WO2021017750A1 - 一种机身左右装有一对半圆锥形风袋的防坠落飞机 - Google Patents

一种机身左右装有一对半圆锥形风袋的防坠落飞机 Download PDF

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WO2021017750A1
WO2021017750A1 PCT/CN2020/100063 CN2020100063W WO2021017750A1 WO 2021017750 A1 WO2021017750 A1 WO 2021017750A1 CN 2020100063 W CN2020100063 W CN 2020100063W WO 2021017750 A1 WO2021017750 A1 WO 2021017750A1
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fixed
umbrella cloth
aircraft
rod
semi
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PCT/CN2020/100063
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English (en)
French (fr)
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吴永高
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吴永高
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Application filed by 吴永高 filed Critical 吴永高
Priority to JP2021600034U priority Critical patent/JP3238261U/ja
Publication of WO2021017750A1 publication Critical patent/WO2021017750A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/028—Hang-glider-type aircraft; Microlight-type aircraft

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  • the embodiments of the present application relate to the technical field of aircraft, in particular to an anti-fall aircraft with a pair of semi-conical wind pockets on the left and right sides of the fuselage.
  • the embodiment of the present application provides a fall prevention aircraft with a pair of semi-conical wind pockets on the left and right sides of the fuselage, so as to solve the problem of insufficient forward power of the existing aircraft in the prior art and easy to fall.
  • a fall protection aircraft with a pair of semi-conical wind sock on the left and right sides of the fuselage includes a body, a landing gear is arranged at the lower part of the body, and a tail is arranged at the tail of the body, and also includes a column and a support The frame, the first umbrella cloth, the second umbrella cloth, the power unit and the propeller.
  • the column is vertically fixed in the middle of the machine body.
  • the support frame is fixed on the column at one end away from the machine body.
  • the plane of the support frame is inclined to the horizontal plane.
  • the front end of the support frame is away from the machine body.
  • the distance between the support frame is greater than the distance between the rear end of the support frame and the body.
  • the support frame is a trapezoidal frame with a front edge smaller than a rear edge.
  • the first umbrella cloth and the second umbrella cloth are both trapezoidal.
  • the two non-parallel edges of the first umbrella cloth and the second are fixed on the support frame, the power device is fixed on the rear end of the middle of the body, and the propeller is fixed on the rotating shaft of the power device.
  • the supporting frame includes a center rod, a first cross rod, a second cross rod, a first side rod and a second side rod;
  • the center rod is obliquely fixed on the end of the column far away from the body, and the distance between the front end of the center rod and the body is greater than the center
  • the distance between the rear end of the rod and the body, the first cross rod is vertically fixed at the front end of the center rod, the second cross rod is vertically fixed at the middle rear end of the center rod, the first cross rod and the second cross rod are located in the same horizontal plane.
  • the crossbar and the second crossbar are symmetrical about the center rod.
  • the length of the first crossbar is less than the length of the second crossbar.
  • the first side rod and the second side rod are respectively arranged on both sides of the center rod.
  • One end of the first side bar is fixed to one end of the first cross bar
  • the middle of the first side bar is fixed to one end of the second side bar
  • one end of the second side bar is fixed to the other end of the first cross bar
  • the middle of the second side bar is fixed to At the other end of the second crossbar, the two non-parallel edges of the first umbrella cloth are respectively fixed on the center rod and the first side rod
  • the two non-parallel edges of the second umbrella cloth are respectively fixed on the center rod and the second side rod on.
  • first umbrella cloth and the second umbrella cloth have the same shape, the front end trapezoidal edge of the first umbrella cloth is longer than half the length of the first crossbar, and the front end trapezoidal edge of the second umbrella cloth is larger than the first crossbar. One half of the length.
  • stiffener plate also includes a stiffener plate.
  • Two stiffener plates are arranged at the connection between the column and the center rod. The two stiffener plates are located in the same plane and are respectively located on the front and rear sides of the column.
  • the power plant is an internal combustion engine or an electric motor.
  • the landing gear includes a front landing bracket and two rear landing brackets, one front landing bracket is fixed at the front end of the bottom of the body, two rear landing brackets are fixed at the middle of the bottom of the body, one front landing bracket and two rear landing brackets Distributed in a triangle.
  • both the first umbrella cloth and the second umbrella cloth are made of opaque nylon silk.
  • the length of the upright post is equal to the length between the front end of the body and the rear end of the tail wing.
  • first draw ropes one first draw rope is fixed at both ends of the first cross bar, and the ends of the two first draw ropes away from the first cross rod are both fixed on the body.
  • it also includes two second pull ropes, two second pull ropes are respectively fixed at both ends of the second cross bar, and the ends of the two second pull ropes away from the second cross bar are both fixed on the body.
