CN113525679A - Electric vertical take-off and landing aircraft structure and working method thereof - Google Patents
Electric vertical take-off and landing aircraft structure and working method thereof Download PDFInfo
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- CN113525679A CN113525679A CN202111005488.3A CN202111005488A CN113525679A CN 113525679 A CN113525679 A CN 113525679A CN 202111005488 A CN202111005488 A CN 202111005488A CN 113525679 A CN113525679 A CN 113525679A
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- tilting
- nacelle
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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
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/78—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement in association with pitch adjustment of blades of anti-torque rotor
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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
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
Abstract
The invention relates to the technical field of urban air traffic and discloses an electric vertical take-off and landing aircraft structure and a working method thereof, wherein the electric vertical take-off and landing aircraft structure comprises an airframe component, wing components (2) connected to the left side and the right side of the middle upper part of the airframe component, and horizontal tail components connected to the left side and the right side of the tail part of the airframe component; the end parts of the left wing part and the right wing part and the end parts of the left horizontal tail part and the right horizontal tail part are respectively provided with a tilting propeller; the middle parts of the left wing part and the right wing part are respectively connected with a nacelle part, and a foldable propeller is arranged on the nacelle part. The tilting power system has higher take-off and cruising performance, and the increase of the cruising flight speed obviously improves the operation efficiency of the aircraft; a propeller tilting mechanism is designed, so that the vertical take-off and landing function is met, and meanwhile, course thrust can be provided for cruising; the pitch-variable mechanism is designed to change the propeller pitch, so that the propeller works in a high-efficiency region under two working conditions of low-speed incoming flow during vertical take-off and landing and high-speed incoming flow during a cruise stage, and the endurance performance of the whole machine is improved.
Description
Technical Field
The invention relates to the technical field of urban air traffic, in particular to an electric vertical take-off and landing aircraft structure and a working method thereof.
Background
With the increasing density of urban road vehicles, the daily commuting time of human beings is gradually increased. By taking advantage of the Urban condition of low-medium airspace which is not completely developed and utilized, the concept of Urban Air traffic (UAM) is proposed. The electric vertical take-off and landing aircraft becomes the most important urban air traffic solution by virtue of the important advantages of environmental protection and small dependence on infrastructure. There are two common layout styles in the industry today, one being a multi-rotor layout style: the aircraft provides vertical take-off and landing and forward flight power for the aircraft by virtue of a plurality of groups of lift rotors, and has lower flight speed due to the limitation of rotor load because of not having a mechanical structure which is the same as a helicopter rotor, and poorer cruising ability due to lower flight efficiency; another common layout is the "lift + push" combination layout: the aircraft combines the traditional fixed wing layout, and a plurality of groups of lift rotors are added on the aircraft to realize the vertical take-off and landing functions, when cruising, the lift rotors are closed and only depend on propulsive power to fly forward, and the waste resistance generated by the lift rotors in the cruising stage can greatly reduce the flight efficiency.
Therefore, an electric vertical take-off and landing aircraft structure is designed.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides an electric vertical take-off and landing aircraft structure, which solves the problems of low cruising efficiency and poor cruising performance of the conventional equipment.
In order to achieve the purpose, the invention adopts the technical scheme that:
an electric vertical take-off and landing aircraft structure comprises a fuselage component (1), wing components (2) connected to the left side and the right side of the middle upper part of the fuselage component (1), and horizontal tail components (3) connected to the left side and the right side of the tail part of the fuselage component (1); the end parts of the left wing part (2) and the right wing part (3) and the end parts of the left horizontal tail part and the right horizontal tail part are respectively provided with a tilting propeller; the middle parts of the left wing part and the right wing part (2) are respectively connected with a nacelle part (4), and the nacelle part (4) is provided with a foldable propeller.
