CN110683046B - 飞行器 - Google Patents

飞行器 Download PDF

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CN110683046B
CN110683046B CN201910597976.4A CN201910597976A CN110683046B CN 110683046 B CN110683046 B CN 110683046B CN 201910597976 A CN201910597976 A CN 201910597976A CN 110683046 B CN110683046 B CN 110683046B
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aircraft
battery
energy
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vehicle
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CN110683046A (zh
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M·米勒
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Dr Ing HCF Porsche AG
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L58/00—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
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Abstract

本发明提供一种飞行器(10)，该飞行器具有以下特征：所述飞行器(10)包括第一电池(11)；所述飞行器(10)包括带有第二电池(14)的用于短途的运输工具(13)；并且所述飞行器(10)包括用于在所述第一电池(11)与所述第二电池(14)之间传输能量的管理系统。

Description

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、可垂直地起飞和降落(verticaltake-off and landing，VTOL)的飞行器。
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，其能够基本垂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)以及可垂直升降的飞机。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垂直地降落(short take-off and verticallanding，STOVL)、或垂直地起飞但水平地降落(vertical take-off and horizontallanding，VTHL)的飞行器。
CN 1288843 A公布了一种没有自身的蓄能器的用于可垂直起飞的飞行器的救生舱。
CN 1772561 A描述了一种用于VTOL的、带有降落伞的救生舱(参见第14页上的图11)。
US 3113747 A涉及一种VTOL飞行器和可独立降落的牵引车的组合，其中然而后者并没有运输飞行器乘客的能力。
DE 102010003760 A1涉及一种方法，该方法用于基于能量消耗模型、可用的能量量和道路数据库来管理带有电动驱动器的载具的续航里程。
DE 10252292 A1说明了一种用于控制交通工具中能量分配的方法，该方法包括以下步骤：建立能量源的价值-数量函数，建立能量阱(Energiesenken)的价值-数量函数，将能量源和能量阱的价值-数量函数传输给计算装置，根据价值-数量函数计算当前的价值，并且将当前价值传输给能量阱和能量源。就能量阱而言，价值-数量函数说明了怎样获取特定的功率；而就能量源而言，价值-数量函数说明了，用于输出特定功率所限定的就绪程度有多大，并且其中计算出的价值是指交通工具内部功率的供给和需求程度，在此考虑了输出就绪程度和获取功率的重要性。
发明内容
本发明提供了一种根据优选技术方案的飞行器，尤其一种全电动的、按上述意义可垂直起降的飞行器。
本解决方案的优点在于，提高了本发明所述飞行器的个性化续航里程以及为顾客使用而集成的灵活性。在此，本发明所述的方案大体上可以被转让用于各种集成的运输系统，所述运输系统包括分配有一个或多个子系统或补充系统的主运输系统并且允许在总距离上将能量有效分配到不同的运输工具上。
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垂直起降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
附图中展示了本发明的一个实施例且将在下文中进行更详细的说明。
附图展示了一个根据本发明设计方案的飞行器。
具体实施方式
唯一的附图展示了本发明的飞行器(10)的优选设计方案的结构上的特征。
如图中可以轻松看出地，在VTOL——飞行器(10)中存在结构空间(12)，该结构空间用于以节省空间的方式放置至少一个适合短途的单人运输工具(13)。在此，集成有电气/电子接口。通过该方式，提供了主运载系统和第二辅助运载系统，以便借此使用户到达其目标。这两个系统构成虚拟单元，该虚拟单元通过由计算机支持的系统协调。
例如，如果用户想要借助该电力推进工具(10)经过一段已知的距离，则为此需要特定的能量量。为此，能量管理系统确定针对不同的运载工具、针对相应的续航里程所需的相应能量量。使用该能量量对相应的运载工具充电或者可以在运行期间对能量进行重新分配。在已知总续航里程的情况下，所述能量或续航里程管理系统为此目的给负责所述距离的主要部分的系统(10，13)分配较大比例的能量，而给其他系统(13，10)分配较小比例的能量。
通过这种方式可以在初级的飞行器(10)与下级的运输工具(13)之间按需求(例如依赖于两个载具的续航里程)相似地“移动”能量。尤其在紧急情况下，VTOL飞行器(10)还可以从短途运输工具(13)的蓄积器中获取额外的能量。
用户(15)可以通过这种方式利用VTOL——飞行器(10)靠近其目的地(17)，并且然后用其他运输工具(13)经过剩余的距离(16)。在不脱离本发明范围的情况下，可设想的是甚至在这个象征意义上的“最后一英里”内进行自主导航。

Claims (5)

1.一种飞行器，包括：
-第一电池，
-飞行器的推进系统，该推进系统由所述第一电池供电，
-至少一个运输工具，其呈辅助飞行器的形式并且放置在所述飞行器内，所述辅助飞行器具有第二电池，并且
-用于在所述飞行器的第一电池与所述辅助飞行器的第二电池之间传输能量的管理系统，
其中，在前往预定目的地的途中，所述管理系统被配置成取决于所述飞行器和所述辅助飞行器到预定目的地的剩余距离将一定比例的能量转移到所述第一电池和所述第二电池。
2.根据权利要求1所述的飞行器，还包括：
-在所述第一电池与所述第二电池之间的电气或电子连接。
3.根据权利要求1所述的飞行器，其特征在于：
-所述飞行器具有全电动的驱动器。
4.根据权利要求1所述的飞行器，其特征在于：
-所述飞行器包括能够快速充电的电池系统。
5.根据权利要求1所述的飞行器，还包括：
-所述辅助飞行器的推进工具，其由所述第二电池供电。
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