CN110683051A - 用于飞行器的电力供应系统以及对应的飞行器 - Google Patents

用于飞行器的电力供应系统以及对应的飞行器 Download PDF

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CN110683051A
CN110683051A CN201910597963.7A CN201910597963A CN110683051A CN 110683051 A CN110683051 A CN 110683051A CN 201910597963 A CN201910597963 A CN 201910597963A CN 110683051 A CN110683051 A CN 110683051A
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S·本德尔
M·福里
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Dr Ing HCF Porsche AG
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    • B60L2210/00—Converter types
    • B60L2210/10—DC to DC converters
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
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    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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Abstract

本发明提供一种用于飞行器(10)的电力供应系统，该电力供应系统具有以下特征：该电力供应系统包括能够飞行的无人机(12)，该无人机带有多个旋翼(13)、直流变压器(14)、用于驱动这些旋翼(13)的电池(15)、以及用于固定该无人机(12)与该飞行器(10)之间的插接连接(16)的锁定装置(17)；该无人机(12)被配置为，借助该锁定装置(17)来固定该插接连接(16)，直到该飞行器(10)达到预定的飞行高度；并且该电力供应系统被配置成使得只要存在该插接连接(16)，则该电池(15)借助该直流变压器(14)给该飞行器(10)供电。

Description

用于飞行器的电力供应系统以及对应的飞行器
技术领域
本发明涉及一种飞行器、尤其一种完全电动的、可竖直地起飞和降落(verticaltake-off and landing，VTOL)的飞行器。本发明此外涉及一种对应的电力供应系统。
背景技术
VTOL在航空航天技术中跨语言地指如下任何类型的飞机、无人机或火箭，其能够基本竖直地且无需起飞和降落跑道的情况下升起和再次着陆。这个通称术语在下文中被广义地使用，其不仅包括带有机翼的固定翼飞机，而且同样包括旋翼飞机(如直升旋翼机、自转旋翼机、螺旋桨旋翼机)和混合式飞机(如复合式直升旋翼机或组合式旋翼机)以及可竖直升降的飞机。此外，还包括能够在特别短的距离内起飞和降落(short take-off andlanding，STOL)、在短的距离内起飞但竖直地降落(short take-off and verticallanding，STOVL)、或竖直地起飞但水平地降落(vertical take-off and horizontallanding，VTHL)的飞行器。
VTOL在起飞和降落阶段期间的电力需求高。因此，根据现有技术的电驱动的VTOL的电池不仅必须考虑其容量，而且还要在其功率密度方面满足最高要求。
WO 2010/031384 A2公开了一种用于使无人机借助施加起飞能量的起飞弹射器起飞的方法，其方式为首先在起飞之前对该起飞弹射器进行定向。在此，该起飞弹射器借助防窥件被遮盖，在定向之后并且邻近起飞之前才移除该防窥件。
DE 10 2016 219 473 A1涉及一种用于与载具对接的无人机。在此，该无人机包括蓄能器以及用于使无人机与载具对接的对接设备。此外，该无人机还包括用于与载具和/或与载具的用户的外部仪器通信的至少一个通信单元以及用于识别载具的用户的位置的至少一个位置确定单元。在此，该无人机被设计为，根据能够由通信单元检测的可预先确定的触发信号，通过位置确定单元确定用户的位置、与载具解除对接、与已识别出的位置对应地前往载具的用户处并自动地跟随该用户。
DE 10 2007 003 458 A1描述了一种用于为电池驱动的小型飞行仪器自动地供应能量的装置，以便确保飞行仪器几乎不中断的使用并且避免操纵人员持续待命。为此目的设置有降落和充电平台，该降落和充电平台配有电池盒或在该降落和充电平台下方设置有充电装置。
为了解决如上简述的问题，提出一种替代性的能量源，该能量源不增加飞行器的总重量。这个建议是基于以下认知：配备有机载电池的飞行器具有质量MeVTOL+M电池以及旋翼面积AeVTOL.。对于升起所需的功率PeVTOL/电池适用的是
Figure BDA0002118219260000021
当从飞行器中移除电池时，对于该飞行器升起所需的功率PeVTOL适用的是
Figure BDA0002118219260000022
具有自身旋翼的电池可能具有质量M电池+M上部机和旋翼面积A电池。在这种情况下，对于升起所需的功率适用的是
Figure BDA0002118219260000023
如果满足以下等式，则悬停所需的总功率减小，从而使得带有耦合的自主飞行器电池的、电驱动的VTOL可能是有利的：
Figure BDA0002118219260000024
发明内容
因此，本发明根据优选技术方案提供一种飞行器(尤其全电动的、如上所述可竖直地起飞和降落的飞行器)以及一种用于这种飞行器的电力供应系统。
本发明的其他有利的设计方案在可选技术方案中给出。因此，例如该飞行器可以设计有被折弯的或者甚至选择性地能够折弯的机翼。对应的变体增大了水平飞行中有效的机翼面积，而不扩展飞行器的占地面积。
此外，该飞行器能够具有可快速充电的电池系统，该电池系统提供用于竖直起飞和降落以及水平飞行的驱动能量并且可以实现能够对飞行器进行短暂的充电。
在此，为了驱动飞行器，可以使用不同尺寸的多个涵道风扇式螺旋桨(ductedfans)来代替自由旋翼，例如这些涵道风扇式螺旋桨在航空技术以外如从气垫船或风扇船(Sumpfbooten)中已知。在这种实施方式中，包围螺旋桨的柱形壳体由于叶片尖端处的湍流而能够明显减小推进损失。适合的涵道风扇式螺旋桨能够水平地或竖直地定向、在这两种位置之间可枢转地实施、或者出于空气动力学原因在水平飞行中由片(louvers)遮盖。此外可设想借助固定的涵道风扇式螺旋桨产生纯水平的推进。
最后，除了飞行器的优选完全自主的运行之外，在资格足够的情况下也考虑允许人类飞行员手动控制，这使得根据本发明的设备在操纵中被赋予最大可能的灵活性。
附图说明
本发明的实施例在附图中示出并将在下文中更详细地说明。
图1示出根据本发明的飞行器的升起。
图2示出在飞行器过渡至巡航飞行之前的飞行器。
具体实施方式
图1和2以其概览图展示了根据本发明的飞行器10的优选设计方案的结构性和功能性特征。
在图1中示出的起飞期间，借助飞行器10与无人机12之间的通信连接18彼此协调的旋翼系统11，13共同升起。在此，飞行器10是主导设备(主动)而配备有自身的电池15的无人机12是随从设备(从动)。两个电池15是彼此连接的并且给飞行器10以及无人机12的旋翼13供电。无人机12的机载的直流变压器(DC-to-DC converter，14)确保电压一致并且控制能量流。
当达到过渡高度时，自主的电池无人机12脱开并飞回地面。随后，飞行器10仅用其自身的机载电池15继续飞行。