Preferably, the left and right wing parts (2) are symmetrical about the symmetrical plane of the aircraft, arranged in an upper single gull wing and swept back; the wing tilting nacelle (21) is installed on one side of the outer portion of the left wing part and the right wing part (2), the end portion of the wing tilting nacelle (21) is connected with a first tilting propeller (22), the inner side aileron (23) and the outer side aileron (24) are installed on the other side of the outer portion of the left wing part and the right wing part (2), and the inner side aileron (23) and the outer side aileron (24) are respectively driven by two steering engines in the inner portion.
Preferably, the wing tilting nacelle (21) is tilted by an internal tilting mechanism; the wing tilting nacelle (21) is internally provided with a motor, a controller and a pitch varying mechanism, and an output shaft of the motor is connected with a tilting propeller.
Preferably, the left and right horizontal tail parts (3) are symmetrical about the symmetrical plane of the aircraft, and the conventional tail wing arrangement is adopted, and the vertical tail is swept backwards; a horizontal tail tilting nacelle (31) is arranged on one side of the outer part of each of the left and right horizontal tail parts (3), the end part of the horizontal tail tilting nacelle (31) is connected with a second tilting propeller (32), an elevator (33) is arranged on the other side of the outer part of each of the left and right horizontal tail parts (3), and the elevator (33) is driven by an internal steering engine; the horizontal tail tilting nacelle (31) realizes tilting through the internal tilting mechanism (5).
Preferably, the horizontal tail tilting nacelle (31) is tilted through an internal tilting mechanism; the wing tilting nacelle (21) is internally provided with a motor, a controller and a pitch varying mechanism, and an output shaft of the motor is connected with a tilting propeller.
Preferably, the tilting mechanism comprises a tilting rod (51), a connector (52), a tilting steering engine (53), a steering engine sleeve ring (54) and an installation base (55), wherein the tilting rod (51) is fixedly connected with an inner end wing structure and the connector (52), the connector (52) and the output end of the tilting steering engine (53) realize relative rotation through a fisheye bearing, the tilting steering engine (53) is connected with the steering engine sleeve ring (54) through threads, mutual rotation is realized between the steering engine sleeve ring (54) and the installation base (55) through a bearing, and the installation base (55) is fixedly connected with the wing tilting nacelle (21) through a fastener.
Preferably, the variable-pitch mechanism (6) specifically comprises a variable-pitch motor protective cover (61), a hub (62), a blade (63), a hub fastener (64), a variable-pitch screw slider (65) and a sliding ring (66), wherein a variable-pitch motor is arranged in the variable-pitch motor protective cover (61), the hub (62) and the blade (63) are fixed through the hub fastener (64) and are uniformly installed around a blade bearing, one end of the blade bearing is connected with the variable-pitch screw slider (65), the variable-pitch motor protective cover (61) is installed on the variable-pitch screw slider (65), and the sliding ring (66) is arranged at one end of the blade bearing.
Preferably, the left and right nacelle components (4) are symmetrical with respect to the plane of symmetry of the aircraft; a motor and a controller are installed in the nacelle part (4), a foldable propeller (41) is installed on the end part of the nacelle part (4) in an upward direction, and the foldable propeller (41) is installed on an output shaft of the motor.
Preferably, an undercarriage (7) is further mounted at the bottom of the fuselage component (1), and the undercarriage (7) is a fixed three-point nose landing gear and is mounted on the fuselage bulkhead.