  • This application has the following advantages: Through this application, the phenomenon of losing balance caused by the left and right skew of the wings of the aircraft is avoided.
  • the first umbrella cloth and the second umbrella cloth are two protruding upwards under the action of wind.
  • a conical surface prevents the aircraft from falling when it loses power.
  • the power unit is arranged behind the cockpit to reduce vibration.
  • the first and second umbrella cloths of the aircraft in this application are both trapezoidal, which greatly improves the air collection. It has high air buoyancy, stable flight and high safety, effectively avoiding the casualties of the manned aircraft or the damage of the valuable equipment of the drone caused by the accidental fall.
  • Figure 1 is a front view of a fall-prevention aircraft with a pair of semi-conical wind pockets on the left and right sides of the fuselage provided by some embodiments of the application.
  • Fig. 2 is a top view of the anti-fall aircraft provided in Fig. 1 with a pair of semi-conical wind pockets on the left and right sides of the fuselage.
  • Fig. 3 is a right side view of the anti-fall aircraft provided in Fig. 1 with a pair of semi-conical wind pockets on the left and right sides of the fuselage.
  • Fig. 4 is a front view of a fall-prevention aircraft with a pair of semi-conical wind pockets on the left and right sides of the fuselage provided by other embodiments of the application.
  • Fig. 5 is a right side view of the anti-fall aircraft provided in Fig. 4 with a pair of semi-conical wind pockets on the left and right sides of the fuselage.
  • a fall prevention aircraft with a pair of semi-conical wind sock on the left and right sides of the fuselage in this embodiment includes a body 1, and a landing gear is arranged on the lower part of the body 1.
  • the tail is provided with a tail wing 13, which also includes a column 2, a supporting frame, a first umbrella cloth 9, a second umbrella cloth 8, a power unit 14 and a propeller 15.
  • the column 2 is made of rectangular steel pipe or round steel pipe, and the column 2 is vertically fixed on In the middle of the body 1, the support frame is fixed on the column 2 at one end away from the body 1.
  • the plane of the support frame is inclined to the horizontal plane.
  • the distance between the front end of the support frame and the body 1 is greater than the distance between the rear end of the support frame and the body 1, and the support frame is the front end A trapezoidal frame with an edge smaller than the rear edge, the first umbrella cloth 9 and the second umbrella cloth 8 are both trapezoidal, the two non-parallel edges of the first umbrella cloth 9 and the two non-parallel edges of the second umbrella cloth 8 are fixed on the support
  • the front end edges of the first umbrella cloth 9 and the second umbrella cloth 8 are perpendicular to the length direction of the body 1, and the front ends of the first umbrella cloth 9 and the second umbrella cloth 8 are both air inlets
  • the first umbrella cloth 9 and The rear edges of the second parachute cloth 8 are all air outlets
  • the power unit 14 is fixed at the rear end of the middle of the body 1
  • the propeller 15 is fixed on the shaft of the power unit 14.
  • the first parachute cloth 9 and the second parachute cloth 8. A semi-conical wind sock under the action of wind.
  • the upper supporting frame is a cone-shaped wind sock skeleton.
  • the tail has a horizontal tail and a vertical tail.
  • the cone-shaped wind sock frame is composed of 5 alloy aluminum tubes.
  • the length of the rod 3, the first side rod 6 and the second side rod 7 are equal.
  • the front cross tube is the first cross rod 4, and the rear cross tube is the second cross rod 5.
  • a crossbar 4 is twice as long, and a total of 5 aluminum alloy tubes form the skeleton of the left and right conical wind sock.
  • the left and right ends of the front cross tube of the first crossbar 4 have two steel cables of equal length connected to the left and right sides of the nose. Ensure that the front cross tube is level.
  • the second cross bar 5 that is, the rear cross tube
  • the second cross bar 5 has two steel cables of equal length fixed on both sides of the fuselage. Ensure that the rear cross tube is level. Do not install an engine or electric motor on the column 2 to avoid Vibration, the engine and the motor can be installed on the short engine seat immediately behind the column 2.
  • the propeller 15 is installed on the engine or the motor; the landing gear is three-point rear, one wheel in the front, two wheels in the back, sliding Used for running, take-off and landing; the left and right half-cone wind pockets are made of air-tight satin cotton silk for parachutes.
  • the first umbrella cloth 9 and the second umbrella cloth 8 form two wind sock symmetrical about the vertical plane where the column 2 is under the action of wind, and the lower part of the wind sock is a small front end and a large rear end.
  • the tapered surface improves the strong buoyancy support for the flight of the aircraft.
  • the technical effect achieved by this embodiment is: through this embodiment, the phenomenon of loss of balance caused by the left and right skew of the wings of the aircraft is avoided.
  • the first umbrella cloth 9 and the second umbrella cloth 8 are under the action of wind Two tapered curved surfaces protruding upwards avoid the aircraft falling after losing power.
