WO2013037178A1 - 一种新型飞机 - Google Patents

一种新型飞机 Download PDF

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Publication number
WO2013037178A1
WO2013037178A1 PCT/CN2012/000107 CN2012000107W WO2013037178A1 WO 2013037178 A1 WO2013037178 A1 WO 2013037178A1 CN 2012000107 W CN2012000107 W CN 2012000107W WO 2013037178 A1 WO2013037178 A1 WO 2013037178A1
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WO
WIPO (PCT)
Prior art keywords
wing
propeller
fuselage
horizontal
aircraft
Prior art date
Application number
PCT/CN2012/000107
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English (en)
French (fr)
Inventor
赵文志
Original Assignee
Zhao Wenzhi
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.)
Filing date
Publication date
Priority claimed from CN201110291060XA external-priority patent/CN102991668A/zh
Application filed by Zhao Wenzhi filed Critical Zhao Wenzhi
Priority to CN201280044221.8A priority Critical patent/CN104812666A/zh
Publication of WO2013037178A1 publication Critical patent/WO2013037178A1/zh

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Classifications

    • 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
    • B64C29/0033—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 tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft

Definitions

  • the present invention relates to an aerospace vehicle, including a fuselage, a wing, a propeller, a empennage, a transmission mechanism and other electronic equipment, which is substantially the same as an existing aircraft, and incorporates a new structural design to make it a flight that can be changed. State of the aircraft. Background technique
  • the aircraft has fixed wings on both sides of the fuselage, and a propeller is arranged below the wing.
  • the propeller has a fixed orientation, and the tail of the fuselage is equipped with a tail.
  • This type of aircraft requires a longer runway during take-off and landing.
  • the helicopter is subject to speed and voyage limitation; the invention is based on a utility model patent: a new type of aircraft, patent number: ZL 2007 2 0000872. 3, which is improved to become an aerospace aircraft with superior performance. Summary of the invention
  • the object of the present invention is to provide a new type of aircraft, the aerodynamic shape and the orientation of the propeller can be changed, the flight attitude, the flight mode is more flexible, the propeller can rotate 180 degrees, and can take off and land vertically, because the wing can be folded, not It occupies the ground floor area and can take off and land vertically without the runway.
  • the organic wing can achieve fast and long-range flight.
  • Embodiment 1 is a new type of aircraft, having a fuselage, a telescopic wing, a 180 degree rotating propeller, a horizontal tail fin and a vertical wing, etc.; the retractable wing is fixedly connected to the fuselage by a shaft, and Part of it is set as a joint, the faster the wing is more stable, the wing is provided with several sets of risers, which have the function of reinforcing ribs and increase the lifting force. The length of the wing is close to the front of the fuselage after being gathered.
  • the propeller can be a cylinder
  • the propeller can also be a common propeller.
  • the propeller can be controlled by a servo motor or other mechanical means to rotate 180 degrees to achieve direct ascent, air berthing, fast moving, backward, backward, suitable for speed stop, and a propeller horizontal movement adjustment mechanism.
  • a servo motor or other mechanical means to rotate 180 degrees to achieve direct ascent, air berthing, fast moving, backward, backward, suitable for speed stop, and a propeller horizontal movement adjustment mechanism.
  • horizontal tail is set to two left and right sections, the angle can be adjusted to adjust the flight state of the aircraft, and the vertical wing that can be rotated to realize the turning function, or can be set at the tail of the machine, etc.
  • Appropriate position can also be set to other forms of turning facilities;