The invention also provides a working method of the electric vertical take-off and landing aircraft structure, which comprises the following steps:
an initial stage: the aircraft is initially in a multi-rotor state, the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles rotate upwards by 90 degrees in the multi-rotor state, and the foldable propellers on the nacelle parts are unfolded into a four-blade propeller state;
a flight phase: after passengers finish boarding, six groups of power systems consisting of the left wing part, the right wing part, the left horizontal tail part, the right horizontal tail part and the left nacelle part provide lift force to take off vertically and fly to a safe height;
the tilting nacelles of the left wing and the right wing and the tilting nacelles of the left horizontal tail and the right horizontal tail are controlled to tilt forwards slowly, so that forward flight thrust is provided for the aircraft; the forward flying speed of the aircraft is continuously increased until a specific speed is reached, foldable propellers on the left and right nacelle parts are folded, feathered and completely closed, the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles rotate to 0 degree, and the propeller pitch is gradually increased; the method comprises the steps that the tilting propellers on a left wing tilting nacelle and a right wing tilting nacelle and on a left horizontal tail tilting nacelle and a right horizontal tail tilting nacelle provide thrust to ensure the cruise stage of the aircraft;
an approach stage: the left foldable propeller and the right foldable propeller are started to work to provide lift force, the left wing tilting nacelle and the right wing tilting nacelle and the left horizontal tail tilting nacelle gradually rotate to 90 degrees from 0 degrees, so that the forward flying speed of the aircraft is gradually reduced until the aircraft is in a hovering state, and the propeller pitch is gradually reduced in the hovering state;
and (5) finishing: six groups of power systems consisting of left and right wing parts, left and right horizontal tail parts and left and right nacelle parts provide lift force to vertically land to a destination to complete a flight task.
The invention has the beneficial effects that:
1. compared with the traditional 'lifting + pushing' layout form, the performance of the tilting power system is obviously improved, the tilting power system has higher take-off and cruising performances, and the operation efficiency of the aircraft is obviously improved by improving the cruising flight speed; (ii) a
2. The propeller tilting mechanism is designed, so that the vertical take-off and landing function is met, the course thrust can be provided for cruising, the cruising resistance can be effectively reduced, the cruising lift-drag ratio is improved, and the cruising performance is improved;
3. the pitch-variable mechanism is designed to change the propeller pitch, so that the propeller works in a high-efficiency region under two working conditions of low-speed incoming flow during vertical take-off and landing and high-speed incoming flow during a cruise stage, and the cruising performance of the whole machine is improved;
4. the 6 groups of power systems in the multi-rotor state provide power for the whole machine, so that the safety problem possibly caused by single-point failure can be effectively prevented; the 4 groups of power systems in the fixed wing state can provide power for the whole machine, and the safety problem possibly caused by single-point failure can be effectively prevented.
Drawings
FIG. 1 is a schematic structural diagram of an electric VTOL (vertical takeoff and landing) aircraft provided by the invention;
FIG. 2 is a schematic view of a left wing component;
FIG. 3 is a schematic view of the left butt section;
FIG. 4 is a state diagram of the tilting mechanism corresponding to the tilting nacelle in the fixed wing state;
FIG. 5 is a state diagram of the tilt mechanism corresponding to the tilt nacelle in a multi-rotor state;
FIGS. 6-8 are schematic views of a pitch-changing mechanism;
FIG. 9 is a schematic view of the pitch effect;
FIG. 10 is a schematic view of the aircraft initially in a multi-rotor state;
FIG. 11 is a schematic view of an aircraft in a transition state;
fig. 12 is a schematic view of the fixed wing state of the aircraft.
