TWI782333B

TWI782333B - Flying vehicle

Info

Publication number: TWI782333B
Application number: TW109133977A
Authority: TW
Inventors: 余知洋; 李晨暢; 陳坤揚; 林愷澤
Original assignee: 瑞鑑航太科技股份有限公司; 英商瑞鑒有限責任公司
Priority date: 2020-09-29
Filing date: 2020-09-29
Publication date: 2022-11-01
Also published as: TW202212199A

Abstract

Provided herein is a flying vehicle, comprising a fuselage; a front mounting base connecting to the front of fuselage; a rear mounting base connecting the rear of the fuselage; a plurality of external duct disposed around the fuselage; a plurality of housing disposed in the external duct; and a plurality of ducted fan disposed in the housing. The external ducts rotatably connect between the front mounting base and the fuselage and between the rear mounting base and the fuselage according to a first axis; and the housings rotatably connect the corresponding external duct according to a second axis.

Description

飛行載具flying vehicle

本發明係關於一種飛行載具；特定而言，該飛行載具包括多個外部涵道以及多個涵道風扇增壓器。 The present invention relates to an aerial vehicle; specifically, the aerial vehicle includes a plurality of external ducts and a plurality of ducted fan superchargers.

飛行器之發展大幅地改變人類交通的便利度。惟目前交通狀況於大都市中已漸趨飽和，交通堵塞問題也成為城市治理的麻煩之處。目前市面上已經大量販售無人飛行器，應用於各領域，例如拍攝或農業等，但鮮少研發者結合飛行器以及座車而完成飛行交通載具。因此，有必要研發一種可載人之飛行載具，已改善交通問題以及提高行動便利性。 The development of aircraft has greatly changed the convenience of human transportation. However, the current traffic situation in the metropolis has gradually become saturated, and the problem of traffic congestion has become a troublesome part of urban governance. At present, a large number of unmanned aerial vehicles have been sold on the market, which are used in various fields, such as photography or agriculture, but few developers have combined aircraft and cars to complete flying transportation vehicles. Therefore, it is necessary to develop a manned flying vehicle, which improves traffic problems and improves mobility.

本發明之目的係提供一種飛行載具，包括：一主體機身；連接該主體機身之前部之一前基座；連接該主體機身之後部之一後基座；分別位於該主體機身之四周之多個外部涵道；分別設於該些外部涵道中之多個涵道風扇側壁；以及設於對應之涵道風扇側壁中之多個涵道風扇增壓器。該些外部涵道分別沿一第一軸轉動連接於該前基座與該主體機身之間以及該後基座與該主體機身之間，該些涵道風扇側壁沿一第二軸轉動連接對應之外部涵道。 The purpose of the present invention is to provide a kind of flying vehicle, comprising: a main fuselage; a front base connected to the front part of the main fuselage; a rear base connected to the rear part of the main fuselage; A plurality of external ducts around the perimeter; a plurality of ducted fan side walls respectively arranged in the outer ducts; and a plurality of ducted fan superchargers arranged in the corresponding ducted fan side walls. The external channels They are not 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 rotatably connected to the corresponding external culverts along a second axis. road.

於一特定實施例，另包括一水平尾翼，其中該水平尾翼連接該主體機身之後部，以及對應之外部涵道位於該後基座與該水平尾翼之間。 In a specific embodiment, a horizontal stabilizer is further included, wherein the horizontal stabilizer is connected to the rear of the main fuselage, and a corresponding external duct is located between the rear base and the horizontal stabilizer.

於一實施例，該飛行載具另包括二升降舵，該二升降舵分別沿第二軸轉動連接對應之水平尾翼之後側。 In one embodiment, the flying vehicle further includes two elevators, and the two elevators are respectively connected to the rear side of the corresponding horizontal stabilizer for rotation along the second axis.

於一特定實施例，其中該第一軸與該第二軸彼此垂直。 In a specific embodiment, the first axis and the second axis are perpendicular to each other.

於一特定實施例，其中該涵道風扇增壓器係沿該第三軸固定於對應之涵道風扇側壁中，該第一軸、該第二軸、與該第三軸彼此垂直。 In a specific embodiment, wherein the ducted fan supercharger is fixed in the corresponding side wall of the ducted fan along the third axis, the first axis, the second axis, and the third axis are perpendicular to each other.

於一特定實施例，另包括一後上部機翼與二後側中部機翼，其中該後上部機翼連接該主體機身之後部之上側，以及該些後側中部機翼分別連接該後上部機翼之相對兩側並分別沿該第二軸延伸。 In a specific embodiment, 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 body fuselage, and the rear middle wings are respectively connected to the rear upper part The two opposite sides of the airfoil respectively extend along the second axis.

於一特定實施例，另包括二後中部襟副翼，其中該些後中部襟副翼分別沿該第二軸轉動連接對應之後側中部機翼之後部。 In a specific embodiment, it further includes two rear middle flaperons, wherein the rear middle flaperons are respectively connected to the rear part of the corresponding rear middle wing by rotating along the second axis.

於一特定實施例，另包括二後側垂直尾翼與二後側垂直尾翼方向舵，其中該些後側垂直尾翼分別連接對應之後側中部機翼之遠離該後上部機翼之一側並分別沿該第三軸延伸，該些後側垂直尾翼方向舵分別沿該第三軸轉動連接對應之後側垂直尾翼之後部。 In a specific embodiment, it also includes two rear vertical tails and two rear vertical tail rudders, wherein these rear vertical tails are respectively connected to one side of the corresponding rear middle wing away from the rear upper wing and respectively along the The third axis extends, and the rudders of the rear vertical tail are respectively rotated along the third axis and connected to the rear part of the corresponding rear vertical tail.

於一特定實施例，其中該些後側中部機翼分別沿該第三軸對齊對應之外部涵道，以及該後側垂直尾翼分別沿該第二軸對齊對應之外部涵道。 In a specific embodiment, the rear middle wings are respectively aligned with the corresponding outer ducts along the third axis, and the rear vertical tails are respectively aligned with the corresponding outer ducts along the second axis.

於一特定實施例，其中該第一軸、該第二軸、與該第三軸彼此垂直。 In a specific embodiment, the first axis, the second axis, and the third axis are perpendicular to each other.

