WO2005058696A1 - A device capable of taking-off vertically without rotors - Google Patents

A device capable of taking-off vertically without rotors Download PDF

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Publication number
WO2005058696A1
WO2005058696A1 PCT/CN2004/000113 CN2004000113W WO2005058696A1 WO 2005058696 A1 WO2005058696 A1 WO 2005058696A1 CN 2004000113 W CN2004000113 W CN 2004000113W WO 2005058696 A1 WO2005058696 A1 WO 2005058696A1
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WIPO (PCT)
Prior art keywords
fan
wing
link
vertical lift
rotorless
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Application number
PCT/CN2004/000113
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French (fr)
Chinese (zh)
Inventor
Kaixing Gao
Zhiguo Li
Shengjun Liu
Original Assignee
Tangshan Da Tang Power Machinery Co., Ltd
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Publication date
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Publication of WO2005058696A1 publication Critical patent/WO2005058696A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage

Definitions

  • the invention relates to the technical field of an active vertical lift-off aircraft, in particular to a rotorless vertical lift-off device.
  • Object of the present invention is to provide an off vertically and overcome the drawbacks of the background art (2), a high CL: C D wing stay provided cruise lift, to overcome the drawbacks of the background art (2) In order to achieve the voyage-free vertical lift-off device.
  • the technical solution for achieving the above-mentioned object of the invention is:
  • the rotorless vertical lift-off device includes an engine, a gearbox, a fan, and other components, and it also includes wind shields at the left and right ends constituting a half-wind tunnel structure, and the fan is accommodated therein.
  • the fan blast air direction is provided with a stern wing group mechanism composed of fins, and each fin is movably installed on the left and right wind deflectors through its end shaft, and the fins are arranged from high to low along the air flow direction.
  • the sternwing group is equipped with a blade angle of attack adjustment mechanism.
  • the good aerodynamic shape formed by the upper and lower breathable "semi-wind tunnel structure" and the stern wing first generates lift, and after lift-off, it generates forward pull and thrust.
  • the formation of lift and pull depends on The angle-of-attack adjustment mechanism of the fins constituting the wing group.
  • the rotorless vertical lift-off device of the present invention is called "active vertical lift-off aircraft”.
  • the rotorless vertical lift-off device implemented in accordance with the above technical solution can only realize its value when installed on an aircraft.
  • the manufacture of a class of rotorless long-range helicopter WVH which is popularized and used, reduces the aircraft cost by a factor of two or more, reduces aircraft fuel consumption by 50% or less, reduces aircraft passenger and freight costs by 1/3 or less, and reduces aircraft failure rates. To about 1/10. So I actually used this hair
  • FIG. 1 is a schematic diagram of a connecting component / implementable structure of a lift device of the present invention.
  • the rotorless vertical lift-off device described in this embodiment is composed of an engine 1, a gearbox 2, a fan 3, a windshield 4, a fin 5, a link shaft knot 6, a posture adjustment link 7, a link hook 8, a slide Rail 9, handle 10, fixed axle wheel 11, attitude adjustment knot 12, directional knot 13, movable link 14, rectifying grid mechanism 15, engine 1-gearbox 2 behind the left and right windshields 4 (Figure The left and right panels are shown in the middle (the left and right panels are omitted) to form a half-wind tunnel structure, and the fan 3 is accommodated in the half-wind tunnel structure.