In the figure: 1. a body component; 2. a wing component; 3. a horizontal tail part; 4. a nacelle component; 5. a tilting mechanism; 6. a pitch change mechanism; 7. a landing gear; 21. a wing tilt nacelle; 22. a first tilt propeller; 23. an inboard flap; 24. an outboard flap; 31. a horizontal tail tilting nacelle; 32. a second tilt propeller; 33. an elevator; 41. a foldable propeller; 51. a tilting lever; 52. a joint; 53. a tilting steering engine; 54. a steering engine lantern ring; 55. installing a base; 61. a variable pitch motor protective cover; 62. a propeller hub; 63. a paddle; 64. a hub fastener; 65. a variable-pitch screw slider; 66. and a slip ring.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example one
Referring to fig. 1, an electric vertical take-off and landing aircraft structure includes a fuselage component 1, wing components 2 connected to the left and right sides of the middle upper portion of the fuselage component 1, and horizontal tail components 3 connected to the left and right sides of the tail of the fuselage component 1; the end parts of the left wing part 2 and the right wing part 3 and the end parts of the left horizontal tail part 3 are both provided with tilting propellers; the middle parts of the left wing part and the right wing part 2 are respectively connected with a nacelle part 4, and a foldable propeller is arranged on the nacelle part 4. Preferably, four groups of tilting propellers, namely four groups of power systems, are arranged at the end parts of the left wing part 2 and the right wing part 3, two groups of foldable propellers, namely two groups of power systems, are arranged on the nacelle parts of the left wing part 2 and the right wing part 2, six groups of power systems provide power for the whole machine in a multi-rotor state to effectively prevent the safety problem possibly caused by single-point failure, and four groups of power systems provide power for the whole machine in a fixed wing state to effectively prevent the safety problem possibly caused by single-point failure.
Specifically, the left wing part 2 and the right wing part 2 are symmetrical about the symmetrical plane of the aircraft to form an aircraft wing structure, the upper single gull wing is arranged and swept backwards, the height above the ground is increased, and the risk of injury to passengers during boarding and disembarking can be reduced; wing tilting nacelle 21 is installed to 2 outside one sides of left and right wing part, wing tilting nacelle 21 end connection first tilting screw 22 (including the first left tilting screw of connecting left wing tilting nacelle and the first right tilting screw of connecting right wing tilting nacelle), about inboard aileron 23 and outside aileron 24 are installed to 2 outside opposite sides of wing part, inboard aileron 23 and outside aileron 24 are driven respectively by two inside steering engines, every side wing design has 2 sets of ailerons, can be for the redundant security that improves of backup each other (figure 2 is left wing part schematic diagram, right wing part structure and left wing part symmetry, do not describe repeatedly).
The left and right horizontal tail parts 3 are symmetrical about the symmetrical plane of the aircraft, the conventional tail wing arrangement is adopted, and the vertical tail sweepback is adopted to increase the tail force arm so as to form an aircraft tail wing structure; the nacelle 31 that verts of horizontal tail is all installed to 3 outside one sides of left and right horizontal tail parts, and the second screw 32 that verts of horizontal tail 31 end connection (including the second left screw that verts of connecting the nacelle of horizontal tail on the left side and the second right screw that verts of connecting the nacelle of horizontal tail on the right side) of verting of horizontal tail, controls 3 outside opposite sides of horizontal tail parts and installs elevator 33, elevator 33 is by inside steering wheel drive (fig. 3 is left horizontal tail part schematic diagrams, and right horizontal tail part structure is symmetrical with left horizontal tail part, does not describe repeatedly).
The tilting of-10 degrees to 110 degrees is realized by the wing tilting nacelle 21 and the horizontal tail tilting nacelle 31 through the internal tilting mechanism 5 (namely, the first internal tilting mechanism is arranged in the wing tilting nacelle 21, and the second internal tilting mechanism is arranged in the horizontal tail tilting nacelle 31); by the propeller tilting design, the vertical take-off and landing function is met, and meanwhile, the course thrust can be provided for cruising, so that the cruising resistance can be effectively reduced, the cruising lift-drag ratio can be improved, and the cruising performance can be improved;
specifically, tilting mechanism 5 includes tilting rod 51, connect 52, tilting steering wheel 53, steering wheel lantern ring 54 and installation base 55, wherein tilting rod 51 links firmly with inner wing structure (the schematic diagram is not drawn) and connect 52, connect 52 and tilting steering wheel 53 output and realize relative rotation through the fisheye bearing, tilting steering wheel 53 passes through threaded connection with steering wheel lantern ring 54, realize mutual rotation through the bearing between steering wheel lantern ring 54 and the installation base 55, installation base 55 links firmly with wing tilting nacelle 21 through the fastener. Whole nacelle rotates around pole 51 that verts through verting 5 mechanisms along with the flexible of verting steering wheel 53 output in order to realize the function of verting. Wherein the state of fig. 4 corresponds to the tilt nacelle being in a fixed wing state and the state of fig. 5 corresponds to the tilt nacelle being in a multi-rotor state.