於一特定實施例，另包括二後下部機翼，其中該些後下部機翼分別連接對應之後側垂直尾翼之遠離該後側中部機翼之一側並分別沿該第二軸朝該主體機身延伸。 In a specific embodiment, it further includes two rear lower wings, wherein the rear lower wings are respectively connected to one side of the corresponding rear vertical empennage away from the rear middle wing and are respectively moved toward the main body along the second axis. body extension.

於一特定實施例，其中該外部涵道與對應之後下部機翼於該第三軸上彼此不重疊。 In a specific embodiment, the outer duct and the corresponding rear lower airfoil do not overlap each other on the third axis.

於一特定實施例，另包括一座艙，其中該座艙設於該主體機身之上部。 In a specific embodiment, a cockpit is further included, wherein the cockpit is arranged on the upper part of the main fuselage.

於一特定實施例，另包括一座艙-機身連接件與一前方機翼，其中該前方機翼位於該主體機身之前部，以及該座艙-機身連接件連接於該座艙與該前方機翼之間。 In a specific embodiment, it further includes a cockpit-fuselage connection and a front wing, wherein the front wing is located at the front of the main fuselage, and the cockpit-fuselage connection is connected between the cockpit and the front wing. between the wings.

於一特定實施例，其中該前方機翼之相對兩側連接該前基座與該主體機身之相對兩側，該座艙-機身連接件連接該前方機翼之相對兩側之間。 In a particular embodiment, wherein opposite sides of the front wing are connected to opposite sides of the front base and the body fuselage, the cockpit-to-fuselage connection is connected between opposite sides of the front wing.

於一特定實施例，其中該座艙位於該主體機身之相對兩側之間，該座艙-機身連接件連接該座艙之前端。 In a particular embodiment, wherein the cabin is located between opposite sides of the main body fuselage, the cabin-fuselage connection connects the front end of the cabin.

於一特定實施例，其中該座艙可分離地連接該主體機身。 In a specific embodiment, wherein the cockpit is detachably connected to the main fuselage.

於一特定實施例，另包括二前側小翼，其中該些前側小翼分別位於該主體機身之相對兩側並沿該第二軸延伸，該些前側小翼分別沿第二軸轉動連接對應之主體機身之相對兩側。 In a specific embodiment, it further includes two front side winglets, wherein the front side winglets are respectively located on opposite sides of the main fuselage and extend along the second axis, and the front side winglets are respectively rotatably connected to corresponding The opposite sides of the main body of the fuselage.

於一特定實施例，其中該些前側小翼分別沿該第二軸對齊對應之外部涵道。 In a specific embodiment, the front winglets are respectively aligned with the corresponding outer ducts along the second axis.

於一特定實施例，其中該外部涵道之數量係至少四，該些外部涵道其中二者分別位於該主體機身之相對兩側且靠近該主體機身之前部，以及該些外部涵道另二者分別位於該主體機身之相對兩側且靠近該主體機身之後部。 In a specific embodiment, wherein the number of the external ducts is at least four, two of the external ducts are respectively located on opposite sides of the main body fuselage and near the front of the main body fuselage, and the external ducts The other two are respectively located on opposite sides of the main fuselage and close to the rear part of the main fuselage.

於一特定實施例，其中各外部涵道設置該涵道風扇側壁，各外部涵道中之涵道風扇側壁沿該第一軸排列，以及各涵道風扇側壁中設置該涵道風扇增壓器。 In a specific embodiment, each outer duct is provided with the ducted fan sidewall, the ducted fan sidewalls in each outer duct are arranged along the first axis, and the ducted fan supercharger is provided in each ducted fan sidewall.

1:前基座 1: Front base

2:涵道風扇增壓器 2: Ducted fan supercharger

3:涵道風扇側壁 3: Ducted fan side wall

4:座艙 4: Cockpit

5:外部涵道 5: External duct

6:主體機身 6: Main fuselage

7:後上部機翼 7: rear upper wing

8:後基座 8: rear base

9:後側中部機翼 9: Rear middle wing

10:水平尾翼 10: horizontal tail

11:垂直尾翼方向舵 11:Vertical tail rudder

12:後中部襟副翼 12: Rear center flaperon

13:後側垂直尾翼 13: Rear vertical tail

14:後下部機翼 14: rear lower wing

15:前側小翼 15: Front winglet

16:座艙-機身連接件 16: Cockpit-fuselage connection

17:前方機翼 17: Front wing

18:升降舵 18:Elevator

茲配合附圖以更佳地說明前述發明內容以及下述之本發明實施方式。 The foregoing invention and the following embodiments of the invention are better described with reference to the accompanying drawings.

圖1是本發明一實施例的飛行載具的上方視角示意圖；圖2是本發明一實施例的飛行載具的下方視角示意圖；以及圖3是本發明一實施例的飛行載具的外部涵道、涵道風扇側壁與涵道風扇增壓器的局部放大示意圖。 Fig. 1 is a schematic diagram of an upper perspective of a flying vehicle according to an embodiment of the present invention; Fig. 2 is a schematic diagram of a lower perspective of a flying vehicle according to an embodiment of the present invention; and Fig. 3 is an external view of a flying vehicle according to an embodiment of the present invention Partial enlarged schematic diagram of duct, ducted fan side wall and ducted fan supercharger.

本發明之技術特徵，包含特定特徵，係揭示於申請專利範圍，針對本發明之技術特徵，較佳之理解茲配合說明書、依據本發明原理之實施例、和圖式將本發明詳細說明如下。 The technical features of the present invention, including specific features, are disclosed in the scope of the patent application. Aiming at the technical features of the present invention, a better understanding is given below in conjunction with the description, embodiments based on the principles of the present invention, and drawings.

本發明說明書及申請專利範圍中所述之所有技術性及科學用語，除非另有所定義，皆為本發明所屬技術領域具有通常知識者可知曉之定義。其中單數用語「一」、「一個」、「該」、或其近似用語，除非另有說明，皆可指涉多於一個對象。本說明書使用之「或」、「以及」、「和」，除非另有說明，皆指涉「或/和」。此外，用語「包含」、「包括」皆非有所限制之開放式連接詞。前述定義僅說明用語定義之指涉而不應解釋為對發明標的之限制。除非另有說明，本發明所用之材料皆為市售易於取得。 All technical and scientific terms described in the description of the present invention and the scope of the patent application, unless otherwise defined, are definitions known to those with ordinary knowledge in the technical field to which the present invention belongs. The singular terms "a", "an", "the", or similar expressions thereof, unless otherwise specified, may refer to more than one object. "Or", "and", "and" used in this manual, unless otherwise stated, all refer to "or/and". In addition, the terms "comprises" and "including" are not intended to be restrictive connective words. The foregoing definitions only illustrate the meaning of the term definitions and should not be construed as limitations on the subject matter of the invention. Unless otherwise stated, the materials used in the present invention are commercially available and readily available.