Claims (10)

1.一种用于飞行器(10)的电力供应系统，
其特征在于以下特征：
-该电力供应系统包括能够飞行的无人机(12)，该无人机带有旋翼(13)、直流变压器(14)、用于驱动所述旋翼(13)的电池(15)、以及用于固定该无人机(12)与该飞行器(10)之间的插接连接(16)的锁定装置(17)，
-该无人机(12)被设置为，借助该锁定装置(17)来固定该插接连接(16)，直到该飞行器(10)达到预定的飞行高度，并且
-该电力供应系统被配置成使得只要存在该插接连接(16)，则该电池(15)就借助该直流变压器(14)向给该飞行器(10)供电。
2.根据权利要求1所述的电力供应系统，
其特征在于以下特征：
-该无人机(12)进一步被设置为，当达到该飞行高度时自主地返回近地面。
3.根据权利要求1或2所述的电力供应系统，
其特征在于以下特征：
-该无人机(12)进一步被设置为用于与该飞行器(10)形成通信连接(18)以协调共同的飞行行为。
4.一种飞行器(10)，
其特征在于以下特征：
-该飞行器(10)具有根据权利要求1至3之一所述的电力供应系统，并且
-该飞行器(10)具有全电动的驱动器。
5.根据权利要求1至4之一所述的飞行器(10)，
其特征在于以下特征：
-该飞行器(10)包括折弯的或能够折弯的机翼。
6.根据权利要求1至5之一所述的飞行器(10)，
其特征在于以下特征：
-该飞行器(10)包括能够快速充电的电池系统。
7.根据权利要求1至6之一所述的飞行器(10)，
其特征在于以下特征：
-该飞行器(10)包括用于起飞和降落的水平固定的涵道风扇式螺旋桨(11)。
8.根据权利要求7所述的飞行器(10)，
其特征在于以下特征：
-该飞行器(10)具有多个片，并且
-水平固定的所述涵道风扇式螺旋桨(11)能够借助这些片选择性地被遮盖。
9.根据权利要求1至8之一所述的飞行器(10)，
其特征在于以下特征：
-该飞行器(10)包括用于产生推进的竖直固定的涵道风扇式螺旋桨。
10.根据权利要求1至9之一所述的飞行器(10)，
其特征在于以下特征：
-该飞行器(10)能够选择性地全自主地控制。
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