WO2023060679A1 - 飞行器、机翼组件及飞行汽车 - Google Patents

飞行器、机翼组件及飞行汽车 Download PDF

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Publication number
WO2023060679A1
WO2023060679A1 PCT/CN2021/129539 CN2021129539W WO2023060679A1 WO 2023060679 A1 WO2023060679 A1 WO 2023060679A1 CN 2021129539 W CN2021129539 W CN 2021129539W WO 2023060679 A1 WO2023060679 A1 WO 2023060679A1
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WO
WIPO (PCT)
Prior art keywords
rotor
aircraft
turning
wing
assembly
Prior art date
Application number
PCT/CN2021/129539
Other languages
English (en)
French (fr)
Inventor
王谭
梁毅诚
史翊辰
娄津源
曹雪宇
王伟民
Original Assignee
广东汇天航空航天科技有限公司
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Application filed by 广东汇天航空航天科技有限公司 filed Critical 广东汇天航空航天科技有限公司
Publication of WO2023060679A1 publication Critical patent/WO2023060679A1/zh

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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
    • B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
    • B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C27/50—Blades foldable to facilitate stowage of aircraft
    • 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
    • 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
    • Y02T50/40—Weight reduction

Definitions

  • the invention relates to the technical field of flight equipment, in particular, to an aircraft, a wing assembly and a flying car.
  • flying devices In addition to being used for video shooting, agricultural irrigation and fire rescue, flying devices can also be used for people's daily travel.
  • Embodiments of the present invention achieve the above object through the following technical solutions.
  • the present invention provides an aircraft, which includes a fuselage, a wing assembly, a tilt connector and a rotor assembly.
  • the wing assembly includes a fixed part and a turning part, the fixing part is arranged on the fuselage, the turning part is movably connected to the fixing part, and can be folded relative to the fixing part; the tilting connector is rotatably arranged on the wing assembly;
  • the rotor assembly is connected to the tilting link in transmission to change the spatial angle driven by the tilting link, so that the wing assembly can be folded, which improves the flexibility of the aircraft during parking and transition; in addition, the rotor assembly can be in the Driven by the tilting connector, the space angle is changed, so that the aircraft also has the functions of vertical take-off, landing and level flight, which can fully meet the travel needs of various scenarios.
  • the fixed part extends along a first direction
  • the turning part has a first rotation axis and a second rotation axis
  • the first rotation axis extends along a first direction
  • the second rotation axis extends along a second direction
  • the second rotation axis extends along a second direction.
  • One direction is perpendicular to the second direction, so as to realize step-by-step folding of the wing assembly and reduce damage caused by the wing assembly during the folding process.
  • the aircraft further includes a turning mechanism, the turning part can turn relative to the fixed part through the turning mechanism, the turning mechanism includes a first rotating shaft and a second rotating shaft, and the turning part moves along the first rotating shaft through the first rotating shaft.
  • the rotation axis rotates, and the turning part rotates along the second rotation axis through the second rotation shaft, so as to realize the step-by-step folding of the wing assembly and reduce the damage caused by the wing assembly during the folding process.
  • the rotor assembly has a rotor state and a fixed wing state.
  • the rotation axis of the rotor assembly extends along a third direction.
  • the rotation axis of the rotor assembly extends along the third direction.
  • the third direction is perpendicular to the first direction and the second direction, so that the aircraft not only has the capability of vertical take-off and landing, but also has the capability of high-speed level flight.
  • the rotor assembly includes a tilt rotor body and a rotor mount, the rotor mount is in transmission connection with the tilt connector, the tilt rotor body is rotatably arranged on the rotor mount, and the tilt rotor body includes a tilt
  • the rotor blade and the tilt rotor blade can be bent relative to the rotor mount, which can reduce the length of the aircraft and improve the flexibility of the aircraft during parking and transition.
  • the turning part includes a first turning section and a second turning section, the first turning section is movably connected to the fixing part, and can turn relative to the fixing part, and the first turning section is provided with There is a tilting connector, the second turning section is connected to the tilting connecting piece, the rotor assembly includes a straight rotor module, the straight rotor module is arranged on the second turning section, and the straight rotor module is arranged on the wing assembly The end away from the fuselage prevents the influence of the wing assembly on the tilt of the straight rotor module.
  • the wing assembly also includes a nacelle, the nacelle is connected to the fixed part, the aircraft also includes a turning mechanism, the turning mechanism is arranged in the nacelle, and the turning part can be turned relative to the fixed part through the turning mechanism , so that the turning part can be turned more smoothly relative to the fixing part, and the turning efficiency of the turning part can be improved.
  • the engine nacelle is provided with a tilting connector
  • the rotor assembly includes a tilting rotor module
  • the tilting rotor module is connected to the tilting connector, which can ensure that the direction of the motor pulling force or The direction of thrust is vertical.
  • the aircraft also includes a fixed rotor module, the fixed rotor module and the tilt rotor module are respectively arranged at opposite ends of the nacelle, the fixed rotor module includes a fixed shaft and a fixed rotor blade, and the fixed rotor module includes a fixed shaft and a fixed rotor blade.
  • the paddles are rotatably arranged on the fixed shaft, and the fixed shaft is fixedly arranged on the engine compartment, so as to keep the pitching balance of the whole machine.
  • each wing assembly there are two wing assemblies, and the two wing assemblies are respectively connected to opposite sides of the fuselage, each turning portion is provided with a straight rotor module, and each engine compartment is provided with There is a fixed-rotor module and a tilt-rotor module to realize the high safety redundancy of the aircraft.
  • the straight rotor module, the tilt rotor module and the fixed rotor module form a six-rotor module, and the center of gravity of the aircraft is located at the center of the six-rotor module, so that the overall center of gravity of the aircraft does not shift Guarantee the stable flight and safe landing of the aircraft.
  • the six-rotor module is controlled to start rotating, so that the aircraft rises vertically.
  • the nacelle includes opposite first ends and second ends, the first end is facing the direction of travel of the aircraft, the second end is away from the direction of travel of the aircraft, the tilt rotor module is arranged at the first end, fixed The rotor module is arranged at the second end.
  • the straight rotor module and the second turning section form a power mechanism
  • the center of gravity of the power mechanism is located on the rotation axis of the second turning section, which can ensure the stability of the center of gravity of the power mechanism and ensure the vertical lift efficiency.
  • the length of the fixing part is 10%-30% of the length of the wing assembly, which greatly reduces the width of the folded aircraft and facilitates the transition of the aircraft.
  • the aircraft further includes an empennage, which is connected to the fuselage so as to avoid wake interference and improve the efficiency of horizontal tail manipulation.
  • the empennage includes a horizontal wing and a vertical wing, the vertical wing is connected between the fuselage and the horizontal wing and extends upward, and the extension direction of the horizontal wing is the same as that of the wing assembly, thereby controlling the flight of the aircraft attitude.
  • the aircraft further includes a wheel set, the wheel set is arranged at the bottom of the fuselage, and the fuselage can move along the ground through the wheel set, so as to meet the transition requirements of the aircraft.
  • the present invention also provides a wing assembly, the wing assembly includes a fixed part and a turning part, the fixing part is arranged on the fuselage, the turning part is movably connected to the fixing part, and can be folded relative to the fixing part , so that the wing assembly can be folded, which improves the flexibility of the aircraft during parking and transition.
  • the present invention also provides a flying car, including a body, a wing assembly, a tilting connector, and a rotor assembly.
  • the wing assembly includes a fixed part and a turning part, the fixing part is arranged on the vehicle body, the turning part is movably connected to the fixing part, and can be folded relative to the fixing part; the tilting connecting part is rotatably arranged on the wing assembly; the rotor
  • the component is connected with the tilting connector in transmission to change the spatial angle driven by the tilting connector, which improves the flexibility of the flying car in the process of parking and transition, and makes the flying car also have vertical take-off and landing and level flight
  • the functions can fully meet the travel needs of various scenarios.
  • the turning part of the wing assembly of the aircraft or flying car provided by the present invention can be folded relative to the fixed part, so that the wing assembly can be folded, which improves the parking and transition process of the aircraft or flying car.
  • the rotor assembly can change the spatial angle under the drive of the tilting connector, so that the aircraft or flying car can also have the functions of vertical take-off, landing and level flight, which can fully meet the travel needs of various scenarios.
  • Fig. 1 is a schematic structural diagram of an aircraft provided by an embodiment of the present invention.
  • Fig. 2 is a structural schematic diagram of the tilting connector, the rotor assembly and the nacelle of the aircraft shown in Fig. 1 .
  • FIG. 3 is a schematic structural view of the aircraft shown in FIG. 1 in a vertical take-off and landing condition.
  • Fig. 4 is a structural schematic diagram of the aircraft shown in Fig. 1 in a level flight cruising condition.
