WO2022067492A1 - 飞行载具 - Google Patents

飞行载具 Download PDF

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Publication number
WO2022067492A1
WO2022067492A1 PCT/CN2020/118792 CN2020118792W WO2022067492A1 WO 2022067492 A1 WO2022067492 A1 WO 2022067492A1 CN 2020118792 W CN2020118792 W CN 2020118792W WO 2022067492 A1 WO2022067492 A1 WO 2022067492A1
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WO
WIPO (PCT)
Prior art keywords
axis
main body
flying vehicle
along
fuselage
Prior art date
Application number
PCT/CN2020/118792
Other languages
English (en)
French (fr)
Inventor
余知洋
李晨畅
陈坤扬
林恺泽
Original Assignee
瑞鉴航太科技股份有限公司
瑞鉴有限责任公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Application filed by 瑞鉴航太科技股份有限公司, 瑞鉴有限责任公司 filed Critical 瑞鉴航太科技股份有限公司
Priority to PCT/CN2020/118792 priority Critical patent/WO2022067492A1/zh
Publication of WO2022067492A1 publication Critical patent/WO2022067492A1/zh

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    • 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
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/26—Ducted or shrouded rotors

Definitions

  • the present invention relates to an air vehicle; in particular, the air vehicle includes a plurality of external ducts and a plurality of ducted fan superchargers.
  • the purpose of the present invention is to provide a flying vehicle, comprising: a main body; a front base connected to the front part of the main body; a rear base connected to the rear part of the main body; A plurality of external ducts around the body; a plurality of ducted fan side walls respectively arranged in the external ducts; and a plurality of ducted fan superchargers arranged in the corresponding ducted fan side walls.
  • the external ducts are respectively rotatably connected between the front base and the main body and between the rear base and the main body along a first axis, and the side walls of the ducted fans are along a second axis Rotate to connect the corresponding external duct.
  • a horizontal stabilizer is further included, wherein the horizontal stabilizer is connected to the rear part of the main fuselage, and the corresponding external duct is located between the rear base and the horizontal stabilizer.
  • the flying vehicle further includes two elevators, and the two elevators are respectively rotatably connected to the rear sides of the corresponding horizontal stabilizers along the second axis.
  • first axis and the second axis are perpendicular to each other.
  • the ducted fan supercharger is fixed in the corresponding ducted fan sidewall along the third axis, and the first axis, the second axis, and the third axis are perpendicular to each other.
  • it further includes a rear upper wing and two rear middle wings, wherein the rear upper wing is connected to the upper side of the rear part of the main fuselage, and the rear middle wings are respectively connected to the rear Opposite sides of the upper wing extend along the second axis respectively.
  • it further includes two rear middle flaperons, wherein the rear middle flaperons are respectively rotatably connected to the rear portions of the rear middle wing along the second axis.
  • it further includes two rear vertical fins and two rear vertical fin rudders, wherein the rear vertical fins are respectively connected to a side of the rear middle wing away from the rear upper wing and along the The third axis extends, and the rear vertical tail rudders are respectively connected to the rear part of the rear vertical tail rotatably along the third axis.
  • the rear middle wings are respectively aligned with corresponding external ducts along the third axis, and the rear vertical tails are respectively aligned with corresponding external ducts along the second axis.
  • first axis, the second axis, and the third axis are perpendicular to each other.
  • it further includes two rear lower wings, wherein the rear lower wings are respectively connected to a side of the rear vertical tail that is away from the rear middle wing and are respectively directed toward the main body along the second axis. body extension.
  • the outer duct and the corresponding rear lower wing do not overlap each other on the third axis.
  • it further includes a cockpit, wherein the cockpit is disposed on the upper part of the main body.
  • it further includes a cockpit-fuselage connector and a forward wing, wherein the forward wing is located at the front of the main fuselage, and the cockpit-fuselage connector is connected to the cockpit and the forward wing between the wings.
  • opposite sides of the front wing are connected between opposite sides of the front base and the main fuselage, and the cockpit-fuselage connector is connected between opposite sides of the front wing.
  • the cockpit-fuselage connector connects the front end of the cockpit.
  • the cockpit is detachably connected to the main body.
  • it further includes two front winglets, wherein the front winglets are respectively located on opposite sides of the main body and extend along the second axis, and the front winglets are respectively along the second axis Rotate and connect the opposite sides of the corresponding main body.
  • the front winglets are respectively aligned with corresponding external ducts along the second axis.
  • the number of the external ducts is at least four, two of the external ducts are located on opposite sides of the main body and close to the front of the main fuselage, and the external ducts The other two are respectively located on opposite sides of the main body and close to the rear of the main body.
  • the ducted fan sidewall is provided in each external duct, the ducted fan sidewall in each external duct is arranged along the first axis, and the ducted fan sidewall is provided in each ducted fan sidewall. press.
  • FIG. 1 is a schematic diagram of a top perspective view of an air vehicle according to an embodiment of the present invention
  • FIG. 2 is a schematic bottom view of the flying vehicle according to an embodiment of the present invention.
  • FIG 3 is a partial enlarged schematic view of an external duct, a side wall of a ducted fan, and a ducted fan supercharger of an air vehicle according to an embodiment of the present invention.
  • the present invention provides an air vehicle; in particular, the air vehicle is used for carrying people.
  • the present invention is also an unmanned vehicle operated by remote control.
  • the flying vehicle is a vehicle capable of carrying people, and its volume is smaller than that of a traditional manned aircraft and is close to a passenger car, and the flying vehicle has the characteristics of vertical take-off and landing and in-situ steering.
  • the flying vehicle of the present invention includes a main body 6, a front base 1, a rear base 8, a plurality of external ducts 5, a plurality of ducted fan side walls 3, and a plurality of Ducted fan supercharger 2.