另，本說明書用語「上」、「之上」、「上方」、或相似用語指涉一元件與另一元件直接接觸，但亦指涉一元件與另一元件不直接接觸。 In addition, the terms "on", "on", "above", or similar terms in this specification refer to an element in direct contact with another element, but also mean that an element is not in direct contact with another element.

本說明書和請求項所提及的序數，例如「第一」、「第二」等，僅用於說明所揭露之元件，而非指稱或表示元件之間具有任何執行次序，亦非指稱或表示於一元件和另一元件之間的次序、或製程之步驟次序。該些序數僅用於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區分。 The ordinal numbers mentioned in this specification and claims, such as "first", "second", etc., are only used to describe the disclosed components, not to refer to or represent any execution order between the components, nor to refer to or represent The sequence between one component and another, or the sequence of steps in a process. These ordinal numbers are only used to clearly distinguish one element with a certain designation from another element with the same designation.

請參照圖1至圖3，本發明提供一種飛行載具；特定而言，該飛行載具係用於載人。但於一替代實施例，本發明亦為通過遙控操作之無人載具。在本實施例中，該飛行載具係可載人之載具，其體積小於傳統載人飛行器而接近於自用客車，且該飛行載具具備垂直起降、原地轉向的特性。 Please refer to FIG. 1 to FIG. 3 , the present invention provides an air vehicle; specifically, the air vehicle is used for carrying people. But in an alternative embodiment, the present invention is also an unmanned vehicle operated by remote control. In this embodiment, the flight vehicle is a vehicle that can carry people, and its volume is smaller than that of a traditional manned aircraft and close to that of a self-use passenger car, and the flight vehicle has the characteristics of vertical take-off and landing, and turning on the spot.

在一實施例中，本發明之飛行載具包括一主體機身6、一前基座1、一後基座8、多個外部涵道5、多個涵道風扇側壁3、與多個涵道風扇增壓器2。該主體機身6可區分為前部與後部，該前基座1係連接該主體機身6的前部，該後基座8係連接該主體機身6的後部。該些外部涵道5分別位於該主體機身6之四周，該些外部涵道5之其中數者分別沿第一軸(於圖1中為x軸)可轉動地連接於該前基座1與該主體機身6之間，該些外部涵道5之其他者分別沿第一軸轉動連接於該後基座8與該主體機身6之間。該些涵道風扇側壁3分別設於該些外部涵道5中，且該些涵道風扇側壁3沿第二軸(於圖1中為y軸)可轉動地連接對應之外部涵道5。該些涵道風扇增壓器2設於對應之涵道風扇側壁3中。 In one embodiment, the flying vehicle of the present invention includes a main fuselage 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 ducts Road fan booster 2. The main fuselage 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 fuselage 6 , and the rear base 8 is connected to the rear part of the main fuselage 6 . The external ducts 5 are respectively located around the main body 6, and the middle of the external ducts 5 are respectively rotatably connected to the front base 1 along the first axis (x-axis in FIG. 1 ). Between the main fuselage 6 and the other of the external ducts 5 are respectively rotatably connected between the rear base 8 and the main fuselage 6 along a first axis. The ducted fan sidewalls 3 are respectively disposed in the outer ducts 5 , and the ducted fan sidewalls 3 are rotatably connected to the corresponding outer ducts 5 along a second axis (y-axis in FIG. 1 ). These ducted fan superchargers 2 are arranged in corresponding ducted fan side walls 3 .

於一實施例，該外部涵道5、該涵道風扇側壁3、與該涵道風扇增壓器2組成飛行載具之推進系統。該外部涵道5之數量有4個，但不限於此。二外部涵道5分別位於該主體機身6之相對左右兩側且靠近該主體機身6的前部，另二外部涵道5分別位於該主體機身6之相對左右兩側且靠近該主體機身6的後部。於一實施例，該外部涵道5係長圓形的柱狀中空結構，其平行第一軸之長度較長(長度方向)，而平行第二軸之長度較短(寬度方向)。該涵道風扇側壁3係圓形之柱狀中空結構，各外部涵道5中設有至少二涵道風扇側壁3，各外部涵道5中之涵道風扇側壁3係沿第一軸排列。 In one embodiment, the external duct 5 , the side wall of the ducted fan 3 , and the ducted fan supercharger 2 constitute a propulsion system of an aircraft. The number of the external ducts 5 is 4, but not limited thereto. Two external ducts 5 are respectively located on the opposite left and right sides of the main body 6 and are close to the front of the main body 6, and the other two external ducts 5 are respectively located on the relative left and right sides of the main body 6 and are close to the main body The rear portion of the fuselage 6. In one embodiment, the external duct 5 is an oblong columnar hollow structure, the length parallel to the first axis is longer (in the length direction), and the length parallel to the second axis is shorter (in the width direction). The sidewalls 3 of the ducted fans are circular columnar hollow structures, and at least two sidewalls 3 of the ducted fans are arranged in each outer duct 5, and the sidewalls 3 of the ducted fans in each outer duct 5 are arranged along the first axis.

各涵道風扇側壁3中設有一涵道風扇增壓器2，該涵道風扇增壓器2係沿第三軸(於圖1中為z軸)固定於對應之涵道風扇側壁3中。該涵道風扇增壓器2包括多個扇葉與轉軸，轉軸可帶動扇葉旋轉，氣流自涵道風扇側壁3之一端被吸入該涵道風扇增壓器2，並由該涵道風扇側壁3之另一端噴出，以產生噴射氣流，並推進飛行載具。於圖式中，本發明之飛行載具之各外部涵道5設有二涵道風扇增壓器2，但本發明不限於此，該涵道風扇增壓器2之數量可為1、3、4、或更多。 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, and the rotating shaft can drive the fan blades to rotate. The other end of 3 is ejected to generate a jet stream and propel the flying vehicle. In the drawings, each external duct 5 of the flying vehicle of the present invention is provided with two ducted fan superchargers 2, but the present invention is not limited thereto, the number of the ducted fan superchargers 2 can be 1, 3 , 4, or more.