In addition, motors, controllers and pitch varying mechanisms 6 are respectively arranged in the wing tilting nacelle 21 and the horizontal tail tilting nacelle 31 (namely, a first pitch varying mechanism is arranged in the wing tilting nacelle 21, and a second pitch varying mechanism is arranged in the horizontal tail tilting nacelle 31), and tilting propellers are connected to output shafts of the motors; the change of the blade angle is realized through the pitch-variable mechanism, so that the propeller can work in a high-efficiency interval under two working conditions of low-speed incoming flow during vertical take-off and landing and high-speed incoming flow during a cruise stage, the endurance performance of the whole aircraft is improved, and the aircraft can have ideal propeller efficiency in a multi-rotor state and a fixed-wing state;
specifically, as shown in fig. 6-8, the pitch-variable mechanism is driven by a linear motor to change the pitch of the propeller; the variable-pitch mechanism (6) specifically comprises a variable-pitch motor protective cover 61, a hub 62, a blade 63, a hub fastener 64, a variable-pitch screw slider 65 and a slip ring 66, wherein a variable-pitch motor is arranged in the variable-pitch motor protective cover 61, the hub 62 and the blade 63 are fixed through the hub fastener 64 and are uniformly arranged around a blade bearing, one end of the blade bearing is connected with the variable-pitch screw slider 65, the variable-pitch motor protective cover 61 is arranged on the variable-pitch screw slider 65, and the slip ring 66 is arranged at one end of the blade bearing.
When the variable-pitch motor works, the rotation output by the motor is converted into linear motion of a variable-pitch screw slider through the working principle of a lead screw, and the variable-pitch motor drives the variable-pitch screw slider to move up and down; the root of the paddle is connected in the groove structure of the variable-pitch screw slider, and when the variable-pitch motor drives the variable-pitch screw slider to move up and down, the variable-pitch screw slider can drive the paddle to rotate so as to achieve the purpose of variable pitch; the propeller hub is divided into an upper part and a lower part, and a clamping blade bearing is installed through a propeller hub fastener, and the propeller blades realize variable-pitch rotation through the blade bearing; the variable pitch motor is powered by slip rings and brushes, and the variable pitch effect is shown in fig. 9.
The middle parts of the left wing part and the right wing part 2 are respectively provided with a nacelle part 4, and the left nacelle part and the right nacelle part 4 are symmetrical about the plane of symmetry of the airplane. A motor and a controller are arranged in each nacelle part 4, a foldable propeller 41 is arranged at the end part of each nacelle part 4 in an upward direction, and the foldable propeller 41 is arranged on an output shaft of the motor. The foldable propeller 41 is preferably a 4-blade propeller, the normal direction of a propeller disc is vertical upwards, the foldable propeller is matched with other power systems to provide lift force for the aircraft during vertical take-off and landing, and the foldable propeller is folded into a 2-blade state and feathered to reduce resistance in a cruising state, so that the extra resistance generated by the foldable propeller is reduced to the maximum extent, and the cruising performance is improved.
Preferably, the screw that verts adopts 5 blade oar designs, collapsible screw adopts 4 blade oar designs, can balance the unbalanced load that preceding paddle and back row paddle produced, compare 2 blade oar designs and can reduce the amplitude of alternating load effectively, effectively reduce the life-span decline that leads to because of alternating load leads to corresponding structure fatigue and then leads to, effectively reduce wingtip linear velocity, combine the bigger diameter of many blades, lower oar dish load, these all can reduce the noise effectively, noise pollution when reducing the operation.