  • the main body 6 can be divided into a front part and a rear part, the front base 1 is connected to the front part of the main body 6 , and the rear base 8 is connected to the rear part of the main body 6 .
  • the external ducts 5 are respectively located around the main body 6 , and several of the external ducts 5 are respectively rotatably connected to the front base 1 along a first axis (the x-axis in FIG. 1 ).
  • the other ones of the external ducts 5 are respectively rotatably connected between the rear base 8 and the main body 6 along the first axis.
  • the ducted fan side walls 3 are respectively disposed in the external ducts 5, and the ducted fan side walls 3 are rotatably connected to the corresponding external ducts along the second axis (y-axis in FIG. 1 ). 5.
  • the ducted fan superchargers 2 are arranged in the corresponding ducted fan side walls 3 .
  • the external duct 5 , the side wall 3 of the ducted fan, and the ducted fan supercharger 2 form a propulsion system of the flight vehicle.
  • the number of the external ducts 5 is 4, but not limited to this.
  • Two external ducts 5 are located on opposite left and right sides of the main body 6 and close to the front of the main body 6, respectively, and the other two external ducts 5 are located on opposite left and right sides of the main body 6 and close to the main body The rear of the fuselage 6.
  • the outer duct 5 is an oval cylindrical hollow structure, the length parallel to the first axis is longer (length direction), and the length parallel to the second axis is shorter (width direction).
  • the ducted fan side wall 3 is a circular cylindrical hollow structure, each external duct 5 is provided with at least two ducted fan side walls 3, and the ducted fan side walls 3 in each external duct 5 are arranged along the first axis .
  • Each ducted fan side wall 3 is provided with a ducted fan supercharger 2, and the ducted fan supercharger 2 is fixed in the corresponding ducted fan side wall 3 along the third axis (z-axis in FIG. 1 ).
  • the ducted fan supercharger 2 includes a plurality of fan blades and a rotating shaft. The rotating shaft can drive the fan blades to rotate, and the air flow is sucked into the ducted fan supercharger 2 from one end of the side wall 3 of the ducted fan, and is driven by the ducted fan. The other end of the side wall 3 is ejected to generate jet airflow and propel the flying vehicle.
  • the flight vehicle of the present invention is provided with two ducted fan superchargers 2, but the present invention is not limited thereto, and the number of the ducted fan superchargers 2 can be 1, 3, 4, or more .
  • the jet flow generated by the ducted fan supercharger 2 and ejected from the ducted fan side wall 3 is propelled.
  • the flying vehicle moves on the third axis.
  • the first axis, the second axis, and the third axis are perpendicular to each other.
  • the first axis is the X axis
  • the second axis is the Y axis
  • the third axis is the Z axis.
  • the first axis and the second axis are relative to the horizontal direction of the ground
  • the third axis is relative to the vertical direction of the ground.
  • the external duct 5 can be rotated relative to the main body 6 around the first axis to endow the entire propulsion system with the ability to rotate on the first axis, and to change the angle between the thrust direction of the propulsion system and the first axis to change The propulsion direction of the flight vehicle.
  • the side wall 3 of the ducted fan can rotate relative to the external duct 5 around the second axis, so as to give the whole propulsion system the ability to rotate on the second axis, and to change the angle between the thrust direction of the propulsion system and the second axis, so as to Change the propulsion direction of the flying vehicle.
  • the external duct 5 cooperates with the side wall 3 of the ducted fan to change the rotation ability of the whole propulsion system on the first axis and the second axis, so that the flight vehicle is propelled along the first axis and the second axis.
  • changing the operating power of the ducted fan supercharger 2 can change the intensity of the jet air flow, and correspondingly can change the height of the flying vehicle.
  • the aircraft further includes a horizontal stabilizer 10 , and the horizontal stabilizer 10 is connected to the rear base 8 and the outer duct 5 located on the rear base.
  • the aircraft further includes a rear upper wing 7 and two rear middle wings 9, the rear upper wing 7 is connected to the upper side of the rear part of the main body 6, and the two rear middle wings 9.
  • the wings 9 are respectively connected to the opposite left and right sides of the rear upper wing 7 , and the two rear middle wings 9 respectively extend in a direction away from the rear upper wing 7 along the second axis.
  • the rear upper wing 7 and the rear middle wing 9 can provide lift for the aircraft.
  • the flying vehicle further includes two rear middle flaperons 12 , and the two rear middle flaperons 12 are respectively rotatably connected along the second axis to the rear side of the rear middle wing 9 (that is, relative to the front direction). the other side).
  • the two rear middle flaperons 12 can rotate around the second axis, and the two rear middle flaperons 12 can change the lift of the rear middle wing 9 when the vehicle is flying at low speed; act in concert with the front winglets It can be used as an auxiliary to increase the control and flexibility of the flying vehicle when performing Roll and Pitch flight actions.
  • the aircraft further includes two rear vertical tails 13 and two rear vertical tail rudders 11 , the two rear vertical tails 13 are respectively connected to the corresponding rear middle wing 9 away from the rear upper wing. 7 side, and the two rear vertical fins 13 extend downward along the third axis respectively, and the two rear vertical fin rudders 11 are respectively rotatably connected to the rear sides of the corresponding rear vertical fins 13 along the third axis.
  • the two rear vertical tail rudders 11 can be rotated around the third axis, which can be used to adjust the nose of the aircraft in the direction of the x-y plane during horizontal flight, and assist the fuselage to perform yaw flight.
  • the two rear middle wings 9 are respectively aligned with the corresponding external ducts 5 along the third axis, and the two rear vertical tail wings 13 are respectively aligned with the corresponding external ducts 5 along the second axis.
  • the above-mentioned external ducts 5 are, for example, two external ducts 5 near the rear of the main body 6 .