  • the fins 5 are movably mounted on the left and right windshields 4 through their end shafts.
  • the fins 5 are arranged from high to low along the airflow direction.
  • the wing group is equipped with an angle of attack adjustment mechanism of the fins 5.
  • -Each stern wing group in this embodiment is composed of 1 to 8 fins.
  • the wing angle of attack adjustment mechanism in this embodiment is a manual link mechanism.
  • the movable link 14 and the attitude adjustment link 7 of the linkage mechanism are positioned by the slide rail 9.
  • the upper end of the attitude adjustment link 7 passes through the link shaft.
  • the knot 6 is connected to the wing 5 and its lower end is connected to the movable link 14 through a link hook 8.
  • the movable link 14 forms a manual control mechanism through the directional knot 13, the posture adjusting knot 12, the fixed shaft wheel 11 and the handle 10.
  • the adjustment range of the angle of attack of the fins in this embodiment is 4 ° -15 °.
  • a rectifying grid 15 composed of upright and parallel rectifying plates is provided between the fan 3 and the wing group.
  • the rectifying grid is composed of 0 to 10 rectifying plates.
  • the fan 3-blade wing combination may be single-stage or multi-stage, and the range is 1 to 5 stages.
  • Fan 3 has a radius of 0.5 to 2.5 m and fan 3 has 2 to 30 blades.
  • the wing angle of attack adjustment mechanism described in the present invention may also be an electronic control mechanism, a servo control mechanism, or other mechanical control mechanisms.
  • the rotor-less vertical lift-off device belongs to a small aspect ratio.
  • the page is replaced (Details * 26) Force, and prevent the airflow from escaping to the left and right, and two baffles 4 are erected to accommodate the fan 3 and the stern wings, forming a "half wind tunnel" with upper and lower ventilation, each end of each small wing 5 It is sticky with dense fluff and elastically contacts the baffle 4 to form a dynamic airtightness in a "semi-wind tunnel".
  • SURE 0.42CL P oS W U 2 , system quality factor
  • the target of total takeoff weight / total engine power 6Kgf / KW can be achieved.
  • a multi-stage semi-wind tunnel structure can be used to distribute power on several fans, and lift is provided by several groups of wing.
  • a hollow shaft is used for the shaft, and nylon is used for the universal joint; a carbon fiber composite material is used for the combination of the shaft and the wing; and the fan blade is also made of a carbon fiber composite material.
  • the angle of attack ⁇ of each winglet 5 is 15 ° ⁇ Adjust within a range of 4 °.
  • the angle of attack ⁇ of each small fin 5 is 4 °, and the system resistance is minimal at this time to achieve high-speed cruising. Because each small wing 5 is staggered up and down, it can make This is a new set of lift. Thrust combination, high quality, can achieve vertical take-off and landing at zero speed, and can also achieve a range of R 1600 km.
  • the rotorless vertical lift-off device implemented in accordance with the above technical solution can only realize its value when installed on an aircraft.
  • the manufacture of a class of rotorless long-range helicopter WVH which is popularized and used, can reduce the cost of flying aircraft by 100% or more, reduce aircraft fuel consumption by 50% or less, reduce passenger and freight costs to 1/3 or less, and reduce aircraft failure.