當全部外部涵道5與涵道風扇側壁3位於垂直位置，即與第三軸對齊之位置，該涵道風扇增壓器2產生之自該涵道風扇側壁3噴出之噴射氣流推進飛行載具於第三軸移動。於一實施例，第一軸、第二軸、與第三軸互相垂直，例如第一軸為X軸、第二軸為Y軸而第三軸為Z軸。第一軸與第二軸係相對於地面之水平方向，第三軸係相對於地面之垂直方向。 When all the external ducts 5 and ducted fan sidewalls 3 are in a vertical position, that is, a position aligned with the third axis, the jet airflow generated by the ducted fan supercharger 2 and ejected from the ducted fan sidewall 3 propels the flying vehicle Move on the third axis. In one embodiment, the first axis, the second axis, and the third axis are perpendicular to each other, for example, the first axis is the X axis, the second axis is the Y axis, and the third axis is the Z axis. The horizontal direction of the first axis and the second axis relative to the ground, and the vertical direction of the third axis relative to the ground.

該外部涵道5可相對於該主體機身6繞第一軸進行轉動，以賦予整體推進系統於第一軸上之轉動能力，改變推進系統的推力方向與第一軸之夾角，以改變飛行載具的推進方向。該涵道風扇側壁3可相對於該外部涵道5繞第二軸進行轉動，以賦予整體推進系統於第二軸之轉動能力，改變推進系統之推力方向與第二軸的夾角，以改變飛行載具的推進方向。該外部涵道5與該涵道風扇側壁3共同配合可改變整體推進系統於第一軸與第二軸轉動能力，使飛行載具沿第一軸與第二軸推進。而改變該涵道風扇增壓器2之運作功率，可改變噴射氣流之強度，相應可改變飛行載具之高度。 The external duct 5 can rotate around the first axis relative to the main fuselage 6, so as to give the whole propulsion system the ability to rotate on the first axis, change the angle between the thrust direction of the propulsion system and the first axis, and change the flight direction. The propulsion direction of the vehicle. The side wall 3 of the ducted fan can rotate around the second axis relative to the external duct 5, so as to give the overall propulsion system the ability to rotate on the second axis, change the angle between the thrust direction of the propulsion system and the second axis, and change the flight direction. The propulsion direction of the vehicle. The cooperation between the external duct 5 and the side wall of the ducted fan 3 can change the rotation capability of the overall propulsion system on the first axis and the second axis, so that the flying vehicle can be propelled along the first axis and the second axis. And changing the operating power of the ducted fan supercharger 2 can change the intensity of the jet airflow, and accordingly can change the altitude of the flying vehicle.

在一實施例中，該飛行載具還包括一水平尾翼10，該水平尾翼10連接該後基座8，且連接位於該後基座8之外部涵道5。 In one embodiment, the flying vehicle further includes a horizontal stabilizer 10 , the horizontal stabilizer 10 is connected to the rear base 8 and connected to the external duct 5 located on the rear base 8 .

於一實施例，該飛行載具另包括一後上部機翼7與二後側中部機翼9，該後上部機翼7連接該主體機身6之後部之上側，該二後側中部機翼9分別連接該後上部機翼7之相對之左右兩側，且該二後側中部機翼9分別沿第二軸朝遠離後上部機翼7的方向延伸。該後上部機翼7與該後側中部機翼9可為飛行載具提供升力。 In one embodiment, the flying vehicle 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 fuselage 6, and the two rear middle wings 9 respectively connects the opposite left and right sides of the rear upper wing 7, and the two rear middle wings 9 extend along the second axis towards the direction away from the rear upper wing 7 respectively. The rear upper wing 7 and the rear middle wing 9 can provide lift for the flying vehicle.

於一實施例，該飛行載具另包括二後中部襟副翼12，該二後中部襟副翼12分別沿第二軸轉動連接對應之後側中部機翼9之後側(即相對於前部方向之另一側)。該二後中部襟副翼12可繞第二軸轉動，該二後中部襟副翼12可以改變飛行載具在低速飛行時該後側中部機翼9之升力；與前側小翼協同作動時可作為輔助，增加該飛行載具進行滾動(Roll)及俯仰(Pitch)飛行動作時的操控與靈活性。 In one embodiment, the flying vehicle further includes two rear middle flaperons 12, and the two rear middle flaperons 12 are respectively rotated along the second axis and connected to the rear side of the corresponding 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 force of the rear middle wing 9 of the flying vehicle when flying at low speed; As an aid, it increases the control and flexibility of the flying vehicle when it performs rolling (Roll) and pitching (Pitch) flight actions.

於一實施例，該飛行載具另包括二後側垂直尾翼13與二後側垂直尾翼方向舵11，該二後側垂直尾翼13分別連接對應的後側中部機翼9的遠離該後上部機翼7的一側，並且該二後側垂直尾翼13分別沿第三軸向下延伸，該二後側垂直尾翼方向舵11分別沿第三軸可轉動地連接對應之後側垂直尾翼13之後側。該二後側垂直尾翼方向舵11可繞第三軸轉動，其可用於水平飛行時調整該飛行載具之機頭於x-y平面之方向，輔助機身進行偏擺(Yaw)飛行動作。 In one embodiment, the flying vehicle further includes two rear vertical tail fins 13 and two rear vertical tail fin rudders 11, and the two rear vertical tail fins 13 are respectively connected to the corresponding rear middle wing 9 which is far away from the rear upper wing. 7, and the two rear vertical tail fins 13 respectively extend downward along the third axis, and the two rear vertical tail fin rudders 11 are respectively rotatably connected to the rear side of the corresponding rear vertical tail fin 13 along the third axis. The two rear vertical tail rudders 11 can rotate around the third axis, which can be used to adjust the direction of the nose of the flying vehicle in the x-y plane during horizontal flight, and assist the fuselage to perform yaw (Yaw) flight actions.

於一實施例，該二後側中部機翼9分別沿第三軸對齊對應之外部涵道5，二後側垂直尾翼13分別沿第二軸對齊對應的外部涵道5。上述外部涵道5例如是靠近該主體機身6後部之二外部涵道5。 In one embodiment, the two rear middle wings 9 are respectively aligned with the corresponding external duct 5 along the third axis, and the two rear vertical tail fins 13 are respectively aligned with the corresponding external duct 5 along the second axis. The above-mentioned external ducts 5 are, for example, two external ducts 5 near the rear of the main fuselage 6 .

