CN117048822A - Electric vertical take-off and landing aircraft with self-balancing tilting rotor - Google Patents
Electric vertical take-off and landing aircraft with self-balancing tilting rotor Download PDFInfo
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- CN117048822A CN117048822A CN202311004751.6A CN202311004751A CN117048822A CN 117048822 A CN117048822 A CN 117048822A CN 202311004751 A CN202311004751 A CN 202311004751A CN 117048822 A CN117048822 A CN 117048822A
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- force assembly
- tilting force
- aircraft
- tilting
- self
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- 230000007246 mechanism Effects 0.000 claims abstract description 24
- 241000272525 Anas platyrhynchos Species 0.000 claims abstract description 15
- 238000006243 chemical reaction Methods 0.000 claims abstract description 6
- 239000003381 stabilizer Substances 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 2
- 230000008569 process Effects 0.000 claims description 2
- 230000007613 environmental effect Effects 0.000 abstract description 3
- 230000001174 ascending effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
Abstract
The invention discloses an electric vertical take-off and landing aviation aircraft with a self-balancing tilting rotor, which comprises a fuselage, a control system in the fuselage and a power system connected with the control system, wherein two sides of the fuselage are provided with a pair of main wings and a pair of duck wings, the power system comprises two front tilting force assembly systems and two rear tilting force assembly systems, the tail ends of the duck wings on two sides of the front part of the fuselage are respectively provided with a front tilting force assembly system, the main wings on two sides of the rear part of the fuselage are respectively provided with a rear tilting force assembly system, the control system controls the front tilting force assembly systems and the rear tilting force assembly systems, and the integral tilting angles of the front tilting force assembly systems and the rear tilting force assembly systems are adjusted to realize conversion of flight modes. The rotating mechanism can utilize the differential rotation of the propeller to realize self-balancing of tilting moment, so that the reliability of the tilting system and the safety of the whole flight system are improved; the distributed power propulsion system promotes aerodynamic efficiency, carrying capacity and environmental protection of the aircraft.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to an electric vertical take-off and landing aviation aircraft with a self-balancing tilting rotor wing, which realizes the vertical take-off and landing on a fixed wing plane.
Background
With the continuous development of technology, manned aircraft have been widely developed and applied in military and civil fields of countries around the world, and common manned aircraft mainly include fixed-wing aircraft and rotary-wing aircraft. The fixed wing aircraft has long voyage and high speed; the rotor craft takes off and land flexibly, stably, and has strong controllability. Vertical take-off and landing fixed wing aircraft that combine fixed wings with rotors have also been in sequential use in recent years. The aircraft has the advantages of vertical take-off and landing of the rotorcraft and high-speed cruising of the fixed-wing aircraft. For most tiltrotor-type fixed wing aircraft, the design output torque of the tilter mechanism is high, so that the tilter mechanism has high complexity and low reliability.
Disclosure of Invention
The invention aims to solve the technical problems in the prior art, and provides an electric vertical take-off and landing aircraft with a self-balancing tilt rotor, which can solve the technical defects of complex tilt mechanism and redundant system of the conventional vertical take-off and landing rotor aircraft; the distributed power propulsion system improves the propulsion efficiency, the handling performance, the aerodynamic efficiency, the carrying capacity and the environmental protection of the aircraft.
The technical scheme adopted is as follows:
an electric vertical take-off and landing aircraft with self-balancing tilting rotor comprises a fuselage, a cabin door, a control system in the fuselage and a power system connected with the control system, wherein a pair of main wings and a pair of duck wings are arranged on two sides of the fuselage, the power system comprises two forward tilting force assembly systems and two backward tilting force assembly systems, the tail ends of the duck wings on two sides of the front part of the fuselage are respectively provided with one forward tilting force assembly system, the main wings on two sides of the rear part of the fuselage are respectively provided with one backward tilting force assembly system, the whole of the forward tilting force assembly system and the backward tilting force assembly system respectively correspond to different flight modes when tilting angles are different,
the control system controls the two front tilting force assembly systems and the two rear tilting force assembly systems, and adjusts the integral tilting angle of each front tilting force assembly system and each rear tilting force assembly system so as to realize the conversion of the flight mode.
Further, the forward tilting power assembly system consists of a single pair of three-blade propellers, a single power plant nacelle with a built-in propeller driving device, a rotatable wing member fixedly connected with the power plant nacelle and a rotating mechanism for controlling the rotating angle of the rotatable wing member.