Abstract

The invention provides an aircraft capable of taking-off vertically, in particular a device of taking-off vertically without rotors. Besides an engine, a gearbox, a fan, the device also includes two boards set in the left and right sides for wind blocking, which form a kind of structure like a half wind tunnel. The fan is contained therein. The multiple flaps group is set along the direction of flow. Each flap is rotatablely mounted on the wind-blocking boards and is arranged from higher to lower along the direction of airflow. The flaps group is equipped with the attack angle adjustment mechanism. The special feature of the arrangement of flaps could attain CL/CD≈20±5 and higher. Accordingly the device according to the invention is a novel combination of the lift and the drag, and is able to perform landing and taking-off vertically under zero cruising speed and attains the cruising distance R≥1600km.

Description

无旋翼垂直升空装置  Rotorless vertical lift
技术领域  Technical field
本发明涉及主动型垂直升空飞行器技术领域， 特别是一种无旋翼垂 直升空装置。  The invention relates to the technical field of an active vertical lift-off aircraft, in particular to a rotorless vertical lift-off device.
背景技术 Background technique
现代直升机存在的弊端： （1 ) 在巡航中， 旋翼倾斜向前， 既提 供升力， 又提供前进的拉力， 由于旋翼品质因数太低， 能量损耗太 大， 因而直升机航程苦短， 致使在浩瀚的大海中、 大漠中、 草原中 ' 无力执行任务， 更无力越洋飞行。 （2 ) 旋翼裸暴飞转， 不能在复杂 的地物中穿行， 执行救援、 消防、 缉捕。 发明的公开  Disadvantages of modern helicopters: (1) During cruise, the rotor tilts forward, providing both lift and forward pulling force. Because the rotor quality factor is too low and the energy loss is too large, the helicopter has a short flight range. In the sea, in the desert, in the steppe ', we are unable to perform missions, and even more unable to fly across the ocean. (2) Rotors fly barely and cannot travel through complicated grounds, and perform rescue, fire fighting and arrest. Disclosure of invention
本发明的目的旨在提供一种可垂直升空并克服背景技术中所述弊 端 （2)， 以高 CL : CD的呆翼提供巡航中的升力， 克服背景技术中所述 弊端 （2)， 以实现远航的无旋翼垂直升空装置。 Object of the present invention is to provide an off vertically and overcome the drawbacks of the background art (2), a high CL: C D wing stay provided cruise lift, to overcome the drawbacks of the background art (2) In order to achieve the voyage-free vertical lift-off device.
实现上述发明目的的技术方案是： 该无旋翼垂直升空装置包括发动 机、 变速箱、 风扇等部件外， 它还包括构成半风洞结构的左右两端挡风 板， 所述风扇容入其内， 风扇鼓出的气流方向设置有由翼片组成的衿翼 群机构， 每个翼片均通过其端轴活动安装在左右两端挡风板上， 各翼片 沿气流方向由高向低排列， 衿翼群配置有翼片迎角调节机构。 在外部人 为风源的作用下， 上、 下透气的 "半风洞结构"和衿翼形成的良好气动 外形首先产生升力， 升空后再产生向前的拉力和推力， 升力和拉力的形 成靠组成衿翼群的翼片的迎角调节机构。 由此使本发明无旋翼垂直升空 装置被称为 "主动型垂直升空飞行器"。  The technical solution for achieving the above-mentioned object of the invention is: The rotorless vertical lift-off device includes an engine, a gearbox, a fan, and other components, and it also includes wind shields at the left and right ends constituting a half-wind tunnel structure, and the fan is accommodated therein. The fan blast air direction is provided with a stern wing group mechanism composed of fins, and each fin is movably installed on the left and right wind deflectors through its end shaft, and the fins are arranged from high