於一實施例，該飛行載具另包括二後下部機翼14，該二後下部機翼14分別連接對應之後側垂直尾翼13之遠離該後側中部機翼9之一側，並且該二後下部機翼14分別沿第二軸朝該主體機身6延伸。於一實施例，該後下部機翼14沿第二軸延伸之長度小於該後側中部機翼9沿第二軸延伸的長度，並且該外部涵道5與對應之後下部機翼14於第三軸上未重疊，換言之，該後下部機翼14不阻擋該涵道風扇增壓器2與第三軸平行之噴射氣流。 In one embodiment, the flying vehicle further includes two rear lower wings 14, the two rear lower wings 14 are respectively connected to one side of the corresponding rear vertical tail 13 away from the rear middle wing 9, and the two rear The lower wings 14 respectively extend towards the main fuselage 6 along the second axis. In one embodiment, 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 on the third axis. There is no overlap on the axis, in other words, the rear lower wing 14 does not block the jet flow of the ducted fan supercharger 2 parallel to the third axis.

於一實施例，該飛行載具另包括二前側小翼15，該二前側小翼15分別位於該主體機身6之相對之左右兩側，並且該二前側小翼15沿第二軸延伸，且該二前側小翼15可繞第二軸轉動。該二前側小翼15分別沿第二軸對齊對應之外部涵道5，前述外部涵道5係靠近該主體機身6前部之二外部涵道5。 In one embodiment, the flying vehicle further includes two front winglets 15, the two front winglets 15 are respectively located on the opposite left and right sides of the main fuselage 6, and the two front winglets 15 extend along the second axis, And the two front winglets 15 can rotate around the second axis. The two front winglets 15 are respectively aligned with the corresponding external ducts 5 along the second axis, and the aforementioned external ducts 5 are two external ducts 5 close to the front part of the main fuselage 6 .

於一實施例，該飛行載具另包括可載人座艙4，該座艙4設於該主體機身6之上部。於一實施例，該飛行載具另包括一座艙-機身連接件16與一前方機翼17，該前方機翼17位於該主體機身6的前部，該座艙-機身連接件16連接於該座艙4與該前方機翼17之間。該座艙-機身連接件16用於連結與固定該主體機身6和該座艙4。在一實施例中，該座艙4可分離地連接該主體機身6，也就是在需要的時候，座艙4可與主體機身6分離。 In one embodiment, the flight vehicle further includes a cabin 4 that can carry people, and the cabin 4 is arranged on the upper part of the main fuselage 6 . In one embodiment, the flight vehicle further includes a cabin-fuselage connection 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 to connect and fix the main fuselage 6 and the cockpit 4 . In one embodiment, the cockpit 4 is detachably connected to the main fuselage 6 , that is, the cockpit 4 can be separated from the main fuselage 6 when needed.

於一實施例，該前方機翼17之相對之左右兩側連接該前基座1與該主體機身6之相對兩側，該座艙-機身連接件16連接該前方機翼17之左右兩側之間。該座艙4位於該主體機身6的相對兩側之間，而該座艙-機身連接件16連接該座艙4的前端。 In one embodiment, 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 fuselage 6, and 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 .

於一實施例，該飛行載具另包括二升降舵18，該二升降舵18分別沿第二軸轉動連接對應之水平尾翼10之後側。該二升降舵18可繞第二軸轉動，該二升降舵18可以改變飛行載具在飛行時該後側水平尾翼10之升力，增加該飛行載具進行俯仰(Pitch)飛行動作時的操控與靈活性。 In one embodiment, the flying vehicle further includes two elevators 18 , and the two elevators 18 are respectively connected to the rear side of the corresponding horizontal stabilizer 10 for rotation 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 tail 10 of the flight vehicle during flight, increasing the control and flexibility of the flight vehicle when it is pitching (Pitch) .

以下舉例說明飛行載具之作動原理，並以第一軸為X軸、第二軸為Y軸而第三軸為Z軸為例。 The following is an example to illustrate the operating principle of the flying vehicle, and the first axis is the X axis, the second axis is the Y axis, and the third axis is the Z axis as an example.

當飛行載具沿第三軸垂直起飛或降落時，全部涵道風扇增壓器2垂直於地面並向下噴氣，通過加大或減小該涵道風扇增壓器2的功率而使飛行載具升高或下降。若在垂直起飛、降落、懸停或低速飛行時，飛行載具需要在機頭指向不變時向左或者向右傾斜飄動，推進系統(或可稱動力系統)的該涵道風扇增壓器2會被該外部涵道5帶動，而繞X軸逆時針或順時針轉動一定角度，使該涵道風扇增壓器2的排氣端(例如該涵道風扇側壁3的下端)向右或向左轉動。若在垂直起飛、降落、懸停或低速飛行時，飛行載具需要在機頭指向不變時向前或者向後傾斜飄動，推進系統的該涵道風扇增壓器2會被該涵道風扇側壁3帶動，而繞Y軸逆時針或順時針轉動較小的一定角度，使該涵道風扇增壓器2的排氣端(例如該涵道風扇側壁3的下端)向後或向前轉動。 When the flight vehicle took off or landed vertically along the third axis, all the ducted fan superchargers 2 were vertical to the ground and sprayed downwards, and the flight vehicle was increased or decreased by increasing or decreasing the power of the ducted fan supercharger 2 to make the flight vehicle With rise or fall. If during vertical take-off, landing, hovering or low-speed flight, the flight vehicle needs to tilt left or right when the nose pointing is constant, the ducted fan supercharger of the propulsion system (or power system) 2 will be driven by the external duct 5, and turn around the X-axis counterclockwise or clockwise at a certain angle, so that the exhaust end of the ducted fan supercharger 2 (such as the lower end of the ducted fan side wall 3) moves to the right or Turn left. During vertical take-off, landing, hovering or low-speed flight, the vehicle needs to Floating forward or backward, the ducted fan supercharger 2 of the propulsion system will be driven by the side wall 3 of the ducted fan, and rotate around the Y axis counterclockwise or clockwise at a small certain angle to make the ducted fan supercharged The exhaust end of device 2 (such as the lower end of the ducted fan side wall 3) rotates backward or forward.