Furthermore, an undercarriage (7) is also mounted at the bottom of the fuselage part, and the undercarriage (7) is a fixed front three-point undercarriage and is mounted on a fuselage bulkhead; the fixed front three-point landing gear is used, the sliding landing capability is provided for the aircraft, the possibility of installation and landing is reserved for the aircraft when the vertical landing function fails due to certain faults, and the safety of the aircraft can be improved.
When the aircraft provided by the invention is used for urban air traffic operation: when the aircraft is in a multi-rotor state (see figure 10) initially, the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles rotate to 90 degrees upwards, and the foldable propellers on the nacelle parts are unfolded to be in a four-blade state; after passengers finish boarding, the six groups of power systems provide lift force to take off vertically and fly to a safe height. And then, controlling the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles to tilt forwards slowly to provide forward flight thrust for the aircraft (a transition state, see fig. 11). The front flying speed of the aircraft is continuously increased until a certain specific speed, and the foldable propellers on the left and right nacelle parts are folded, feathered and completely closed; the tilting nacelles of the left wing and the right wing and the tilting nacelles of the left horizontal tail and the right horizontal tail rotate to 0 degree, and the blade pitch is gradually increased (the fixed wing state, see figure 12). And then, propellers on the left wing tilting nacelle and the right wing tilting nacelle and propellers on the left horizontal tail tilting nacelle and the right horizontal tail tilting nacelle provide thrust to ensure the cruising stage of the aircraft. The left foldable propeller and the right foldable propeller are started to work to provide lift force in the approach stage, the left wing tilting nacelle and the right wing tilting nacelle and the left horizontal tail tilting nacelle gradually rotate to 90 degrees from 0 degrees, the forward flying speed of the aircraft is gradually reduced until the aircraft is in a hovering state, and the propeller pitch is gradually reduced in the process. Then, six groups of power systems provide lift force to vertically land to a destination, and the flight mission is completed.
In addition, the tilting power type aircraft provided by the invention can provide 2/3 times of thrust of maximum takeoff weight when cruising, so that the takeoff and cruising performance of the aircraft is obviously improved, and the operation efficiency of the aircraft is obviously improved by improving the cruising flight speed.
Example two
The second embodiment of the invention provides a working method of an electric vertical take-off and landing aircraft structure, which comprises the following steps:
an initial stage: the aircraft is initially in a multi-rotor state, the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles rotate upwards by 90 degrees in the multi-rotor state, and the foldable propellers on the nacelle parts are unfolded into a four-blade propeller state;
a flight phase: after passengers finish boarding, six groups of power systems consisting of the left wing part, the right wing part, the left horizontal tail part, the right horizontal tail part and the left nacelle part provide lift force to take off vertically and fly to a safe height;
the tilting nacelles of the left wing and the right wing and the tilting nacelles of the left horizontal tail and the right horizontal tail are controlled to tilt forwards slowly, so that forward flight thrust is provided for the aircraft; the forward flying speed of the aircraft is continuously increased until a specific speed is reached, foldable propellers on the left and right nacelle parts are folded, feathered and completely closed, the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles rotate to 0 degree, and the propeller pitch is gradually increased; the method comprises the steps that the tilting propellers on a left wing tilting nacelle and a right wing tilting nacelle and on a left horizontal tail tilting nacelle and a right horizontal tail tilting nacelle provide thrust to ensure the cruise stage of the aircraft;
an approach stage: the left foldable propeller and the right foldable propeller are started to work to provide lift force, the left wing tilting nacelle and the right wing tilting nacelle and the left horizontal tail tilting nacelle gradually rotate to 90 degrees from 0 degrees, so that the forward flying speed of the aircraft is gradually reduced until the aircraft is in a hovering state, and the propeller pitch is gradually reduced in the hovering state;
and (5) finishing: six groups of power systems consisting of left and right wing parts, left and right horizontal tail parts and left and right nacelle parts provide lift force to vertically land to a destination to complete a flight task.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. An electric vertical take-off and landing aircraft structure is characterized by comprising a fuselage component (1), wing components (2) connected to the left side and the right side of the middle upper part of the fuselage component (1) and horizontal tail components (3) connected to the left side and the right side of the tail part of the fuselage component (1); the end parts of the left wing part (2) and the right wing part (3) and the end parts of the left horizontal tail part and the right horizontal tail part are respectively provided with a tilting propeller; the middle parts of the left wing part and the right wing part (2) are respectively connected with a nacelle part (4), and the nacelle part (4) is provided with a foldable propeller.
