WO2019170158A1 - 变体平流层飞艇 - Google Patents

变体平流层飞艇 Download PDF

Info

Publication number
WO2019170158A1
WO2019170158A1 PCT/CN2019/077575 CN2019077575W WO2019170158A1 WO 2019170158 A1 WO2019170158 A1 WO 2019170158A1 CN 2019077575 W CN2019077575 W CN 2019077575W WO 2019170158 A1 WO2019170158 A1 WO 2019170158A1
Authority
WO
WIPO (PCT)
Prior art keywords
airship
capsule
closed
ballonet
folded
Prior art date
Application number
PCT/CN2019/077575
Other languages
English (en)
French (fr)
Inventor
赵明
周萌
谭百贺
徐忠新
鞠金彪
李琦
袁军行
Original Assignee
中国电子科技集团公司第三十八研究所
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
Application filed by 中国电子科技集团公司第三十八研究所 filed Critical 中国电子科技集团公司第三十八研究所
Publication of WO2019170158A1 publication Critical patent/WO2019170158A1/zh
Priority to US17/015,247 priority Critical patent/US11459080B2/en

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/02—Non-rigid airships
    • B64B1/04—Non-rigid airships the profile being maintained by ties or cords connecting opposite surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/58—Arrangements or construction of gas-bags; Filling arrangements