  • the wheel can be equipped with a shock absorbing spring, the driving wheel can be set to drive like a car, easy to park, or other landing gear can be set as needed;
  • the front panel of the fuselage is set to a lower slope, It can generate lifting force when going forward; overcome the pure resistance of ordinary aircraft, and can also set ⁇ -shaped hem to increase the lifting force; all the facilities outside the fuselage are designed according to the principle of fluid mechanics;
  • the position of the wing and propeller can be as needed Adjustment, the wing and the propeller can be set in multiple groups, set up anti-collision facilities such as radar, set the alarm when the dangerous distance from the obstacle is set, and automatically avoid the facility when there is danger of collision; the other is
  • the second embodiment of the dish type aircraft has aerodynamic shape and screw-to-turn direction.
  • the flight mode is more flexible and flexible, and it is not restricted by the field. It can take off and land vertically, and can also fly at a high level. It has wide adaptability.
  • the wing of the invention is designed to be foldable, connected by hinges or other means, and the wing and the body joint are designed to be in a shape, the faster the horizontal flight speed, the stronger the wing and the fuselage are connected, and the wing is arranged
  • the current limiting thin plate can increase the lift force by about 10%, so that the setting can play the role of reinforcing ribs.
  • the wing can be made into a thin plate type, the front edge of the wing is folded, material is saved, and the setting can be omitted. The ordinary wing is used.
  • the wing is controlled by a short rod, and the short rod has a supporting function to reduce the requirement on the wing;
  • the propeller adopts a barrel propeller, and the ordinary propeller can also be placed at the center of gravity of both sides of the fuselage, and the propeller can be 180 degrees. Rotate to achieve straight rise and fall, fast horizontal flight, air berthing and retreat;
  • wing and propeller can be set to different positions according to different needs;
  • the vertical wing can also be placed at the front end or at the front and rear ends respectively; the bottom of the machine is provided with a spring wheel for parking, or can be set as a drive wheel, can be driven like a car, or can be set as a floating frame type landing gear.
  • Small wheel set to adjust the propeller in the center of gravity of the whole machine under different load conditions, in order to maintain the level of the whole machine during the landing and landing, the position of the propeller and the wing can be interchanged as needed, or Take the form of one or a set of propellers at the head and the tail; set up anti-collision facilities such as radar.
  • the top of the machine is arranged in a shape of a dome, the negative pressure is generated when flying horizontally, the front end is set to be inclined, and an adjustable angle inclined panel is arranged, and the hinge is connected to the front panel to support the rod to adjust the angle, and the inclined section is arranged at the rear of the vehicle.
  • These several settings all play the role of the wing. With the horizontal tail and vertical wing, the wing can be used to achieve direct flight with a straight-down straight-down level. When the lower-folding wing is used, the above-mentioned roof shape can also be avoided.
  • the front end is provided with a slanting panel, and the rear end slanting panel has three settings; at the same time, all the settings are better.
  • the invention can be made into small private aircraft, large transport aircraft, large passenger aircraft, military aircraft, drones, toy airplanes according to different needs.
  • it is especially suitable for carrier-based aircraft. It will launch an aircraft carrier to launch a military stage.
  • An aircraft carrier can build several carrier ships. The aircraft carrier transformation will become inevitable.
  • the invention is low in cost, safe to drive, free from site restrictions, and does not require an airport. Will replace the existing aircraft.