  • the power unit 14 is arranged behind the cockpit to reduce vibration.
  • the aircraft first parachute cloth 9 and second parachute cloth 8 of this embodiment All are set in a trapezoid shape, which greatly improves the ability to collect air, has a large air buoyancy, stable flight, high safety, and effectively avoids casualties of manned aircraft or damage to valuable equipment of drones caused by accidental fall.
  • a fall-prevention aircraft with a pair of semi-conical wind pockets on the left and right sides of the fuselage in this embodiment includes all the technical features in embodiment 1, in addition,
  • the supporting frame includes a center rod 3, a first cross rod 4, a second cross rod 5, a first side rod 6 and a second side rod 7; for example, the center rod 3, the first cross rod 4, the second cross rod 5, the first
  • the side rods 6 and the second side rods 7 are both round pipes or rectangular steel pipes, which are welded to each other to form a support frame.
  • the center rod 3 is obliquely fixed on the end of the column 2 away from the body 1, and the distance between the front end of the center rod 3 and the body 1 is greater than
  • the distance between the rear end of the center rod 3 and the body 1 preferably, the included angle between the center rod 3 and the horizontal plane is between 16° and 24°
  • the first cross rod 4 is vertically fixed at the front end of the center rod 3
  • the second The cross bar 5 is vertically fixed to the rear end of the center bar 3, the first cross bar 4 and the second cross bar 5 are located in the same horizontal plane, the first cross bar 4 and the second cross bar 5 are symmetrical about the center bar 3, respectively.
  • the length of a cross bar 4 is less than the length of the second cross bar 5.
  • the first side bar 6 and the second side bar 7 are respectively arranged on both sides of the center bar 3, and one end of the first side bar 6 is fixed to the first cross bar 4
  • One end of the first side bar 6 is fixed to one end of the second cross bar 5
  • one end of the second side bar 7 is fixed to the other end of the first cross bar 4
  • the middle of the second side bar 7 is fixed to the second cross bar.
  • the other end of the rod 5, wherein the first cross rod 4, the center rod 3, the second cross rod 5 and the first side rod 6 are enclosed into a right-angled trapezoid
  • the second side rod 7 also forms a right-angled trapezoid.
  • the right angles of the two right-angled trapezoids are adjacent.
  • the two non-parallel edges of the first umbrella cloth 9 are respectively fixed on the central rod 3 and the first side rod 6.
  • the second umbrella cloth The two non-parallel edges of 8 are respectively fixed on the center rod 3 and the second side rod 7; the shape of the first umbrella cloth 9 and the second umbrella cloth 8 are the same, and the front end trapezoidal edge of the first umbrella cloth 9 is longer than the first horizontal One-half the length of the rod 4, and the trapezoidal edge of the front end of the second umbrella cloth 8 is greater than one-half the length of the first cross-bar 4; it also includes a stiffener plate 12, and the connection between the column 2 and the center rod 3 is provided with two There are two stiffener plates 12, and the two stiffener plates 12 are located in the same plane and are respectively located on the front and rear sides of the column 2.
  • the beneficial effects in this embodiment are: by setting the support frame as a structure in which a plurality of rods are connected, the gravity of the support frame is reduced, and the flight stability is improved.
  • the front end edge of the first umbrella cloth 9 is set to be greater than one-half the length of the first crossbar 4 and the front edge of the second umbrella cloth 8 is set to be greater than one-half the length of the first crossbar 4, so that the first umbrella cloth 9 and the Both umbrella cloths 8 can form an upwardly protruding cone-shaped wind sock under the action of wind, which enhances the supporting force for the flight of the aircraft and avoids the occurrence of aircraft falling when the power unit 14 is insufficient;
  • the rib 12 enhances the connection strength between the column 2 and the center rod 3.
  • a fall-preventing aircraft with a pair of semi-conical wind pockets on the left and right sides of the fuselage in this embodiment includes all the technical features in embodiment 2.
  • the power unit 14 is an internal combustion engine or an electric motor.
  • a battery that provides electrical energy for the motor is also provided in the body 1 of the aircraft;
  • the landing gear includes a front landing support 10 and two rear landing supports 11, the front landing support 10 and the rear landing bracket 11 are both structures with rollers fixed at the end of the connecting rod.
  • a front landing bracket 10 is fixed at the front end of the bottom of the body 1, two rear landing brackets 11 are fixed at the middle of the bottom of the body 1, and one front landing bracket 10 And two rear landing supports 11 are distributed in a triangle; the first umbrella cloth 9 and the second umbrella cloth 8 are made of opaque nylon silk; the length of the column 2 is equal to the length between the front end of the body 1 and the rear end of the tail wing 13 .