在高速飛行時，推進系統內的該涵道風扇增壓器2會被該涵道風扇側壁3帶動而繞Y軸逆時針旋轉較大角度，使機身獲得較多向前的推力。若在高速飛行時需要加大機身的仰角，可由以下三種作動方式組合而達成，靠近該主體機身6前部之涵道風扇增壓器2之前端風扇推力增加，靠近該主體機身6後部之涵道風扇增壓器2之後端風扇推力減小，或該後中部襟副翼12會繞Y軸順時針旋轉一定角度且同時前側小翼15以相反方向繞Y軸旋轉一定角度，或該些升降舵18會繞Y軸順時針旋轉，增加飛行載具在飛行時該後側水平尾翼10之升力。若在高速飛行時需要減小機身的仰角，可由以下三種作動方式組合而達成，靠近該主體機身6前部之涵道風扇增壓器2之前端風扇推力減小，靠近該主體機身6後部之涵道風扇增壓器2之後端風扇推力增加，或該後中部襟副翼12會繞Y軸逆時針旋轉一定角度且同時前側小翼15以相反方向繞Y軸旋轉一定角度，或該些升降舵18會繞Y軸逆時針旋轉，減少飛行載具在飛行時該後側水平尾翼10之升力。 When flying at high speed, the ducted fan supercharger 2 in the propulsion system will be driven by the side wall 3 of the ducted fan to rotate counterclockwise at a large angle around the Y axis, 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 combining the following three actuation modes. The thrust of the fan at the front end of the ducted fan supercharger 2 near the front of the main body 6 is increased, and the thrust of the fan near the main body 6 is increased. The thrust of the rear fan of the ducted fan supercharger 2 at the rear is reduced, or the rear middle flaperon 12 rotates clockwise around the Y axis for a certain angle and at the same time the front winglet 15 rotates around the Y axis for a certain angle in the opposite direction, or The elevators 18 rotate clockwise around the Y axis to increase the lift force of the rear horizontal stabilizer 10 when the flying vehicle is flying. If it is necessary to reduce the elevation angle of the fuselage during high-speed flight, it can be achieved by combining the following three actuation methods. The thrust of the fan at the front end of the ducted fan supercharger 2 near the front of the main fuselage 6 is reduced, and the thrust of the fan near the main fuselage 6 is reduced. 6. The rear fan thrust of the ducted fan supercharger 2 at the rear increases, or the rear middle flaperon 12 rotates counterclockwise around the Y axis for a certain angle and at the same time the front winglet 15 rotates around the Y axis for a certain angle in the opposite direction, or The elevators 18 rotate counterclockwise around the Y axis to reduce the lift force of the rear horizontal stabilizer 10 when the flying vehicle is flying.

在高速飛行中若需要機身向左傾斜時，左側之後中部襟副翼12繞Y軸順時針旋轉一角度且同時前側小翼15以相同繞行方向繞Y軸旋轉一定角度，以減少左半機身之升力，右側之後中部襟副翼12及前側小翼15(即左側之後中部襟副翼12與前側小翼15之對側)各以相反於左側之後中部襟副翼12與前側小翼15繞行方向繞Y軸旋轉一角度，以增加右半邊機身之升力。已使得整體機身達到向左滾轉之目的；高速飛行中若需要機身向右傾斜時，左側之後中部襟副翼12繞Y軸逆時針旋轉一角度且同時前側小翼15以相同繞行方向繞Y軸旋轉一定角度，以增加左半機身之升力，右側之後中部襟副翼12及前側小翼15(即左側之後中部襟副翼12與前側小翼15之對側)各以相反於左側之後中部襟副翼12與前側小翼15繞行方向繞Y軸旋轉一角度，以減少右半邊機身之升力。已使得整體機身達到向右滾轉之目的。 In high-speed flight, if the fuselage is required to tilt to the left, the left rear middle flaperon 12 rotates clockwise around the Y axis for a certain angle and at the same time the front winglet 15 rotates around the Y axis for a certain angle in the same direction to reduce the left half The lift force of the fuselage, the right rear middle flaperon 12 and the front side winglet 15 (that is, the opposite side of the left rear middle flaperon 12 and the front side winglet 15) are respectively opposite to the left side rear middle flaperon 12 and the front side winglet 15 The direction of rotation rotates an angle around the Y axis to increase the lift of the right half of the fuselage. The overall fuselage has achieved the purpose of rolling to the left; if the fuselage needs to tilt to the right during high-speed flight, the left rear middle flap The aileron 12 rotates an angle counterclockwise around the Y axis and at the same time the front side winglet 15 rotates a certain angle around the Y axis in the same orbiting direction to increase the lift of the left half of the fuselage. (That is, the opposite sides of the left rear middle flaperon 12 and the front side winglet 15) each rotate an angle around the Y axis in the direction opposite to the left side rear middle flaperon 12 and the front side winglet 15, so as to reduce the right half of the fuselage of lift. The overall fuselage has achieved the purpose of rolling to the right.

在高速或低速飛行時若需要調整機頭向左時，後側之垂直尾翼方向舵11繞Z軸逆時針旋轉一角度；在高速或低速飛行時若需要調整機頭向右時，後側之垂直尾翼方向舵11繞Z軸順時針旋轉一角度(另一側之後側之垂直尾翼方向舵11轉向相同)。 When flying at high speed or low speed, if it is necessary to adjust the nose to the left, the vertical tail rudder 11 on the rear side rotates an angle counterclockwise around the Z axis; The tail rudder 11 rotates an angle clockwise around the Z axis (the vertical tail rudder 11 on the rear side of the other side turns to the same direction).

在高速或低速飛行時，前方機翼17可引導氣流更高效地通過飛行器上表面，使載人飛行器整體產生升力，抵銷自身重力，間接達到使涵道風扇增壓器需要之功耗降低，更高效飛行。 When flying at high speed or low speed, 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.