2. The structure according to claim 1, wherein the left and right wing members (2) are symmetrical about the plane of symmetry of the aircraft, in an upper single gull wing arrangement and swept backward; the wing tilting nacelle (21) is installed on one side of the outer portion of the left wing part and the right wing part (2), the end portion of the wing tilting nacelle (21) is connected with a first tilting propeller (22), the inner side aileron (23) and the outer side aileron (24) are installed on the other side of the outer portion of the left wing part and the right wing part (2), and the inner side aileron (23) and the outer side aileron (24) are respectively driven by two steering engines in the inner portion.
3. The electric vtol aircraft structure according to claim 2, characterized in that the wing tilt nacelle (21) is tilted by means of an internal tilting mechanism; the wing tilting nacelle (21) is internally provided with a motor, a controller and a pitch varying mechanism, and an output shaft of the motor is connected with a tilting propeller.
4. The structure of an electric VTOL aerial vehicle according to claim 1, characterized in that the left and right horizontal tail parts (3) are symmetrical about the plane of symmetry of the aerial vehicle, with conventional tail arrangement, vertical tail sweep; a horizontal tail tilting nacelle (31) is arranged on one side of the outer part of each of the left and right horizontal tail parts (3), the end part of the horizontal tail tilting nacelle (31) is connected with a second tilting propeller (32), an elevator (33) is arranged on the other side of the outer part of each of the left and right horizontal tail parts (3), and the elevator (33) is driven by an internal steering engine; the horizontal tail tilting nacelle (31) realizes tilting through the internal tilting mechanism (5).
5. The electric vtol aircraft structure according to claim 4, characterized in that the flattail tilt nacelle (31) is tilted by an internal tilting mechanism; the wing tilting nacelle (21) is internally provided with a motor, a controller and a pitch varying mechanism, and an output shaft of the motor is connected with a tilting propeller.
6. The electric vertical take-off and landing aircraft structure as claimed in claim 3 or 5, wherein the tilting mechanism comprises a tilting rod (51), a connector (52), a tilting steering engine (53), a steering engine lantern ring (54) and a mounting base (55), wherein the tilting rod (51) is fixedly connected with the inner end wing structure and the connector (52), the connector (52) and the output end of the tilting steering engine (53) realize relative rotation through a fisheye bearing, the tilting steering engine (53) is connected with the steering engine lantern ring (54) through threads, the steering engine lantern ring (54) and the mounting base (55) realize mutual rotation through a bearing, and the mounting base (55) is fixedly connected with the tilting wing nacelle (21) through a fastener.
7. The structure of an electric VTOL (vertical take-off and landing) aircraft as claimed in claim 3 or 5, wherein the pitch-change mechanism (6) comprises a pitch-change motor protective cover (61), a hub (62), a blade (63), a hub fastener (64), a pitch-change screw slider (65) and a slip ring (66), a pitch-change motor is arranged in the pitch-change motor protective cover (61), the hub (62) and the blade (63) are fixed by the hub fastener (64) and are uniformly installed around the blade bearing, one end of the blade bearing is connected with the pitch-change screw slider (65), the pitch-change motor protective cover (61) is installed on the pitch-change screw slider (65), and the slip ring (66) is arranged at one end of the blade bearing.