  • the beneficial effects of this embodiment are: by setting the power unit 14 as an internal combustion engine or an electric motor, the power options are increased, by setting the rear triangular undercarriage with the rear end larger than the front end, the structure is stable, and the first umbrella cloth 9 and the second umbrella cloth 8 are made of opaque cotton fabric, which reduces the impact of light transmittance on the aircraft. At the same time, the material has a strong bearing capacity. By setting the length of the column 2 to the length of the body 1 from the front The same way to the rear end of the tail wing 13 reduces the manufacturing difficulty.
  • the fall protection aircraft with a pair of semi-conical wind pockets on the left and right sides of the fuselage in this embodiment includes all the technical features in embodiment 3, in addition to two Two first draw ropes 16, a first draw rope 16 is fixed at both ends of the first cross bar 4, and the ends of the two first draw ropes 16 far away from the first cross rod 4 are both fixed on the body 1; Two second drawstrings 17, two second drawstrings 17 are respectively fixed at both ends of the second crossbar 5, and the ends of the two second drawstrings 17 far away from the second crossbar 5 are both fixed on the body 1; this embodiment Both the first draw rope 16 and the second draw rope 17 are made of nylon rope or steel wire rope. Both ends of the first draw rope 16 are connected to the first crossbar 4 and the body 1 by bolts and other fixed connectors. The two ends of the pull rope 17 are connected to the second crossbar 5 and the body 1 by a fixed connecting member such as bolts.
  • the beneficial effect of this embodiment is that by providing two first draw ropes 16 and two second draw ropes 17, the stability of the connection between the support frame and the body 1 is significantly improved, and the connection between the column 2 and the body 1 is reduced. The strength of the force increases the service life of the column 2 and the supporting frame.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Walking Sticks, Umbrellas, And Fans (AREA)
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Abstract