Further, the backward tilting force assembly system consists of an upper pair of three-blade propellers, a lower pair of three-blade propellers, a power plant nacelle with a built-in propeller driving device, a vertical stabilizer fixedly connected with the upper power plant nacelle and the lower power plant nacelle, and a rotating mechanism for controlling the rotating angle of the vertical stabilizer.
Further, the rotating mechanism is arranged at the root of each side duck wing and on the vertical stabilizer of each side main wing, and the overall tilting angles of each front tilting force assembly system and each rear tilting force assembly system are respectively changed, so that the direction of the propeller disc is controlled.
Further, in the vertical take-off and landing process of the aircraft, six pairs of three-blade propeller plates on the front and back tilting force assembly systems are in a horizontal state, so that vertical upward thrust is provided for the aircraft; when the vertical take-off or landing state is changed into the horizontal flight state, the whole forward tilting force assembly system is tilted to a vertical state of the propeller disc through the rotating mechanism; simultaneously, the whole backward tilting force assembly system is tilted to the propeller disc to be in a vertical direction through the rotating mechanism, so that horizontal advancing power is provided for the aircraft; after the aircraft has completely rotated to a stable horizontal flight phase, the propeller blades on the aft pitch force assembly system are stowed and horizontal forward power is provided only by the forward pitch force assembly system.
Further, a battery management module and electrical equipment are arranged in the short cabin of the power device and are respectively connected with a motor end of the propeller driving device to provide power.
Further, the elevator is arranged on the duck wings, and the pitching attitude of the aircraft can be adjusted by deflecting the elevator on the same side; the vertical stabilizer of the main wing is provided with a rudder, and the rudder biased on the same side can adjust the yaw attitude of the aircraft.
Further, the backward tilting force assembly system is arranged at one third of the main wing at two sides of the rear part of the fuselage and close to the wing root.
Further, with the skid landing gear, 2 skids are connected with the machine body in an inverted V shape.
Further, the upper and lower sets of propellers of the backward tilting power assembly system perform differential rotation, so that the tilting mechanism moment is self-balanced.
Advantageous effects
The invention takes the two forward tilting force assembly systems and the two backward tilting force assembly systems as take-off and forward power. Six pairs of propeller plates are in a horizontal posture, and a skid below the machine body falls to the ground; six pairs of propellers provide vertical ascending power during take-off, and a runway is not needed; the control system adjusts each rotating mechanism to drive the front and rear tilting force assembly systems to realize the conversion of flight gestures, the propeller plates are gradually tilted to be in a vertical state, the direction of the thrust line of the power device is changed into a horizontal state along with the wing from the vertical state, after the aircraft completely rotates to a stable horizontal flight stage, four pairs of propeller blades of the rear tilting force assembly systems are retracted, and horizontal advancing power is provided by the front tilting force assembly systems only. The aircraft adopts a distributed power propulsion system, so that the aerodynamic efficiency, carrying capacity and environmental friendliness of the aircraft are improved.
Drawings
FIG. 1 is a perspective view of an embodiment of the present invention in vertical flight;
FIG. 2 is a front view of an aircraft in a vertical flight configuration in accordance with an embodiment of the present invention;
FIG. 3 is a side view of an aircraft in a vertical flight configuration in accordance with an embodiment of the present invention;
FIG. 4 is a top view of an aircraft in a vertical flight configuration in accordance with an embodiment of the present invention;
FIG. 5 is a perspective view of a tiltrotor aircraft according to embodiments of the present invention when in horizontal flight;
FIG. 6 is a front view of an aircraft in a horizontal flight configuration in accordance with an embodiment of the present invention;
FIG. 7 is a side view of an aircraft in a horizontal flight configuration in accordance with an embodiment of the present invention;
fig. 8 is a side view of an aircraft in a horizontal flight configuration in accordance with an embodiment of the present invention.
In the figure:
100 fuselage, 110 wings, 120 duck wings, 130 cabin doors, 210 rotatable wing segment members, 220 power plant nacelle, 230 three-bladed propeller, 240 landing gear, 250 vertical stabilizer
Detailed Description
Other advantages and effects of the present invention will become readily apparent to those skilled in the art from the following disclosure, when considered in light of the following detailed description of the invention.