  • the flying vehicle further includes two rear lower wings 14, the two rear lower wings 14 are respectively connected to a side of the rear vertical tail 13 away from the rear middle wing 9, and the two rear The lower wings 14 respectively extend along the second axis towards the main fuselage 6 .
  • the length of the rear lower wing 14 extending along the second axis is smaller than the length of the rear middle wing 9 extending along the second axis, and the outer duct 5 and the corresponding rear lower wing 14 are in the third position.
  • the shafts do not overlap, in other words, the rear lower wing 14 does not block the jet flow of the ducted fan supercharger 2 .
  • the flying vehicle further includes two front winglets 15, the two front winglets 15 are respectively located on opposite left and right sides of the main fuselage 6, and the two front winglets 15 are along the second side.
  • the shaft extends, and the two front winglets 15 are rotatable around the second shaft.
  • the two front winglets 15 are respectively aligned with the corresponding external ducts 5 along the second axis.
  • the aforementioned external ducts 5 are the two external ducts 5 near the front of the main body 6 .
  • the flight vehicle further includes a passenger-carrying cockpit 4 , and the cockpit 4 is disposed on the upper portion of the main fuselage 6 .
  • the aircraft further includes a cockpit-fuselage connector 16 and a front wing 17, the front wing 17 is located at the front of the main fuselage 6, and the cockpit-fuselage connector 16 is connected between the cockpit 4 and the front wing 17 .
  • the cockpit-fuselage connector 16 is used for connecting and fixing the main fuselage 6 and the cockpit 4 .
  • the cabin 4 is detachably connected to the main body 6 , that is, the cabin 4 can be detached from the main body 6 when needed.
  • the opposite left and right sides of the front wing 17 are connected to the opposite sides of the front base 1 and the main body 6
  • the cockpit-fuselage connector 16 is connected to the left and right sides of the front wing 17 . between the sides.
  • the cockpit 4 is located between opposite sides of the main fuselage 6 and the cockpit-fuselage connection 16 connects the front end of the cockpit 4 .
  • the flying vehicle further includes two elevators 18 , and the two elevators 18 are respectively rotatably connected to the rear side of the corresponding horizontal stabilizer 10 along the second axis.
  • the two elevators 18 can rotate around the second axis, and the two elevators 18 can change the lift force of the rear horizontal stabilizer 10 when the aircraft is flying, so as to increase the control and flexibility of the aircraft when it performs a pitch flight. .
  • the following is an example to illustrate the operation principle of the flying vehicle, taking the first axis as the X axis, the second axis as the Y axis, and the third axis as the Z axis as an example.
  • the flying vehicle needs to tilt forward or backward when the nose of the aircraft remains unchanged, the ducted fan supercharger 2 of the propulsion system will be replaced by the ducted fan.
  • the side wall 3 is driven, and rotates counterclockwise or clockwise around the Y axis by a small certain angle, so that the exhaust end of the ducted fan supercharger 2 (for example, the lower end of the ducted fan side wall 3) is backward or forward. before turning.
  • the ducted fan supercharger 2 in the propulsion system will be driven by the ducted fan side wall 3 to rotate counterclockwise around the Y axis by a large angle, so that the fuselage can obtain more forward thrust. If it is necessary to increase the elevation angle of the fuselage during high-speed flight, it can be achieved by a combination of the following three operation methods.
  • the rear end fan thrust of the ducted fan supercharger 2 at the rear of the body 6 is reduced, or the rear middle flaperon 12 will rotate clockwise around the Y axis by a certain angle and at the same time the front winglet 15 will rotate around the Y axis in the opposite direction.
  • the elevators 18 will rotate clockwise around the Y axis to increase the lift of the rear horizontal stabilizer 10 when the aircraft is flying. If it is necessary to reduce the elevation angle of the fuselage during high-speed flight, it can be achieved by a combination of the following three operation methods.
  • the rear end fan thrust of the ducted fan supercharger 2 at the rear of the fuselage 6 is increased, or the rear middle flaperon 12 will rotate counterclockwise around the Y axis by a certain angle and the front winglet 15 will rotate in the opposite direction around the Y axis.
  • the elevators 18 rotate counterclockwise around the Y axis, the lift force of the rear horizontal stabilizer 10 is reduced when the aircraft is flying.
  • the left rear middle flaperon 12 rotates clockwise around the Y axis by an angle
  • the front winglet 15 rotates around the Y axis by a certain angle in the same orbiting direction to reduce
  • the lift force of the left half fuselage, the right rear middle flaperon 12 and the front winglet 15 (that is, the opposite side of the left rear middle flaperon 12 and the front winglet 15) are opposite to the left rear middle flap
  • the aileron 12 and the front winglet 15 are rotated at an angle around the Y-axis in the revolving direction to increase the lift of the right half of the fuselage.
  • the whole fuselage has been made to roll to the left; if the fuselage needs to be tilted to the right during high-speed flight, the left rear middle flaperon 12 rotates counterclockwise around the Y axis by an angle, and at the same time the front winglet 15 rotates in the same direction. Rotate a certain angle around the Y axis in the detour direction to increase the lift of the left half fuselage. Opposite side) each rotates an angle around the Y-axis in the opposite direction of the left rear middle flaperon 12 and the front winglet 15 to reduce the lift of the right half of the fuselage. The whole fuselage has been made to roll to the right.
  • the vertical tail rudder 11 on the rear side rotates an angle counterclockwise around the Z-axis; if the nose needs to be adjusted to the right during high-speed or low-speed flight, the vertical rear rudder 11
  • the tail rudder 11 is rotated clockwise around the Z-axis by an angle (the vertical tail rudder 11 on the rear side of the other side turns the same).