to low along the air flow direction. The sternwing group is equipped with a blade angle of attack adjustment mechanism. Under the action of an external artificial wind source, the good aerodynamic shape formed by the upper and lower breathable "semi-wind tunnel structure" and the stern wing first generates lift, and after lift-off, it generates forward pull and thrust. The formation of lift and pull depends on The angle-of-attack adjustment mechanism of the fins constituting the wing group. As a result, the rotorless vertical lift-off device of the present invention is called "active vertical lift-off aircraft".
依照上述技术方案实施的无旋翼垂直升空装置， 设置于飞机上才能 体现其价值。 如制造一类无旋翼远程直升机 WVH， 推广使用， 飞机造 价降低一倍乃至更多， 飞机燃料消耗降少 50%甚至更少， 飞机客货运成 本降至 1/3或更低， 飞机故障率降至 1/10左右。故而实际上釆用了本发  The rotorless vertical lift-off device implemented in accordance with the above technical solution can only realize its value when installed on an aircraft. For example, the manufacture of a class of rotorless long-range helicopter WVH, which is popularized and used, reduces the aircraft cost by a factor of two or more, reduces aircraft fuel consumption by 50% or less, reduces aircraft passenger and freight costs by 1/3 or less, and reduces aircraft failure rates. To about 1/10. So I actually used this hair
替换页（细則第 26条） 明技术的飞机， 其性能优异， 用途广泛。 Replacement page (Article 26) Ming-tech aircraft has excellent performance and a wide range of uses.
附图的简要说明 Brief description of the drawings
图 1为本发明升力装置连接部件 /可实施性结构示意图。  FIG. 1 is a schematic diagram of a connecting component / implementable structure of a lift device of the present invention.
实现本发明的最佳方式 Best way to implement the invention
以下结合附图给出本发明的一个具体实施例。该实施例所述的无旋 翼垂直升空装置由发动机 1、 变速箱 2、 风扇 3、 挡风板 4、 翼片 5、 连 杆轴结 6、 调姿连杆 7、 连杆挂钩 8、 滑轨 9、 手柄 10、 固定轴轮 11、 调姿活结 12、 整向活结 13、 活动连杆 14、整流栅机构 15组成， 发动机 1--变速箱 2后面以左右两端挡风板 4 (图中显示左板， 右板略） 构成半 风洞结构， 风扇 3容入该半风洞结构之中， 风扇 3鼓出的气流方向设置 有由翼片 5组成的衿翼群机构， 每个翼片 5均通过其端轴活动安装在左 右两端挡风板 4上， 各翼片 5沿气流方向由高向低排列， 衿翼群配置有 翼片 5的迎角调节机构。 - 本实施例中的每个衿翼群由 1〜8片翼片组成。  A specific embodiment of the present invention is given below with reference to the drawings. The rotorless vertical lift-off device described in this embodiment is composed of an engine 1, a gearbox 2, a fan 3, a windshield 4, a fin 5, a link shaft knot 6, a posture adjustment link 7, a link hook 8, a slide Rail 9, handle 10, fixed axle wheel 11, attitude adjustment knot 12, directional knot 13, movable link 14, rectifying grid mechanism 15, engine 1-gearbox 2 behind the left and right windshields 4 (Figure The left and right panels are shown in the middle (the left and right panels are omitted) to form a half-wind tunnel structure, and the fan 3 is accommodated in the half-wind tunnel structure. The fins 5 are movably mounted on the left and right windshields 4 through their end shafts. The fins 5 are arranged from high to low along the airflow direction. The wing group is equipped with an angle of attack adjustment mechanism of the fins 5. -Each stern wing group in this embodiment is composed of 1 to 8 fins.