  • FIG. 1 is a schematic view showing the structure of a first embodiment of the present invention.
  • Figure 2 is a schematic diagram of the structural principle of the wing.
  • Figure 3 is a schematic view of the structure of the second embodiment of the present invention.
  • Figure 4 is an enlarged schematic view of the downward connection of the lower flap and the fuselage.
  • Figure 5 is a schematic view of the rod-shaped folding of the lower flap.
  • Embodiment 1 Referring to FIG. 1 and FIG. 2, the present invention is a novel aircraft having a fuselage 1, a telescopic wing 3, a propeller 2 capable of rotating 180 degrees, a horizontal tail 6, 8 and a vertical wing 7, and the like;
  • the extendable wing 3 is connected to the fuselage 1 by the shaft 5 and is fixedly disposed 18, and the other part is arranged to be coupled with the joints 4 and 13. The faster the speed, the more stable the wing 3 is, and the wing 3 is provided with several sets of risers.
  • the length of the wing 3 is aligned with the front edge of the fuselage 1, the left and right outer edges and the outer edge of the propeller 2, which is convenient for parking, close
  • the servo motor control can also be set as the tension rod control, or can be set to gather backwards, 5 and 19 are the connecting shaft holes of the wing;
  • the propeller 2 can be a barrel propeller or a common propeller
  • the propeller 2 is controlled by a servo motor or other mechanical means to control the rotation of 180 degrees to achieve straight rise and fall, air berthing, speeding, retreating, retreating suitable for speed stop, and propeller 2 horizontal movement adjustment mechanism to ensure the propeller 2 when the load changes In the center of gravity of the fuselage 1, to ensure that the whole machine is in a horizontal state when it is parked in the straight down air, it can be set to automatic adjustment or manual adjustment;
  • the horizontal tails 6, 8 are set to two left and right, angle left 6 right 8 They are respectively adjustable to adjust the flight state of
  • the invention is a new type of aircraft, the aerodynamic shape and the orientation of the propeller can be changed, the flight attitude and the flight mode are more flexible and flexible, the propeller can rotate 180 degrees, and can take off and land vertically, because the wing can be extended, and the ground use area is not occupied. It can take off and land vertically without the runway; the organic wing can achieve fast and long-range flight, safe driving, low cost and worth promoting.
  • Embodiment 2 Referring to FIG. 3, FIG. 4, FIG. 5, a new type of aircraft has a wing 22 that can be folded down, a wing 22 and a fuselage 20 Connected by means of hinges 34, etc., the contact portions are arranged in a chevron shape, a concave end 15 and a convex end 35.
  • the wing 22 is provided with a finite flow thin plate 23, and the top of the machine is designed to have a hem type 24, horizontal flight Negative pressure is generated, the front panel of the fuselage is arranged in a bevel shape, and an inclined panel 28 with an adjustable angle is additionally provided, and the hinge is coupled with the front panel to support the rod 36 to adjust the angle, 29 is a see-through window, and 30 is a meandering flange.
  • 31 is a small wheel provided with a spring 32, which can be arranged to drive the wheel like a driving, convenient parking
  • 25 is a horizontal wing and a rotatable vertical wing which can be respectively adjusted to the left and right
  • 26 is a slanting panel
  • 24, 28, 26, 25 with the front bevel can not fly the wing 22 horizontally fast
  • the wing 22 can also not 24, 28, 26
  • 33 is the window
  • 21 is a 180-degree rotating barrel propeller, can also use ordinary propeller to achieve Straight up and down, horizontal fast flight, air berthing and retreat
  • 36 is the support rod that controls the wing to expand, and has the effect of strengthening the wing.
  • the invention has low cost, safe driving, no need for an airport, and has good development potential.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

