公开(公告)号：WO2004100289A2

公开(公告)日：2004-11-18

申请号：PCT/US2004/013895

申请日：2004-05-05

Applicant: ION AMERICA CORPORATION ,  MCELROY, James, Frederick ,  SRIDHAR, K. R.

Inventor： MCELROY, James, Frederick ,  SRIDHAR, K. R.

IPC: H01M

CPC classification number: H01M8/186 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/101 ,  B64C2201/127 ,  B64C2201/148 ,  B64C2201/165 ,  B64D27/24 ,  B64D2041/005 ,  B64D2211/00 ,  H01M8/04007 ,  H01M8/2475 ,  H01M2250/20 ,  Y02E60/528 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62 ,  Y02T90/32 ,  Y02T90/36 ,  Y10S429/901

Abstract: A neutral buoyant airship, such as a blimp, contains a lifting body which allows the airship to remain neutrally buoyant in air and fuel cell located in the airship. A method of generating power in the neutrally buoyant airship, comprising providing a fuel and a oxidizer to a solid oxide fuel cell to generate power, and providing heat from the fuel cell to a remotely located lifting body, wherein the lifting body allows the airship to remain neutrally buoyant in air.

Abstract translation: 一个中性浮力的飞艇，如飞艇，包含一个提升体，允许飞艇在位于飞艇的空气和燃料电池中保持中性浮力。 一种在中性浮力飞艇中产生动力的方法，包括向固体氧化物燃料电池提供燃料和氧化剂以产生动力，并将热量从燃料电池提供到位于远处的提升体，其中提升体允许飞艇 在空气中保持中性浮力。

公开(公告)号：KR101883896B1

公开(公告)日：2018-08-01

申请号：KR1020187000289

申请日：2016-06-15

Applicant: 나카무라 고헤이

Inventor： 나카무라고헤이

IPC: B64B1/30 ,  B64B1/58 ,  B64C25/06 ,  B64C27/08 ,  B64C39/02

CPC classification number: B64B1/30 ,  B64B1/58 ,  B64C25/06 ,  B64C27/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/127

Abstract: (과제) 본발명은, 추락리스크를감소하여높은안전성을확보하고, 바람의영향을억제하여이동제어를쉽게하여높은이동능력을발휘할수 있는부양형비행체를제공한다. (해결수단) 내부에공기보다작은비중의가스를밀폐하여이루어지는부양기체와, 이부양기체에수직방향의추진력을부여하는수직추진용프로펠러와, 상기부양기체에수평방향의추진력을부여하는수평추진용프로펠러를구비하고, 상기부양기체는, 수평방향의바람통로가적어도 2방향으로형성되어있음과아울러그 외주가장자리의각도가측면에서볼 때에예각모양으로형성되어있다.

公开(公告)号：KR1020160024363A

公开(公告)日：2016-03-04

申请号：KR1020157037252

申请日：2014-06-26

Applicant: 에건 에어쉽스, 인크.

Inventor： 에간,제임스,씨. ,  에간,조엘,디.

IPC: B64B1/00 ,  B64B1/14 ,  B64B1/20 ,  B64B1/22 ,  B64B1/28 ,  B64B1/30 ,  B64B1/38 ,  B64B1/58 ,  B64B1/70

CPC classification number: B64B1/20 ,  B64B1/14 ,  B64B1/22 ,  B64B1/28 ,  B64B1/30 ,  B64B1/34 ,  B64B1/38 ,  B64B1/58 ,  B64B1/60 ,  B64B1/70 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/104

Abstract: 하이브리드수직이착륙운송수단은유체정역학부력을제공하도록구성된기낭, 기낭에부착되고움직임을통하여동적양력을생성하기위해동체의반대측면들로부터연장되는적어도한쌍의날개들을갖는동체및 각각의날개상에그리고수직이륙또는착륙성능들을제공하기위해서기낭의종축에횡방향에있는축에대하여각각의날개와함께회전하도록구성된추력생성디바이스를갖는다. 이상적으로는, 기낭은저-속도및 대지상에서의안정성을증강시키기위해음(negative)의유체정역학양력을제공한다.

公开(公告)号：KR100974484B1

公开(公告)日：2010-08-10

申请号：KR20090103016

申请日：2009-10-28

Applicant: KOREA INST GEOSCIENCE & MINERA

Inventor： CHO SEONG JUN ,  PARK JONG SOU ,  PARK GYE SOON

IPC: B64B1/06 ,  B25J5/00 ,  B64C13/16 ,  B64D47/00

CPC classification number: G01R33/0385 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/127 ,  B82Y25/00 ,  G01R33/038

Abstract: PURPOSE: A portable unmanned airship for magnetic survey and a magnetic survey system using the same are provided to examine geological structure and to detect mineral resource using magnetic force. CONSTITUTION: A portable unmanned airship for magnetic survey comprises an airship main body, an autonomous vehicle apparatus(120), a magnetic force measure system(130), a wireless telecommunications installation(140), and a control module(150). The airship main body comprises an air bag filled with gas and a drive unit(113) for offering the driving force to the airship main body. The power unit is made of a non-magnetic material. An autonomous vehicle apparatus automatically moves the airship main body. The control module controls the operation of the magnetic force measure system and autonomous vehicle apparatus.

