CN1639500A - 飞行器 - Google Patents
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/60—Tethered aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/20—Transmission of mechanical power to rotors or propellers
- B64U50/23—Transmission of mechanical power to rotors or propellers with each propulsion means having an individual motor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F19/00—Hoisting, lifting, hauling or pushing, not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L37/00—Couplings of the quick-acting type
- F16L37/28—Couplings of the quick-acting type with fluid cut-off means
- F16L37/38—Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in only one of the two pipe-end fittings
- F16L37/44—Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in only one of the two pipe-end fittings with one lift valve being actuated to initiate the flow through the coupling after the two coupling parts are locked against withdrawal
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/16—Flying platforms with five or more distinct rotor axes, e.g. octocopters
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
- B64U2201/202—Remote controls using tethers for connecting to ground station
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- Mechanical Engineering (AREA)
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Abstract
本发明涉及一种具有多个提升转子和推力转子的飞行器,每个转子对应一个电动机,且每个电动机具有一个逆变器。为提供一种有更大有效负载的飞行器,在发动机之间设置连接棒杆。在这一点上本发明是基于以下认识:即如果此连接棒杆以网格方式设置时,能为飞行器提供一个轻而稳定的结构,该结构相应地可以运输更大的负载。
Description
建立高的建筑和建筑物通常需要起重机。起重机自然也应用于如风力发电设备的塔之类建筑楼。值得注意的是风力发电设备正越来越庞大,这就意味着一方面起重机必须能达到越来越高的高度,另一方面必须能移动越来越大的质量。这样就导致了更大更重的起重机。这些起重机理所当然地更为昂贵,并且将这样的起重机从一个建筑点运送到另一个建筑点的成本也随之增加,同样增加的还有安装和拆卸起重机的费用。
一种可以替换的方案是飞行器,它能够运送建筑或建筑物(如风力发电设备)的组件。
DE 22 34 524公开了一种具有多个升力转子和推力转子的飞行平台,且每个转子配备有一电机,同时每个电机配备有一个逆变器。
不过这种公知的飞行器有一个不足,那就是所述电机安装于一通用平台。该平台一方面有一很高的固有高度,并且由于涉及的建筑不同,需要分别预先确定发动机和转子的可能数量。
因此,本发明的目的是提供一种具有更大有效载荷的飞行器。
根据本发明的飞行器,通过发动机之间的连接棒杆可以实现所述目的。对于这一点本发明基于这样的认识:单个发动机之间的稳定连接是必需的,但是使用棒杆结构有可能减小所述平台的固有高度。以此方式节省下来的重量,在飞行器具有相同的运输能力时,就可以用作额外的有效载荷。
在本发明一个优选实施方式中,能量供应是通过至少一根拖尾线缆完成的。显然这种方式下飞行器也必须提升线缆的重量,但相应地因为这个原因就不再需要搬运贵而且重的能量存储装置。通过多根优选地安装于飞行器上各个位置的拖尾线缆实现所述能量供应意味着即使在某一根线缆失效的情况仍可能进行可靠运转。
在一个特别优选的实施方式中,飞行器通过地面的无线或有线遥控系统控制。在这点上也可以提供两个或更多交替作用于飞行器的遥控系统。这样就有可能进行如提升负载等的粗定位以及基本确定相对地面的飞行方向,而如所述设备的塔体某一部分的精确定位将由塔架上可以精确监控整个过程的某一位置作用。
在本发明一个优选实施方式中,所述飞行器有着陆脚,可以使其着陆。为此目的在每个转子的末端设置了一远离轴的弹性安装的支撑盘。
在一个特别优选的实施方式中,本发明的飞行器有一用于自动控制飞行姿态或飞行高度的装置。该装置可与全球定位系统相连,以此为预定位置提供自动导航。这样可以自动进行本发明飞行器的粗定位。
为尽可能小地增加飞行器的固有重量,即使所述装置安装在飞行器上,该装置由连接棒杆优选地安装在至少两个发动机之间。这时该装置尤其优选地安装在一平面下方,棒杆在此平面内在两发动机之间延伸。这样,即使飞行不携带负载,飞行器的重心也低,有利于飞行姿态的稳定性。
在一个优选实施方式中,发动机和逆变器结构上联合这样其可以作为一个单元进行预装配和处理。
为保护飞行器上所需电缆,在一个特别优选的实施方式中,连接棒杆是中空的,线缆从棒杆内部穿过。