一种新型飞机，具有机身（1），可收展的机翼（3），可180度旋转的螺旋桨（2），水平尾翼（6，8）和竖翼（7）。所述可收展的机翼以轴连接于机身，另一部分设置成楔形连接，机翼设置有限流竖板，机翼的收展以伺服电机或拉伸杆控制，机身前端面设置成下斜面。所述新型飞机成本低，驾驶安全，不受场地限制。

Description

说 明 书
一种新型飞机 技术领域
本发明涉及航空飞行器， 包括机身， 机翼， 螺旋桨， 尾翼， 传动机构及其它电子设备， 与现有飞机大体相同， 在这基础上结合了新的结构设计， 使之成为一种可以改变飞行状态的 飞机。 背景技术
现有技术中， 飞机的机身两侧有固定机翼， 机翼的下方布置有螺旋桨， 螺旋桨的朝向是 固定的， 机身尾部装有尾翼， 这种飞机在起飞和降落时需较长跑道； 直升机又受速度， 航程 限制； 本发明是在实用新型专利： 一种新型飞机， 专利号： ZL 2007 2 0000872. 3的基础上 进行改进，使之成为一种性能更优越的航空飞行器。 发明内容
本发明的目的是提供一种新型飞机，其气动外形和螺旋桨的朝向都可以改变，飞行姿态， 飞行方式更加机动灵活， 螺旋桨可 180度旋转， 可垂直起降， 由于机翼可收展， 不占地面使 用面积， 可垂直起降， 不需跑道； 有机翼可实现快速远程飞行。 实现上述目的， 本发明采用 以下技术方案：
实施例一， 一种新型飞机， 具有机身， 可收展机翼， 可 180度旋转螺旋桨， 水平尾翼和 竖翼等； 所述可收展机翼以轴连接于机身固结设置， 另外一部分又设置成契型联结， 速度越 快机翼越稳， 机翼设置几组竖板， 既有加强筋的作用， 又可提高上升力， 机翼的长度以收拢 后与机身前沿平齐为准， 左右外沿与嫘旋桨的外沿为准， 可便于停放， 收展以伺服电机控制， 也可设置成拉伸杆控制， 也可设置成向后收拢； 所述螺旋桨可以是筒式螺旋桨也可以是普通 螺旋桨， 螺旋桨以伺服电机或其它机械形式控制 180度旋转， 以实现直升直降， 空中停泊， 速行， 后退， 后退适合于速停， 另外设置螺旋桨水平移动调节机构， 以确保螺旋桨在载重变 化时始终处于机身的重心位置， 保障直升直降空中停泊时整机处于水平状态， 可以设置成自 动调节也可设置成手动调节； 水平尾翼设置成左右两段， 角度左右分别可调， 以调节飞机的 飞行状态， 与可旋转以实现转弯功能的竖翼设置在一起， 也可分别设置在机首机尾等适当位 置， 也可设置成其它形式的转弯设施； 车轮可设置减震弹簧， 可设置驱动轮象车一样驾驶， 便于停放， 也可以根据需要设置其它起落架； 机身前端面板设置成下斜面， 前行时可以产生 上升力； 克服了普通飞机的纯阻力， 也可设置簸箕型折边， 以提高上升力； 机身外部所有设 施皆根据流体力学原理设计； 机翼与螺旋桨的位置可根据需要调整， 机翼与螺旋桨皆可设置 成多组的形式，设置雷达等防撞设施，设置与障碍物危险距离时示警，有撞伤危险时自动躲避 设施； 其它与普通飞机基本相同。
实施例二」 皿型飞机，其气动外形和螺^ W向都¾3¾¾¾,¾¾,_飞行方式更 加机动灵活,不受场地限制，可垂直起降，也可快速水平飞行,具有广泛的适应性.
本发明的机翼设计成可下折型，以合页或其它方式连接,机翼与机身连接部位设计成契形, 水平飞行速度越快机翼与机身联结越牢固，机翼上设置限流薄板，可提高升力 10%左右，由此设 置可起到加强筋作用，机翼可作成薄板型的,机翼前沿折边，节约材料，也可不要此设置，采用 普通机翼,机翼以短杆控制收展，短杆同时具有支撑的作用，可降低对机翼的要求；螺旋桨采用 筒式螺旋桨,普通螺旋桨也可，置于机身两侧的重心所在部位,螺旋桨可 180度旋转，以实现直 升直降，快速水平飞行，空中停泊及后退;机翼及螺旋桨根据不同需要可以设置多组于不同适 当位置;机顶尾部设置左右分别可调角度的水平翼，和可旋转的竖翼，以调整飞行状态,水平翼 说 明 书
和竖翼也可置于前端或分别置于前后端；机底设置有弹簧机轮，便于停放，也可设置成可驱动 轮,可以象车一样驾驶,也可设置成浮箱式起落架外加小车轮；设置用以调节螺旋桨在不同载 重情况下始终处于整机的重心部位的设施， 以维持整机起降停时处于水平状态， 螺旋桨和机 翼的位置可以根据需要前后互换， 也可以采取机首和机尾各设一个或一组螺旋桨的形式； 设 置雷达等防撞设施。
