WO2016000486A1 - 无人直升机的尾气平衡*** - Google Patents

无人直升机的尾气平衡*** Download PDF

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Publication number
WO2016000486A1
WO2016000486A1 PCT/CN2015/077907 CN2015077907W WO2016000486A1 WO 2016000486 A1 WO2016000486 A1 WO 2016000486A1 CN 2015077907 W CN2015077907 W CN 2015077907W WO 2016000486 A1 WO2016000486 A1 WO 2016000486A1
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WO
WIPO (PCT)
Prior art keywords
unmanned helicopter
fuselage
balance system
tail gas
exhaust pipe
Prior art date
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PCT/CN2015/077907
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English (en)
French (fr)
Inventor
赵曙光
赵泓波
李朝阳
Original Assignee
青岛宏百川金属精密制品有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from CN201420366388.2U external-priority patent/CN203958623U/zh
Priority claimed from CN201410315531.XA external-priority patent/CN104044743B/zh
Application filed by 青岛宏百川金属精密制品有限公司 filed Critical 青岛宏百川金属精密制品有限公司
Publication of WO2016000486A1 publication Critical patent/WO2016000486A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes

Definitions

  • the invention relates to the technical field of unmanned helicopters, in particular to an exhaust gas balance system of an unmanned helicopter.
  • Unmanned rotor helicopters are widely used in civil and military applications due to their adaptability to weather, such as aerial photography, aerial wiring, and line inspections.
  • the conventional unmanned helicopter adopts a balanced design at the center of gravity, so that the center of gravity 8 of the unmanned helicopter is located on the axis 2 of the main shaft 2 of the rotor 1, and the front and rear sides of the main shaft 2 of the unmanned helicopter rotor 1
  • the balance of gravity is favorable for the flight and operation of the unmanned helicopter.
  • the exhaust pipe 3 is generally designed on both sides or one side of the casing, and the exhaust gas is ineffectively discharged to the rear.
  • the unmanned helicopter can install the parachute 5 on top of the rotor head. Since the center of gravity of the unmanned helicopter is located on the axis 2 of the rotor 1 of the rotor 1, as shown in Figure 3, after the parachute 5 is opened, the unmanned helicopter is horizontal. The attitude of landing, so that when the unmanned helicopter landed, it is very likely to damage the equipment 7 located in the front of the unmanned helicopter, and the equipment 7 is very expensive, and the damage of the equipment 7 will bring greater economic losses. Increase the risk cost of unmanned helicopter operations.
  • the invention is directed to the current unmanned helicopter exhaust emission and the center of gravity of the unmanned helicopter on the axis of the rotor main shaft, the attitude level at the time of the parachute, the damage of the equipment when landing, the economic loss, the risk cost of the drone operation, etc.
  • An exhaust gas balance system for an unmanned helicopter was designed.
  • the exhaust gas balance system of the unmanned helicopter of the present invention comprises: a fuselage, an engine, a rotor, a parachute device, a tail pipe, a parachute device mounted on a rotor head of the rotor, and a mounting device mounted on the nose of the fuselage,
  • the exhaust gas balance system includes an exhaust pipe installed at the rear of the fuselage and connected to the engine. The exhaust port of the exhaust pipe faces directly below, and a center of gravity adjustment device is also installed in the fuselage.
  • the center of gravity adjustment device is other effective load mounted within the fuselage.
  • the utility model has the beneficial effects that the exhaust port of the exhaust pipe of the exhaust gas balance system faces downward, so that the exhaust gas discharged from the engine is discharged downward through the exhaust port of the exhaust pipe, so that the discharged exhaust gas is lifted to the rear of the fuselage, and the lift
  • the increase can increase the corresponding load, and adjust the arrangement of the weight in the center of gravity in the center of gravity adjustment device, so that the center of the unmanned helicopter moves backward and balances the exhaust gas.
  • the lift ensures the balance of the unmanned helicopter during normal operation; when an unmanned helicopter encounters an accident during the flight, the engine idles or stops, the parachute opens, and the unmanned helicopter's dynamic center of gravity moves backward from the main shaft, and the center of gravity moves backward.
  • the tail of the unmanned helicopter is tilted down and the nose is tilted up, so that the tail pipe of the unmanned helicopter first touches the ground, buffering the impact when landing, preventing the damage of the equipment on the nose, avoiding unnecessary economic losses and reducing the The risk cost of human helicopter operations.
  • Figure 1 is a side elevational view of a conventional unmanned helicopter.
  • FIG. 2 is a top plan view of a conventional unmanned helicopter.
  • Figure 3 is a state diagram of a conventional unmanned helicopter when landing with a parachute.
  • Figure 4 is a structural view of the exhaust gas balance system.
  • Figure 5 is a state diagram of an unmanned helicopter equipped with an exhaust gas balance system when landing with a parachute.
  • the unmanned helicopter includes a fuselage 4, an engine, a rotor 1, a parachute 5, and a tail pipe 9, and the parachute 5 is mounted on the rotor head 6 of the rotor 1.
  • the equipment 7 is mounted on the nose of the body 4.
  • the exhaust gas balance system includes an exhaust pipe 3 installed at the rear of the fuselage 4 and connected to the engine.
  • the exhaust port of the exhaust pipe 3 faces directly below, and a center of gravity adjusting device is also installed in the body 4.
  • the center of gravity adjustment device is a plurality of weight packs or other effective loads installed in the fuselage.
  • the center of gravity 8 of the unmanned helicopter is located at the rear of the fuselage 4, the main shaft 2 of the rotor 1 and the rear side of the rotor head 6, using the rotor 1
  • the lift force and the upward thrust generated by the downward exhaust of the exhaust port of the exhaust pipe 3 balance the unmanned helicopter after the center of gravity 8 is moved backward.
  • the unmanned helicopter fails, the engine stops, the exhaust pipe 3 stops exhausting, the parachute 5 opens, the unmanned helicopter landed, and the unmanned helicopter loses the lift generated by the rotor 1 and the exhaust pipe 3
  • the upward thrust generated by the exhaust gas, the connection point of the parachute 5 and the unmanned helicopter is located on the rotor head 6 of the rotor 1, and the center of gravity 8 of the unmanned helicopter is located at the rear side of the rotor head 6, so that the tail of the unmanned helicopter is made
  • the sinking tube 9 at the tail is tilted downward, and the carrying device 7 on the nose of the body 4 is tilted upward.
  • the low-cost tail pipe 9 was first contacted with the ground to reduce the drop of the unmanned helicopter.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