  • the front wing 17 can guide the airflow to pass through the upper surface of the aircraft more efficiently, so that the manned aircraft can generate lift as a whole, offset its own gravity, and indirectly reduce the power consumption required by the ducted fan supercharger. Fly more efficiently.
  • the propulsion system of the flight vehicle is provided by the external duct 5, the ducted fan side wall 3 and the ducted fan supercharger 2, together with the wings and ailerons, and can pass through the The external duct 5, the side wall 3 of the ducted fan, and the rotational degrees of freedom of the ducted fan supercharger 2 on multiple axes guide the intake and exhaust, in addition to advancing in a specific direction, it can also achieve vertical The ability to take off and land and turn in place.
  • a plurality of small-sized wings are arranged around the cockpit 4 and the main fuselage 6, which can be used as aerodynamic components to provide lift, and can also be used as structural components to carry the weight of the entire aircraft and as an assembly body.
  • the lift generated by the fuselage of the aircraft through fluid is not the main source of power, but it can generate a lot of lift in medium and high-speed cruising, reducing energy consumption and gaining the advantages of fixed wings in a smaller size range.
  • the propulsion system of the flight vehicle can be powered by a power source (for example: electric power and hydrogen fuel cell or electric power and fuel hybrid power, pure hydrogen fuel cell, or fuel power generation), and the battery can be provided in the cockpit 4 and/or the main body Inside the fuselage 6, but not limited to this.
  • the cockpit 4 is independently and detachably installed on the main fuselage 6, and can be detached in a crisis state, for example, in the event of a crash, the cockpit 4 can be separated from the fuselage to ensure the integrity of the cockpit 4, so as to achieve better High security.
  • the ducted fan supercharger 2 is covered by the external duct 5, the side wall 3 of the ducted fan, and the main body 6 layers, so that the rotating parts or moving parts cannot be directly connected with people or animals and plants. Contact can reduce the threat of rotating parts and moving parts to people and things in the surrounding environment, and improve safety. With the help of the advantages of size, maneuverability and safety, the flying vehicle of the present invention can operate in urban building clusters, has good maneuverability for free shuttle, and has less impact on the surrounding environment.

