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11. 发明授权

US10843784B2 Hydrogen recycling flight system and flight method 有权
公开(公告)号：US10843784B2
公开(公告)日：2020-11-24
申请号：US15758870
申请日：2015-12-03
申请人： UNIVERSITY OF SEOUL INDUSTRY COOPERATION FOUNDATION
发明人： Byung Deok Yu , Hyunsoo Min , Junjin Jeon
IPC分类号： B64B1/24 , H02S20/30 , H02S10/10 , B64B1/64 , C25B15/02 , B64B1/00 , H02J15/00 , H01M8/04082 , B64D27/24 , B64B1/62 , B64B1/36 , B64D41/00 , H02S10/20 , B64B1/20 , B64D9/00 , C25B1/04 , H01M8/0432 , H01M8/0438 , H01M8/04746 , H01M8/0656 , H01M10/46 , H01M16/00 , H02J7/34 , H02J7/35 , H01M8/04119
CPC分类号： B64B1/24 , B64B1/00 , B64B1/20 , B64B1/36 , B64B1/62 , B64B1/64 , B64D9/00 , B64D27/24 , B64D41/00 , C25B1/04 , C25B15/02 , H01M8/0432 , H01M8/0438 , H01M8/04208 , H01M8/04776 , H01M8/0656 , H01M10/465 , H01M16/006 , H02J7/34 , H02J7/35 , H02J15/00 , H02S10/10 , H02S10/20 , H02S20/30 , B64B2201/00 , B64D2211/00 , B64D2221/00 , H01M8/04156 , H01M2220/20 , H01M2250/20 , H01M2250/402 , Y02B90/10 , Y02E60/32 , Y02E60/36 , Y02E60/50 , Y02P20/129 , Y02T90/40
摘要： The present invention relates to a hydrogen recycling flight system and flight method, the hydrogen recycling flight system including: a flight fuselage which has at least one pair of wings at each of both sides of a body; a hydrogen gas balloon which is air-tightly connected to the flight fuselage; a hydrogen fuel cell which is connected with the hydrogen gas balloon and is installed outside or inside the flight fuselage; and a secondary battery which is charged with electricity generated from the hydrogen fuel cell, electricity generated from a solar cell provided at an outer peripheral portion of the flight fuselage, or electricity of an external power network, in which by using a switch, the hydrogen fuel cell is switched to a water electrolysis device or the water electrolysis device is switched to the hydrogen fuel cell, the hydrogen recycling flight system includes: a water tank which stores water generated from the hydrogen fuel cell; the water electrolysis device which electrolyzes the stored water; a switch control device which switches functions of the hydrogen fuel cell and the water electrolysis device; and a high-pressure gas barrel which high-pressure stores hydrogen gas and oxygen gas generated in the water electrolysis device, and the flight fuselage flies by controlling the volume of the hydrogen gas balloon that is flotation power of a flight vehicle by an operation of the hydrogen fuel cell or the high-pressure gas barrel.

12. 发明授权

US10301002B2 Hot air balloon steering system 有权
公开(公告)号：US10301002B2
公开(公告)日：2019-05-28
申请号：US15407861
申请日：2017-01-17
申请人： Chris D. Palmby
发明人： Chris D. Palmby
IPC分类号： B64B1/42 , B64D9/00 , B64B1/00
摘要： A hot air balloon steering system for steering a hot air balloon includes a hot air balloon that includes a basket. A stand unit is movably coupled to the basket. The stand unit abuts a support surface thereby facilitating the basket to be spaced from the support surface when the hot air balloon is not in flight. A sail unit is movably coupled to the basket. The sail unit captures air when the hot air balloon is in flight. Moreover, the sail unit steers the hot air balloon when the hot air balloon is in flight.