一种机身左右装有一对半圆锥形风袋的防坠落飞机，其机体（1）下部设置有起落架，机体（1）的尾部设置有尾翼（13），立柱（2）垂直固定在机体（1）的中部，支撑框架固定在立柱（2）上远离机体（1）的一端，支撑框架所在平面与水平面倾斜设置，支撑框架前端距离机体（1）的间距大于支撑框架后端距离机体（1）的间距，支撑框架为前端边缘小于后端边缘的梯形框架，第一伞布（9）和第二伞布（8）均为梯形，第一伞布（9）的两个非平行边缘以及第二伞布（8）的两个非平行边缘固定在支撑框架上，动力装置（14）固定在机体（1）的中部后端，动力装置（14）的转轴上固定有螺旋桨（15）。该方案减小了飞机坠落风险，飞机航行动力不足时靠伞布的浮力滑行降落。

Description

一种机身左右装有一对半圆锥形风袋的防坠落飞机
本申请要求于2019年7月26日提交中国专利局、申请号为CN201921201856.X、申请名称为“一种机身左右装有一对半圆锥形风袋的防坠落飞机”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。
技术领域
本申请实施例涉及航空器技术领域，具体涉及一种机身左右装有一对半圆锥形风袋的防坠落飞机。
背景技术
随着航空技术的发展，飞机坠落导致的损失比较惨重，现有的载人飞机例如三角滑翔伞、动力三角翼和超轻型飞机等发生意外摔死人都是因为机翼左右歪斜、横侧安定性不好而摔死人的；现有无人机应用广泛，用于航拍、药物喷洒等作业的无人机往往携带贵重的拍摄仪器和药物，当固定翼无人机动力不足时容易产生坠落问题。
申请内容
为此，本申请实施例提供一种机身左右装有一对半圆锥形风袋的防坠落飞机，以解决现有技术中现有飞机前进动力不足容易坠落的问题。
为了实现上述目的，本申请实施例提供如下技术方案：
根据本申请实施例的第一方面，一种机身左右装有一对半圆锥形风袋的防坠落飞机，包括机体，机体下部设置有起落架，机体的尾部设置有尾翼，还包括立柱、支撑框架、第一伞布、第二伞布、动力装置和螺旋桨，立柱垂直固定 在机体的中部，支撑框架固定在立柱上远离机体的一端，支撑框架所在平面与水平面倾斜设置，支撑框架前端距离机体的间距大于支撑框架后端距离机体的间距，支撑框架为前端边缘小于后端边缘的梯形框架，第一伞布和第二伞布均为梯形，第一伞布的两个非平行边缘以及第二伞布的两个非平行边缘固定在支撑框架上，动力装置固定在机体的中部后端，动力装置的转轴上固定有螺旋桨。
进一步地，支撑框架包括中心杆、第一横杆、第二横杆、第一边杆和第二边杆；中心杆倾斜固定在立柱上远离机体的一端，中心杆前端距离机体的间距大于中心杆后端距离机体的间距，第一横杆垂直固定在中心杆的前端，第二横杆垂直固定在中心杆的中部后端，第一横杆以及第二横杆位于同一水平面内，第一横杆以及第二横杆均分别关于中心杆对称，第一横杆的长度小于第二横杆的长度，第一边杆和第二边杆分别设置在中心杆的两侧，第一边杆的一端固定在第一横杆的一端，第一边杆的中部固定在第二横杆的一端，第二边杆的一端固定在第一横杆的另一端，第二边杆的中部固定在第二横杆的另一端，第一伞布的两个非平行边缘分别固定在中心杆以及第一边杆上，第二伞布的两个非平行边缘分别固定在中心杆以及第二边杆上。
进一步地，第一伞布和第二伞布的形状相同，第一伞布的前端梯形边缘长度大于第一横杆的二分之一长度，第二伞布的前端梯形边缘大于第一横杆的二分之一长度。
进一步地，还包括加强筋板，立柱和中心杆的连接处设置有两个加强筋板，两个加强筋板位于同一平面内且分别位于立柱的前后两侧。
进一步地，动力装置为内燃机或电动机。
进一步地，起落架包括一个前起落支架和两个后起落支架，一个前起落支架固定在机体底部的前端，两个后起落支架固定在机体底部的中部，一个前起落支架及两个后起落支架呈三角形分布。
进一步地，第一伞布和第二伞布均采用不透光的锦纶绸制成。
进一步地，立柱的长度等于机体前端至尾翼后端之间的长度。
进一步地，还包括两个第一拉绳，第一横杆的两端分别固定有一个第一拉 绳，两个第一拉绳远离第一横杆的一端均固定在机体上。
进一步地，还包括两个第二拉绳，第二横杆的两端分别固定有一个第二拉绳，两个第二拉绳远离第二横杆的一端均固定在机体上。
本申请具有如下优点：通过本申请，避免了飞机的机翼的左右歪斜导致的失去平衡的现象发生，使用时，第一伞布和第二伞布在风力的作用下呈向上凸出的两个锥形曲面，避免了飞机失去动力后的坠落，动力装置设置在座舱后边，减少了震动的产生，本申请的飞机第一伞布和第二伞布均设置为梯形，大大提高了收集空气的能力，具备较大的空气浮力，飞行平稳，安全性高，有效避免了意外坠落导致的载人飞机的人员伤亡或无人机的贵重设备损坏。
附图说明
为了更清楚地说明本申请的实施方式或现有技术中的技术方案，下面将对实施方式或现有技术描述中所需要使用的附图作简单地介绍。显而易见地，下面描述中的附图仅仅是示例性的，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据提供的附图引伸获得其它的实施附图。
本说明书所绘示的结构、比例、大小等，均仅用以配合说明书所揭示的内容，以供熟悉此技术的人士了解与阅读，并非用以限定本申请可实施的限定条件，故不具技术上的实质意义，任何结构的修饰、比例关系的改变或大小的调整，在不影响本申请所能产生的功效及所能达成的目的下，均应仍落在本申请所揭示的技术内容得能涵盖的范围内。
图1为本申请一些实施例提供的一种机身左右装有一对半圆锥形风袋的防坠落飞机的主视图。
图2为图1提供的一种机身左右装有一对半圆锥形风袋的防坠落飞机的俯视图。