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Abstract

一种飞行载具，包括：一主体机身（6）；连接主体机身（6）的前部的一前基座（1）；连接主体机身（6）的后部的一后基座（8）；分别位于主体机身（6）的四周的多个外部涵道（5）；分别设于这些外部涵道（5）中的多个涵道风扇侧壁（3）；以及设于对应的涵道风扇侧壁（3）中的多个涵道风扇增压器（2）。这些外部涵道（5）分别沿一第一轴转动连接于前基座（1）与主体机身（6）之间以及后基座（8）与主体机身（6）之间，这些涵道风扇侧壁（3）沿一第二轴转动连接对应的外部涵道（5）。

Description

飞行载具 技术领域
本发明关于一种飞行载具；特定而言，该飞行载具包括多个外部涵道以及多个涵道风扇增压器。
背景技术
飞行器之发展大幅地改变人类交通的便利度。惟目前交通状况于大都市中已渐趋饱和，交通堵塞问题也成为城市治理的麻烦之处。目前市面上已经大量贩售无人飞行器，应用于各领域，例如拍摄或农业等，但鲜少研发者结合飞行器以及座车而完成飞行交通载具。因此，有必要研发一种可载人之飞行载具，已改善交通问题以及提高行动便利性。
发明内容
本发明之目的是提供一种飞行载具，包括：一主体机身；连接该主体机身之前部之一前基座；连接该主体机身之后部之一后基座；分别位于该主体机身之四周之多个外部涵道；分别设于该些外部涵道中之多个涵道风扇侧壁；以及设于对应之涵道风扇侧壁中之多个涵道风扇增压器。该些外部涵道分别沿一第一轴转动连接于该前基座与该主体机身之间以及该后基座与该主体机身之间，该些涵道风扇侧壁沿一第二轴转动连接对应之外部涵道。
于一特定实施例，另包括一水平尾翼，其中该水平尾翼连接该主体机身之后部，以及对应之外部涵道位于该后基座与该水平尾翼之间。
于一实施例，该飞行载具另包括二升降舵，该二升降舵分别沿第二轴转动连接对应之水平尾翼之后侧。
于一特定实施例，其中该第一轴与该第二轴彼此垂直。
于一特定实施例，其中该涵道风扇增压器沿该第三轴固定于对应之涵道风扇侧壁中，该第一轴、该第二轴、与该第三轴彼此垂直。
于一特定实施例，另包括一后上部机翼与二后侧中部机翼，其中该后上部机翼连接该主体机身之后部之上侧，以及该些后侧中部机翼分别连接该后上部机翼之相对两侧并分别沿该第二轴延伸。
于一特定实施例，另包括二后中部襟副翼，其中该些后中部襟副翼分别沿该第二轴转动连接对应之后侧中部机翼之后部。
于一特定实施例，另包括二后侧垂直尾翼与二后侧垂直尾翼方向舵，其中该些后侧垂直尾翼分别连接对应之后侧中部机翼之远离该后上部机翼之一侧并分别沿该第三轴延伸，该些后侧垂直尾翼方向舵分别沿该第三轴转动连接对应之后侧垂直尾翼之后部。
于一特定实施例，其中该些后侧中部机翼分别沿该第三轴对齐对应之外部涵道，以及该后侧垂直尾翼分别沿该第二轴对齐对应之外部涵道。
于一特定实施例，其中该第一轴、该第二轴、与该第三轴彼此垂直。
于一特定实施例，另包括二后下部机翼，其中该些后下部机翼分别连接对应之后侧垂直尾翼之远离该后侧中部机翼之一侧并分别沿该第二轴朝该主体机身延伸。
于一特定实施例，其中该外部涵道与对应之后下部机翼于该第三轴上彼此不重迭。
于一特定实施例，另包括一座舱，其中该座舱设于该主体机身之上部。
于一特定实施例，另包括一座舱-机身连接件与一前方机翼，其中该前方机翼位于该主体机身之前部，以及该座舱-机身连接件连接于该座舱与该前方机翼之间。
于一特定实施例，其中该前方机翼之相对两侧连接该前基座与该主体机身之相对两侧，该座舱-机身连接件连接该前方机翼之相对两侧之间。
于一特定实施例，其中该座舱位于该主体机身之相对两侧之间，该座舱-机身连接件连接该座舱之前端。
于一特定实施例，其中该座舱可分离地连接该主体机身。
于一特定实施例，另包括二前侧小翼，其中该些前侧小翼分别位于该主体机身之相对两侧并沿该第二轴延伸，该些前侧小翼分别沿第二轴转动连接对应之主体机身之相对两侧。
于一特定实施例，其中该些前侧小翼分别沿该第二轴对齐对应之外部涵道。
于一特定实施例，其中该外部涵道之数量是至少四个，该些外部涵道其中二者分别位于该主体机身之相对两侧且靠近该主体机身之前部，以及该些外部涵道另二者分别位于该主体机身之相对两侧且靠近该主体机身之后部。
于一特定实施例，其中各外部涵道设置该涵道风扇侧壁，各外部涵道中之涵道风扇侧壁沿该第一轴排列，以及各涵道风扇侧壁中设置该涵道风扇增压器。
附图说明
兹配合附图以更佳地说明前述发明内容以及下述之本发明实施方式。
图1是本发明一实施例的飞行载具的上方视角示意图；
图2是本发明一实施例的飞行载具的下方视角示意图；以及
图3是本发明一实施例的飞行载具的外部涵道、涵道风扇侧壁与涵道风扇增压器的局部放大示意图。
附图元件符号
1前基座
2涵道风扇增压器
3涵道风扇侧壁
4座舱
5外部涵道
6主体机身
7后上部机翼
8后基座
9后侧中部机翼
10水平尾翼
11垂直尾翼方向舵
12后中部襟副翼
13后侧垂直尾翼
14后下部机翼
15前侧小翼
16座舱-机身连接件
17前方机翼
18升降舵
具体实施方式
针对本发明之技术特征，较佳之理解兹配合说明书、依据本发明原理之实施例、和附图将本发明详细说明如下。
本发明说明书及申请专利范围中所述之所有技术性及科学用语，除非另有所定义，皆为本发明所属技术领域普通技术人员可知晓之定义。其中单数用语「一」、「一个」、「该」、或其近似用语，除非另有说明，皆可指涉多于一个对象。本说明书使用之「或」、「以及」、「和」，除非另有说明，皆指涉「或/和」。此外，用语「包含」、「包括」皆非有所限制之开放式连接词。前述定义仅说明用语定义之指涉而不应解释为对发明标的之限制。除非另有说明，本发明所用之材料皆为市售易于取得。