  • Fig. 5 is a structural schematic diagram of the aircraft shown in Fig. 1 under the ground transition condition.
  • FIG. 6 is a structural schematic view of the aircraft shown in FIG. 5 from another viewing angle.
  • Fig. 7 is a schematic structural diagram of a wing assembly provided by an embodiment of the present invention.
  • Fig. 8 is a schematic structural diagram of a flying car provided by an embodiment of the present invention.
  • the inventor of the present application has found through research that many companies have developed a variety of urban aircrafts, including urban helicopters, aircrafts using the principle of multi-rotors, aircrafts that adopt the short-distance taxi take-off and landing, and aircrafts that use Multi-rotor aircraft.
  • Joby S4 adopts the six-rotor tilt-rotor scheme, which has a large wingspan and can only take off and land on a fixed dedicated apron, which cannot meet the needs of transition.
  • both take-off and landing need to run, and a certain distance of barrier-free runway is required to take off and land.
  • Klein With the combination of fixed wing and car, both takeoff and landing need to run, and a certain distance of barrier-free runway is required to take off and land.
  • the traditional dual-rotor tilt-rotor aircraft has both the characteristics of a helicopter and a fixed-wing. Compared with fixed-wing aircraft, the tilt-rotor can take off and land vertically without relying on the airport runway; compared with the traditional helicopter, the tilt-rotor has a greater cruising speed and range. When cruising, it flies in the form of a fixed wing. More economical than helicopters.
  • the existing tilt-rotor models include Bell’s V22 and V280, both of which adopt the conventional layout of horizontal double-rotors.
  • the attitude is controlled by the same rotor cycle as the helicopter.
  • the same rudder surface as that of the fixed wing is mainly used to control the attitude.
  • the object of the present invention is to address the deficiencies in the existing aircraft technology, and provide an aircraft, a wing assembly and a flying car, which have the functions of vertical take-off and landing, level flight and transition, and have broad application prospects.
  • the present invention provides an aircraft 1 , which includes a fuselage 10 , a wing assembly 20 , a tilting connector 30 and a rotor assembly 50 .
  • the wing assembly 20 includes a fixed portion 21 and a turning portion 23, the fixing portion 21 is arranged on the fuselage 10, the turning portion 23 is movably connected to the fixing portion 21, and can be folded relative to the fixing portion 21; the tilting connector 30 It is rotatably arranged on the wing assembly 20 ; the rotor assembly 50 is in driving connection with the tilting link 30 , so as to change the spatial angle driven by the tilting link 30 .
  • the aircraft 1 is an urban flying device, that is, a flying device for supplementary traffic between cities.
  • the aircraft 1 can also be used in fields such as video shooting, agricultural irrigation and fire rescue.
  • the cross section of the wing assembly 20 is roughly oval, and the wing assembly 20 can be used to bear aerodynamic force.
  • the air flow velocity under the wing assembly 20 is slow and the pressure is strong. Therefore, a pressure difference is formed between the upper and lower surfaces of the wing assembly 20 , which generates lifting force on the fuselage 10 , which is beneficial to the ascent of the aircraft 1 .
  • the wing assembly 20 is in direct contact with the outside, so the material of the wing assembly 20 needs to have high strength, good plasticity, smooth surface, and high corrosion resistance.
  • the extending direction of the wing assembly 20 is perpendicular to the extending direction of the fuselage 10 .
  • the wing assembly 20 includes a fixed portion 21 and a turning portion 23, the fixing portion 21 and the turning portion 23 are sequentially arranged along the extending direction of the wing assembly 20, wherein the fixing portion 21 is arranged on the fuselage 10, for example, the fixing portion 21 can be It is fixed to the fuselage 10 by means of welding, rivet connection and the like.
  • the turning part 23 is movably connected to the fixing part 21, and can turn relative to the fixing part 21.
  • the turning part 23 can be turned relative to the fixed part 21, so that the wing assembly 20 can be folded, and the folding of the wing assembly 20 can reduce the overall size of the aircraft 1, especially the width of the aircraft 1, so that the aircraft 1 can turn on a road surface. There is still the possibility of parking and transition when parking in a parking lot or a relatively narrow berth, which improves the flexibility of the aircraft 1 in the process of parking and transition.
  • the fixing portion 21 extends along the first direction, that is, the wing assembly 20 and the turning portion 23 also extend along the first direction.
  • the length of the fixing portion 21 is 10%-30% of the length of the wing assembly 20 , which greatly reduces the width of the folded aircraft 1 and facilitates the transition of the aircraft 1 .
  • the length of the fixing portion 21 is approximately 1/4 of the length of the wing assembly 20 , that is, the length of the turning portion 23 is approximately 3/4 of the length of the wing assembly 20 .
  • the turning portion 23 has a first rotation axis and a second rotation axis, the first rotation axis extends along the first direction, the second rotation axis extends along the second direction, the first direction is perpendicular to the second direction, In order to realize step-by-step folding of the wing assembly 20, the damage caused by the wing assembly 20 during the folding process is reduced.
  • the turning portion 23 first rotates 90° upward or downward along the second axis of rotation, and then rotates 90° backward along the first axis of rotation.
  • the turning part 23 has a first rotation axis and a third rotation axis, wherein the third rotation axis extends along the third direction, the first direction, the second direction and the third direction are perpendicular to each other, and the turning The part 23 can first rotate 90° along the first axis of rotation, and then rotate back 90° along the third axis of rotation.
  • “up”, “down”, and “backward” are all defined from the perspective of the normal flight of the aircraft 1 .
  • the wing assembly 20 extends along a first direction
  • the fuselage 10 extends along a second direction.
  • first direction as the X direction
  • second direction as the Y direction
  • third direction as the Z direction
  • the three directions are perpendicular to each other.
  • the turning portion 23 includes a first turning section 231 and a second turning section 232 , and the second turning section 232 is rotatable relative to the first turning section 231 .
  • the rotation axis of the second turning section 232 extends along the X direction.
  • the first turning section 231 is movably connected to the fixing part 21 and can turn relative to the fixing part 21 .
  • the first turning section 231 can drive the second turning section 232 to turn.
  • the first turning section 231 is fixedly connected to the fixed part 21.
  • the first turning section 231 can be manually adjusted or electrically controlled to turn relative to the fixed part 21, so as to realize the wing assembly 20. Folding is convenient for the ground transition of the aircraft 1.
  • the first turning section 231 is provided with a tilting connecting piece 30, and the tilting connecting piece 30 is rotatably arranged on the first turning section 231, and the tilting connecting piece 30 can be used to drive the second turning The section 232 rotates so that the second turning section 232 turns relative to the first turning section 231 .
  • the second turning section 232 is connected to the tilting connecting member 30 , and the second turning section 232 is also provided with the rotor assembly 50 .
  • the rotor assembly 50 can be fixedly arranged on the second turning section 232 , for example, the rotor assembly 50 can be fixedly connected to the second turning section 232 by means of screw connection.
  • the wing assembly 20 further includes an engine nacelle 25 connected to the fixing portion 21 , for example, the engine nacelle 25 is connected below the fixing portion 21 .
  • the nacelle 25 extends in the Y direction.
  • the engine compartment 25 can be used to install structures such as an engine. In this embodiment, there are two engine compartments 25 , and each engine compartment 25 is connected to one fixing portion 21 .
  • the nacelle 25 includes a first end 252 and a second end 254 opposite to each other, wherein the first end 252 faces the traveling direction of the aircraft 1 and is a front end.
  • the second end 254 faces away from the traveling direction of the aircraft 1 and is the rear end.
  • the traveling direction refers to the flying direction of the aircraft 1 during normal flight.
  • the nacelle 25 is provided with a tilting connector 30, the tilting connector 30 is rotatably arranged at the first end 252 (Fig. 4), and the tilting connector 30 can be used to drive the rotor assembly 50 Tilt to change the state of rotor assembly 50 .
  • the tilting link 30 is rotatably disposed on the wing assembly 20 ( FIG. 1 ), and the tilting link 30 can be driven to rotate by a motor (not shown).
  • the number of tilting connectors 30 is four, wherein two tilting connectors 30 are respectively arranged on the first ends 252 of the two engine compartments 25, and the other two tilting connectors 30 are respectively arranged at the two first turning sections 231 .
  • the first end 252 of the nacelle 25 is provided with a motor, and the motor is in transmission connection with the tilting connector 30.
  • the rotation of the motor can drive the tilting connector 30 to rotate, thereby driving the rotor assembly 50 to tilt and changing the state of the rotor assembly 50.
  • the tilting connecting member 30 may be a hinge structure.