As shown in fig. 1 to 8, an electric vertical take-off and landing aircraft with a self-balancing tilt rotor according to the present invention includes a fuselage 100, wings 110, a duck wing 120, a door 130, and landing gear 240, a control system within the fuselage, and a power system connected to the control system, the power system including two forward tilting force assembly systems and two backward tilting force assembly systems. The left and right sides of the front part of the machine body are respectively provided with a duck wing 120, the tail end of each side of the duck wing is respectively provided with a forward tilting force assembly system, and the single side forward tilting force assembly system consists of a single pair of three-blade propellers 230, a single power plant nacelle 220 with a built-in propeller driving device, a rotatable wing section component 210 fixedly connected with the power plant nacelle and a rotating mechanism for controlling the rotating angle of the wing section component; the left side and the right side of the tail of the airplane body are respectively provided with a main wing 110, one third of the position, close to the wing root, of each main wing is respectively provided with a backward tilting force assembly system, and the backward tilting force assembly system on one side is composed of an upper three-blade propeller 230, a lower three-blade propeller 230, a power device nacelle 220 with an upper built-in propeller driving device and a lower built-in propeller driving device, a vertical stabilizer fixedly connected with the upper power device nacelle and the lower power device nacelle and a rotating mechanism for controlling the rotating angle of the vertical stabilizer 250, and the upper propeller and the lower propeller of the backward tilting force assembly system rotate in a differential mode, so that the moment of the tilting mechanism is self-balanced. The propeller driving device is any one of a matched motor and an internal combustion engine and is arranged in a short cabin of the power device; a battery, a battery management module and electrical equipment are arranged in the short cabin of the power device and are respectively connected with a motor end of the propeller driving device to provide power; the rotating mechanism is arranged at the root of each side duck wing and on the vertical stabilizer of each side main wing, and the overall tilting angles of each forward tilting force assembly system and each backward tilting force assembly system are respectively changed, so that the direction of the propeller disk is controlled.
The wing is provided with an elevator, and the elevation of the aircraft can be adjusted by the same side of the elevator; the vertical stabilizer of the main wing is provided with a rudder, and the rudder biased on the same side can adjust the yaw attitude of the aircraft.
The aircraft adopts skid-type landing gear, and 2 skids are connected with the aircraft body in an inverted V shape.
The control system controls the two front tilting force assembly systems and the two rear tilting force assembly systems, and adjusts the integral tilting angles of the front tilting force assembly systems and the rear tilting force assembly systems so as to realize the conversion of the flight modes.
During take-off, landing and flying of the aircraft, the rotating mechanisms (not shown) provided at the respective side of the main wing and the main wing rotate (e.g., pivot) such that the angle of the power tilting system connected thereto is changed as a whole, for example:
specifically, during lifting, the chord of the wing section component at the root of each side of the duck wing is changed into horizontal from the vertical position through the rotating wing chord of the rotating device at the root; the front power tilting system is wholly tilted by 90 degrees, and the propeller disc is turned from a horizontal state to a vertical state. The rotating mechanism arranged on the vertical stabilizer of each side main wing rotates to change the relative included angle between each side outer wing and the wing, namely: the vertical stabilizer deflects from a vertical state parallel to the wing to a horizontal state perpendicular to the wing; the rear power tilting system is wholly tilted by 90 degrees, and the propeller disc is turned from a horizontal state to a vertical state. The whole aircraft is changed from being subjected to vertical pulling force to being subjected to horizontal pushing force.
The invention takes the two forward tilting force assembly systems and the two backward tilting force assembly systems as take-off and forward power. Six pairs of propeller plates are in a horizontal posture, and a skid below the machine body falls to the ground; six pairs of propellers provide vertical ascending power during take-off, and a runway is not needed; the control system adjusts each rotating mechanism to drive the front and rear tilting force assembly systems to realize the conversion of flight gestures, the propeller plates are gradually tilted to be in a vertical state, the direction of the thrust line of the power device is changed into a horizontal state along with the wing from the vertical state, after the aircraft completely rotates to a stable horizontal flight stage, four pairs of propeller blades of the rear tilting force assembly systems are retracted, and horizontal advancing power is provided by the front tilting force assembly systems only.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (10)
1. The utility model provides an electronic perpendicular take off and land aircraft with rotor that verts of self-balancing, includes fuselage, hatch door, control system and the driving system who is connected with this control system in the fuselage, and the both sides of this fuselage are provided with a pair of main wing and a pair of duck wing, its characterized in that: the power system comprises two forward tilting force assembly systems and two backward tilting force assembly systems, wherein the tail ends of the duck wings at the two sides of the front part of the machine body are respectively provided with one forward tilting force assembly system, the main wings at the two sides of the rear part of the machine body are respectively provided with one backward tilting force assembly system, the whole forward tilting force assembly system and the whole backward tilting force assembly system respectively correspond to different flight modes when tilting angles are different,
the control system controls the two front tilting force assembly systems and the two rear tilting force assembly systems, and adjusts the integral tilting angle of each front tilting force assembly system and each rear tilting force assembly system so as to realize the conversion of the flight mode.