Definitions

  • the invention relates to the technical field of airships, and in particular to a variant stratospheric airship.
  • the airship is an aircraft that relies on buoyancy to overcome its own weight and has the advantages of long empty time and high cost-effectiveness.
  • the airships of the conventional primary and secondary airbag structures are limited by the volume of the sub-bags, and the lift-off height is limited.
  • Increasing the volume of the sub-balloon can increase the altitude of the airship, but the energy and weight requirements of the pressure regulation system will be very large.
  • the conventional axial fan has a low head and the capsule is difficult to maintain.
  • the existing variant airship adopts a segmented hard skin, and the shape of the hull is changed by coordinating the movement of the telescopic struts and the fixed length struts on the foldable frame to achieve the boat volume (airship volume). change. Due to the heavy weight of the hard skin structure and the difficulty in ensuring airtightness, it is difficult to achieve safe use.
  • a flap type airbag is often used, and the natural shape of the airbag is forcibly changed during the modification process, and the airbag is unevenly stressed, which tends to cause stress concentration of the capsule body, which has a risk of damage and a poor deformation effect.
  • the present invention provides a variant stratospheric airship that uses an integral closed capsule and controls the tensioning of the closed capsule by using a wire arranging mechanism to control the tensioning cable outside the closed capsule. Expand.
  • the present invention provides a variant stratospheric airship, comprising: an upper casing, a lower casing, a folded capsule, and a row disposed on the upper casing and the lower casing Line mechanism
  • the folding capsule comprises a closed capsule, a guiding hole disposed outside the closed capsule, and a tension cable passing through the guiding hole in a set order, the tension cable being used for Maintaining the shape of the closed capsule, the tension cable is connected to the wire arranging mechanism, and the closed capsule is fixed to the upper and lower casings, and the wire arranging mechanism controls the
  • the length of the cable is such that the folded bladder can be folded and unfolded in the vertical direction of the airship.
  • the outer side of the closed capsule is further provided with a conformal cord, and the guiding hole is disposed on the conformal cord.
  • the upper and lower casings include a skin and a rigid support skeleton supporting the skin.
  • the rigid support skeleton comprises an annular truss and a plurality of transverse keels and longitudinal keels.
  • annular truss and the transverse keel and the longitudinal keel are respectively composed of carbon fiber frame structural members.
  • the skin is a flexible capsule or a rigid sheet.
  • the wire arranging mechanism is mounted on the annular truss of the upper and lower casings, and the wire arranging mechanisms are connected to each other by the tensioning cable.
  • the airship further includes a tail fin, a propeller, a valve and a battery mounted on the top of the upper casing.
  • the battery is a solar battery.
  • the airship further includes a nacelle, a landing gear and a mission load installed at the bottom of the lower casing.
  • the variant stratospheric airship of the present invention when flying at low altitude, receives the tension line cable through the cable arranging mechanism, so that the capsule body is in a folded state, and the airship has a low-resistance flat shape; when flying at a high altitude, the floating gas in the capsule expands.
  • the cable arranging mechanism releases the cable, the capsule is vertically deployed, and the airship is increased in volume.
  • the airship of the invention has a simple form and a light structure, thereby facilitating operation and use, and at the same time, an integral closed capsule is used, and the shape is maintained by the tension cable, so that the airbag is not easily deformed, and the use is safe and reliable.
  • Fig. 1 is a schematic view showing the structure of a variant stratospheric airship according to an embodiment of the present invention.
  • Fig. 2 is a schematic view showing the structure of a folded capsule according to an embodiment of the present invention.
  • Fig. 3 is a schematic view showing the structure of a rigid support frame according to an embodiment of the present invention.
  • Figure 4 shows a top plan view of the upper housing of the variant stratospheric airship of the present invention.
  • Fig. 5 is a schematic view showing a variant process of a variant stratospheric airship according to an embodiment of the present invention.
  • Figure 1 is a schematic view showing the structure of a variant stratospheric airship of the present invention.
  • a variant stratospheric airship specifically includes an upper casing 1, a lower casing 2, a folded capsule 3, and the upper casing 1 and the lower casing 2. Cable arranging mechanism 4.
  • the folded capsule 3 includes a closed capsule 31, a guide hole 7 provided outside the closed capsule, and a tension cable 6 passing through the guide hole 7 in a set order.
  • the tension cable 6 is used to maintain the shape of the closed capsule 31, and the tension cable 6 is connected to the wire arranging mechanism 4, and the closed capsule 31 is fixed to the upper casing 1 and the lower casing 2, and the wire arranging mechanism 4 is controlled.
  • the cable 6 is tensioned so that the folded capsule 31 can be folded and unfolded in the vertical direction of the airship.
  • the outer side of the closed capsule 31 is further provided with a conformal cord 32, and a guiding hole 7 is formed at a corresponding position on the conformal cord 32, and the tensioning cable 6 sequentially passes through the guiding hole 7 according to the designed wiring manner. Controlling the length of the tension cable 6 by the wire arranging mechanism 4 enables the closed capsule to be folded and unfolded in the vertical direction. In this configuration, the tension cable passes through the guide hole and serves as a guiding action to prevent the folded capsule 3 from shaking during flight.
  • the upper and lower housings 1 and 2 are comprised of a skin and a rigid support frame that supports the skin.
  • the rigid support frame includes an annular truss 15 and a plurality of transverse keels 14 and longitudinal keels 13.
  • the truss 15 and the keels 13 and 14 are composed of small sections of carbon fiber frame structural components for easy assembly and disassembly.
  • the skin can be made of a flexible pouch or a rigid sheet as needed.
  • the wire arranging mechanism 4 is mounted on the annular truss 15 of the upper and lower casings 1 and 2, and the wire arranging mechanisms 4 are connected to each other by the tensioning cable 6.
  • the airship of the embodiment of the present invention further includes a tail fin 11, a pusher 8, a valve 9, and a battery 12 mounted on the top of the upper casing 1.
  • the battery 12 can be a solar cell that is laid over the top flat space of the upper housing 1.
  • the empennage 11 is used to implement motion control of the airship's roll, yaw, pitch, etc.
  • the propeller is used to drive the airship
  • the valve 9 is an exhaust valve that closes the floating gas (helium or hydrogen) in the airbag.
  • the bottom of the lower casing 2 of the airship is further provided with a nacelle 5, and an airship common device such as an inflation port, a landing gear and a mission load which are not shown.
  • the floating gas in the bladder expands, the wire arranging mechanism releases the tension cable, the capsule body is vertically expanded, and the airship is increased in volume.
  • the tension wire is pulled through the cable arranging mechanism, so that the capsule is gradually folded and finally folded, and the airship has a low-resistance flat shape.
  • the airship of the invention has the advantages of simple form and light structure, thereby being convenient for operation and use, and at the same time, an integral closed capsule is used, and the shape is maintained by the tension cable, so that the airbag structure is not easily deformed, and the use is safe and reliable.