8. The structure of an electric VTOL aerial vehicle according to claim 1, characterized in that the left and right nacelle parts (4) are symmetrical with respect to the plane of symmetry of the aircraft; a motor and a controller are installed in the nacelle part (4), a foldable propeller (41) is installed on the end part of the nacelle part (4) in an upward direction, and the foldable propeller (41) is installed on an output shaft of the motor.
9. An electric VTOL aerial vehicle structure according to claim 1, characterized in that landing gear (7) is further mounted at the bottom of the fuselage section (1), the landing gear (7) being selected as a fixed nose three point landing gear and mounted on the fuselage bulkhead.
10. An electric VTOL aircraft structure working method is characterized by comprising the following steps:
an initial stage: the aircraft is initially in a multi-rotor state, the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles rotate upwards by 90 degrees in the multi-rotor state, and the foldable propellers on the nacelle parts are unfolded into a four-blade propeller state;
a flight phase: after passengers finish boarding, six groups of power systems consisting of the left wing part, the right wing part, the left horizontal tail part, the right horizontal tail part and the left nacelle part provide lift force to take off vertically and fly to a safe height;
the tilting nacelles of the left wing and the right wing and the tilting nacelles of the left horizontal tail and the right horizontal tail are controlled to tilt forwards slowly, so that forward flight thrust is provided for the aircraft; the forward flying speed of the aircraft is continuously increased until a specific speed is reached, foldable propellers on the left and right nacelle parts are folded, feathered and completely closed, the left and right wing tilting nacelles and the left and right horizontal tail tilting nacelles rotate to 0 degree, and the propeller pitch is gradually increased; the method comprises the steps that the tilting propellers on a left wing tilting nacelle and a right wing tilting nacelle and on a left horizontal tail tilting nacelle and a right horizontal tail tilting nacelle provide thrust to ensure the cruise stage of the aircraft;
an approach stage: the left foldable propeller and the right foldable propeller are started to work to provide lift force, the left wing tilting nacelle and the right wing tilting nacelle and the left horizontal tail tilting nacelle gradually rotate to 90 degrees from 0 degrees, so that the forward flying speed of the aircraft is gradually reduced until the aircraft is in a hovering state, and the propeller pitch is gradually reduced in the hovering state;
and (5) finishing: six groups of power systems consisting of left and right wing parts, left and right horizontal tail parts and left and right nacelle parts provide lift force to vertically land to a destination to complete a flight task.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111005488.3A CN113525679A (en) | 2021-08-30 | 2021-08-30 | Electric vertical take-off and landing aircraft structure and working method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111005488.3A CN113525679A (en) | 2021-08-30 | 2021-08-30 | Electric vertical take-off and landing aircraft structure and working method thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113998103A (en) * | 2021-10-29 | 2022-02-01 | 南京华航翼飞行器技术有限公司 | Working method of tilt rotor aircraft with propeller-rotor composite configuration |
| CN114408191A (en) * | 2022-02-21 | 2022-04-29 | 上海时的科技有限公司 | Power electrical system of electric aircraft |
| CN116215852A (en) * | 2023-05-08 | 2023-06-06 | 成都沃飞天驭科技有限公司 | Vertical take-off and landing aircraft and control method thereof |
-
2021
- 2021-08-30 CN CN202111005488.3A patent/CN113525679A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113998103A (en) * | 2021-10-29 | 2022-02-01 | 南京华航翼飞行器技术有限公司 | Working method of tilt rotor aircraft with propeller-rotor composite configuration |
| CN113998103B (en) * | 2021-10-29 | 2024-02-02 | 南京华航翼飞行器技术有限公司 | Working method of tiltrotor aircraft with composite configuration of propeller and rotor |
| CN114408191A (en) * | 2022-02-21 | 2022-04-29 | 上海时的科技有限公司 | Power electrical system of electric aircraft |
| CN116215852A (en) * | 2023-05-08 | 2023-06-06 | 成都沃飞天驭科技有限公司 | Vertical take-off and landing aircraft and control method thereof |
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