  • the rotor assembly 50 has a rotor state and a fixed wing state, wherein, during the rotor state, the axis of rotation of the rotor assembly 50 extends along the Z direction, which can generate lift, so that the aircraft 1 has the ability to take off and land vertically; during the fixed wing state, the rotor assembly 50 The axis of rotation extends along the Y direction and can generate thrust so that the aircraft 1 has the capability of high-speed level flight.
  • the flight mode of the aircraft 1 can be controlled, and the wing assembly 20 can be folded so that the aircraft 1 can be parked and transferred flexibly.
  • the aircraft 1 also has the advantages of good flexibility in vertical take-off and landing, level flight, parking and transition, and can meet the needs of short- and medium-distance manned missions in the air, improving the practicability of the aircraft 1 .
  • the rotor assembly 50 is in drive connection with the tilting link 30 to change the spatial angle driven by the tilting link 30 , thereby realizing the transition between the rotor state of the rotor assembly 50 and the fixed wing state. switch.
  • the tilting connector 30 is directly connected to the rotor assembly 50 to drive the rotor assembly 50 to tilt, or is connected to the second turning section 232 to drive the second turning section 232 to tilt, thereby driving the second turning section 232 to tilt.
  • the rotor assembly 50 on the section 232 is tilted to ensure that the thrust direction of the rotor assembly 50 can be changed upwards or forwards to meet the requirements of providing lift or thrust when the aircraft 1 is in VTOL and VTOL-to-level flight transition conditions. Purpose.
  • the rotor assembly 50 includes a tilt rotor body 51 and a rotor mount 53 , the rotor mount 53 is in transmission connection with the tilt connector 30 , and the tilt rotor body 51 is rotatably arranged on the rotor mount 53 , the tilt rotor body 51 includes a tilt rotor blade 512, and the tilt rotor blade 512 can be bent relative to the rotor mount 53, which can reduce the length of the aircraft 1 and improve the flexibility of the aircraft 1 during parking and field transition. sex.
  • the rotor assembly 50 includes a straight rotor module 55, and the straight rotor module 55 is arranged on the second turning section 232, that is, the straight rotor module 55 is arranged on the wing assembly 20 away from the aircraft.
  • the straight rotor module 55 can be fixedly connected to one end of the second turning section 232 facing the traveling direction of the aircraft 1 through the connecting column 54 .
  • the straight rotor module 55 is in the Horizontal position; when the turning portion 23 extends along the X direction, and the second turning section 232 rotates relative to the first turning section 231, the rotation axis of the straight rotor assembly 50 extends along the Z direction. At this time, the straight rotor module 55 is in a vertical position.
  • the straight rotor module 55 also includes a tilt rotor body 51 and a rotor mount 53 .
  • the straight rotor module 55 and the second turning section 232 form a power mechanism, and the center of gravity of the power mechanism is positioned at the axis of rotation of the second turning section 232, so that the rotation of the straight rotor module 55 will not change the center of gravity of the power mechanism, which can Ensure the stability of the center of gravity of the power mechanism and the efficiency of the vertical lift.
  • the center of gravity of the power mechanism is located at the rotation axis of the second turning section 232, which can also effectively reduce the driving torque of the motor that drives the tilting connector 30 ( Figure 2) to rotate, and reduce the weight of the motor that drives the tilting connector 30 to rotate. Thereby reducing the overall weight of the aircraft 1 .
  • the number of straight rotor modules 55 is two, and one straight rotor module 55 is correspondingly arranged on one turning portion 23, that is, two straight rotor modules 55 are respectively connected to two corresponding a second turning section 232.
  • the rotor assembly 50 includes a tilt rotor module 57 disposed at the first end 252 of the nacelle 25 and connected to the tilt connector 30 .
  • the tilt rotor module 57 is arranged at the first end 252, which can ensure that the direction of the pulling force or thrust of the motor of the aircraft 1 is in the vertical direction when the aircraft 1 is hanging up.
  • the structure of the tilt rotor module 57 is substantially the same as that of the straight rotor module 55 .
  • the rotation axis of the tilt rotor module 57 selectively extends along the Y direction or along the Z direction.
  • the tilt rotor module 57 When the rotation axis of the tilt rotor module 57 extends along the Y direction, the tilt rotor module 57 is in a horizontal position, and when the rotation axis of the tilt rotor module 57 extends along the Z direction, the tilt rotor module 57 is in a vertical position. Location.
  • the aircraft 1 also includes a turning mechanism 70, the turning mechanism 70 is arranged on the nacelle 25, and the turning portion 23 can turn relative to the fixed portion 21 through the turning mechanism 70, so that the turning portion 23 is relatively fixed.
  • the turning of the turning part 23 is more smooth, and the turning efficiency of the turning part 23 is improved.
  • the folding mechanism 70 may be fixed to the engine compartment 25 .
  • the turning mechanism 70 may include a first rotating shaft 71 and a second rotating shaft 73, wherein the first rotating shaft 71 is used to drive the turning portion 23 to rotate along the first axis of rotation, and the second rotating shaft 73 is used to drive the turning portion 23 to rotate along the second axis of rotation.
  • the rotation axis rotates to realize step-by-step folding of the wing assembly 20 and reduce the damage caused by the wing assembly 20 during the folding process.
  • the turning mechanism 70 can drive the turning part 23 to rotate automatically or manually.
  • both the first rotating shaft 71 and the second rotating shaft 73 can be driven by a motor, or both the first rotating shaft 71 and the second rotating shaft 73 can be driven manually. way of driving.
  • aircraft 1 also comprises fixed rotor module 80, and fixed rotor module 80 and tilt rotor module 57 are respectively arranged on the opposite two ends of nacelle 25, that is, fixed rotor module 80 is arranged on The second end 254.
  • the fixed rotor module 80 will not tilt relative to the engine nacelle 25, and only works to provide part of the lift and pitching balance moment for the whole machine in the vertical take-off and landing and the vertical lift/level flight configuration conversion conditions.
  • each nacelle 25 is provided with a fixed rotor module 80 and a tilt rotor module 57 , that is, there are two fixed rotor modules 80 and two tilt rotor modules 57 .
  • the fixed rotor module 80 includes a fixed shaft 81 and a fixed rotor blade 83, wherein the fixed shaft 81 is fixedly arranged on the nacelle 25, and the fixed rotor blade 83 is rotatably arranged on the fixed shaft 81, for example, the fixed shaft 81 can be provided with The motor, the fixed rotor blade 83 is installed on the output shaft of the motor, so that the motor drives the fixed rotor blade 83 to rotate.
  • the quantity of straight rotor module 55, tilt rotor module 57 and fixed rotor module 80 is two, straight rotor module 55, tilt rotor module 57 and fixed rotor module 80 can form a six-rotor module, two straight rotor modules 55, two fixed rotor modules 80 and two tilt rotor modules 57 in the six-rotor module are respectively located in the hexagonal , wherein two straight rotor modules 55 are located on a set of diagonals of the hexagon, wherein the straight rotor module 55 on one nacelle 25 and the fixed rotor module on the other nacelle 25 80 is located on a group of diagonals of the hexagon, wherein the fixed rotor module 80 on one nacelle 25 and the straight rotor module 55 on the other nacelle 25 are located on a group of diagonals of the hexagon .
  • the center of gravity of the aircraft 1 is located at the center of the six-rotor module, that is, three groups of diagonal lines have an intersection point, the center of gravity of the aircraft 1 is located at the intersection point, and the aircraft 1 adopts a six-rotor layout.
  • the six-rotor layout can realize the high safety redundancy of the aircraft 1. Specifically, when the aircraft 1 is flying, if any motor fails and the corresponding rotor module stops rotating, it can control the rotor module located on the diagonal. Stop the rotation so that the overall center of gravity of the aircraft 1 will not shift, that is, the sufficient lift provided by the remaining four rotor modules can ensure the stable flight and safe landing of the aircraft 1 within a period of time.
  • the power balance can be realized by controlling the other straight rotor module 55 to stop rotating.
  • the remaining two fixed rotor modules 80 and the two tilt rotor modules 57 can still output sufficient power to ensure the stable flight and safe landing of the aircraft 1 within a period of time.
  • the aircraft 1 also includes an empennage 90 .
  • the arrangement of the empennage 90 can avoid wake interference and improve the efficiency of horizontal tail manipulation.
  • Empennage 90 is roughly " T " shape, and empennage 90 comprises horizontal wing 92 and vertical wing 94, and wherein, the direction of extension of horizontal wing 92 is identical with the direction of wing assembly 20, that is, horizontal wing 92 extends along X direction; Vertical wing 94 Connected between the fuselage 10 and the horizontal wing 92 and extend upwards, that is, along the Z direction, to control the pitch, yaw and tilt of the aircraft 1 , thereby controlling the flight attitude of the aircraft 1 .
  • the aircraft 1 also includes a wheel set 100, which is arranged at the bottom of the fuselage 10.