图3为图1提供的一种机身左右装有一对半圆锥形风袋的防坠落飞机的右视图。
图4为本申请另一些实施例提供的一种机身左右装有一对半圆锥形风袋 的防坠落飞机的主视图。
图5为图4提供的一种机身左右装有一对半圆锥形风袋的防坠落飞机的右视图。
图中：1、机体，2、立柱，3、中心杆，4、第一横杆，5、第二横杆，6、第一边杆，7、第二边杆，8、第二伞布，9、第一伞布，10、前起落支架，11、后起落支架，12、加强筋板，13、尾翼，14、动力装置，15、螺旋桨，16、第一拉绳，17、第二拉绳。
具体实施方式
以下由特定的具体实施例说明本申请的实施方式，熟悉此技术的人士可由本说明书所揭露的内容轻易地了解本申请的其他优点及功效，显然，所描述的实施例是本申请一部分实施例，而不是全部的实施例。基于本申请中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本申请保护的范围。
实施例1
如图1、图2和图3所示，本实施例中的一种机身左右装有一对半圆锥形风袋的防坠落飞机，包括机体1，机体1下部设置有起落架，机体1的尾部设置有尾翼13，还包括立柱2、支撑框架、第一伞布9、第二伞布8、动力装置14和螺旋桨15，立柱2为矩形钢管或圆形钢管制成，立柱2垂直固定在机体1的中部，支撑框架固定在立柱2上远离机体1的一端，支撑框架所在平面与水平面倾斜设置，支撑框架前端距离机体1的间距大于支撑框架后端距离机体1的间距，支撑框架为前端边缘小于后端边缘的梯形框架，第一伞布9和第二伞布8均为梯形，第一伞布9的两个非平行边缘以及第二伞布8的两个非平行边缘固定在支撑框架上，第一伞布9和第二伞布8的前端边缘垂直于机体1的长度方向，第一伞布9和第二伞布8的前端边缘均为进风口，第一伞布9和第二伞布8的后端边缘均为出风口，动力装置14固定在机体1的中部后端，动力装置14的转轴上固定有螺旋桨15，飞行时，第一伞布9和第二伞布8在 风力的作用下呈半圆锥形的风袋。
需要说明的是，在一些具体的实施例中，原来有些飞机例如三角滑翔伞、动力三角翼和超轻型飞机、偶尔摔下来摔死了人，其原因在于在飞行之中左右机翼歪斜了，左右不平衡了，横侧稳定性不够好，而摔下来的，本申请就是要专门解决这个问题而发明出来的，在机身的左右各设计安装一对不透气的半圆锥形的风袋，在飞行中可以收集大量的空气，好比左右有两个强有力的大手，扶着飞机平稳安全的飞向前方，大大提高了飞机的横侧安定性，机翼再也不可能左右歪斜了，确保了飞行的安全；此外，机体1近中段有一个立柱2，上面支撑框架为锥形风袋的骨架，尾部有水平尾翼和垂直尾翼，锥形风袋骨架由5根合金铝管组成，其中中心杆3、第一边杆6和第二边杆7，三根杆的长度相等，前横管也就是第一横杆4为一根，后横管也就是第二横杆5一根比前第一横杆4长一倍，共5根铝合金管组成左右圆锥形风袋的骨架，第一横杆4的前横管左右两端有两根相等长度的钢索和机头左右连接固定，保证前横管水平，同样第二横杆5也就是后横管左右两端有两根长度相等的钢索固定在机身两边，保证后横管水平，立柱2上不要安装发动机以及电动机，以免震动，发动机和电动机可以安装在紧靠着立柱2后面的短短的发动机座上，发动机或电动机上安装有螺旋桨15；起落架是后三点的，前面一个机轮，后面两机轮，滑跑起飞降落用；左右半圆锥风袋用不透气的做降落伞用的扎光绵轮绸做成。
本实施例在飞行过程中，第一伞布9和第二伞布8在风力的作用下形成两个关于立柱2所在竖直面对称的风袋，风袋下部为前端小后端大的锥形面，为飞机飞行提高了强力的浮力支撑。
本实施例达到的技术效果为：通过本实施例，避免了飞机的机翼的左右歪斜导致的失去平衡的现象发生，使用时，第一伞布9和第二伞布8在风力的作用下呈向上凸出的两个锥形曲面，避免了飞机失去动力后的坠落，动力装置14设置在座舱后边，减少了震动的产生，本实施例的飞机第一伞布9和第二伞布8均设置为梯形，大大提高了收集空气的能力，具备较大的空气浮力，飞行平稳，安全性高，有效避免了意外坠落导致的载人飞机的人员伤亡或无人机 的贵重设备损坏。
实施例2
如图1、图2和图3所示，本实施例中的一种机身左右装有一对半圆锥形风袋的防坠落飞机，包括实施例1中的全部技术特征，除此之外，支撑框架包括中心杆3、第一横杆4、第二横杆5、第一边杆6和第二边杆7；例如中心杆3、第一横杆4、第二横杆5、第一边杆6和第二边杆7均为圆管或矩形钢管，相互之间焊接形成支撑框架，中心杆3倾斜固定在立柱2上远离机体1的一端，中心杆3前端距离机体1的间距大于中心杆3后端距离机体1的间距，优选的，中心杆3和水平面之间的夹角范围为16°至24°之间，第一横杆4垂直固定在中心杆3的前端，第二横杆5垂直固定在中心杆3的中部后端，第一横杆4以及第二横杆5位于同一水平面内，第一横杆4以及第二横杆5均分别关于中心杆3对称，第一横杆4的长度小于第二横杆5的长度，第一边杆6和第二边杆7分别设置在中心杆3的两侧，第一边杆6的一端固定在第一横杆4的一端，第一边杆6的中部固定在第二横杆5的一端，第二边杆7的一端固定在第一横杆4的另一端，第二边杆7的中部固定在第二横杆5的另一端，其中，第一横杆4、中心杆3、第二横杆5以及第一边杆6围合成直角梯形，第一横杆4、中心杆3、第二横杆5以及第二边杆7围也合成直角梯形，两个直角梯形的直角处相邻，第一伞布9的两个非平行边缘分别固定在中心杆3以及第一边杆6上，第二伞布8的两个非平行边缘分别固定在中心杆3以及第二边杆7上；第一伞布9和第二伞布8的形状相同，第一伞布9的前端梯形边缘长度大于第一横杆4的二分之一长度，第二伞布8的前端梯形边缘大于第一横杆4的二分之一长度；还包括加强筋板12，立柱2和中心杆3的连接处设置有两个加强筋板12，两个加强筋板12位于同一平面内且分别位于立柱2的前后两侧。