Abstract

一种变体平流层飞艇包括：上壳体（1）、下壳体（2）、折叠囊体（3）、以及设置在所述上壳体和下壳体上的排线机构（4）；其中所述折叠囊体包括封闭囊体（31）、设置在所述封闭囊体外部的导引孔（7）以及依照设定顺序穿过所述导引孔的张线拉索（6），所述张线拉索用于保持所述封闭囊体的形状，所述张线拉索与所述排线机构连接，将所述封闭囊体与所述上壳体和下壳体固定，所述排线机构通过控制所述张线拉索的长度，使得所述折叠囊体可沿飞艇竖直方向折叠和展开。所述飞艇使用整体式的封闭囊体，并通过使用排线机构对封闭囊体外侧的张线拉索进行控制，从而实现封闭囊体的折叠和展开。

Description

变体平流层飞艇 技术领域
本发明涉及飞艇技术领域，尤其涉及一种变体平流层飞艇。
背景技术
飞艇是一种依靠浮力克服自身重量升空的飞行器，有着留空时间长、效费比高等优点。传统主、副气囊结构的飞艇受副气囊体积限制，升空高度有限。增大副气囊体积可以提高飞艇升空高度，但随之压力调节系统对能源、重量的需求都会非常巨大；随着飞艇升空高度的增加，常规轴流风机压头低，囊体保持外形困难，必须用重量大、结构复杂的风机；低空时，巨大的副气囊体积导致平流层飞艇惯量巨大，低空返场飞行对能源、动力的需求高，操纵困难，同时着陆的危险性也高。
现有的变体式飞艇，采用分段式硬蒙皮，通过可折叠式隔框上的伸缩支杆和定长支杆协调动作之后使艇体剖面形状改变，从而达到艇容积(飞艇体积)的改变。由于硬蒙皮结构重量大，且气密性难以保证，从而难以达到安全使用的目的。
另外，现有的飞艇中常使用瓣型气囊，该气囊在变体过程中自然外形被强制改变，气囊受力不均匀，容易造成囊体应力集中，存在破坏风险，且变形效果不佳。
发明内容
基于上述问题，本发明提供一种变体平流层飞艇，使用整体式的封闭囊体，并通过使用排线机构对封闭囊体外侧的张线拉索进行控制，从而实现封闭囊体的折叠和展开。
为解决上述问题，本发明提供了一种变体平流层飞艇，其特征在于，包括：上壳体、下壳体、折叠囊体、以及设置在所述上壳体和下 壳体上的排线机构；
其中，所述折叠囊体包括封闭囊体、设置在所述封闭囊体外部的导引孔以及依照设定顺序穿过所述导引孔的张线拉索，所述张线拉索用于保持所述封闭囊体的形状，所述张线拉索与所述排线机构连接，将所述封闭囊体与所述上壳体和下壳体固定，所述排线机构通过控制所述张线拉索的长度，使得所述折叠囊体可沿飞艇竖直方向折叠和展开。
其中，所述封闭囊体外部还设置有保形帘布，所述导引孔设置在所述保形帘布上。
其中，所述上壳体和下壳体包括蒙皮以及支撑所述蒙皮的刚性支撑骨架。
其中，所述刚性支撑骨架包括环形桁架和多个横向龙骨和纵向龙骨。
其中，所述环形桁架和横向龙骨、纵向龙骨分别由碳纤维框架结构件组成。
其中，所述蒙皮为柔性囊皮或刚性薄板。
其中，所述排线机构安装在所述上壳体和下壳体的环形桁架上，通过所述张线拉索将所述排线机构相互连接。
其中，所述飞艇还包括安装于所述上壳体顶部的尾翼、推进器、阀门和电池。
其中，所述电池为太阳能电池。
其中，所述飞艇还包括安装于所述下壳体底部的吊舱、起落架和任务载荷。
本发明的变体平流层飞艇，当低空飞行时，通过排线机构收紧张线拉索，使得囊体处于折叠状态，飞艇为低阻扁平外形；当高空飞行时，囊内浮升气体膨胀，排线机构释放张线拉索，囊体竖向展开，飞艇体积增大。本发明的飞艇形式简单、结构轻便、从而便于操作和使 用，同时使用一个整体的封闭囊体，并通过张线拉索保持形状，使得气囊结果不易发生变形，使用安全可靠。