2. The electric vertical takeoff and landing aircraft with self-balancing tilt rotor of claim 1, wherein: the forward tilting power assembly system consists of a single auxiliary three-blade propeller, a single power plant nacelle with a built-in propeller driving device, a rotatable wing member fixedly connected with the power plant nacelle and a rotating mechanism for controlling the rotating angle of the rotatable wing member.
3. The electric vertical takeoff and landing aircraft with self-balancing tilt rotor according to claim 1 or 2, characterized in that: the backward tilting force assembly system consists of an upper pair of three-blade propellers, a lower pair of three-blade propellers, an upper power plant nacelle and a lower power plant nacelle with built-in propeller driving devices, a vertical stabilizer fixedly connected with the upper power plant nacelle and the lower power plant nacelle, and a rotating mechanism for controlling the rotating angle of the vertical stabilizer.
4. An electric vertical takeoff and landing aircraft having a self-balancing tilt rotor according to claim 3, characterized in that: the rotating mechanism is arranged at the root of each side duck wing and on the vertical stabilizer of each side main wing, and the overall tilting angles of each front tilting force assembly system and each rear tilting force assembly system are respectively changed, so that the direction of the propeller disk is controlled.
5. The electric vertical takeoff and landing aircraft with self-balancing tilt rotor of claim 4, wherein: in the vertical take-off and landing process of the aircraft, six pairs of three-blade propeller discs on the front and rear tilting force assembly systems are in a horizontal state, so that vertical upward thrust is provided for the aircraft; when the vertical take-off or landing state is changed into the horizontal flight state, the whole forward tilting force assembly system is tilted to a vertical state of the propeller disc through the rotating mechanism; simultaneously, the whole backward tilting force assembly system is tilted to the propeller disc to be in a vertical direction through the rotating mechanism, so that horizontal advancing power is provided for the aircraft; after the aircraft has completely rotated to a stable horizontal flight phase, the propeller blades on the aft pitch force assembly system are stowed and horizontal forward power is provided only by the forward pitch force assembly system.
6. The electric vertical takeoff and landing aircraft with self-balancing tilt rotor of claim 5, wherein: and a battery, a battery management module and electrical equipment are arranged in the short cabin of the power device and are respectively connected with the motor end of the propeller driving device to provide power.
7. The electric vertical take-off and landing aircraft with self-balancing tilt rotor of claim 6, wherein the duckwing is provided with an elevator, and the same side offset elevator can adjust the pitch attitude of the aircraft; the vertical stabilizer of the main wing is provided with a rudder, and the rudder biased on the same side can adjust the yaw attitude of the aircraft.
8. The electric vertical takeoff and landing aircraft with self-balancing tilt rotor of claim 1, wherein: the backward tilting force assembly system is arranged at one third of the main wing close to the wing root at the two sides of the rear part of the machine body.
9. The electric vertical takeoff and landing aircraft with self-balancing tilt rotor of claim 1, wherein: and 2 skids are connected with the machine body in an inverted V shape by adopting a skid type landing gear.
10. An electric vertical takeoff and landing aircraft having a self-balancing tilt rotor according to claim 3, characterized in that: and the upper and lower sets of propellers of the backward tilting power assembly system rotate in a differential speed manner, so that the moment of the tilting mechanism is self-balanced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311004751.6A CN117048822A (en) | 2023-08-10 | 2023-08-10 | Electric vertical take-off and landing aircraft with self-balancing tilting rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311004751.6A CN117048822A (en) | 2023-08-10 | 2023-08-10 | Electric vertical take-off and landing aircraft with self-balancing tilting rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117048822A true CN117048822A (en) | 2023-11-14 |
Family
ID=88658269
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311004751.6A Pending CN117048822A (en) | 2023-08-10 | 2023-08-10 | Electric vertical take-off and landing aircraft with self-balancing tilting rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117048822A (en) |
-
2023
- 2023-08-10 CN CN202311004751.6A patent/CN117048822A/en active Pending
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