13. 发明授权

US10246176B2 Automated balloon launching system and method for launching 有权
公开(公告)号：US10246176B2
公开(公告)日：2019-04-02
申请号：US15229248
申请日：2016-08-05
申请人： Vaisala Oyj
发明人： Ismo Leinonen , Tuomo Saari
IPC分类号： G01W1/08 , B64B1/00 , B64B1/40 , B64B1/62
摘要： According to an example aspect of the present invention, there is provided an automated balloon launching system for launching at least one balloon such as a meteorological balloon or a radiosonde. The system comprises a container and a storage arranged in the container for storing at least one box at a defined storage position p=1, 2, . . . , n. The at least one box includes a balloon and a sonde. A release silo is arranged at least partially on top of or above and adjacent to the container for sheltering the balloon during inflation. A x-, y- and z-manipulator is arranged in the container for removing a specific box from one of the defined storage positions p=1, 2, . . . , n, and for subsequent feeding the release silo with the specific box. The present invention also concerns a method for launching at least one balloon such as a meteorological balloon or a radiosonde.

14. 发明授权

US09840318B2 Lenticular airship and associated controls 有权
公开(公告)号：US09840318B2
公开(公告)日：2017-12-12
申请号：US14080314
申请日：2013-11-14
申请人： Pierre Balaskovic
发明人： Pierre Balaskovic
IPC分类号： B64C13/18 , B64B1/00 , B64B1/34 , B64B1/36 , B64C13/04 , B64D43/00
CPC分类号： B64B1/00 , B64B1/34 , B64B1/36 , B64C13/04 , B64D43/00 , Y02T50/44
摘要： A system for controlling yaw associated with an airship may include one or more vertical control surfaces associated with the airship, a first power source and a second power source, each configured to provide a thrust associated with the airship, and a yaw control configured to receive an input indicative of a desired yaw angle. The system may further include a controller communicatively connected to the yaw control, the one or more vertical control surfaces, and the first and second power sources. The controller may be configured to receive an output signal from the yaw control corresponding to the desired yaw angle and to generate a control signal configured to modify a state associated with at least one of the one or more vertical control surfaces, the first power source, and the second power source, such that the airship substantially attains the desired yaw angle.

15. 发明授权

US09809293B2 Methods and mechanisms for balloon launching 有权
公开(公告)号：US09809293B2
公开(公告)日：2017-11-07
申请号：US15086918
申请日：2016-03-31
申请人： X Development LLC
发明人： Daniel Ratner
IPC分类号： B64B1/40 , B64B1/00 , B64F1/04 , B64B1/58
CPC分类号： B64B1/005 , B64B1/40 , B64B1/58 , B64F1/04
摘要： A method for balloon launching may include loading a pre-packaged balloon and payload into a shell structure. The pre-packaged balloon may be pulled out of its packaging in a vertical direction, for instance using a gantry crane. The gantry crane may be configured to inflate the balloon from the top of the envelope. The balloon may be inflated while substantially within the shell structure, which may provide protection from wind gusts. A vehicle, such as a heavy forklift, may provide mobility and support for the balloon and shell. Once the balloon is inflated, the vehicle may move the balloon/shell combination at a rate and direction substantially matching the current wind direction/speed. Furthermore, after reaching a zero-velocity condition relative to the wind, the vehicle may assist and/or initiate the opening of the shell. A tether connecting the balloon to the shell structure may be disconnected, allowing the balloon to launch.

16. 发明授权

US09775305B2 Method for controlling land surface temperature using stratospheric airships and reflector 有权
公开(公告)号：US09775305B2
公开(公告)日：2017-10-03
申请号：US15011359
申请日：2016-01-29
申请人： KOREA AEROSPACE RESEARCH INSTITUTE
发明人： Joon-Min Choi
IPC分类号： G02B26/02 , A01G15/00 , G02B7/183 , G02B19/00 , F24J2/10 , A45B23/00 , G02B7/00 , G02B7/18 , G02B5/08 , G02B5/09 , B64B1/00
CPC分类号： A01G15/00 , A45B23/00 , A45B2023/0093 , B64B1/00 , F24S23/70 , F24S23/77 , G02B5/08 , G02B5/09 , G02B7/00 , G02B7/18 , G02B7/183 , G02B19/00 , G02B19/0019 , G02B19/0042 , G02B26/02
摘要： The present invention relates to a method for controlling land surface temperature using stratospheric airships and a reflector. In the method for controlling land surface temperature using stratospheric airships and a reflector, four corners are connected to a lower end of support lines coupled to be disposed vertically downward from a plurality of airships, and sunlight is reflected by a reflector unfolded into a tetragonal shape in the air, wherein the reflecting surface of the reflector plate is maintained at an angle to remain perpendicular to an incident angle of sunlight to shield, or redirect, the land surface from incident sunlight.