  • the fuselage 10 can move along the ground through the wheel set 100, so that the aircraft 1 can run on the ground to meet the transition requirements of the aircraft 1.
  • the wheel set 100 may be driven by a hub motor.
  • the aircraft 1 mainly includes three working states: 1. vertical take-off and landing; 2. level flight cruising; 3. ground transition.
  • the aircraft 1 is located on the road and moves to the takeoff and landing platform through the wheel set 100 .
  • the tilt connector 30 arranged at the first end 252 of the nacelle 25 drives the tilt rotor mold.
  • the group 57 is tilted upward by 90°, and the tilting connector 30 arranged on the first turning section 231 drives the second turning section 232 to turn and tilt upward by 90°, thereby driving the straight rotor module 55 to tilt upward by 90°.
  • Both the straight rotor module 55 and the tilt rotor module 57 are turned from the horizontal position to the vertical position, so that the tilt rotor module 57 and the straight rotor module 55 are all switched to the rotor state, and the six rotor modules start to rotate, so that the aircraft 1 vertical rise.
  • the landing conditions include:
  • the tilting connector 30 drives the straight rotor module 55 and the tilting rotor module 57 to slowly tilt from the horizontal position to the vertical position.
  • the wing has a certain angle to improve the lift of the wing assembly 20.
  • the fixed rotor module 80 starts to work to maintain the pitch balance of the whole machine, and the rotor assembly 50 increases the upward lift while reducing the effective pulling force.
  • the aircraft 1 When the aircraft 1 is located above the take-off and landing airport, it drives the tilt rotor module 57 and the straight rotor module 55 to tilt upward by 90°, the six rotor module starts to rotate, and the aircraft 1 lands downward.
  • the level flight cruise conditions include:
  • the tilting connector 30 drives the straight rotor module 55 and the tilting rotor module 57 to tilt to the horizontal position.
  • the fixed rotor module located at the second end 254 of the nacelle 25 The group 80 continues to work to maintain the pitch balance of the whole machine.
  • the flaps of the whole machine have a certain angle to improve the lift of the wing assembly 20, and the rotor assembly 50 increases the forward pulling force while providing effective lift.
  • ground transition conditions include:
  • the folding of the wing assembly 20 and the bending of the tilt rotor blade 512 include: the tilt rotor blade 512 of the straight rotor module 55 is folded backward along the Y direction, and the tilt rotor blade 512 of the tilt rotor module 57 is folded backward.
  • the blade 512 is folded backward along the Y direction, the fixed rotor blade 83 is rotated to be parallel to the nacelle 25, the turning mechanism 70 drives the turning part 23 to turn 90° upwards or downwards along the second axis of rotation, and then rotates along the first axis of rotation.
  • the axis of rotation is rotated 90° backwards.
  • the turning part 23 of the wing assembly 20 of the aircraft 1 provided by the present invention can be turned relative to the fixed part 21, so that the wing assembly 20 can be folded, and the aircraft can be completed automatically or automatically when there is a transition requirement on the ground.
  • the folding of the wing assembly 20 improves the flexibility of the aircraft 1 during parking and transition; in addition, the rotor assembly 50 can change the spatial angle under the drive of the tilting connector 30, so that the aircraft 1 also has the functions of vertical take-off and landing and The function of level flight can fully meet the travel needs of various scenarios.
  • any motor failure will cause the corresponding rotor module to
  • the rotor modules located on the diagonal can be controlled to stop the rotation, so that the overall center of gravity of the aircraft 1 will not shift, that is, the sufficient lift provided by the remaining four rotor modules can ensure that the aircraft 1 is in the The stable flight and safe landing within a period of time can realize the high safety redundancy feature of the aircraft 1 .