本实施例中的翼片迎角调节机构为手动连杆机构， 该连杆机构的活 动连杆 14和调姿连杆 7由滑轨 9定位， 该调姿连杆 7其上端通过连杆 轴结 6与翼片 5连接， 其下端通过连杆挂钩 8与活动连杆 14连接， 该 活动连杆 14通过整向活结 13、 调姿活结 12、 固定轴轮 11与手柄 10构 成手动控制机构。  The wing angle of attack adjustment mechanism in this embodiment is a manual link mechanism. The movable link 14 and the attitude adjustment link 7 of the linkage mechanism are positioned by the slide rail 9. The upper end of the attitude adjustment link 7 passes through the link shaft. The knot 6 is connected to the wing 5 and its lower end is connected to the movable link 14 through a link hook 8. The movable link 14 forms a manual control mechanism through the directional knot 13, the posture adjusting knot 12, the fixed shaft wheel 11 and the handle 10.
本实施例中的翼片迎角调节范围为 4° -15° 。  The adjustment range of the angle of attack of the fins in this embodiment is 4 ° -15 °.
本实施例中风扇 3与衿翼群之间设置有由直立平行的整流板组成的 整流栅 15， 该整流栅由 0~10片整流板组成。  In this embodiment, a rectifying grid 15 composed of upright and parallel rectifying plates is provided between the fan 3 and the wing group. The rectifying grid is composed of 0 to 10 rectifying plates.
本实施例中风扇 3-衿翼组合可以是单级， 也可以是多级， 范围 1~5 级。 风扇 3半径为 0.5〜2.5m， 风扇 3叶片为 2〜30片。  In this embodiment, the fan 3-blade wing combination may be single-stage or multi-stage, and the range is 1 to 5 stages. Fan 3 has a radius of 0.5 to 2.5 m and fan 3 has 2 to 30 blades.
本发明中所述的翼片迎角调节机构还可以是电子控制机构、伺服控 制机构或其它方式的机械控制机构。  The wing angle of attack adjustment mechanism described in the present invention may also be an electronic control mechanism, a servo control mechanism, or other mechanical control mechanisms.
以下简述本发明的设计原理：  The following briefly describes the design principles of the present invention:
本发明所述的无旋翼垂直升空装置属小展弦比者， 为了降低诱导阻 替换页（细則 *26条） 力， 并防止气流向左右两侧逃逸， 而竖起两挡板 4， 将风扇 3、 衿翼容 入其内， 构成上、 下透气的 "半风洞"， 每片小翼片 5两端粘以致密绒 毛， 与挡板 4弹性接触形成动态气密于 "半风洞 "中， 翼前气流动能为
Figure imgf000005_0001
* 1/2 P QSWU2， 衿翼中会消耗 一部分动能， 气流离开速度会有所降低， 大约
Figure imgf000005_0002
所以作用 在衿翼上的气流有效值约为 UEI=0.918U， 实际升力值为 FL.SURE=0.42CL P oSWU2, 系统品质因数
Figure imgf000005_0003
The rotor-less vertical lift-off device according to the present invention belongs to a small aspect ratio. In order to reduce the induced resistance, the page is replaced (Details * 26) Force, and prevent the airflow from escaping to the left and right, and two baffles 4 are erected to accommodate the fan 3 and the stern wings, forming a "half wind tunnel" with upper and lower ventilation, each end of each small wing 5 It is sticky with dense fluff and elastically contacts the baffle 4 to form a dynamic airtightness in a "semi-wind tunnel". The forward air flow energy of the wing is
Figure imgf000005_0001
* 1/2 P QS W U 2 , a part of kinetic energy is consumed in the stern wing, and the airflow exit speed will be reduced, about
Figure imgf000005_0002
Therefore, the effective value of the airflow acting on the stern wing is about U EI = 0.918U, and the actual lift value is FL. SURE = 0.42CL P oS W U 2 , system quality factor
Figure imgf000005_0003
适当选择 (^、 SW、 U等主要参数， 就可以实现起飞总重量 /发 动机总功率 6Kgf/KW之标的。 By properly selecting the main parameters (^, S W , U, etc.), the target of total takeoff weight / total engine power 6Kgf / KW can be achieved.