另，本说明书用语「上」、「之上」、「上方」、或相似用语指涉一元件与另一元件直接接触，但亦指涉一元件与另一元件不直接接触。
本说明书所提及的序数，例如「第一」、「第二」等，仅用于说明所揭露之元件，而非指称或表示元件之间具有任何执行次序，亦非指称或表示于一元件和另一元件之间的次序、或制程之步骤次序。该些序数仅用于使具有某命名的一元件得以和另一具有相同命名的元件能清楚区分。
请参照图1至图3，本发明提供一种飞行载具；特定而言，该飞行载具用于载人。但于一替代实施例，本发明亦为通过遥控操作之无人载具。在本实施例中，该飞行载具可载人之载具，其体积小于传统载人飞行器而接近于自用客车，且该飞行载具具备垂直起降、原地转向的特性。
在一实施例中，本发明之飞行载具包括一主体机身6、一前基座1、一后基座8、多个外部涵道5、多个涵道风扇侧壁3、与多个涵道风扇增压器2。该主体机身6可区分为前部与后部，该前基座1连接该主体机身6的前部，该后基座8连接该主体机身6的后部。该些外部涵道5分别位于该主体机身6之四周，该些外部涵道5之其中数者分别沿第一轴(于图1中为x轴)可转 动地连接于该前基座1与该主体机身6之间，该些外部涵道5之其他者分别沿第一轴转动连接于该后基座8与该主体机身6之间。该些涵道风扇侧壁3分别设于该些外部涵道5中，且该些涵道风扇侧壁3沿第二轴(于图1中为y轴)可转动地连接对应之外部涵道5。该些涵道风扇增压器2设于对应之涵道风扇侧壁3中。
于一实施例，该外部涵道5、该涵道风扇侧壁3、与该涵道风扇增压器2组成飞行载具之推进***。该外部涵道5之数量有4个，但不限于此。二外部涵道5分别位于该主体机身6之相对左右两侧且靠近该主体机身6的前部，另二外部涵道5分别位于该主体机身6之相对左右两侧且靠近该主体机身6的后部。于一实施例，该外部涵道5是长圆形的柱状中空结构，其平行第一轴之长度较长(长度方向)，而平行第二轴之长度较短(宽度方向)。该涵道风扇侧壁3是圆形之柱状中空结构，各外部涵道5中设有至少二涵道风扇侧壁3，各外部涵道5中之涵道风扇侧壁3沿第一轴排列。
各涵道风扇侧壁3中设有一涵道风扇增压器2，该涵道风扇增压器2沿第三轴(于图1中为z轴)固定于对应之涵道风扇侧壁3中。该涵道风扇增压器2包括多个扇叶与转轴，转轴可带动扇叶旋转，气流自涵道风扇侧壁3之一端被吸入该涵道风扇增压器2，并由该涵道风扇侧壁3之另一端喷出，以产生喷射气流，并推进飞行载具。于图式中，本发明之飞行载具设有二涵道风扇增压器2，但本发明不限于此，该涵道风扇增压器2之数量可为1、3、4、或更多。
当全部外部涵道5与涵道风扇侧壁3位于垂直位置，即与第三轴对齐之位置，该涵道风扇增压器2产生之自该涵道风扇侧壁3喷出之喷射气流推进飞行载具于第三轴移动。于一实施例，第一轴、第二轴、与第三轴互相垂直，例如第一轴为X轴、第二轴为Y轴而第三轴为Z轴。第一轴与第二轴相对于地面之水平方向，第三轴相对于地面之垂直方向。
该外部涵道5可相对于该主体机身6绕第一轴进行转动，以赋予整体推进***于第一轴上之转动能力，改变推进***的推力方向与第一轴之夹角，以改变飞行载具的推进方向。该涵道风扇侧壁3可相对于该外部涵道5绕第二轴进行转动，以赋予整体推进***于第二轴之转动能力，改变推进***之推力方向与第二轴的夹角，以改变飞行载具的推进方向。该外部涵道5与该涵道风扇侧壁3共同配合可改变整体推进***于第一轴与第二轴转动能力， 使飞行载具沿第一轴与第二轴推进。而改变该涵道风扇增压器2之运作功率，可改变喷射气流之强度，相应可改变飞行载具之高度。
在一实施例中，该飞行载具还包括一水平尾翼10，该水平尾翼10连接该后基座8以及位于该后基座之外部涵道5。
于一实施例，该飞行载具另包括一后上部机翼7与二后侧中部机翼9，该后上部机翼7连接该主体机身6之后部之上侧，该二后侧中部机翼9分别连接该后上部机翼7之相对之左右两侧，且该二后侧中部机翼9分别沿第二轴朝远离后上部机翼7的方向延伸。该后上部机翼7与该后侧中部机翼9可为飞行载具提供升力。
于一实施例，该飞行载具另包括二后中部襟副翼12，该二后中部襟副翼12分别沿第二轴转动连接对应之后侧中部机翼9之后侧(即相对于前部方向之另一侧)。该二后中部襟副翼12可绕第二轴转动，该二后中部襟副翼12可以改变飞行载具在低速飞行时该后侧中部机翼9之升力；与前侧小翼协同作动时可作为辅助，增加该飞行载具进行滚动(Roll)及俯仰(Pitch)飞行动作时的操控与灵活性。
于一实施例，该飞行载具另包括二后侧垂直尾翼13与二后侧垂直尾翼方向舵11，该二后侧垂直尾翼13分别连接对应的后侧中部机翼9的远离该后上部机翼7的一侧，并且该二后侧垂直尾翼13分别沿第三轴向下延伸，该二后侧垂直尾翼方向舵11分别沿第三轴可转动地连接对应之后侧垂直尾翼13之后侧。该二后侧垂直尾翼方向舵11可绕第三轴转动，其可用于水平飞行时调整该飞行载具之机头于x-y平面之方向，辅助机身进行偏摆(Yaw)飞行动作。
于一实施例，该二后侧中部机翼9分别沿第三轴对齐对应之外部涵道5，二后侧垂直尾翼13分别沿第二轴对齐对应的外部涵道5。上述外部涵道5例如是靠近该主体机身6后部之二外部涵道5。
于一实施例，该飞行载具另包括二后下部机翼14，该二后下部机翼14分别连接对应之后侧垂直尾翼13之远离该后侧中部机翼9之一侧，并且该二后下部机翼14分别沿第二轴朝该主体机身6延伸。于一实施例，该后下部机翼14沿第二轴延伸之长度小于该后侧中部机翼9沿第二轴延伸的长度，并且该外部涵道5与对应之后下部机翼14于第三轴上未重迭，换言之，该后下部机翼14不阻挡该涵道风扇增压器2之喷射气流。
于一实施例，该飞行载具另包括二前侧小翼15，该二前侧小翼15分别位于该主体机身6之相对之左右两侧，并且该二前侧小翼15沿第二轴延伸，且该二前侧小翼15可绕第二轴转动。该二前侧小翼15分别沿第二轴对齐对应之外部涵道5，前述外部涵道5是靠近该主体机身6前部之二外部涵道5。