  • the present invention also provides a wing assembly 20, the wing assembly 20 includes a fixed portion 21 and a turning portion 23, the fixing portion 21 is arranged on the fuselage, and the turning portion 23 is movably connected to the fixing portion 21 , and can be folded relative to the fixed part 21.
  • the folding part 23 of the wing assembly 20 provided by the present invention can be folded relative to the fixed part 21, so that the wing assembly 20 can be folded, and the wing assembly can be completed automatically or automatically when there is a transition requirement on the ground.
  • the folding of 20, when the wing assembly 20 is used for the aircraft 1, can improve the flexibility of the aircraft 1 during parking and transition.
  • the present invention also provides a flying car 2 , including a body 200 , a wing assembly 20 , a tilting connector 30 ( FIG. 2 ) and a rotor assembly 50 .
  • the wing assembly 20 includes a fixed portion 21 and a turning portion 23, the fixing portion 21 is arranged on the vehicle body 200, the turning portion 23 is movably connected to the fixing portion 21, and can be folded relative to the fixing portion 21; the tilting connector 30 can It is rotatably arranged on the wing assembly 20 ; the rotor assembly 50 is in transmission connection with the tilting link 30 , so as to change the spatial angle driven by the tilting link 30 .
  • the wing assembly 20 can be fixedly arranged on the vehicle body 200 , for example, the wing assembly 20 can be fixed to the vehicle body 200 by rivets.
  • the number of wing assemblies 20 is two, and the two wing assemblies 20 are respectively arranged on both sides of the flying car body 2 along the flight direction.
  • the tilting of the flying car 2 can realize the switching between the rotor flight state and the fixed-wing flight state.
  • the folding part 23 of the wing assembly 20 of the flying car 2 provided by the present invention can be folded relative to the fixed part 21, so that the wing assembly 20 can be folded, and it can be completed automatically or automatically when there is a transition requirement on the ground.
  • the folding of the wing assembly 20 improves the flexibility of the flying car 2 during parking and transition; in addition, the rotor assembly 50 can change the spatial angle under the drive of the tilting connector 30, so that the aircraft 1 also has vertical take-off and The functions of landing and level flight can fully meet the travel needs of various scenarios.

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Abstract

公布了一种飞行器（1）、一种机翼组件和飞行汽车，飞行器（1）包括机身（10）、机翼组件（20）、倾转连接件（30）和旋翼组件（50）。机翼组件（20）包括固定部（21）和折转部（23），固定部（21）设置于机身（10），折转部（23）可活动地连接于固定部（21），并且相对固定部（21）可折转；倾转连接件（30）可转动地设置于机翼组件（20）；旋翼组件（50）与倾转连接件（30）传动连接，以在倾转连接件（30）的带动下改变空间角度。本飞行器的机翼组件的折转部相对固定部可折转，使得机翼组件能够折叠，提高了飞行器在停泊及转场过程中的灵活性；另外，旋翼组件可以在倾转连接件的带动下改变空间角度，使得飞行器还具有垂直起飞及降落及平飞的功能，能够充分满足各场景出行需求。

Description

飞行器、机翼组件及飞行汽车
相关申请的交叉引用
本申请要求于2021年10月11日提交的申请号为2021111838900的中国申请的优先权，其在此处于所有目的通过引用将其全部内容并入本文。
技术领域
本发明涉及飞行设备技术领域，具体而言，涉及一种飞行器、机翼组件及飞行汽车。
背景技术
随着科技的不断发展，飞行装置的应用也越来越广泛，飞行装置除了用于视频拍摄、农业浇灌及消防救援外，还可以用于人们的日常出行。
然而，现有的飞行装置无法兼顾垂直起降、水平飞行及折叠转场，难以满足各场景出行需求。
发明内容
本发明实施例的目的在于提供一种飞行器、机翼组件及飞行汽车，以改善上述问题。本发明实施例通过以下技术方案来实现上述目的。
第一方面，本发明提供一种飞行器，包括机身、机翼组件、倾转连接件和旋翼组件。机翼组件包括固定部和折转部，固定部设置于机身，折转部可活动地连接于固定部，并且相对固定部可折转；倾转连接件可转动地设置于机翼组件；旋翼组件与倾转连接件传动连接，以在倾转连接件的带动下改变空间角度,使得机翼组件能够折叠，提高了飞行器在停泊及转场过程中的灵活性；另外，旋翼组件可以在倾转连接件的带动下改变空间角度，使得飞行器还具有垂直起飞及降落及平飞的功能，能够充分满足各场景出行需求。
在一种实施方式中，固定部沿第一方向延伸，折转部具有第一转动轴线和第二转动轴线，第一转动轴线沿第一方向延伸，第二转动轴线沿第二方向延伸，第一方向与第二方向垂直,以实现分步对机翼组件进行折叠，减少机翼组件在折叠过程中造成的损害。
在一种实施方式中，飞行器还包括折转机构，折转部通过折转机构相对固定部可折转，折转机构包括第一转轴和第二转轴，折转部通过第一转轴沿第一转动轴线转动，折转部通过第二转轴沿第二转动轴线转动，以实现分步对机翼组件进行折叠，减少机翼组件在折叠过程中造成的损害。
在一种实施方式中，旋翼组件具有旋翼状态和固定翼状态，当旋翼组件处于旋翼状态时，旋翼组件的旋转轴线沿第三方向延伸，当旋翼组件处于固定翼状态时，旋翼组件的旋转轴线沿第二方向延伸，第三方向垂直于第一方向和所述第二方向，使得飞行器既具备垂直起降的能力又具备高速平飞的能力。
在一种实施方式中，旋翼组件包括倾转旋翼本体和旋翼安装座，旋翼安装座与倾转连接件传动连接，倾转旋翼本体可转动地设置于旋翼安装座，倾转旋翼本体包括倾转旋翼桨叶，倾转旋翼桨叶相对旋翼安装座可弯折，能够减小飞行器的长度，提高了飞行器在停泊及转场过程中的灵活性。
在一种实施方式中，折转部包括第一折转段和第二折转段，第一折转段可活动地连接于固定部，并且相对固定部可折转，第一折转段设有倾转连接件，第二折转段连接于倾转连接件，旋翼组件包括平直旋翼模组，平直旋翼模组设置于第二折转段，平直旋翼模组设置于机翼组件远离机身的一端，避免机翼组件对平直旋翼模组的倾转产生影响。
在一种实施方式中，机翼组件还包括发动机舱，发动机舱连接于固定部，飞行器还包括折转机构，折转机构设置于发动机舱，折转部通过折转机构相对固定部可折转，使得折转部相对固定部的折转更加顺畅，提升折转部的折转效率。
在一种实施方式中，发动机舱设有倾转连接件，旋翼组件包括倾转旋翼模组，倾转旋翼模组连接于倾转连接件，能够保证飞行器在垂起工况下电机拉力方向或者推力方向为垂直方向。