可见， 提高 Sw/ #或降低 U， 则可提高 Qo， 于是可用多级半风洞结 构， 将功率分布在几个风扇上， 升力由几组衿翼提供。 此系统中， 轴采 用空心轴， 万向结用尼龙； 轴和衿翼组合用碳纤维复合材料； 扇叶也采 用碳纤维复合材料。 It can be seen that increasing S w / # or lowering U can increase Qo. Therefore, a multi-stage semi-wind tunnel structure can be used to distribute power on several fans, and lift is provided by several groups of wing. In this system, a hollow shaft is used for the shaft, and nylon is used for the universal joint; a carbon fiber composite material is used for the combination of the shaft and the wing; and the fan blade is also made of a carbon fiber composite material.
实际飞行： （1 ) 垂直升空阶段——风扇 3提供风源， 衿翼 CL 16， 起飞时， 将手柄 10推至前位， 组成衿翼的各个小翼片 5下摆迎角调到 α =15\ 此时在气流作用下， 衿翼升力系数最大， 在发动机 1额定转速 下， 获得最大升力 /动力率， 大约 6〜15 kg f/KW, 实现垂直起飞； （2 ) 巡航平飞状态——随着飞机在水平方向加速，逐渐操纵衿翼组的每个小 翼片 5使之逐渐向水平方向趋近， 根据飞行速度的需要， 各个小翼片 5 的迎角 α在 15°〜4°范围内调整， 当手柄 10拉至最后位时， 各小翼片 5 迎角 α =4°， 此时系统阻力最小， 以实现高速巡航。 由于各个小翼片 5 上下、 前后错落有致， 可使
Figure imgf000005_0004
， 乃 更高， 这是一套新颖的 升力.推力组合，品质优高，能实现零航速的垂直起降,也能实现航程 R 1600 km。 Actual flight: (1) vertical launch Stage - 3 to provide air supply fan, wing Gum C L 16, take-off, the handle 10 is pushed to the front position, the respective small wing Gum composition flaps 5 hem adjusted angle of attack α = 15 \ At this time, the lift coefficient of the stern wing is the largest under the action of airflow, and the maximum lift / power ratio is obtained at the rated speed of engine 1, about 6 ~ 15 kg f / KW, to achieve vertical take-off; (2) cruise level flight ——As the aircraft accelerates in the horizontal direction, each winglet 5 of the wing group is gradually controlled to gradually approach the horizontal direction. According to the needs of the flying speed, the angle of attack α of each winglet 5 is 15 ° ~ Adjust within a range of 4 °. When the handle 10 is pulled to the final position, the angle of attack α of each small fin 5 is 4 °, and the system resistance is minimal at this time to achieve high-speed cruising. Because each small wing 5 is staggered up and down, it can make
Figure imgf000005_0004
This is a new set of lift. Thrust combination, high quality, can achieve vertical take-off and landing at zero speed, and can also achieve a range of R 1600 km.
工业应用' I"生 Industrial applications
依照上述技术方案实施的无旋翼垂直升空装置， 设置于飞机上才能 体现其价值。 如制造一类无旋翼远程直升机 WVH， 推广使用， 飞^ L造 价降低一倍乃至更多， 飞机燃料消耗降少 50%甚至更少， 飞机客货运成 本降至 1/3或更低， 飞机故障率降至 1/10左右。故而实际上采用了本发 明技术的飞机， 其性能优异， 用途广泛。  The rotorless vertical lift-off device implemented in accordance with the above technical solution can only realize its value when installed on an aircraft. For example, the manufacture of a class of rotorless long-range helicopter WVH, which is popularized and used, can reduce the cost of flying aircraft by 100% or more, reduce aircraft fuel consumption by 50% or less, reduce passenger and freight costs to 1/3 or less, and reduce aircraft failure. The rate dropped to about 1/10. Therefore, in fact, an aircraft using the technology of the present invention has excellent performance and a wide range of uses.
'更正页 (细则第 91条) 'Correction page (Article 91)