於本發明，該飛行載具之推進系統由該外部涵道5、該涵道風扇側壁3與該涵道風扇增壓器2、與該些機翼與副翼共同提供，並可通過該外部涵道5、該涵道風扇側壁3、與該涵道風扇增壓器2於多軸上之轉動自由度對進氣與排氣進行導向，除了朝特定方向推進以外，還可達到垂直起降、原地轉向的能力。多個小尺寸機翼圍繞該座艙4與該主體機身6佈置，作為空氣動力部件提供升力的同時，也可作為結構件承載整機重量與作為裝配主體。飛行載具的機身通過流體產生的升力並非主要的動力來源，但在中高速巡航狀態下可產生大量升力，降低了能耗的同時，在較小的尺寸範圍內獲得了固定翼的優勢。飛行載具之推進系統可由一電源(例如：電能與氫燃料電池或電能與燃油混合動力、純氫燃料電池、或燃油發電)供能，且該電池可設於該座艙4及/或該主體機身6內部，但不限於此。該座艙4獨立且可分離地安裝於該主體機身6，在危機狀態下可分離，例如在墜機時，該座艙4可與機身分離，以保證該座艙4的完整性，從而達成更高的安全性。另外，該涵道風扇增壓器2被由該外部涵道5、該涵道風扇側壁3、與該主體機身6層層包覆，旋轉機件或運動部件無法與人或動植物直接接觸，可減小旋轉機件與運動部件對周圍環境的人事物的威脅，提高了安全性。在尺寸、機動性與安全性的優勢幫助下，本發明之飛行載具可在城市建築群落中運行，具備自由穿梭的良好機動性，且對周圍環境影響較小。 In the present invention, 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, and the wings and ailerons, and can pass through the external Duct 5, the ducted fan side wall 3, and the ducted fan supercharger 2 can be rotated freely on multi-axis to guide the intake and exhaust, in addition to propelling in a specific direction, it can also achieve vertical take-off and landing , The ability to turn in place. A plurality of small-sized wings are arranged around the cockpit 4 and the main fuselage 6 to provide lift as an aerodynamic component and also serve as a structural component to carry the weight of the whole machine and serve as an assembly body. The lift generated by the fuselage of the flying vehicle through the fluid is not the main source of power, but it can generate a large amount of lift in the middle and high speed cruising state, which reduces energy consumption and obtains 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: electricity and hydrogen fuel cells or electricity and fuel hybrid, pure Hydrogen fuel cell, or fuel oil power generation) power supply, and the battery can be arranged in the cabin 4 and/or the main fuselage 6 inside, but not limited thereto. The cockpit 4 is independently and detachably installed on the main fuselage 6, and can be separated in a crisis state. High security. In addition, the ducted fan supercharger 2 is covered layer by layer by the external duct 5, the side wall 3 of the ducted fan, and the main fuselage, so that the rotating parts or moving parts cannot be in direct contact with people, animals or plants. It can reduce the threat of rotating parts and moving parts to people and things in the surrounding environment, and improves safety. With the help of the advantages of size, maneuverability and safety, the flying vehicle of the present invention can operate in urban building groups, has good maneuverability of free shuttle, and has little impact on the surrounding environment.

於本說明書實施例揭示之內容，本發明所屬領域具有通常知識者可明顯得知前述實施例僅為例示而非限制；具本發明所屬技術領域通常知識者可藉由諸多變換、替換而實施，並不與本發明之技術特徵有所差異。依據說明書實施例，本發明可有多種變換仍無礙於實施。本說明書提供之請求項界定本發明之範圍，該範圍涵蓋前述方法與結構及與其相等之創作。 In the content disclosed in the embodiments of this specification, those with ordinary knowledge in the field of the present invention can clearly understand that the above-mentioned embodiments are only illustrative and not limiting; It is not different from the technical features of the present invention. According to the embodiments of the description, the present invention can have various transformations without hindering the implementation. The claims provided in this specification define the scope of the present invention, which covers the aforementioned methods and structures and their equivalent creations.

1:前基座 1: Front base

2:涵道風扇增壓器 2: Ducted fan supercharger

3:涵道風扇側壁 3: Ducted fan side wall

4:座艙 4: Cockpit

5:外部涵道 5: External duct

6:主體機身 6: Main fuselage

7:後上部機翼 7: rear upper wing

8:後基座 8: rear base

9:後側中部機翼 9: Rear middle wing

10:水平尾翼 10: horizontal tail

11:垂直尾翼方向舵 11:Vertical tail rudder

12:後中部襟副翼 12: Rear center flaperon

13:後側垂直尾翼 13: Rear vertical tail

14:後下部機翼 14: rear lower wing

15:前側小翼 15: Front winglet

16:座艙-機身連接件 16: Cockpit-fuselage connection

17:前方機翼 17: Front wing

18:升降舵 18:Elevator

Claims

一種飛行載具，包括：一主體機身；一前基座，連接該主體機身之前部；一後基座，連接該主體機身之後部；多個外部涵道，分別位於該主體機身之四周，該些外部涵道分別沿一第一軸轉動連接於該前基座與該主體機身之間以及該後基座與該主體機身之間；多個涵道風扇側壁，分別設於該些外部涵道中，該些涵道風扇側壁沿一第二軸轉動連接對應之外部涵道；以及多個涵道風扇增壓器，設於對應之涵道風扇側壁中。 A flying vehicle, comprising: a main fuselage; a front base, connected to the front part of the main body; a rear base, connected to the rear of the main body; A plurality of external ducts are respectively located around the main fuselage, and these external ducts are respectively rotatably connected between the front base and the main fuselage and between the rear base and the main fuselage along a first axis between; A plurality of ducted fan sidewalls are respectively arranged in the external ducts, and the ducted fan sidewalls are rotatably connected to the corresponding external ducts along a second axis; and A plurality of ducted fan superchargers are arranged in the side walls of the corresponding ducted fans.

如請求項1之飛行載具，另包括一水平尾翼，其中該水平尾翼連接該主體機身之後部，以及對應之外部涵道位於該後基座與該水平尾翼之間。The flight vehicle according to claim 1, further comprising a horizontal stabilizer, wherein the horizontal stabilizer is connected to the rear of the main fuselage, and the corresponding external duct is located between the rear base and the horizontal stabilizer.

如請求項1之飛行載具，另包括二升降舵，該二升降舵分別沿第二軸轉動連接對應之水平尾翼之後側。As in the flying vehicle of claim 1, it further includes two elevators, and the two elevators are respectively rotated along the second axis and connected to the rear side of the corresponding horizontal stabilizer.

如請求項1之飛行載具，其中該第一軸與該第二軸彼此垂直。The flying vehicle according to claim 1, wherein the first axis and the second axis are perpendicular to each other.