附图说明
图1示出了本发明实施例的变体平流层飞艇的结构示意图。
图2示出了本发明实施例的折叠囊体的结构示意图。
图3示出了本发明实施例的刚性支撑骨架的结构示意图。
图4示出了本发明的变体平流层飞艇的上壳体的俯视图。
图5示出了本发明实施例的变体平流层飞艇的变体过程示意图。
具体实施方式
下面结合附图和实施例，对本发明的具体实施方式作进一步详细描述。以下实施例用于说明本发明，但不用来限制本发明的范围。
图1示出了本发明的一种变体平流层飞艇的结构示意图。
参照图1，本发明实施例的变体平流层飞艇，其结构具体包括：上壳体1、下壳体2、折叠囊体3、以及设置在所述上壳体1和下壳体2上的排线机构4。
具体地，如图2所示，折叠囊体3包括封闭囊体31、设置在封闭囊体外部的导引孔7以及依照设定顺序穿过导引孔7的张线拉索6。
张线拉索6用于保持封闭囊体31的形状，张线拉索6与排线机构4连接，将封闭囊体31与上壳体1和下壳体2固定，排线机构4通过控制张线拉索6，使得折叠囊体31可沿飞艇竖直方向折叠和展开。
进一步地，封闭囊体31外部还设置有保形帘布32，在保形帘布32上的对应位置开设导引孔7，张线拉索6根据设计的布线方式按序穿过导引孔7，通过排线机构4控制张线拉索6长度，能够使得封闭囊体可以在竖直方向上折叠和展开。此种结构中，张线拉索从导引孔中穿过，起到引导作用，防止折叠囊体3在飞行过程中晃动。
在本发明的实施例中，上壳体1和下壳体2由蒙皮以及支撑蒙皮的刚性支撑骨架构成。如图3所示，刚性支撑骨架包括环形桁架15和多个横向龙骨14和纵向龙骨13。考虑到飞艇的工程可行性，桁架15和龙骨13和14由小段碳纤框架结构件组成，便于组装和拆卸。此外，蒙皮可以根据需要采用柔性囊皮或刚性薄板。
进一步的实施例中，排线机构4安装在上壳体1和下壳体2的环形桁架15上，通过张线拉索6将排线机构4相互连接。
此外，如图1和4所示，本发明的实施例的飞艇还包括安装于上壳体1顶部的尾翼11、推进器8、阀门9以及电池12。在一个实施例中，该电池12可以是太阳能电池，铺设于上壳体1的顶部平坦空间上。
进一步地，尾翼11用于实施对飞艇的滚转、偏航、俯仰等运动控制，推进器用于驱动飞艇，阀门9为封闭气囊内浮升气体(氦气或氢气)的排气阀门。
此外，该飞艇的下壳体2的底部还设置有吊舱5、以及未在图中示出的充气口、起落架和任务载荷等飞艇常用装置。
本发明实施例的变体平流层飞艇，如图5所示，当在高空飞行时，囊内浮升气体膨胀，排线机构释放张线拉索，囊体竖向展开，飞艇体积增大。当飞艇需要降落或在低空飞行时，通过排线机构收紧张线拉索，使得囊体逐渐折叠，最终处于折叠状态，飞艇为低阻扁平外形。
本发明的飞艇形式简单、结构轻便、从而便于操作和使用，同时使用一个整体的封闭囊体，并通过张线拉索保持形状，使得气囊结构不易发生变形，使用安全可靠。
以上实施方式仅用于说明本发明，而并非对本发明的限制，有关技术领域的普通技术人员，在不脱离本发明的精神和范围的情况下，还可以做出各种变化和变型，因此所有等同的技术方案也属于本发明的范畴，本发明的专利保护范围应由权利要求限定。

Claims (10)