17. 发明授权

US09302788B2 Stratospheric-airship-assisted orbital payload launching system 有权
标题翻译：平流层 - 飞艇辅助轨道载荷发射系统
公开(公告)号：US09302788B2
公开(公告)日：2016-04-05
申请号：US14282987
申请日：2014-05-20
申请人： Li Wan
发明人： Li Wan
IPC分类号： B64C37/02 , B64G1/00 , B64B1/00 , B64G1/40 , B64G1/62 , B64G1/64 , B64G1/52 , B64B1/62
CPC分类号： B64G1/005 , B64B1/00 , B64B1/005 , B64B1/06 , B64B1/60 , B64B1/62 , B64D5/00 , B64G1/00 , B64G1/14 , B64G1/40 , B64G1/401 , B64G1/402 , B64G1/52 , B64G1/62 , B64G1/64 , B64G5/00
摘要： The present invention is a stratospheric-airship-assisted orbital payload launching system that features with high reusability ratio, low cost, short launch-preparation time and robust reliability. The system consists of an airship-based stratospheric launch platform (1), a stratospheric-launched suborbital shuttle (2, SLSS) and an upper stage (3, a modified version of conventional upper stage or a spaceplane). The airship-based stratospheric launch platform (1) employs hydrogen and helium to provide buoyancy in its ascent and high-altitude cruise stages. Given the substantially lower ambient pressure, the usage of hydrogen at high altitude is much safer than on the ground. The SLSS (2) is mounted beneath the platform (1), and an assembly of payload (4) and upper stage (3) is loaded in the cargo bay (2B) of SLSS (2). In a typical orbital payload launching mission, the airship-based stratospheric launch platform (1) ascends to a predetermined altitude in stratosphere, where the air density is much lower than the sea level and wind is relatively slow and steady comparing with the upper troposhere, and then launches the SLSS (2) in a predetermined position and time. After the SLSS (2) is launched, the platform (1) vents hydrogen lifting gas to swiftly unload the extra buoyancy. Subsequently, the platform (1) descends and returns to its ground base. Meanwhile, the SLSS (2) rockets to a predetermined velocity and altitude (above the atmosphere), opens its cargo bay doors (2D) and releases its cargo (i.e., the assembly of upper stage (3) and payload (4)). The upper stage (3) ignites and propels the payload to a predetermined space orbit. At the same time, the SLSS (2) re-enters, and decelerates via aerobraking. It is finally recovered via a conventional wheel landing.
摘要翻译：本发明是具有高可重用性，低成本，短启动准备时间和鲁棒可靠性的平流层 - 飞艇辅助轨道有效载荷发射系统。该系统由基于飞艇的平流层发射平台（1），平流层发射的眶下穿梭（2，SLSS）和上段（3，常规上段或空间飞机的修改版本）组成。基于飞艇的平流层发射平台（1）采用氢气和氦气在其上升和高空巡航阶段提供浮力。考虑到环境压力大大降低，高空使用氢气比地面上安全得多。 SLSS（2）安装在平台（1）下方，有效载荷（4）和上部（3）的组件装载到SLSS（2）的货舱（2B）中。在典型的轨道有效载荷发射任务中，基于飞艇的平流层发射平台（1）上升到平流层预定的高度，空气密度远低于海平面，与上层相比，风相对较慢，稳定，然后在预定的位置和时间上启动SLSS（2）。 SLSS（2）启动后，平台（1）通过排气提升气体，迅速卸载额外的浮力。随后，平台（1）下降并返回其底座。同时，SLSS（2）火箭以预定的速度和高度（大气层以上）打开货舱门（2D）并释放其货物（即上级（3）和有效载荷（4））。上级（3）点燃并将有效载荷推进到预定的空间轨道。同时，SLSS（2）重新进入，并通过航空制动减速。最终通过传统的轮辋着陆来恢复。