在一种实施方式中，飞行器还包括固定旋翼模组，固定旋翼模组与倾转旋翼模组分别设置于发动机舱 的相对两端，固定旋翼模组包括固定轴和固定旋翼桨叶，固定旋翼桨叶可转动地设置于固定轴，固定轴固定设置于发动机舱，以保持整机俯仰平衡。
在一种实施方式中，机翼组件为两个，两个机翼组件分别连接于机身的相对两侧，每个折转部均设有一个平直旋翼模组，每个发动机舱均设有一个固定旋翼模组和一个倾转旋翼模组，实现飞行器的高安全冗余特性。
在一种实施方式中，平直旋翼模组、倾转旋翼模组与固定旋翼模组组成六旋翼模组，飞行器的重心位于六旋翼模组的中心，使得飞行器的整体重心不会发生偏移保，保证飞行器的稳定飞行和安全降落。
在一种实施方式中，当平直旋翼模组和倾转旋翼模组均由水平位置转至垂直位置，控制六旋翼模组开始旋转，使得飞行器垂直上升。
在一种实施方式中，发动机舱包括相对的第一端和第二端，第一端朝向飞行器的行进方向，第二端背离飞行器的行进方向，倾转旋翼模组设置于第一端，固定旋翼模组设置于第二端。
在一种实施方式中，平直旋翼模组与第二折转段形成动力机构，动力机构的重心位于第二折转段的转动轴线，能够保证动力机构的重心的稳定性，以及确保垂起升力的效率性。
在一种实施方式中，固定部的长度为机翼组件的长度的10％-30％，大大减小了折叠后的飞行器的宽度，利于飞行器的转场。
在一种实施方式中，飞行器还包括尾翼，尾翼连接于机身，以避开尾流干扰，提高了平尾操纵效率。
在一种实施方式中，尾翼包括水平翼和垂直翼，垂直翼连接于机身和所述水平翼之间并且向上延伸，水平翼的延伸方向与机翼组件的方向相同，从而控制飞行器的飞行姿态。
在一种实施方式中，飞行器还包括轮组，轮组设置于机身的底部，机身通过轮组沿地面可移动，从而满足飞行器的转场需求。
第二方面，本发明还提供一种机翼组件，机翼组件包括固定部和折转部，固定部设置于机身，折转部可活动地连接于固定部，并且相对固定部可折转，使得机翼组件能够折叠，提高了飞行器在停泊及转场过程中的灵活性。
第三方面，本发明还提供一种飞行汽车，包括车身、机翼组件、倾转连接件和旋翼组件。机翼组件包括固定部和折转部，固定部设置于车身，折转部可活动地连接于固定部，并且相对固定部可折转；倾转连接件可转动地设置于机翼组件；旋翼组件与倾转连接件传动连接，以在倾转连接件的带动下改变空间角度，提高了飞行汽车在停泊及转场过程中的灵活性，并且使得飞行汽车还具有垂直起飞及降落及平飞的功能，能够充分满足各场景出行需求。
相较于现有技术，本发明提供的飞行器或飞行汽车的机翼组件的折转部相对固定部可折转，使得机翼组件能够折叠，提高了飞行器或飞行汽车在停泊及转场过程中的灵活性；另外，旋翼组件可以在倾转连接件的带动下改变空间角度，使得飞行器或飞行汽车还具有垂直起飞及降落及平飞的功能，能够充分满足各场景出行需求。
本发明的这些方面或其他方面在以下实施例的描述中会更加简明易懂。
附图说明
为了更清楚地说明本申请实施例中的技术方案，下面将对实施例描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本申请的一些实施例，对于本领域技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1是本发明实施例提供的飞行器的结构示意图。
图2是图1所示的飞行器的倾转连接件、旋翼组件和发动机舱的结构示意图。
图3是图1所示的飞行器在垂直起降工况下的结构示意图。
图4是图1所示的飞行器在平飞巡航工况下的结构示意图。
图5是图1所示的飞行器在地面转场工况下的结构示意图。
图6是图5所示的飞行器在另一视角下的结构示意图。
图7是本发明实施例提供的机翼组件的结构示意图。
图8是本发明实施例提供的飞行汽车的结构示意图。
具体实施方式
为了便于理解本发明实施例，下面将参照相关附图对本发明实施例进行更全面的描述。附图中给出了本发明的较佳实施方式。但是，本发明可以以许多不同的形式来实现，并不限于本文所描述的实施方式。相反地，提供这些实施方式的目的是使对本发明的公开内容理解的更加透彻全面。
除非另有定义，本文所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本文中在本发明实施例中所使用的术语只是为了描述具体的实施方式的目的，不是旨在于限制本发明。
本申请的发明人经过研究发现，目前已有多家公司研制出了多种城市用飞行器，有城市用直升机、有采用多旋翼原理的飞行器、有采用短距滑跑起降的飞行器、有采用多倾转旋翼的飞行器。
然而，现有的飞行器设计方案并不能兼顾道路上行驶、垂直起降、水平飞行及转场功能，大部分不能在道路上行驶或者不能垂直起飞。例如亿航216和
Figure PCTCN2021129539-appb-000001
本身只具有固定式起落架，降落后无法自主移动，乘客需要下机后再采用其他交通方式到达目的地。再例如Joby
Figure PCTCN2021129539-appb-000002
S4，采用六旋翼的倾转旋翼方案，翼展较大，只能在固定的专用停机坪起降，不能满足转场需求。例如
Figure PCTCN2021129539-appb-000003
采用三轮车与旋翼机结合的方式，起飞和降落都需要滑跑，需要一定距离的无障碍跑道才能起飞和降落。又例如Klein
Figure PCTCN2021129539-appb-000004
采用固定翼与汽车结合的方式，起飞和降落都需要滑跑，需要一定距离的无障碍跑道才能起飞和降落。
传统双旋翼的倾转旋翼飞行器兼有直升机和固定翼的特点。与固定翼飞机相比，倾转旋翼可以垂直起降，没有对机场跑道的依赖；与传统直升机相比，倾转旋翼有更大的巡航速度和航程，巡航时，以固定翼的形式飞行，比直升机更经济。
现有的倾转旋翼机型有贝尔公司的V22和V280，其都采用横列式双旋翼常规布局，在垂直飞行及垂直平飞转换阶段都是靠和直升机一样的旋翼周期变距控制姿态，在平飞构型下，主要采用和固定翼一样的舵面控制姿态。
现有双旋翼倾转旋翼机型非常依赖周期变距机构来实现控制，在使用周期变距控制纵向姿态的时候，会引起飞机向前飞行的耦合效应。而且周期变距机构结构复杂，复杂的结构和控制方式极大增加了飞机的研发及制造成本，同时对安全性和可靠性也带来很大的挑战。
现有的飞行器产品都没有完美解决航程长、垂起降落、路面转场的问题，而在未来的城市、城际用飞行器应该同时具备以上功能为市场带来一款安全性高、崭新的，突破性的飞行器以满足市场需求。
本发明的目的是针对现有的飞行器技术上存在的不足，提供一种飞行器、机翼组件及飞行汽车，兼有垂直起降、平飞以及转场的功能，具有广阔的应用前景。
以下结合具体实施方式和说明书附图对本发明提供的飞行器、机翼组件及飞行汽车进行详细说明。
请参阅图1和图2，本发明提供一种飞行器1，包括机身10、机翼组件20、倾转连接件30和旋翼组件50。机翼组件20包括固定部21和折转部23，固定部21设置于机身10，折转部23可活动地连接于固定部21，并且相对固定部21可折转；倾转连接件30可转动地设置于机翼组件20；旋翼组件50与倾转连接件30传动连接，以在倾转连接件30的带动下改变空间角度。
在本实施例中，飞行器1为城市用飞行设备，即，在城市之间进行交通补充的飞行设备。在其他实施方式中，飞行器1还可以用于视频拍摄、农业浇灌及消防救援等领域。
机翼组件20的横截面大致为椭圆形，机翼组件20可以用于承受空气动力，机翼组件20大致椭圆形的结构使得位于机翼组件20上方的空气流动速度快，压强小，而位于机翼组件20下方的空气流动速度慢，压强大，因此，机翼组件20的上下表面之间形成压力差，对机身10产生托举力，利于飞行器1的上升。机翼组件20与外界直接接触，因此机翼组件20的材料需要具有强度高、塑性好、表面光滑的性能，并且具有较高的抗蚀能力。机翼组件20为两个，两个机翼组件20分别连接于机身10的相对两侧，两个机翼组件20之间也可以连接。机翼组件20的延伸方向与机身10的延伸方向垂直。
机翼组件20包括固定部21和折转部23，固定部21和折转部23沿机翼组件20的延伸方向依次设置，其中，固定部21设置于机身10，例如，固定部21可以通过焊接、铆钉连接等方式固定于机身10。折转部 23可活动地连接于固定部21，并且相对固定部21可折转。折转部23相对固定部21可折转，使得机翼组件20能够折叠，机翼组件20的折叠能够减小飞行器1的整体尺寸，尤其是飞行器1的宽度，使得飞行器1能够在有路面转场或较狭窄的停泊位停泊时仍然具有停泊、转场的可能性，提高了飞行器1在停泊及转场过程中的灵活性。
在本实施例中，固定部21沿第一方向延伸，即，机翼组件20和折转部23也沿第一方向延伸。在本实施例中，固定部21的长度为机翼组件20的长度的10％-30％，大大减小了折叠后的飞行器1的宽度，利于飞行器1的转场。例如，固定部21的长度大致为机翼组件20长度的1/4，即，折转部23的长度大致为机翼组件20长度的3/4。
在本实施例中，折转部23具有第一转动轴线和第二转动轴线，第一转动轴线沿第一方向延伸，第二转动轴线沿第二方向延伸，第一方向与第二方向垂直,以实现分步对机翼组件20进行折叠，减少机翼组件20在折叠过程中造成的损害。在本实施例中，折转部23先沿第二转动轴线向上或者向下转动90°，再沿第一转动轴线向后转动90°。在其他实施方式中，折转部23具有第一转动轴线和第三转动轴线，其中，第三转动轴线沿第三方向延伸，第一方向、第二方向和第三方向两两垂直，折转部23可以先沿第一转动轴线转动90°，再沿第三转动轴线向后转动90°。其中“向上”、“向下”、“向后”均是以飞行器1的正常飞行的视角进行定义的。
在本实施例中，机翼组件20沿第一方向延伸，机身10沿第二方向延伸。为了便于描述，定义第一方向为X方向，第二方向为Y方向，第三方向为Z方向，三个方向相互垂直。
折转部23包括第一折转段231和第二折转段232，第二折转段232相对第一折转段231可转动。当折转部23未相对固定部21折转，即，折转部23沿X方向延伸时，第二折转段232的转动轴线沿X方向延伸。