一种无人直升机的尾气平衡***，无人直升机包括机身、发动机、旋翼、降落伞装置、尾管，降落伞装置安装在旋翼的旋翼头上，机身的机头上安装搭载设备，所述的尾气平衡***包括排气管，排气管安装在机身的后部，并与发动机相连，排气管的排气口朝向正下方，机身内还安装有重心调节装置。尾气平衡***排气管的排气口朝向正下方，升力增加即可增加相应载重，同时调节重心调节装置中配重包在机体内的布置，使无人直升机的中心后移，平衡尾气产生的升力，保证了无人直升机正常工作时的平衡；当无人直升机飞行过程中遇到事故时，后移的重心使无人直升机的尾部下倾、机头上翘，让无人直升机的尾管先着地，缓冲降落时的冲击，防止位于机头上的搭载设备损坏，避免了不必要的经济损失，降低无人直升机作业的风险成本。

Description

无人直升机的尾气平衡*** 技术领域
本发明涉及无人直升机技术领域，具体涉及一种无人直升机的尾气平衡***。
背景技术
无人驾驶的旋翼直升机由于天气适应能力强，广泛应用在民用和军用领域，进行例如航拍、高空架线、线路巡查等作业。如图1至2所示，传统的无人直升机在重心位置上皆采用平衡设计，使无人直升机的重心8位于旋翼1的主轴2轴线上，无人直升机旋翼1的主轴2前后两侧的重力保持平衡，利于无人直升机的飞行及操作，其排气管3一般简单设计在机壳两侧或一侧，尾气向后面无效排放。为了回收以及防止降落伞坠毁，无人直升机可在旋翼头顶部安装降落伞5，由于无人直升机的重心位于旋翼1的主轴2轴线上，如图3所示，降落伞5打开以后，无人直升机以水平的姿态降落，这样在无人直升机着陆的瞬间，极有可能损坏位于无人直升机前部的搭载设备7，而搭载设备7都十分昂贵，搭载设备7的损坏将会带来较大的经济损失，增加无人直升机作业的风险成本。
发明内容
本发明针对目前的无人直升机尾气无效排放以及无人直升机重心位于旋翼主轴的轴线上，伞降时姿态水平，着陆时容易损坏搭载设备，造成经济损失，增加无人机作业的风险成本等问题，设计了一种无人直升机的尾气平衡***。
本发明的无人直升机的尾气平衡***，无人直升机包括机身、发动机、旋翼、降落伞装置、尾管，降落伞装置安装在旋翼的旋翼头上，机身的机头上安装搭载设备，所述的尾气平衡***包括排气管，排气管安装在机身的后部，并与发动机相连，排气管的排气口朝向正下方，机身内还安装有重心调节装置。
优选的是，重心调节装置为安装在机身内的其他有效载重。
本发明的有益效果是：尾气平衡***排气管的排气口朝向正下方，使发动机排出的尾气通过排气管的排气口向下排出，让排出的尾气给机身后部升力，升力增加即可增加相应载重，同时调节重心调节装置中配重包在机体内的布置，使无人直升机的中心后移，平衡尾气产生 的升力，保证了无人直升机正常工作时的平衡；当无人直升机飞行过程中遇到事故时，发动机怠速或停车，降落伞打开，使无人直升机动态重心由主轴处后移，后移的重心使无人直升机的尾部下倾、机头上翘，让无人直升机的尾管先着地，缓冲降落时的冲击，防止位于机头上的搭载设备损坏，避免了不必要的经济损失，降低无人直升机作业的风险成本。
附图说明
附图1为传统无人直升机的侧视结构图。
附图2为传统无人直升机的俯视结构图。
附图3为传统无人直升机利用降落伞降落时的状态图。
附图4为尾气平衡***的结构图。
附图5为装有尾气平衡***的无人直升机利用降落伞降落时的状态图。
具体实施方式
本发明的无人直升机的尾气平衡***，如图4至5所示，无人直升机包括机身4、发动机、旋翼1、降落伞5、尾管9，降落伞5安装在旋翼1的旋翼头6上，机身4的机头上安装搭载设备7。
尾气平衡***包括排气管3，排气管3安装在机身4的后部，并与发动机相连，排气管3的排气口朝向正下方，机身4内还安装有重心调节装置。
重心调节装置为安装在机身内的多个配重包或其他有效载重。
调节配重包在机身4内的分布，如图4所示，使无人直升机的重心8位于机身4的后部，旋翼1的主轴2以及旋翼头6的后侧，利用旋翼1产生的升力以及通过排气管3的排气口向下排气产生的向上的推力，使重心8后移后的无人直升机保持平衡。
如图5所示，当无人直升机发生故障时，发动机停转，排气管3停止排气，降落伞5打开，无人直升机降落，由于无人直升机失去旋翼1产生的升力以及排气管3排出的尾气产生的向上的推力，降落伞5与无人直升机的连接点位于旋翼1的旋翼头6上，而无人直升机的重心8位于旋翼头6的后侧，所以使无人直升机的机尾下沉，处于机尾的尾管9朝下倾斜，而位于机身4的机头上的搭载设备7则向上翘起。
当无人直升机降落触地时，使成本低廉的尾管9先与地面接触，降低无人直升机下降的 速度，缓冲地面给无人直升机的冲击，然后无人直升机自后向前逐渐接触地面，避免位于机头上的搭载设备7先触地，造成损坏，产生经济损失。