Claims

权利 要 求 Rights request
1、 一种无旋翼垂直升空装置， 包括发动机、 变速箱、 风扇， 其特征 在于它还包括构成半风洞结构的左右两端挡风板， 所述风扇容入 其内， 风扇鼓出的气流方向设置有由翼片组成的衿翼群机构， 每 个翼片均通过其端轴活动安装在左右两端挡风板上， 各翼片沿气 流方向由高向低排列， 衿翼群配置有翼片迎角调节机构。 1. A rotorless vertical lift-off device, including an engine, a gearbox, and a fan, characterized in that it further includes left and right wind deflectors forming a semi-wind tunnel structure, the fan is accommodated therein, and the fan swells out. The airfoil direction is provided with a sacral wing group mechanism composed of fins, and each wing is movably installed on the left and right windshields through its end shafts. Each wing is arranged from high to low along the airflow direction, and the sacral wing group is configured. With wing angle of attack adjustment mechanism.
2、 根据权利要求 1 所述的无旋翼垂直升空装置， 其特征在于每个衿 翼群由 1〜8片翼片组成。 2. The non-rotor-less vertical lift-off device according to claim 1, characterized in that each salamander wing group is composed of 1 to 8 fins.
3、 根据权利要求 1 所述的无旋翼垂直升空装置， 其特征在于该翼片 迎角调节机构为手动连杆机构， 该连杆机构的活动连杆和调姿连 杆由滑轨定位， 该调姿连杆其上端通过连杆轴结与翼片连接， 其 下端通过连杆挂钩与活动连杆连接， 该活动连杆通过整向活结、 调姿活结、 固定轴轮与手柄构成手动控制机构。 3. The rotorless vertical lift-off device according to claim 1, wherein the blade angle-of-attack adjustment mechanism is a manual link mechanism, and the movable link and the attitude adjustment link of the link mechanism are positioned by slide rails, The upper end of the posture adjusting link is connected to the flap through a link shaft knot, and the lower end is connected to a movable link through a link hook. The movable link is manually controlled by a directional knot, a posture adjusting knot, a fixed shaft wheel and a handle. mechanism.
4、 根据权利要求 1 或 3所述的无旋翼垂直升空装置， 其特征在于翼 片迎角调节范围 4'〜15° 。 4. The rotor-less vertical lift-off device according to claim 1 or 3, characterized in that the adjustment range of the angle of attack of the blades is 4 '~ 15 °.
5、 根据权利要求 1 所述的无旋翼垂直升空装置， 其特征在于风扇与 衿翼群之间设置有由直立平行的整流板组成的整流栅。  5. The rotorless vertical lift-off device according to claim 1, wherein a rectifying grid composed of vertical and parallel rectifying plates is provided between the fan and the sternwing group.
6、 根据权利要求 1 或 5所述的无旋翼垂直升空装置， 其特征在于整 流栅由 0~10片整流板组成。 6. The rotorless vertical lift-off device according to claim 1 or 5, characterized in that the rectification grid is composed of 0 to 10 rectifier plates.
7、 根据权利要求 1所述的无旋翼垂直升空装置， 其特征在于风扇-衿 翼组合可以是单级， 也可以是多级， 范围 1〜5级。 7. The rotorless vertical lift-off device according to claim 1, characterized in that the fan-pull wing combination can be a single stage or a multi-stage, ranging from 1 to 5 stages.
8、 根据权利要求 1 所述的无旋翼垂直升空装置， 其特征在于风扇半径 为 0.5〜2.5m， 风扇叶片为 2~30片。 替换页（细则第 26条） 8. The rotorless vertical lift-off device according to claim 1, wherein the fan radius is 0.5 to 2.5 m, and the fan blades are 2 to 30 pieces. Replacement page (Article 26)
PCT/CN2004/000113 2003-12-18 2004-02-11 A device capable of taking-off vertically without rotors WO2005058696A1 (en)

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CN105947176A (en) * 2016-04-08 2016-09-21 梁平 Composite wing

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CN103754372B (en) * 2013-10-01 2015-09-09 魏伯卿 Vertical takeoff and landing can stop the aircraft with inverted flight in the air
CN107089321A (en) * 2017-04-26 2017-08-25 浙江点辰航空科技有限公司 A kind of pusher multi-rotor unmanned aerial vehicle of adjustable lift vector

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WO1988005011A1 (en) * 1987-01-03 1988-07-14 Christian Taramasco Vertical take-off and landing aircraft
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DE2657714A1 (en) * 1976-12-20 1978-06-22 Reinhard Oster Aircraft wing with cascade configuration - has horizontal aerofoil section blades mounted in frame with wing section top and bottom members
WO1988005011A1 (en) * 1987-01-03 1988-07-14 Christian Taramasco Vertical take-off and landing aircraft
US6446908B1 (en) * 1999-08-12 2002-09-10 Manuel Munoz Saiz Aircraft lift arrangement
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CN105947176A (en) * 2016-04-08 2016-09-21 梁平 Composite wing

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