于一实施例，该飞行载具另包括可载人座舱4，该座舱4设于该主体机身6之上部。于一实施例，该飞行载具另包括一座舱-机身连接件16与一前方机翼17，该前方机翼17位于该主体机身6的前部，该座舱-机身连接件16连接于该座舱4与该前方机翼17之间。该座舱-机身连接件16用于连结与固定该主体机身6和该座舱4。在一实施例中，该座舱4可分离地连接该主体机身6，也就是在需要的时候，座舱4可与主体机身6分离。
于一实施例，该前方机翼17之相对之左右两侧连接该前基座1与该主体机身6之相对两侧，该座舱-机身连接件16连接该前方机翼17之左右两侧之间。该座舱4位于该主体机身6的相对两侧之间，而该座舱-机身连接件16连接该座舱4的前端。
于一实施例，该飞行载具另包括二升降舵18，该二升降舵18分别沿第二轴转动连接对应之水平尾翼10之后侧。该二升降舵18可绕第二轴转动，该二升降舵18可以改变飞行载具在飞行时该后侧水平尾翼10之升力，增加该飞行载具进行俯仰(Pitch)飞行动作时的操控与灵活性。
以下举例说明飞行载具之作动原理，并以第一轴为X轴、第二轴为Y轴而第三轴为Z轴为例。
当飞行载具沿第三轴垂直起飞或降落时，全部涵道风扇增压器2垂直于地面并向下喷气，通过加大或减小该涵道风扇增压器2的功率而使飞行载具升高或下降。若在垂直起飞、降落、悬停或低速飞行时，飞行载具需要在机头指向不变时向左或者向右倾斜飘动，推进***(或可称动力***)的该涵道风扇增压器2会被该外部涵道5带动，而绕X轴逆时针或顺时针转动一定角度，使该涵道风扇增压器2的排气端(例如该涵道风扇侧壁3的下端)向右或向左转动。若在垂直起飞、降落、悬停或低速飞行时，飞行载具需要在机头指向不变时向前或者向后倾斜飘动，推进***的该涵道风扇增压器2会被该涵道风扇侧壁3带动，而绕Y轴逆时针或顺时针转动较小的一定角度，使该涵道风扇增压器2的排气端(例如该涵道风扇侧壁3的下端)向后或向前转动。
在高速飞行时，推进***内的该涵道风扇增压器2会被该涵道风扇侧壁3带动而绕Y轴逆时针旋转较大角度，使机身获得较多向前的推力。若在高速飞行时需要加大机身的仰角，可由以下三种作动方式组合而达成，靠近该主体机身6前部之涵道风扇增压器2之前端风扇推力增加，靠近该主体机身6后部之涵道风扇增压器2之后端风扇推力减小，或该后中部襟副翼12会绕Y轴顺时针旋转一定角度且同时前侧小翼15以相反方向绕Y轴旋转一定角度，或该些升降舵18会绕Y轴顺时针旋转，增加飞行载具在飞行时该后侧水平尾翼10之升力。若在高速飞行时需要减小机身的仰角，可由以下三种作动方式组合而达成，靠近该主体机身6前部之涵道风扇增压器2之前端风扇推力减小，靠近该主体机身6后部之涵道风扇增压器2之后端风扇推力增加，或该后中部襟副翼12会绕Y轴逆时针旋转一定角度且同时前侧小翼15以相反方向绕Y轴旋转一定角度，或该些升降舵18会绕Y轴逆时针旋转，减少飞行载具在飞行时该后侧水平尾翼10之升力。
在高速飞行中若需要机身向左倾斜时，左侧之后中部襟副翼12绕Y轴顺时针旋转一角度且同时前侧小翼15以相同绕行方向绕Y轴旋转一定角度，以减少左半机身之升力，右侧之后中部襟副翼12及前侧小翼15(即左侧之后中部襟副翼12与前侧小翼15之对侧)各以相反于左侧之后中部襟副翼12与前侧小翼15绕行方向绕Y轴旋转一角度，以增加右半边机身之升力。已使得整体机身达到向左滚转之目的；高速飞行中若需要机身向右倾斜时，左侧之后中部襟副翼12绕Y轴逆时针旋转一角度且同时前侧小翼15以相同绕行方向绕Y轴旋转一定角度，以增加左半机身之升力，右侧之后中部襟副翼12及前侧小翼15(即左侧之后中部襟副翼12与前侧小翼15之对侧)各以相反于左侧之后中部襟副翼12与前侧小翼15绕行方向绕Y轴旋转一角度，以减少右半边机身之升力。已使得整体机身达到向右滚转之目的。
在高速或低速飞行时若需要调整机头向左时，后侧之垂直尾翼方向舵11绕Z轴逆时针旋转一角度；在高速或低速飞行时若需要调整机头向右时，后侧之垂直尾翼方向舵11绕Z轴顺时针旋转一角度(另一侧之后侧之垂直尾翼方向舵11转向相同)。
在高速或低速飞行时，前方机翼17可引导气流更高效地通过飞行器上表面，使载人飞行器整体产生升力，抵销自身重力，间接达到使涵道风扇增压器需要之功耗降低，更高效飞行。
于本发明，该飞行载具之推进***由该外部涵道5、该涵道风扇侧壁3与该涵道风扇增压器2、与该些机翼与副翼共同提供，并可通过该外部涵道5、该涵道风扇侧壁3、与该涵道风扇增压器2于多轴上之转动自由度对进气与排气进行导向，除了朝特定方向推进以外，还可达到垂直起降、原地转向的能力。多个小尺寸机翼围绕该座舱4与该主体机身6布置，作为空气动力部件提供升力的同时，也可作为结构件承载整机重量与作为装配主体。飞行载具的机身通过流体产生的升力并非主要的动力来源，但在中高速巡航状态下可产生大量升力，降低了能耗的同时，在较小的尺寸范围内获得了固定翼的优势。飞行载具之推进***可由一电源(例如：电能与氢燃料电池或电能与燃油混合动力、纯氢燃料电池、或燃油发电)供能，且该电池可设于该座舱4及/或该主体机身6内部，但不限于此。该座舱4独立且可分离地安装于该主体机身6，在危机状态下可分离，例如在坠机时，该座舱4可与机身分离，以保证该座舱4的完整性，从而达成更高的安全性。另外，该涵道风扇增压器2被由该外部涵道5、该涵道风扇侧壁3、与该主体机身6层层包覆，旋转机件或运动部件无法与人或动植物直接接触，可减小旋转机件与运动部件对周围环境的人事物的威胁，提高了安全性。在尺寸、机动性与安全性的优势帮助下，本发明之飞行载具可在城市建筑群落中运行，具备自由穿梭的良好机动性，且对周围环境影响较小。
于本说明书实施例揭示之内容，本发明所属领域普通技术人员可明显得知前述实施例仅为例示而非限制；本发明所属技术领域普通技术人员可藉由诸多变换、替换而实施，并不与本发明之技术特征有所差异。依据说明书实施例，本发明可有多种变换仍无碍于实施。本发明之范围涵盖前述方法与结构及与其相等之发明。

Claims (21)