第一折转段231可活动地连接于固定部21，并且相对固定部21可折转，第一折转段231可以带动第二折转段232折转。在没有转场需求时，第一折转段231与固定部21固定连接，当需要转动时，可以手动调节或电动控制第一折转段231相对固定部21折转，实现机翼组件20的折叠，便于飞行器1的地面转场。
在本实施例中，第一折转段231设有倾转连接件30，倾转连接件30可转动地设置于第一折转段231，倾转连接件30可以用于带动第二折转段232转动，使得第二折转段232相对第一折转段231转动。
第二折转段232连接于倾转连接件30，第二折转段232还设有旋翼组件50。旋翼组件50可以固定设置于第二折转段232，例如，旋翼组件50可以通过螺钉连接的方式与第二折转段232固定连接。当设置于第一折转段231的倾转连接件30相对第一折转段231转动时会带动第二折转段232转动，第二折转段232的转动可以带动旋翼组件50倾转。
请参阅图3和图4，机翼组件20还包括发动机舱25，发动机舱25连接于固定部21，例如，发动机舱25连接于固定部21的下方。发动机舱25沿Y方向延伸。发动机舱25可以用于安装发动机等结构。在本实施例中，发动机舱25的数量为两个，每个发动机舱25连接于一个固定部21。
发动机舱25包括相对的第一端252和第二端254，其中，第一端252朝向飞行器1的行进方向，为前端。第二端254背离飞行器1的行进方向，为后端。行进方向指的是飞行器1在正常飞行时的飞行方向。
请参阅图2和图3，发动机舱25设有倾转连接件30，倾转连接件30可转动地设置于第一端252(图4)，倾转连接件30可以用于带动旋翼组件50倾转，以改变旋翼组件50的状态。
倾转连接件30可转动地设置于机翼组件20(图1)，倾转连接件30可以由电机(图未示)驱动而转动。在本实施例中，倾转连接件30的数量为四个，其中，两个倾转连接件30分别设置于两个发动机舱25的第一端252，另外两个倾转连接件30分别设置于两个第一折转段231。例如，发动机舱25的第一端252设有电机，电机与倾转连接件30传动连接，电机的转动可以带动倾转连接件30转动，从而带动旋翼组件50倾转，改变旋翼组件50的状态。在本实施例中，倾转连接件30可以是铰链结构。
旋翼组件50具有旋翼状态和固定翼状态，其中，旋翼状态时，旋翼组件50的旋转轴线沿Z方向延伸，能够产生升力，使得飞行器1具备垂直起降的能力；固定翼状态时，旋翼组件50的旋转轴线沿Y方向延伸，能够产生推力，使得飞行器1具备高速平飞的能力。通过控制旋翼组件50的状态，可以控制飞行器1的飞行模式，机翼组件20可折叠，使得飞行器1能够灵活地停泊及转场。飞行器1同时具有垂直起降、平飞、 停泊及转场过程中灵活性好等优点，能够满足中短途空中载人飞行任务的需求，提高了飞行器1的实用性。
请继续参阅图1和图2，旋翼组件50与倾转连接件30传动连接，以在倾转连接件30的带动下改变空间角度，从而实现旋翼组件50的旋翼状态和固定翼状态之间的切换。例如，倾转连接件30直接与旋翼组件50连接以带动旋翼组件50倾转，或者通过与第二折转段232连接，带动第二折转段232倾转，从而带动设置于第二折转段232上的旋翼组件50倾转，保证飞行器1在垂直起降以及垂直起降到平飞转换工况下，旋翼组件50的推力方向可变为向上或向前，以满足提供升力或推力的目的。
请参阅图2和图5，旋翼组件50包括倾转旋翼本体51和旋翼安装座53，旋翼安装座53与倾转连接件30传动连接，倾转旋翼本体51可转动地设置于旋翼安装座53，倾转旋翼本体51包括倾转旋翼桨叶512，倾转旋翼桨叶512相对旋翼安装座53可弯折，能够减小飞行器1的长度，提高了飞行器1在停泊及转场过程中的灵活性。
请参阅图3和图5，旋翼组件50包括平直旋翼模组55，平直旋翼模组55设置于第二折转段232，即，平直旋翼模组55设置于机翼组件20远离机身10的一端，避免机翼组件20对平直旋翼模组55的倾转产生影响。例如，平直旋翼模组55可以通过连接柱54固定连接于第二折转段232朝向飞行器1的行进方向的一端。当折转部23沿X方向延伸，且第二折转段232未相对第一折转段231转动时，平直旋翼组件50的转动轴线沿Y方向延伸，此时平直旋翼模组55处于水平位置；当折转部23沿X方向延伸，且第二折转段232相对第一折转段231转动时，平直旋翼组件50的转动轴线沿Z方向延伸，此时平直旋翼模组55处于垂直位置。平直旋翼模组55也包括倾转旋翼本体51和旋翼安装座53。
平直旋翼模组55与第二折转段232形成动力机构，动力机构的重心位于第二折转段232的转动轴线，使得平直旋翼模组55的转动不会改变动力机构的重心，能够保证动力机构的重心的稳定性，以及确保垂起升力的效率性。动力机构的重心位于第二折转段232的转动轴线，还可以有效减小驱动倾转连接件30(图2)转动的电机的驱动扭矩，减轻驱动倾转连接件30转动的电机的重量，从而减轻飞行器1的整体重量。
在本实施例中，平直旋翼模组55的数量为两个，一个平直旋翼模组55对应设置于一个折转部23，即，两个平直旋翼模组55分别连接于对应的两个第二折转段232。
旋翼组件50包括倾转旋翼模组57，倾转旋翼模组57设置于发动机舱25的第一端252并连接于倾转连接件30。倾转旋翼模组57设置于第一端252，能够保证飞行器1在垂起工况下电机拉力方向或者推力方向为垂直方向。倾转旋翼模组57的结构与平直旋翼模组55的结构大致相同。在倾转连接件30的带动下，倾转旋翼模组57的转动轴线选择性地沿Y方向或者沿Z方向延伸。当倾转旋翼模组57的转动轴线沿Y方向延伸时，倾转旋翼模组57处于水平位置，当倾转旋翼模组57的转动轴线沿Z方向延伸时，倾转旋翼模组57处于垂直位置。
请参阅图5，飞行器1还包括折转机构70，折转机构70设置于发动机舱25，折转部23通过折转机构70相对固定部21可折转，使得折转部23相对固定部21的折转更加顺畅，提升折转部23的折转效率。折转机构70可以固定于发动机舱25。折转机构70可以包括第一转轴71和第二转轴73，其中，第一转轴71用于带动折转部23沿第一转动轴线转动，第二转轴73用于带动折转部23沿第二转动轴线转动，以实现分步对机翼组件20进行折叠，减少机翼组件20在折叠过程中造成的损害。折转机构70可以通过自动或者手动的方式带动折转部23转动，例如，第一转轴71和第二转轴73都可以由电机驱动，或者，第一转轴71和第二转轴73都可以通过手动的方式驱动。
请参阅图3和图4，飞行器1还包括固定旋翼模组80，固定旋翼模组80与倾转旋翼模组57分别设置于发动机舱25的相对两端，即，固定旋翼模组80设置于第二端254。固定旋翼模组80不会相对发动机舱25倾转，只在垂直起飞降落和空中垂起/平飞构型转换工况下工作为整机提供部分升力和俯仰平衡力矩。在本实施例中，每个发动机舱25均设有一个固定旋翼模组80和一个倾转旋翼模组57，即，固定旋翼模组80和倾转旋翼模组57的数量均为两个。
固定旋翼模组80包括固定轴81和固定旋翼桨叶83，其中，固定轴81固定设置于发动机舱25，固定旋翼桨叶83可转动地设置于固定轴81，例如，固定轴81内可以设置电机，固定旋翼桨叶83安装于电机的输出轴，以使电机带动固定旋翼桨叶83转动。
请继续参阅图3，在本实施例中，平直旋翼模组55、倾转旋翼模组57与固定旋翼模组80的数量均为两个，平直旋翼模组55、倾转旋翼模组57与固定旋翼模组80可以组成六旋翼模组，六旋翼模组中的两个平直旋翼模组55、两个固定旋翼模组80和两个倾转旋翼模组57分别位于六边形的顶点，其中，两个平直旋翼模组55位于六边形的一组对角线上，其中一个发动机舱25上的平直旋翼模组55和另一个发动机舱25上的固定旋翼模组80位于六边形的一组对角线上，其中一个发动机舱25上的固定旋翼模组80和另一个发动机舱25上的平直旋翼模组55位于六边形的一组对角线上。
在本实施例中，飞行器1的重心位于六旋翼模组的中心，即，三组对角线具有一个交点，飞行器1的重心位于交点上，飞行器1采用了六旋翼布局。六旋翼布局能够实现飞行器1的高安全冗余特性，具体地，飞行器1在飞行时，任何一个电机失效导致对应的旋翼模组停止转动的情况下，可以控制位于对角线上的旋翼模组停止转动，使得飞行器1的整体重心不会发生偏移，即，可以通过剩余四个旋翼模组提供的足够升力保证飞行器1在一段时间内的稳定飞行和安全降落。例如，当其中一个平直旋翼模组55由于电机故障或者桨叶故障导致平直旋翼模组55无法转动时，可以通过控制另一个平直旋翼模组55停止转动，来实现动力的平衡，通过剩余两个固定旋翼模组80和两个倾转旋翼模组57仍可输出足够功率，保证飞行器1在一段时间内的稳定飞行和安全降落。
请参阅图6，在本实施例中，飞行器1还包括尾翼90，尾翼90的设置，可以避开尾流干扰，提高了平尾操纵效率。尾翼90大致呈“T”型，尾翼90包括水平翼92和垂直翼94，其中，水平翼92的延伸方向与机翼组件20的方向相同，即，水平翼92沿X方向延伸；垂直翼94连接于机身10和水平翼92之间并且向上延伸，即，沿Z方向延伸，以控制飞行器1的俯仰、偏航和倾斜，从而控制飞行器1的飞行姿态。
飞行器1还包括轮组100，轮组100设置于机身10的底部，机身10可以通过轮组100沿地面可移动，使得飞行器1能够在地面上行驶，满足飞行器1的转场需求。在本实施例中，轮组100可以由轮毂电机带动。
以下对本发明提供的飞行器1的工况进行说明。
飞行器1主要包括三种工作状态:1.垂直起飞及降落；2.平飞巡航；3.地面转场。
请参阅图1和图2，其中，垂直起飞工况包括：
1.飞行器1位于路面，通过轮组100移动至起降平台。
2.当飞行器1位于起降平台，通过自动或者手动展开折叠的机翼组件20以及倾转旋翼桨叶512，设置于发动机舱25的第一端252的倾转连接件30带动倾转旋翼模组57向上倾转90°，设置于第一折转段231的倾转连接件30带动第二折转段232转动向上倾转90°，从而带动平直旋翼模组55向上倾转90°，平直旋翼模组55和倾转旋翼模组57均由水平位置转至垂直位置，使得倾转旋翼模组57和平直旋翼模组55均切换至旋翼状态，六旋翼模组开始旋转，使得飞行器1垂直上升。
请继续参阅图1和图2，降落工况包括：
