawn - After Issue CN210047618U (en) | 2019-05-24 | 2019-05-24 | Variable-wing vertical take-off and landing aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110053767A (en) * | 2019-05-24 | 2019-07-26 | 杨德合 | A kind of VTOL aircraft variable wing |
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2019
- 2019-05-24 CN CN201920760790.1U patent/CN210047618U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110053767A (en) * | 2019-05-24 | 2019-07-26 | 杨德合 | A kind of VTOL aircraft variable wing |
| CN110053767B (en) * | 2019-05-24 | 2023-09-19 | 杨德合 | Variable-wing type vertical take-off and landing aircraft |
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