  1. 一种变体平流层飞艇，其特征在于，包括：上壳体、下壳体、折叠囊体、以及设置在所述上壳体和下壳体上的排线机构；
    其中，所述折叠囊体包括封闭囊体、设置在所述封闭囊体外部的导引孔以及依照设定顺序穿过所述导引孔的张线拉索，所述张线拉索用于保持所述封闭囊体的形状，所述张线拉索与所述排线机构连接，将所述封闭囊体与所述上壳体和下壳体固定，所述排线机构通过控制所述张线拉索的长度，使得所述折叠囊体沿飞艇竖直方向折叠和展开。
  2. 如权利要求1所述的飞艇，其特征在于，所述封闭囊体外部还设置有保形帘布，所述导引孔设置在所述保形帘布上。
  3. 如权利要求1所述的飞艇，其特征在于，所述上壳体和下壳体包括蒙皮以及支撑所述蒙皮的刚性支撑骨架。
  4. 如权利要求3所述的飞艇，其特征在于，所述刚性支撑骨架包括环形桁架和多个横向龙骨和纵向龙骨。
  5. 如权利要求4所述的飞艇，其特征在于，所述环形桁架和横向龙骨、纵向龙骨分别由碳纤维框架结构件组成。
  6. 如权利要求3所述的飞艇，其特征在于，所述蒙皮为柔性囊皮或刚性薄板。
  7. 如权利要求4所述的飞艇，其特征在于，所述排线机构安装在所述上壳体和下壳体的环形桁架上，通过所述张线拉索将所述排线机构相互连接。
  8. 如权利要求4所述的飞艇，其特征在于，所述飞艇还包括安装于所述上壳体顶部的尾翼、推进器、阀门和电池。
  9. 如权利要求8所述的飞艇，其特征在于，所述电池为太阳能电池。
  10. 如权利要求8所述的飞艇，其特征在于，所述飞艇还包括安 装于所述下壳体底部的吊舱、起落架和任务载荷。
PCT/CN2019/077575 2018-03-09 2019-03-09 变体平流层飞艇 WO2019170158A1 (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US17/015,247 US11459080B2 (en) 2018-03-09 2020-09-09 Transformable stratospheric airship

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201810196120.1A CN108408019A (zh) 2018-03-09 2018-03-09 变体平流层飞艇
CN201810196120.1 2018-03-09

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US17/015,247 Continuation US11459080B2 (en) 2018-03-09 2020-09-09 Transformable stratospheric airship

Publications (1)

Publication Number Publication Date
WO2019170158A1 true WO2019170158A1 (zh) 2019-09-12

Family

ID=63130763

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2019/077575 WO2019170158A1 (zh) 2018-03-09 2019-03-09 变体平流层飞艇

Country Status (3)

Country Link
US (1) US11459080B2 (zh)
CN (1) CN108408019A (zh)
WO (1) WO2019170158A1 (zh)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108408019A (zh) * 2018-03-09 2018-08-17 中国电子科技集团公司第三十八研究所 变体平流层飞艇
CN109572981B (zh) * 2018-12-28 2022-08-19 湖南航天远望科技有限公司 一种高超压低阻临近空间浮空器
CN110001916A (zh) * 2019-04-03 2019-07-12 庆安集团有限公司 一种气动外形可变的飞艇
CN110015396B (zh) * 2019-04-08 2022-05-27 上海交通大学 一种大尺度半刚性结构飞艇
CN110979628B (zh) * 2019-11-29 2021-12-24 北京无线电计量测试研究所 一种智能浮空器及控制终端
CN113173241B (zh) * 2021-06-04 2022-06-03 东南大学 一种可变形的混杂式悬浮飞行器及运行控制方法
CN113247313B (zh) * 2021-07-02 2022-08-19 中国人民解放军战略支援部队航天工程大学 一种用于运载火箭助推器回收的柔性变体飞艇及回收方法
CN114162257B (zh) * 2021-12-22 2022-06-10 盐城工学院 折叠船
WO2023209319A1 (en) 2022-04-24 2023-11-02 Morrey Martin High-altitude aerostat with a large surface area

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101229848A (zh) * 2008-01-23 2008-07-30 哈尔滨工业大学 空中展开式飞艇
WO2013113866A1 (fr) * 2012-02-02 2013-08-08 European Aeronautic Defence And Space Company Eads France Ensemble structural fermé à tenue à la compression améliorée
CN103466070A (zh) * 2013-10-12 2013-12-25 哈尔滨工业大学 非硬式平流层飞艇自由伸缩装置
CN104417743A (zh) * 2013-09-09 2015-03-18 陈德荣 一种囊体伸缩式平流层飞艇
CN104554698A (zh) * 2013-10-10 2015-04-29 陈德荣 一种囊体伸缩式飞艇
CN108408019A (zh) * 2018-03-09 2018-08-17 中国电子科技集团公司第三十八研究所 变体平流层飞艇