机顶设置成簸箕形,水平飞行时产生负压，前端设置成斜面形，另设一可调角度斜面板，以 合页连接于前面板，以支撑杆调节角度,车底后段设置斜面翼,此几项设置皆起到机翼的作用， 配合水平尾翼和竖翼，可以不要机翼实现直升直降水平快速飞行；采用下折式机翼时，也可不 要上述车顶簸箕形,前端外加斜面板，车底尾端斜面板三种设置；同时采用所有设置更好. 本发明可根据不同需要可制成小型私家飞机，大型运输机，大型客机，军用飞机，无人机， 玩具飞机等， 尤其适于舰载机,将推出航空母舰推出军事舞台，一艘航母可建造几艘载机舰, 航母变革将成为必然.本发明成本低，驾驶安全,不受场地限制,不需机场,必将取代现有飞机. 附图说明
图 1是本发明的实施例一的结构原理示意图。
图 2是机翼的结构原理示意图。
图 3是本发明的实施例二的结构原理示意图.
图 4是下折翼与机身的契形连接放大示意图.
图 5是下折翼的杆式收展示意图. 具体实施方式
实施例一： 参照图 1， 图 2， 本发明是一种新型飞机， 具有机身 1， 可收展机翼 3， 可 180 度旋转的螺旋桨 2， 水平尾翼 6， 8和竖翼 7等； 所述可收展机翼 3以轴 5连接于机身 1固结 设置 18， 另外一部分又设置成契型 4和 13联结， 速度越快机翼 3越稳， 机翼 3设置几组竖 板 12，既有加强筋的作用，又可提高上升力，机翼 3的长度以收拢后与机身 1前沿平齐为准， 左右外沿与螺旋桨 2的外沿为准， 可便于停放， 收展以伺服电机控制， 也可设置成拉伸杆控 制， 也可设置成向后收拢， 5和 19是机翼的连接轴孔； 所述螺旋桨 2可以是筒式螺旋桨也可 以是普通嫘旋桨， 嫘旋桨 2以伺服电机或其它机械形式控制 180度旋转， 以实现直升直降， 空中停泊， 速行， 后退， 后退适合于速停， 另外设置螺旋桨 2水平移动调节机构， 以确保螺 旋桨 2在载重变化时始终处于机身 1的重心位置， 保障直升直降空中停泊时整机处于水平状 态， 可以设置成自动调节也可设置成手动调节； 水平尾翼 6， 8设置成左右两段， 角度左 6右 8分别可调， 以调节飞机的飞行状态， 与可旋转以实现转弯功能的竖翼 7设置在一起， 也可 分别设置在机首机尾等适当位置； 车轮 11可设置减震弹簧 10， 可设置驱动轮象车一样驾驶， 便于停放， 也可以根据需要设置其它起落架； 机身 1前端面板设置成下斜面 16， 17， 17上设 置有下视窗， 15是设置于斜面 16上尥前视窗 前 可 生士升方， 普通飞机的 纯組力， 也可设 Ϊ簸箕型折边， 以提高上升力； 机身外部所有设施皆根据流体力学原理设计； 机翼 3与螺旋桨 2的位置可根据需要调整， 机翼 3与嫘旋桨 2皆可设置成多组的形式， 设置 雷达防撞设施； 其它与普通飞机基本相同。
本发明是一种新型飞机其气动外形和螺旋桨的朝向都可以改变， 飞行姿态， 飞行方式更 加机动灵活， 螺旋桨可 180度旋转， 可垂直起降， 由于机翼可收展， 不占地面使用面积， 可 垂直起降， 不需跑道； 有机翼可实现快速远程飞行， 驾驶安全， 成本低， 值得推广。
实施例二： 参照图 3,图 4,图 5,—种新型飞机，具有可下折的机翼 22,机翼 22与机身 20 以合页 34等方式连接,接触部位设置成契形，契形凹端 15,凸端 35,机翼 22上设置有限流薄板 23,机顶设计成有折边 24的簸箕型,水平飞行时产生负压,机身前面板设置成斜面形，另设可 调角度的斜面板 28,以合页与前面板联结，以支撑杆 36调节角度, 29是透视窗， 30是簸箕形折 边, 31是设有弹簧 32的小车轮,可设置成驱动轮象驾车一样,方便停放， 25是左右可分别调角 度的水平翼和可旋转的竖翼， 26是斜面板, 24, 28， 26, 25配合前斜面可以不要机翼 22水平快速 飞行，由机翼 22也可以不要 24， 28, 26； 33是机窗 , 21是可 180度旋转的筒式螺旋桨，也可 使用普通螺旋桨，以实现直升直降，水平快速飞行,空中停泊及后退， 36是控制机翼收展的支撑 杆， 又有加强机翼的作用.
本发明成本低，驾驶安全，不需机场,具有很好的开发潜力. 说
书