如請求項1之飛行載具，其中該涵道風扇增壓器係沿該第三軸固定於對應之涵道風扇側壁中，該第一軸、該第二軸、與該第三軸彼此垂直。The flying vehicle according to claim 1, wherein the ducted fan supercharger is fixed in the side wall of the corresponding ducted fan along the third axis, and the first axis, the second axis, and the third axis are perpendicular to each other .

如請求項1之飛行載具，另包括一後上部機翼與二後側中部機翼，其中該後上部機翼連接該主體機身之後部之上側，以及該些後側中部機翼分別連接該後上部機翼之相對兩側並分別沿該第二軸延伸。Such as the flight vehicle of claim 1, further comprising 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 opposite sides of the upper rear wing extend along the second axis respectively.

如請求項6之飛行載具，另包括二後中部襟副翼，其中該些後中部襟副翼分別沿該第二軸轉動連接對應之後側中部機翼之後部。The flying vehicle according to claim 6, further comprising two rear middle flaperons, wherein the rear middle flaperons are respectively rotated along the second axis and connected to the rear part of the corresponding rear middle wing.

如請求項7之飛行載具，另包括二後側垂直尾翼與二後側垂直尾翼方向舵，其中該些後側垂直尾翼分別連接對應之後側中部機翼之遠離該後上部機翼之一側並分別沿該第三軸延伸，該些後側垂直尾翼方向舵分別沿該第三軸轉動連接對應之後側垂直尾翼之後部。Such as the flying vehicle of claim 7, further comprising two rear vertical tails and two rear vertical tail rudders, wherein the rear vertical tails are respectively connected to one side of the corresponding rear middle wing away from the rear upper wing and Extending along the third axis respectively, the rear vertical tail rudders are respectively rotated along the third axis and connected to the rear part of the corresponding rear vertical tail.

如請求項8之飛行載具，其中該些後側中部機翼分別沿該第三軸對齊對應之外部涵道，以及該後側垂直尾翼分別沿該第二軸對齊對應之外部涵道。The flying vehicle according to claim 8, wherein the rear middle wings are respectively aligned with the corresponding external duct along the third axis, and the rear vertical tail is respectively aligned with the corresponding external duct along the second axis.

如請求項9之飛行載具，其中該第一軸、該第二軸、與該第三軸彼此垂直。The flying vehicle according to claim 9, wherein the first axis, the second axis, and the third axis are perpendicular to each other.

如請求項9之飛行載具，另包括二後下部機翼，其中該些後下部機翼分別連接對應之後側垂直尾翼之遠離該後側中部機翼之一側並分別沿該第二軸朝該主體機身延伸。Such as the flying vehicle of claim 9, further comprising two rear lower wings, wherein the rear lower wings are respectively connected to one side of the corresponding rear vertical tail wing away from the rear middle wing and are respectively moved along the second axis toward The main body fuselage is extended.

如請求項11之飛行載具，其中該外部涵道與對應之後下部機翼於該第三軸上彼此不重疊。The flying vehicle according to claim 11, wherein the external duct and the corresponding rear lower wing do not overlap each other on the third axis.

如請求項1之飛行載具，另包括一座艙，其中該座艙設於該主體機身之上部。The flying vehicle as in claim 1 further includes a cabin, wherein the cabin is arranged on the upper part of the main fuselage.

如請求項13之飛行載具，另包括一座艙-機身連接件與一前方機翼，其中該前方機翼位於該主體機身之前部，以及該座艙-機身連接件連接於該座艙與該前方機翼之間。Such as the flight vehicle of claim 13, further comprising a cockpit-fuselage connector and a front wing, wherein the front wing is located at the front part of the main fuselage, and the cockpit-fuselage connector is connected between the cockpit and the fuselage. between the front wings.

如請求項14之飛行載具，其中該前方機翼之相對兩側連接該前基座與該主體機身之相對兩側，該座艙-機身連接件連接該前方機翼之相對兩側之間。The flying vehicle of claim 14, wherein the opposite sides of the front wing are connected to the front base and the opposite sides of the main fuselage, and the cockpit-fuselage connection is connected to the opposite sides of the front wing between.

如請求項14之飛行載具，其中該座艙位於該主體機身之相對兩側之間，該座艙-機身連接件連接該座艙之前端。The flight vehicle according to claim 14, wherein the cockpit is located between opposite sides of the main fuselage, and the cockpit-fuselage connecting piece is connected to the front end of the cockpit.

如請求項14之飛行載具，其中該座艙可分離地連接該主體機身。The flying vehicle according to claim 14, wherein the cockpit is detachably connected to the main fuselage.

如請求項1之飛行載具，另包括二前側小翼，其中該些前側小翼分別位於該主體機身之相對兩側並沿該第二軸延伸，該些前側小翼分別沿第二軸轉動連接對應之主體機身之相對兩側。Such as the flying vehicle of claim 1, further comprising two front side winglets, wherein the front side winglets are respectively located on opposite sides of the main fuselage and extend along the second axis, and the front side winglets are respectively along the second axis The opposite two sides of the corresponding main body fuselage are rotationally connected.

如請求項18之飛行載具，其中該些前側小翼分別沿該第二軸對齊對應之外部涵道。The flying vehicle according to claim 18, wherein the front winglets are respectively aligned with the corresponding external ducts along the second axis.

如請求項1之飛行載具，其中該外部涵道之數量係至少四，該些外部涵道其中二者分別位於該主體機身之相對兩側且靠近該主體機身之前部，以及該些外部涵道另二者分別位於該主體機身之相對兩側且靠近該主體機身之後部。The flying vehicle as in claim 1, wherein the number of the external ducts is at least four, two of the external ducts are respectively located on opposite sides of the main fuselage and close to the front of the main fuselage, and the The other two external ducts are respectively located on opposite sides of the main fuselage and close to the rear of the main fuselage.

如請求項1之飛行載具，其中各外部涵道設置該涵道風扇側壁，各外部涵道中之涵道風扇側壁沿該第一軸排列，以及各涵道風扇側壁中設置該涵道風扇增壓器。Such as the flight vehicle of claim 1, wherein each external duct is provided with the side wall of the ducted fan, the side walls of the ducted fan in each external duct are arranged along the first axis, and the side wall of each ducted fan is provided with the side wall of the ducted fan. compressor.