因此能根据要运送的负载柔性地设定飞行器的尺寸,并在连接棒杆和发动机之间设置固定但可释放的连接装置。这将允许本发明的飞行器可以根据将要运输负载大小而选定的期望数量的发动机进行调整,通过连接棒杆以网格方式连接所述发动机而得到一个稳定的飞行器。
本发明更多优选实施方式将在权利要求书中阐述。
下文将参考附图以示例的方式详细描述本发明一实施方式。
图1所示为本发明飞行器的一个简化视图。
图2所示为本发明飞行器发动机的一个简化视图。
图3所示为本发明一个连接棒杆的末端部分。
图1中,标记10代表发动机,标记12代表转子(螺旋桨),标记14代表逆变器,标记15代表连接棒杆,标记16代表控制飞行姿态及位置或飞行高度的装置(控制装置)。
此处图示本发明的飞行器为一三角形的基本形状。
一些发动机10的安放要使其上的转子12可在垂直平面内旋转。根据发动机10的不同转向,转子12可作为推力转子或者牵引转子。飞行方向相应地受这些转子的影响。
另外一些发动机10安放在所述三角形的顶点,发动机上的转子12在一个近似水平的平面内旋转。它们作提升转子的工作,可以提升负载或者在一预定高度飞行。
每个发动机10都有一逆变器14与之连接,可使每个发动机10单独动作。这样,单个发动机10可以彼此独立致动,这样一方面可非常精确地控制该飞行器,另一方面可以对飞行器分别独立控制方向。
图示三角外形只是作为一种变体。可以理解,其他多边形如四边形、五边形或任何其他合适安放发动机的形状也可能用于提升和运送相应的重负载。
该飞行器中心处设置有一控制装置16,其一方面可以为逆变器14进而为发动机提供电能,另一方面也影响逆变器14产生响应控制指令的飞行动作。同时也有可能在控制装置16上加装一能量储存装置,例如当拖尾线缆断裂时,其仍能为飞行器提供足够能量进行紧急着陆,以避免失控坠毁。
图2所示为本发明飞行器发动机10的一个侧视图。一转子12通过轴与发动机10连接。在发动机10与轴相对的末端设置有一弹簧腿22,弹簧腿22末端安装有一远离发动机的支撑脚20。根据图示安装的位置,其包括一个提升发动机。当本发明飞行器降低时,支撑脚20将首先接触地面,飞行器其余部分将对抗弹簧腿22的压力向下运动。这样本发明飞行器在着陆时,发动机外壳10就不用承担损坏或严重脏污的风险。
图3所示为本发明中连接棒杆15的一部分。连接棒杆15有一个支承18,通过所述支承18连接棒杆固定但可释放与例如发动机10连接在一起,以构建本发明飞行器。示出一位于中空的连接棒杆15中的线缆26。线缆26在连接棒杆15内的这种安放可将线缆导入连接棒杆15内部的一防护环境,这样就可以大大减小线缆26损坏的风险,在建筑地点的恶劣条件下是永远存在这种风险的。
线缆26从连接棒杆15的末端出来,因此靠近发动机10,可与电线28连接。这样,线缆26只有在连接棒杆15的末端和发动机10之间的短短部分是可以随意接近的。这样将线缆26合适地导入由飞行器构成的框架中可以降低损坏的风险。可以理解,该线缆也可连接到与发动机10一起组成一个结构单元的逆变器14。
不过,当逆变器14与控制装置16连接时,以此方式导引缆线也是有利的。在那种情况下,线缆26从带有逆变器14的控制装置16延伸至发动机10。
在所描述的飞行器中,提升转子的数量优选地明显大于推力转子的数量。例如提升转子数量与推力转子的比值可以在5∶1到10∶1之间。
Claims (16)
1.一种具有多个提升转子和推力转子的飞行器,其中各个转子都有一电动机与之相连接,且每个发动机与一逆变器相连,其中,所述飞行器有一个电动机操作的线缆绞盘,通过该绞盘可以提升或降低飞行器的负载物。
2.如权利要求1所述的飞行器,其特征在于,由至少一根拖尾线缆提供的能量供应。
3.如前述权利要求中任一项所述的飞行器,其特征在于,具有一无线或有线遥控系统。
4.如权利要求3所述的飞行器,其特征在于,两套遥控系统交替或同时作用于所述飞行器。
5.如前述权利要求中任一项所述的飞行器,其特征在于,在每个发动机(10)的末端弹性安装的支撑盘(20),该支撑盘(20)远离所述轴。
6.如前述权利要求中任一项所述的飞行器,其特征在于,具有用于自动控制飞行姿态或飞行高度的装置(16)。
7.如权利要求5所述的飞行器,其特征在于,位于至少两发动机(10)和自动控制飞行姿态或飞行高度的装置(16)之间的连接棒杆(15)。
8.如权利要求6或7所述的飞行器,其特征在于,具有一用于为预定位置提供导航的全球定位系统。
9.如权利要求6到8中任一项所述的飞行器,其特征在于,所述装置(16)安装于一平面下方,所述棒杆(15)在该平面内在所述发动机(10)之间延伸。
10.如前述权利要求中任一项所述的飞行器,其特征在于,所述发动机(10)和所述逆变器(14)结构上联合。
11.如前述权利要求中任一项所述的飞行器,其特征在于,所述连接棒杆(15)是中空的,所述线缆(26)安装于所述棒杆内部。
12.如前述权利要求中任一项所述的飞行器,其特征在于,所述连接棒杆(15)和所述发动机(10)之间为固定但可释放连接。
13.如前述权利要求中任一项所述的飞行器,其特征在于,具有一设置在所述飞行器上的能量储存装置。
14.如前述权利要求中任一项所述的飞行器,其特征在于,所述飞行器有一个基本由连接棒杆构建而成的底盘。
15.如前述权利要求中任一项所述的飞行器,其特征在于,电动机通过连接棒杆连接在一起。
16.如前述权利要求中任一项所述的飞行器,其特征在于,所述提升转子基本是单叶片或双叶片转子。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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DE10209881.6 | 2002-03-06 | ||
DE10209881A DE10209881A1 (de) | 2002-03-06 | 2002-03-06 | Fluggerät |
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CN1639500A true CN1639500A (zh) | 2005-07-13 |
CN100343120C CN100343120C (zh) | 2007-10-17 |