Claims

权 利 要 求 书
1. 一种新型飞机， 其特征是其气动外形和螺旋桨的朝向都可以改变， 飞行姿态， 飞行方 式更加机动灵活， 螺旋桨可 180度旋转， 可垂直起降， 由于机翼可收展， 不占地面使用面积， 可垂直起降， 不需跑道.
2.根据权利要求 1所述的一种新型飞机,其特征是所述可收展机翼以轴连接于机身固结 设置， 另外一部分又设置成契型联结， 速度越快机翼越稳， 机翼设置几组竖板， 既有加强筋 的作用， 又可提高上升力， 机翼的长度以收拢后与机身前沿平齐为准， 左右外沿与螺旋桨的 外沿为准， 可便于停放， 收展以伺服电机控制， 也可设置成拉伸杆控制， 也可设置成向后收 拢； 所述螺旋桨可以是筒式螺旋桨也可以是普通螺旋桨， 螺旋桨以伺服电机或其它机械形式 控制 180度旋转， 以实现直升直降， 空中停泊， 速行， 后退， 后退适合于速停， 另外设置螺 旋桨水平移动调节机构， 以确保螺旋桨在载重变化时始终处于机身的重心位置， 保障直升直 降空中停泊时整机处于水平状态， 可以设置成自动调节也可设置成手动调节； 水平尾翼设置 成左右两段， 角度左右分别可调， 以调节飞机的飞行状态， 与可旋转以实现转弯功能的竖翼 设置在一起， 也可分别设置在机首机尾等适当位置， 也可设置成其它形式的转弯设施； 车轮 可设置减震弹簧， 可设置驱动轮象车一样驾驶， 便于停放， 也可以根据需要设置其它起落架; 机身前端面板设置成下斜面， 前行时可以产生上升力； 克服了普通飞机的纯阻力， 也可设置 簸箕型折边， 以提高上升力； 机身外部所有设施皆根据流体力学原理设计； 机翼与螺旋桨的 位置可根据需要调整， 机翼与螺旋桨皆可设置成多组的形式， 设置雷达等防揸设施， 设置与 障碍物危险距离时示警，有撞伤危险时自动躲避设施。
3.根据权利要求 1所述的一种新型飞机,其特征是机翼设计成可下折型，以合页或其它方 式连接,机翼与机身连接部位设计成契形,水平飞行速度越快机翼与机身联结越牢固，机翼上 设置限流薄板，可提高升力 10%左右，由此设置可起到加强筋作用，机翼可作成薄板型的，机翼 前沿折边,节约材料，也可不要此设置，釆用普通机翼，机翼以短杆控制收展，短杆同时具有支 撑的作用，可降低对机翼的要求；机翼及螺旋桨根据不同需要可以设置多组于不同适当位置； 机顶尾部设置左右分别可调角度的水平翼，和可旋转的竖翼，以调整飞行状态,水平翼和竖冀 也可置于前端或分别置于前后端;机底设置有弹簧的机轮,便于停放，也可设置成可驱动轮，可 以象车一样驾驶,也可设置成浮箱式 起落架外加小车轮； 设置用以调节螺旋桨在不同载重情 况下始终处于整机的重心部位的设施， 以维持整机起降停时处于水平状态， 螺旋桨和机翼的 位置可以根据需要前后互换， 也可以采取机首和机尾各设一个或一组螺旋桨的形式； 设置雷 达等防撞设施。
4.根据权利要求 1, 3所述的一种新型飞机,其特征是机顶设置成簸箕形，水平飞行时产生 负压，前端设置成斜面形，另设一可调角度斜面板，以合页连接于前面板，以支撑杆调节角度, 车底后段设置斜面翼，此几项设置皆起到机翼的作用，配合水平尾翼和竖翼,可以不要机翼实 现直升直降水平快速飞行;采用下折式机翼时，也可不荽上述车顶簸箕形，前端外加斜面板,车 底尾端斜面板三种设置；同时采用所有设置更好.
PCT/CN2012/000107 2011-09-16 2012-01-20 一种新型飞机 WO2013037178A1 (zh)

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2196707C2 (ru) * 2001-03-21 2003-01-20 Шуликов Константин Владимирович Двухмоторный многоцелевой самолет наземного и водного базирования с укороченным и вертикальным взлетом и посадкой "ладога-9 ув"
CN200995782Y (zh) * 2007-01-17 2007-12-26 赵文志 一种新型飞机
US20110036939A1 (en) * 2009-07-31 2011-02-17 William Craig Easter Rapidly convertible hybrid aircraft and manufacturing method
DE102009060611A1 (de) * 2009-12-28 2011-06-30 Käser, Uwe, 69427 Tragflächen und Ausstattung für ein flugfähiges Straßenfahrzeug

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2196707C2 (ru) * 2001-03-21 2003-01-20 Шуликов Константин Владимирович Двухмоторный многоцелевой самолет наземного и водного базирования с укороченным и вертикальным взлетом и посадкой "ладога-9 ув"
CN200995782Y (zh) * 2007-01-17 2007-12-26 赵文志 一种新型飞机
US20110036939A1 (en) * 2009-07-31 2011-02-17 William Craig Easter Rapidly convertible hybrid aircraft and manufacturing method
DE102009060611A1 (de) * 2009-12-28 2011-06-30 Käser, Uwe, 69427 Tragflächen und Ausstattung für ein flugfähiges Straßenfahrzeug

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