本实施例中的有益效果为：通过将支撑框架设置为多个杆件连接的结构形式，减轻了支撑框架的重力，提高了飞行的平稳性，通过将第一伞布9的前端边缘设置为大于第一横杆4的二分之一长度以及将第二伞布8的前端边缘设置为大于第一横杆4的二分之一长度，实现了在飞行过程中第一伞布9和第二伞 布8均能够在风力的作用下形成向上凸出的锥面形风袋，增强了对飞机飞行的支撑力，避免了动力装置14动力不足时产生的飞机坠落现象的发生；通过设置加强筋板12，增强了立柱2和中心杆3之间的连接强度。
实施例3
如图1、图2和图3所示，本实施例中的一种机身左右装有一对半圆锥形风袋的防坠落飞机，包括实施例2中的全部技术特征，除此之外，动力装置14为内燃机或电动机，当动力装置14为电动机时，在飞机的机体1内还设置为电动机提供电能的蓄电池；起落架包括一个前起落支架10和两个后起落支架11，前起落支架10和后起落支架11均为连接杆端部固定有滚轮的结构，一个前起落支架10固定在机体1底部的前端，两个后起落支架11固定在机体1底部的中部，一个前起落支架10及两个后起落支架11呈三角形分布；第一伞布9和第二伞布8均采用不透光的锦纶绸制成；立柱2的长度等于机体1前端至尾翼13后端之间的长度。
本实施例中的有益效果为：通过将动力装置14设置为内燃机或者电动机，增加了动力的可选性，通过设置后端大于前端的后三角式起落架，结构稳定，通过将第一伞布9和第二伞布8采用不透光的棉纶绸制成的材质，减少了透光性对飞机的影响，同时材料承受力较强，通过将立柱2的长度设置为和机体1从前端至尾翼13后端长度相同的方式，减轻了制造难度。
实施例4
如图4和图5所示，本实施例中的一种机身左右装有一对半圆锥形风袋的防坠落飞机，包括实施例3中的全部技术特征，除此之外，还包括两个第一拉绳16，第一横杆4的两端分别固定有一个第一拉绳16，两个第一拉绳16远离第一横杆4的一端均固定在机体1上；还包括两个第二拉绳17，第二横杆5的两端分别固定有一个第二拉绳17，两个第二拉绳17远离第二横杆5的一端均固定在机体1上；本实施例中的第一拉绳16和第二拉绳17均采用尼龙绳或者钢丝绳制成，第一拉绳16的两端通过螺栓等固定连接件连接在第一横杆4及机体1上，第二拉绳17的两端通过螺栓等固定连接件连接在第二横杆5及 机体1上。
本实施例中的有益效果为：通过设置两个第一拉绳16以及两个第二拉绳17，显著提高了支撑框架和机体1连接的稳定性，减少了立柱2和机体1连接处的受力强度，增强了立柱2以及支撑框架的使用寿命。
虽然，上文中已经用一般性说明及具体实施例对本申请作了详尽的描述，但在本申请基础上，可以对之作一些修改或改进，这对本领域技术人员而言是显而易见的。因此，在不偏离本申请精神的基础上所做的这些修改或改进，均属于本申请要求保护的范围。
本说明书中所引用的如“上”、“下”、“左”、“右”、“中间”等的用语，亦仅为便于叙述的明了，而非用以限定本申请可实施的范围，其相对关系的改变或调整，在无实质变更技术内容下，当亦视为本申请可实施的范畴。

Claims (10)

  1. 一种机身左右装有一对半圆锥形风袋的防坠落飞机，包括机体(1)，所述机体(1)下部设置有起落架，所述机体(1)的尾部设置有尾翼(13)，其特征在于，还包括立柱(2)、支撑框架、第一伞布(9)、第二伞布(8)、动力装置(14)和螺旋桨(15)，所述立柱(2)垂直固定在所述机体(1)的中部，所述支撑框架固定在所述立柱(2)上远离所述机体(1)的一端，所述支撑框架所在平面与水平面倾斜设置，所述支撑框架前端距离所述机体(1)的间距大于所述支撑框架后端距离所述机体(1)的间距，所述支撑框架为前端边缘小于后端边缘的梯形框架，所述第一伞布(9)和所述第二伞布(8)均为梯形，所述第一伞布(9)的两个非平行边缘以及所述第二伞布(8)的两个非平行边缘固定在所述支撑框架上，所述动力装置(14)固定在所述机体(1)的中部后端，所述动力装置(14)的转轴上固定有所述螺旋桨(15)。
  2. 根据权利要求1所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，所述支撑框架包括中心杆(3)、第一横杆(4)、第二横杆(5)、第一边杆(6)和第二边杆(7)；所述中心杆(3)倾斜固定在所述立柱(2)上远离所述机体(1)的一端，所述中心杆(3)前端距离所述机体(1)的间距大于所述中心杆(3)后端距离所述机体(1)的间距，所述第一横杆(4)垂直固定在所述中心杆(3)的前端，所述第二横杆(5)垂直固定在所述中心杆(3)的中部后端，所述第一横杆(4)以及所述第二横杆(5)位于同一水平面内，所述第一横杆(4)以及所述第二横杆(5)均分别关于所述中心杆(3)对称，所述第一横杆(4)的长度小于所述第二横杆(5)的长度，所述第一边杆(6)和所述第二边杆(7)分别设置在所述中心杆(3)的两侧，所述第一边杆(6)的一端固定在所述第一横杆(4)的一端，所述第一边杆(6)的中部固定在所述第二横杆(5)的一端，所述第二边杆(7)的一端固定在所述第一横杆(4)的另一端，所述第二边杆(7)的中部固定在所述第二横杆(5)的另一端，所述第一伞布(9)的两个非平行边缘分别固定在所述中心杆(3)以及所述第一边杆(6)上，所述第二伞布(8)的两个非平行边缘分别固定在 所述中心杆(3)以及所述第二边杆(7)上。