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CNB038053713A Expired - Fee Related CN100343120C (zh) | 2002-03-06 | 2003-03-05 | 飞行器 |
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US (2) | US7364114B2 (zh) |
EP (1) | EP1483526B1 (zh) |
JP (2) | JP2005526651A (zh) |
KR (1) | KR100612722B1 (zh) |
CN (1) | CN100343120C (zh) |
AR (1) | AR038738A1 (zh) |
AT (1) | ATE343756T1 (zh) |
AU (1) | AU2003218686B2 (zh) |
BR (1) | BR0308012A (zh) |
CA (1) | CA2476749C (zh) |
CY (1) | CY1106292T1 (zh) |
DE (2) | DE10209881A1 (zh) |
DK (1) | DK1483526T3 (zh) |
ES (1) | ES2271545T3 (zh) |
HK (1) | HK1071418A1 (zh) |
PL (1) | PL209400B1 (zh) |
PT (1) | PT1483526E (zh) |
WO (1) | WO2003074924A1 (zh) |
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- 2003-03-05 CA CA002476749A patent/CA2476749C/en not_active Expired - Fee Related
- 2003-03-05 PL PL370665A patent/PL209400B1/pl unknown
- 2003-03-05 JP JP2003573340A patent/JP2005526651A/ja active Pending
- 2003-03-05 ES ES03711921T patent/ES2271545T3/es not_active Expired - Lifetime
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- 2003-03-05 EP EP03711921A patent/EP1483526B1/de not_active Expired - Lifetime
- 2003-03-05 BR BR0308012-9A patent/BR0308012A/pt not_active Application Discontinuation
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- 2003-03-05 AT AT03711921T patent/ATE343756T1/de active
- 2003-03-05 AU AU2003218686A patent/AU2003218686B2/en not_active Ceased
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US10227131B2 (en) | 2014-06-26 | 2019-03-12 | SZ DJI Technology Co., Ltd. | Aerial vehicle and a signal line protection assembly thereof |
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Also Published As
Publication number | Publication date |
---|---|
CY1106292T1 (el) | 2011-10-12 |
DE10209881A1 (de) | 2003-09-18 |
CA2476749C (en) | 2008-04-22 |
EP1483526A1 (de) | 2004-12-08 |
US20050061910A1 (en) | 2005-03-24 |
WO2003074924A1 (de) | 2003-09-12 |
CN100343120C (zh) | 2007-10-17 |
AU2003218686A1 (en) | 2003-09-16 |
ES2271545T3 (es) | 2007-04-16 |
EP1483526B1 (de) | 2006-10-25 |
BR0308012A (pt) | 2005-01-04 |
US7364114B2 (en) | 2008-04-29 |
PL370665A1 (en) | 2005-05-30 |
PL209400B1 (pl) | 2011-08-31 |
DE50305485D1 (de) | 2006-12-07 |
JP2009057044A (ja) | 2009-03-19 |
CA2476749A1 (en) | 2003-09-12 |
PT1483526E (pt) | 2006-12-29 |
JP2005526651A (ja) | 2005-09-08 |
AU2003218686B2 (en) | 2007-04-26 |
AR038738A1 (es) | 2005-01-26 |
WO2003074924A8 (de) | 2004-05-27 |
KR100612722B1 (ko) | 2006-08-17 |
DK1483526T3 (da) | 2007-02-26 |
KR20040094707A (ko) | 2004-11-10 |
ATE343756T1 (de) | 2006-11-15 |
US20080006737A1 (en) | 2008-01-10 |
HK1071418A1 (en) | 2005-07-15 |
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