  1. 一种飞行载具，包括：
    一主体机身；
    一前基座，连接该主体机身之前部；
    一后基座，连接该主体机身之后部；
    多个外部涵道，分别位于该主体机身之四周，该些外部涵道分别沿一第一轴转动连接于该前基座与该主体机身之间以及该后基座与该主体机身之间；
    多个涵道风扇侧壁，分别设于该些外部涵道中，该些涵道风扇侧壁沿一第二轴转动连接对应之外部涵道；以及
    多个涵道风扇增压器，设于对应之涵道风扇侧壁中。
  2. 如权利要求1之飞行载具，另包括一水平尾翼，其中该水平尾翼连接该主体机身之后部，以及对应之外部涵道位于该后基座与该水平尾翼之间。
  3. 如权利要求1之飞行载具，另包括二升降舵，该二升降舵分别沿第二轴转动连接对应之水平尾翼之后侧。
  4. 如权利要求1之飞行载具，其中该第一轴与该第二轴彼此垂直。
  5. 如权利要求1之飞行载具，其中该涵道风扇增压器沿该第三轴固定于对应之涵道风扇侧壁中，该第一轴、该第二轴、与该第三轴彼此垂直。
  6. 如权利要求1之飞行载具，另包括一后上部机翼与二后侧中部机翼，其中该后上部机翼连接该主体机身之后部之上侧，以及该些后侧中部机翼分别连接该后上部机翼之相对两侧并分别沿该第二轴延伸。
  7. 如权利要求6之飞行载具，另包括二后中部襟副翼，其中该些后中部襟副翼分别沿该第二轴转动连接对应之后侧中部机翼之后部。
  8. 如权利要求7之飞行载具，另包括二后侧垂直尾翼与二后侧垂直尾翼方向舵，其中该些后侧垂直尾翼分别连接对应之后侧中部机翼之远离该后上部机翼之一侧并分别沿该第三轴延伸，该些后侧垂直尾翼方向舵分别沿该第三轴转动连接对应之后侧垂直尾翼之后部。
  9. 如权利要求8之飞行载具，其中该些后侧中部机翼分别沿该第三轴对齐对应之外部涵道，以及该后侧垂直尾翼分别沿该第二轴对齐对应之外部涵道。
  10. 如权利要求9之飞行载具，其中该第一轴、该第二轴、与该第三轴彼此垂直。
  11. 如权利要求9之飞行载具，另包括二后下部机翼，其中该些后下部机翼分别连接对应之后侧垂直尾翼之远离该后侧中部机翼之一侧并分别沿该第二轴朝该主体机身延伸。
  12. 如权利要求11之飞行载具，其中该外部涵道与对应之后下部机翼于该第三轴上彼此不重迭。
  13. 如权利要求1之飞行载具，另包括一座舱，其中该座舱设于该主体机身之上部。
  14. 如权利要求13之飞行载具，另包括一座舱-机身连接件与一前方机翼，其中该前方机翼位于该主体机身之前部，以及该座舱-机身连接件连接于该座舱与该前方机翼之间。
  15. 如权利要求14之飞行载具，其中该前方机翼之相对两侧连接该前基座与该主体机身之相对两侧，该座舱-机身连接件连接该前方机翼之相对两侧之间。
  16. 如权利要求14之飞行载具，其中该座舱位于该主体机身之相对两侧之间，该座舱-机身连接件连接该座舱之前端。
  17. 如权利要求14之飞行载具，其中该座舱可分离地连接该主体机身。
  18. 如权利要求1之飞行载具，另包括二前侧小翼，其中该些前侧小翼分别位于该主体机身之相对两侧并沿该第二轴延伸，该些前侧小翼分别沿第二轴转动连接对应之主体机身之相对两侧。
  19. 如权利要求18之飞行载具，其中该些前侧小翼分别沿该第二轴对齐对应之外部涵道。
  20. 如权利要求1之飞行载具，其中该外部涵道之数量是至少四个，该些外部涵道其中二者分别位于该主体机身之相对两侧且靠近该主体机身之前部，以及该些外部涵道另二者分别位于该主体机身之相对两侧且靠近该主体机身之后部。
  21. 如权利要求1之飞行载具，其中各外部涵道设置该涵道风扇侧壁，各外部涵道中之涵道风扇侧壁沿该第一轴排列，以及各涵道风扇侧壁中设置该涵道风扇增压器。
PCT/CN2020/118792 2020-09-29 2020-09-29 飞行载具 WO2022067492A1 (zh)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105151292A (zh) * 2015-05-25 2015-12-16 郝思阳 分布式矢量推进***
CN107697281A (zh) * 2017-09-20 2018-02-16 大连民族大学 一种涵道垂直起降无人飞行器
CN207029549U (zh) * 2017-03-23 2018-02-23 北京天宇新超航空科技有限公司 一种混合式倾转旋翼无人机
CN109017182A (zh) * 2018-10-15 2018-12-18 西安艾尔维克航空科技有限公司 一种垂直起降机翼可折叠的飞行汽车
US20190323563A1 (en) * 2018-04-24 2019-10-24 Bell Helicopter Textron Inc. Compressible driveshaft

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105151292A (zh) * 2015-05-25 2015-12-16 郝思阳 分布式矢量推进***
CN207029549U (zh) * 2017-03-23 2018-02-23 北京天宇新超航空科技有限公司 一种混合式倾转旋翼无人机
CN107697281A (zh) * 2017-09-20 2018-02-16 大连民族大学 一种涵道垂直起降无人飞行器
US20190323563A1 (en) * 2018-04-24 2019-10-24 Bell Helicopter Textron Inc. Compressible driveshaft
CN109017182A (zh) * 2018-10-15 2018-12-18 西安艾尔维克航空科技有限公司 一种垂直起降机翼可折叠的飞行汽车

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