Claims (2)

  1. 一种无人直升机的尾气平衡***，无人直升机包括机身、发动机、旋翼、降落伞、尾管，降落伞安装在旋翼的旋翼头上，机身的机头上安装搭载设备，其特征在于，所述的尾气平衡***包括排气管，排气管安装在机身的后部，并与发动机相连，排气管的排气口朝向正下方，机身内还安装有重心调节装置。
  2. 根据权利要求1所述的无人直升机的尾气平衡***，其特征在于，重心调节装置为安装在机身内的多个配重包。
PCT/CN2015/077907 2014-07-03 2015-04-30 无人直升机的尾气平衡*** WO2016000486A1 (zh)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CN201420366388.2 2014-07-03
CN201410315531.X 2014-07-03
CN201420366388.2U CN203958623U (zh) 2014-07-03 2014-07-03 无人直升机的尾气平衡***
CN201410315531.XA CN104044743B (zh) 2014-07-03 2014-07-03 无人直升机的尾气平衡***

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4506848A (en) * 1980-12-22 1985-03-26 British Aerospace Public Limited Company Aircraft configuration and control arrangement therefor
US5516060A (en) * 1993-03-29 1996-05-14 Mcdonnell; William R. Vertical take off and landing and horizontal flight aircraft
JPH10119897A (ja) * 1996-10-15 1998-05-12 Yamaha Motor Co Ltd 排気装置を有する産業用無人ヘリコプタ
GB201301748D0 (en) * 2013-01-31 2013-03-20 Reiter Johannes Aircraft for Vertical Take-off and Landing with a Wing Arrangement comprising an extendible lift increasing system
CN103274045A (zh) * 2013-05-10 2013-09-04 华南农业大学 一种涵道飞艇直升机
CN104044743A (zh) * 2014-07-03 2014-09-17 青岛宏百川金属精密制品有限公司 无人直升机的尾气平衡***
CN203958623U (zh) * 2014-07-03 2014-11-26 青岛宏百川金属精密制品有限公司 无人直升机的尾气平衡***

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4506848A (en) * 1980-12-22 1985-03-26 British Aerospace Public Limited Company Aircraft configuration and control arrangement therefor
US5516060A (en) * 1993-03-29 1996-05-14 Mcdonnell; William R. Vertical take off and landing and horizontal flight aircraft
JPH10119897A (ja) * 1996-10-15 1998-05-12 Yamaha Motor Co Ltd 排気装置を有する産業用無人ヘリコプタ
GB201301748D0 (en) * 2013-01-31 2013-03-20 Reiter Johannes Aircraft for Vertical Take-off and Landing with a Wing Arrangement comprising an extendible lift increasing system
CN103274045A (zh) * 2013-05-10 2013-09-04 华南农业大学 一种涵道飞艇直升机
CN104044743A (zh) * 2014-07-03 2014-09-17 青岛宏百川金属精密制品有限公司 无人直升机的尾气平衡***
CN203958623U (zh) * 2014-07-03 2014-11-26 青岛宏百川金属精密制品有限公司 无人直升机的尾气平衡***

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