  3. 根据权利要求2所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，所述第一伞布(9)和所述第二伞布(8)的形状相同，所述第一伞布(9)的前端梯形边缘长度大于所述第一横杆(4)的二分之一长度，所述第二伞布(8)的前端梯形边缘大于所述第一横杆(4)的二分之一长度。
  4. 根据权利要求2所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，还包括加强筋板(12)，所述立柱(2)和所述中心杆(3)的连接处设置有两个所述加强筋板(12)，两个所述加强筋板(12)位于同一平面内且分别位于所述立柱(2)的前后两侧。
  5. 根据权利要求1所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，所述动力装置(14)为内燃机或电动机。
  6. 根据权利要求1所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，所述起落架包括一个前起落支架(10)和两个后起落支架(11)，一个所述前起落支架(10)固定在所述机体(1)底部的前端，两个所述后起落支架(11)固定在所述机体(1)底部的中部，一个所述前起落支架(10)及两个所述后起落支架(11)呈三角形分布。
  7. 根据权利要求1所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，所述第一伞布(9)和所述第二伞布(8)均采用不透光的锦纶绸制成。
  8. 根据权利要求1所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，所述立柱(2)的长度等于所述机体(1)前端至所述尾翼(13)后端之间的长度。
  9. 根据权利要求2所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，还包括两个第一拉绳(16)，所述第一横杆(4)的两端分别固定有一个所述第一拉绳(16)，两个所述第一拉绳(16)远离所述第一横杆(4)的一端均固定在所述机体(1)上。
  10. 根据权利要求9所述的一种机身左右装有一对半圆锥形风袋的防坠落飞机，其特征在于，还包括两个第二拉绳(17)，所述第二横杆(5)的两端分 别固定有一个所述第二拉绳(17)，两个所述第二拉绳(17)远离所述第二横杆(5)的一端均固定在所述机体(1)上。
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GB2189752A (en) * 1986-05-02 1987-11-04 John Ievers Weight-shift aircraft
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CN103847963A (zh) * 2014-02-28 2014-06-11 华南农业大学 一种无人驾驶动力三角翼飞行器
CN210681152U (zh) * 2019-07-26 2020-06-05 吴永高 一种机身左右装有一对半圆锥形风袋的防坠落飞机

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Publication number Priority date Publication date Assignee Title
US4158448A (en) * 1976-09-14 1979-06-19 Matsuji Mochizuki Airplane with pivotable wing
FR2555128A1 (fr) * 1983-11-22 1985-05-24 Baffert Hugues Dispositif mecanique pour le pilotage des aeronefs a aile souple de type delta par gauchissement de la voilure
GB2189752A (en) * 1986-05-02 1987-11-04 John Ievers Weight-shift aircraft
RU2198826C2 (ru) * 2001-04-20 2003-02-20 Государственное унитарное научное конструкторско-технологическое предприятие "Парсек" Дельталет
CN103847963A (zh) * 2014-02-28 2014-06-11 华南农业大学 一种无人驾驶动力三角翼飞行器
CN210681152U (zh) * 2019-07-26 2020-06-05 吴永高 一种机身左右装有一对半圆锥形风袋的防坠落飞机

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