18. 发明申请

US20160083067A1 DURABLE AIRSHIP HULL AND IN SITU AIRSHIP HULL REPAIR 审中-公开
公开(公告)号：US20160083067A1
公开(公告)日：2016-03-24
申请号：US14953985
申请日：2015-11-30
申请人： Stratospheric Airships, LLC
发明人： Stephen B. Heppe
IPC分类号： B64B1/00 , G01M3/00 , G01M3/38 , B64F5/00 , G01M3/16
CPC分类号： B64B1/58 , B29C65/50 , B29C65/70 , B29C70/80 , B29C73/02 , B29C73/10 , B29K2995/0005 , B29L2009/00 , B29L2031/3076 , B64B1/00 , B64B1/14 , B64B1/60 , B64F5/40 , B64F5/60 , G01M3/002 , G01M3/16 , G01M3/38 , Y10T29/49718
摘要： A system for airship hull reinforcement and in-situ repair includes a sensor for detecting a leak in the airship hull of a lighter-than-air airship and a repair mechanism inside lighter-than-air airship for dispensing repair material to seal the leak. A durable airship hull includes an inner gas barrier, an outer gas barrier, and a microlattice layer sandwiched between the inner gas barrier and the outer gas barrier.

19. 发明申请

US20160023747A1 HYBRID LIGHTER-THAN-AIR VEHICLE 审中-公开
公开(公告)号：US20160023747A1
公开(公告)日：2016-01-28
申请号：US14746332
申请日：2015-06-22
申请人： Scott R. Kempshall
发明人： Scott R. Kempshall
IPC分类号： B64C3/38 , B64B1/00
CPC分类号： B64C3/38 , B64B1/00 , B64B2201/00 , B64C3/46 , B64D27/02 , B64D2211/00
摘要： The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The aircraft may include variable span, length, and camber. The variability of the structure and the flexible envelope allows the aircraft to adjust its aspect ratio along with the camber of the upper and/or lower surfaces to achieve varying shapes. This transformation changes both the lift and drag characteristics of the craft and may be accomplished while the craft is airborne.

20. 发明申请

US20150028154A1 System, method and apparatus for widespread commercialization of hydrogen as a carbon-free alternative fuel source 有权
标题翻译：氢作为无碳替代燃料源广泛商业化的系统，方法和装置
公开(公告)号：US20150028154A1
公开(公告)日：2015-01-29
申请号：US14324124
申请日：2014-07-04
申请人： Rinaldo Brutoco
发明人： Rinaldo Brutoco
IPC分类号： B64B1/62 , B64B1/00
CPC分类号： B64B1/62 , B64B1/00 , B64B1/06 , B64B1/12 , B64B1/20 , B64B1/32 , B64B1/66 , B64F1/02 , F42B15/00 , Y10T137/6906
摘要： A system for efficiently transporting hydrogen from where it can be economically made to where it is most needed using specially designed airships. Technologies such as geothermal, wind, solar, wave tidal or hydropower can be used to generate electricity in-situ or very near to the primary energy sources. This electricity can then be used to produce hydrogen directly from water through various methods known in the art. Hydrogen can be delivered from the place where it is produced to the place where it is needed using an airship. The hydrogen can provide propulsion energy and serve ancillary needs. In other embodiments of the invention, the airship of the present invention can be used to dramatically reduce the cost of transportation of freight, the cost of passenger transportation, and to save on the area required for landing at the points of loading/unloading and embarkation/debarkation.
摘要翻译：一种能够经济地运输氢气的系统，使用专门设计的飞艇最需要的地方。诸如地热，风能，太阳能，波浪潮汐或水电等技术可用于原地或非常接近主要能源的电力。然后可以通过本领域已知的各种方法将该电直接用于从水中产生氢气。氢气可以从生产地点运送到需要的地方使用飞艇。氢气可以提供推进能量并提供辅助需求。在本发明的其他实施例中，本发明的飞艇可用于显着降低货物运输成本，乘客运输成本，并节省在装卸点和登船点上着陆所需的面积 /剥皮。

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