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3486719A (en) * 1967-12-04 1969-12-30 Aereon Corp Airship
JP3270895B2 (ja) * 1991-09-09 2002-04-02 エイヴィーインテル・インコーポレーテッド 操縦可能な飛行船
FR2740755B1 (fr) * 1995-11-07 1998-01-16 Bernard Alain Aerostat dirigeable a armature gonflable et a pilotage par balancier
US6371409B1 (en) * 2000-09-22 2002-04-16 Lockheed Martin Corporation At least partially bouyant vehicle with movable solar panel assemblies
WO2011042065A1 (en) * 2009-10-09 2011-04-14 Daniel Monsch "momoheli" lifting module and vehicles
US8678309B2 (en) * 2011-06-13 2014-03-25 Stratospheric Airships, Llc Lifting gas replenishment in a tethered airship system
CA2830799A1 (en) * 2011-03-31 2012-10-04 Lta Corporation Airship including aerodynamic, floatation, and deployable structures
CN105644762B (zh) * 2016-01-19 2017-11-28 北京航空航天大学 一种新型平流层飞艇

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101229848A (zh) * 2008-01-23 2008-07-30 哈尔滨工业大学 空中展开式飞艇
WO2013113866A1 (fr) * 2012-02-02 2013-08-08 European Aeronautic Defence And Space Company Eads France Ensemble structural fermé à tenue à la compression améliorée
CN104417743A (zh) * 2013-09-09 2015-03-18 陈德荣 一种囊体伸缩式平流层飞艇
CN104554698A (zh) * 2013-10-10 2015-04-29 陈德荣 一种囊体伸缩式飞艇
CN103466070A (zh) * 2013-10-12 2013-12-25 哈尔滨工业大学 非硬式平流层飞艇自由伸缩装置
CN108408019A (zh) * 2018-03-09 2018-08-17 中国电子科技集团公司第三十八研究所 变体平流层飞艇

Also Published As

Publication number Publication date
CN108408019A (zh) 2018-08-17
US20210155335A1 (en) 2021-05-27
US11459080B2 (en) 2022-10-04

Similar Documents

Publication Publication Date Title
WO2019170158A1 (zh) 变体平流层飞艇
US11608181B2 (en) Rigidized assisted opening system for high altitude parafoils
US9745042B2 (en) Airship including aerodynamic, floatation, and deployable structures
US11203430B2 (en) Airship launch from a cargo airship with a payload return vehicle
US8544797B2 (en) Cargo carrying air vehicle
WO2021068457A1 (zh) 一种大尺度刚柔一体结构的平流层飞艇
US5005783A (en) Variable geometry airship
US7552893B2 (en) Airship & method of operation
DE102010053372B4 (de) Höhen-Luftfahrzeug
US10457394B2 (en) Airship launch from a cargo airship
US10287000B2 (en) Hybrid lighter-than-air vehicle
EP2712346B1 (en) Airborne platform
US5697579A (en) Aircraft having inflatable tubular support structure
US20130068879A1 (en) Wing-in-ground effect vessel
US9522733B2 (en) Airship launch from a cargo airship
CN104276281A (zh) 一种单人飞行器
US20080035787A1 (en) Lighter-than-air gas handling system and method
RU2141911C1 (ru) Комбинированный полужесткий управляемый летательный аппарат легче воздуха
CN103569345B (zh) 半开放式飞艇
CN112224381B (zh) 一种变体飞艇及变形装置
JP2001030995A (ja) 弾性体の曲げ張力で補強された膜構造を持つ飛行体
Nachbar et al. Next generation thermal airship
CN113022846B (zh) 一种混合模式飞行器
KR20230041968A (ko) 적어도 하나의 수류 터빈을 예인하는 공기 예인 선박을 포함하는 전력 생산 디바이스
DE19944199A1 (de) Faltenflugkörper mit Auftriebssteuerung

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19763286

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 19763286

Country of ref document: EP

Kind code of ref document: A1