1.当飞行器1接近目的地时，整机平飞速度下降，倾转连接件30带动平直旋翼模组55和倾转旋翼模组57由水平位置开始缓慢向垂直位置倾转，整机襟翼带有一定角度以提高机翼组件20的升力，此时固定旋翼模组80开始工作保持整机俯仰平衡，旋翼组件50在减小有效拉力的同时增加向上的升力。
2.当飞行器1位于起降机场上方，带动倾转旋翼模组57和平直旋翼模组55向上倾转90°，六旋翼模组开始旋转，飞行器1向下降落。
请参阅图2和图4，平飞巡航工况包括：
1.当飞行器1到达一定高度后，倾转连接件30带动平直旋翼模组55和倾转旋翼模组57向水平位置倾转，此时位于发动机舱25的第二端254的固定旋翼模组80持续工作保持整机俯仰平衡，整机襟翼带有一定角度能够提高机翼组件20的升力，旋翼组件50在提供有效升力的同时增加向前的拉力。
2.当飞行器1的飞行速度高于平飞速度后，平直旋翼模组55和倾转旋翼模组57转动至水平位置，此时飞行器1处于平飞巡航工作状态，固定旋翼模组80停止工作，固定旋翼桨叶83旋转至与发动机舱25平行位置时，将固定旋翼桨叶83固定，以减小平飞阻力，整机襟翼收回，飞行器1的主要升力来源由旋翼组件50转变为机翼组件20，旋翼组件50此时仅提供向前的拉力。
请参阅图5和图6，地面转场工况包括：
1.当飞行器1接触地面，平直旋翼模组55和倾转旋翼模组57转动至水平位置，六旋翼模组均停止工作；
2.自动或者手动完成机翼组件20的折叠及倾转旋翼桨叶512的弯折；
3.当飞行器1离开起降平台后，使用轮组100完成目的地中短距离下的转场需求。
其中，机翼组件20的折叠及倾转旋翼桨叶512的弯折包括：平直旋翼模组55的倾转旋翼桨叶512沿Y方向向后折叠，倾转旋翼模组57的倾转旋翼桨叶512沿Y方向向后折叠，固定旋翼桨叶83旋转至与发动机舱25平行，折转机构70带动折转部23先沿第二转动轴线向上或者向下转动90°，再沿第一转动轴线向后转动90°。
综上，本发明提供的飞行器1的机翼组件20的折转部23相对固定部21可折转，使得机翼组件20能够折叠，在地面有转场需求时可通过自动或者的方式完成机翼组件20的折叠，提高了飞行器1在停泊及转场过程中的灵活性；另外，旋翼组件50可以在倾转连接件30的带动下改变空间角度，使得飞行器1还具有垂直起飞及降落及平飞的功能，能够充分满足各场景出行需求。另外，还通过两个平直旋翼模组55、两个倾转旋翼模组57与两个固定旋翼模组80组成的六旋翼模组的布局方式，使得任何一个电机失效导致对应的旋翼模组停止转动的情况下，可以控制位于对角线上的旋翼模组停止转动，使得飞行器1的整体重心不会发生偏移，即，可以通过剩余四个旋翼模组提供的足够升力保证飞行器1在一段时间内的稳定飞行和安全降落，能够实现飞行器1的高安全冗余特性。
请参阅图7，本发明还提供一种机翼组件20，机翼组件20包括固定部21和折转部23，固定部21设置于机身，折转部23可活动地连接于固定部21，并且相对固定部21可折转。
综上，本发明还提供的机翼组件20的折转部23相对固定部21可折转，使得机翼组件20能够折叠，在地面有转场需求时可通过自动或者的方式完成机翼组件20的折叠，当机翼组件20用于飞行器1时，能够提高飞行器1在停泊及转场过程中的灵活性。
请参阅图8，本发明还提供一种飞行汽车2，包括车身200、机翼组件20、倾转连接件30(图2)和旋翼组件50。机翼组件20包括固定部21和折转部23，固定部21设置于车身200，折转部23可活动地连接于固定部21，并且相对固定部21可折转；倾转连接件30可转动地设置于机翼组件20；旋翼组件50与倾转连接件30传动连接，以在倾转连接件30的带动下改变空间角度。
机翼组件20可以固定设置于车身200，例如，可以通过铆钉将机翼组件20固定于车身200。
在本实施例中，机翼组件20的数量为两个，两个机翼组件20分别设置于飞行汽车车体2沿飞行方向的两侧，通过设置于两个机翼组件20的旋翼组件50的倾转，能够实现飞行汽车2的旋翼飞行状态和固定翼飞行状态的切换。
综上，本发明提供的飞行汽车2的机翼组件20的折转部23相对固定部21可折转，使得机翼组件20能够折叠，在地面有转场需求时可通过自动或者的方式完成机翼组件20的折叠，提高了飞行汽车2在停泊及转场过程中的灵活性；另外，旋翼组件50可以在倾转连接件30的带动下改变空间角度，使得飞行器1还具有垂直起飞及降落及平飞的功能，能够充分满足各场景出行需求。
以上所述实施例仅表达了本发明的几种实施方式，其描述较为具体和详细，但并不能因此而理解为对本发明专利范围的限制。应当指出的是，对于本领域的普通技术人员来说，在不脱离本发明构思的前提下，还可以做出若干变形和改进，这些都属于本发明的保护范围。因此，本发明专利的保护范围应以所附权利要求为准。

Claims (20)

  1. 一种飞行器，其特征在于，包括：
    机身；
    机翼组件，所述机翼组件包括固定部和折转部，所述固定部设置于所述机身，所述折转部可活动地连接于所述固定部，并且相对所述固定部可折转；
    倾转连接件，所述倾转连接件可转动地设置于所述机翼组件；以及
    旋翼组件，所述旋翼组件与所述倾转连接件传动连接，以在所述倾转连接件的带动下改变空间角度。
  2. 根据权利要求1所述的飞行器，其特征在于，所述固定部沿第一方向延伸，所述折转部具有第一转动轴线和第二转动轴线，所述第一转动轴线沿第一方向延伸，所述第二转动轴线沿第二方向延伸，所述第一方向与所述第二方向垂直。
  3. 根据权利要求2所述的飞行器，其特征在于，所述飞行器还包括折转机构，所述折转部通过所述折转机构相对所述固定部可折转，所述折转机构包括第一转轴和第二转轴，所述折转部通过所述第一转轴沿所述第一转动轴线转动，所述折转部通过所述第二转轴沿所述第二转动轴线转动。
  4. 根据权利要求2所述的飞行器，其特征在于，所述旋翼组件具有旋翼状态和固定翼状态，当所述旋翼组件处于所述旋翼状态时，所述旋翼组件的旋转轴线沿第三方向延伸，当所述旋翼组件处于所述固定翼状态时，所述旋翼组件的旋转轴线沿所述第二方向延伸，所述第三方向垂直于所述第一方向和所述第二方向。
  5. 根据权利要求1所述的飞行器，其特征在于，所述旋翼组件包括倾转旋翼本体和旋翼安装座，所述旋翼安装座与所述倾转连接件传动连接，所述倾转旋翼本体可转动地设置于所述旋翼安装座，所述倾转旋翼本体包括倾转旋翼桨叶，所述倾转旋翼桨叶相对所述旋翼安装座可弯折。
  6. 根据权利要求1-5任一项所述的飞行器，其特征在于，所述折转部包括第一折转段和第二折转段，所述第一折转段可活动地连接于所述固定部，并且相对所述固定部可折转，所述第一折转段设有所述倾转连接件，所述第二折转段连接于所述倾转连接件，所述旋翼组件包括平直旋翼模组，所述平直旋翼模组设置于所述第二折转段。
  7. 根据权利要求6所述的飞行器，其特征在于，所述机翼组件还包括发动机舱，所述发动机舱连接于所述固定部，所述飞行器还包括折转机构，所述折转机构设置于所述发动机舱，所述折转部通过所述折转机构相对所述固定部可折转。
  8. 根据权利要求7所述的飞行器，其特征在于，所述发动机舱设有所述倾转连接件，所述旋翼组件包括倾转旋翼模组，所述倾转旋翼模组连接于所述倾转连接件。
  9. 根据权利要求8所述的飞行器，其特征在于，所述飞行器还包括固定旋翼模组，所述固定旋翼模组与所述倾转旋翼模组分别设置于所述发动机舱的相对两端，所述固定旋翼模组包括固定轴和固定旋翼桨叶，所述固定旋翼桨叶可转动地设置于所述固定轴，所述固定轴固定设置于所述发动机舱。
  10. 根据权利要求9所述的飞行器，其特征在于，所述机翼组件为两个，两个所述机翼组件分别连接于所述机身的相对两侧，每个所述折转部均设有一个所述平直旋翼模组，每个所述发动机舱均设有一个所述固定旋翼模组和一个所述倾转旋翼模组。
  11. 根据权利要求10所述的飞行器，其特征在于，所述平直旋翼模组、所述倾转旋翼模组与所述固定旋翼模组组成六旋翼模组，所述飞行器的重心位于所述六旋翼模组的中心。
  12. 根据权利要求11所述的飞行器，其特征在于，当所述平直旋翼模组和所述倾转旋翼模组均由水平位置转至垂直位置，控制所述六旋翼模组开始旋转。
  13. 根据权利要求9所述的飞行器，其特征在于，所述发动机舱包括相对的第一端和第二端，所述第一端朝向所述飞行器的行进方向，所述第二端背离所述飞行器的行进方向，所述倾转旋翼模组设置于所述第一端，所述固定旋翼模组设置于所述第二端。
  14. 根据权利要求6所述的飞行器，其特征在于，所述平直旋翼模组与所述第二折转段形成动力机构，所述动力机构的重心位于所述第二折转段的转动轴线。
  15. 根据权利要求1所述的飞行器，其特征在于，所述固定部的长度为所述机翼组件的长度的10％-30％。
  16. 根据权利要求1-15任一项所述的飞行器，其特征在于，所述飞行器还包括尾翼，所述尾翼连接于所述机身。
  17. 根据权利要求16所述的飞行器，其特征在于，所述尾翼包括水平翼和垂直翼，所述垂直翼连接于所述机身和所述水平翼之间并且向上延伸，所述水平翼的延伸方向与所述机翼组件的方向相同。
  18. 根据权利要求1所述的飞行器，其特征在于，所述飞行器还包括轮组，所述轮组设置于所述机身的底部，所述机身通过所述轮组沿地面可移动。
  19. 一种机翼组件，其特征在于，所述机翼组件包括固定部和折转部，所述固定部设置于机身，所述折转部可活动地连接于所述固定部，并且相对所述固定部可折转。
  20. 一种飞行汽车，其特征在于，包括：
    车身；
    机翼组件，所述机翼组件包括固定部和折转部，所述固定部设置于所述车身，所述折转部可活动地连接于所述固定部，并且相对所述固定部可折转；
    倾转连接件，所述倾转连接件可转动地设置于所述机翼组件；以及
    旋翼组件，所述旋翼组件与所述倾转连接件传动连接，以在所述倾转连接件的带动下改变空间角度。
PCT/CN2021/129539 2021-10-11 2021-11-09 飞行器、机翼组件及飞行汽车 WO2023060679A1 (zh)

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