Abstract translation: 目的：提供用于磁性测量的便携式无人飞艇和使用其的磁性测量系统，以检查地质结构和使用磁力检测矿物资源。 构成：用于磁性测量的便携式无人飞艇包括飞艇主体，自主车辆设备（120），磁力测量系统（130），无线电信设备（140）和控制模块（150）。 飞艇主体包括充满气体的气囊和用于向飞艇主体提供驱动力的驱动单元（113）。 动力单元由非磁性材料制成。 自主车辆装置自动移动飞艇主体。 控制模块控制磁力测量系统和自主车辆装置的操作。

公开(公告)号：KR2020100004308U

公开(公告)日：2010-04-27

申请号：KR2020080013846

申请日：2008-10-17

Applicant: 김종열

Inventor： 김종열 ,  김종배

IPC: B64B1/40 ,  B64B1/58

CPC classification number: B64B1/06 ,  B64B1/10 ,  B64B1/20 ,  B64B1/22 ,  B64B1/32 ,  B64C11/20 ,  B64C39/02 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/101 ,  B64D47/08

Abstract: 본 고안은 무선으로 조종하는 무선 조종 무인비행선에 관한 것으로, 특히 방향 조절이 용이한 조종수단을 갖는 무인비행선에 관한 것이다.
무선 조종 무인비행선은 항공 정찰내지, 항공 사진 촬영용으로 사용되기도 하지만, 하늘을 비행하는 비행선은 지상에서 사람의 시선이 집중됨으로 인해, 큰 부피의 기낭(공기주머니) 외주면에 광고나 홍보문구를 부착하여, 광고내지 홍보용으로 주로 사용되고 있는 것을 볼 수 있다.
본 고안은 무선 조종 무인비행선에 있어서 좌우 선회 능력을 향상시켜 조종을 용이토록 하며, 비행선의 동력원인 밧데리의 용량을 지상에서 확인 가능토록 하여, 안정되게 비행선을 운행할 수 있도록 한 것이다.
본 고안은 다음과 같은 구조를 갖는다.
본 고안은 헬륨이 채워지는 기낭(11)과, 기낭(11) 하방에는 곤도라(21)가 부착되며, 곤도라(21) 좌우 외측에는 프로펠러(25)를 결합한 모터(24)가 장착되며, 상기 곤도라(21) 내측에는 밧데리(31)와, 무선송수신기(27)가 장착되며, 기낭(11)의 선두 하방에는 무선카메라(20)가 장착되며, 기낭(11)의 후미에는 수직타(12-1)를 갖는 상·하수직날개(12)와, 수평타(13-1)를 갖는 좌·우수평날개(13)로 구성되는 무선 조종 무인 비행선에 있어서,
수직 날개(12)의 표면에 구멍(15)을 형성하며, 상기 구멍(15)에 방향 전환용 프로펠러(17)와, 상기 프로펠러(17)를 구동하는 모터(18)가 장착되며,
곤도라(21)의 앞 부분에는 상기 밧데리(31)의 용량은 숫자나, 기호로 표시하는 밧데리 용량표시기(41)를 가지며, 상기 모터지지축(22)에는 모터지지축(22)의 회전각도를 감시하는 레버(22-1)를 가지며, 상기 레버(22-1)에 의해 작동하는 제1리미트스위치(42) 및 제2리미트스위치(43)를 갖도록 한 것이다.
무인조종, 비행선

公开(公告)号：KR1020040043926A

公开(公告)日：2004-05-27

申请号：KR1020020072391

申请日：2002-11-20

Applicant: 한국항공우주연구원

Inventor： 김인규 ,  김태식 ,  이해창 ,  염찬홍

IPC: B64C13/18

CPC classification number: G08G5/0069 ,  B64B1/62 ,  B64B1/64 ,  B64C2201/022 ,  B64C2201/141 ,  B64D2045/0085 ,  G05D1/0011

Abstract: PURPOSE: A flight finishing system of an unmanned aircraft is provided to forcibly land the aircraft by discharging helium gas with opening the helium valve when the large unmanned aircraft gets out of control from communication interruption or defect. CONSTITUTION: A flight finishing system is composed of a ground control tower(200) transmitting the emergency descent command to a large unmanned aircraft in requiring emergency landing; a defect detecting unit(120) loaded in the unmanned aircraft to output a defect sensing signal by detecting fault of power, communication and control; a flight end system(110) commanding the end of flight in detecting the emergency descent command of the ground control tower and the defect sensing signal of the defect detecting unit; and an operating unit(130) discharging helium gas by opening the helium valve according to the command of the flight end system.

Abstract translation: 目的：提供无人驾驶飞机的飞行整理系统，以便在大型无人驾驶飞机失控以防止通信中断或缺陷时，通过氦气排放氦气强制着陆飞机。 规定：飞行整理系统由地面控制塔（200）组成，将紧急下降指令传送到需要紧急降落的大型无人飞机; 通过检测电力故障，通信和控制，装载在无人机中的缺陷检测单元（120）输出缺陷感测信号; 指示飞行结束的飞行终端系统（110），用于检测地面控制塔的紧急下降命令和缺陷检测单元的缺陷感测信号; 以及操作单元（130），其根据飞行终端系统的命令打开氦气阀来排出氦气。

公开(公告)号：KR1020140115910A

公开(公告)日：2014-10-01

申请号：KR1020130065709

申请日：2013-06-10

Applicant: 이영석

Inventor： 이영석

IPC: B64B1/40 ,  G01W1/08

CPC classification number: B64C39/02 ,  B64B1/62 ,  B64C2201/022 ,  B64C2201/024 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/185 ,  B64D17/80 ,  B64D2211/00 ,  H02S10/40 ,  Y02E10/52

Abstract: The present invention relates to an aircraft for astronomical observation of which the recyclability is high. The aircraft has a helium balloon which is free to charge or discharge helium gas from a helium gas storage tank. A flight control program which controls the elevation and direction of the aircraft and a propeller operated in response to the program are provided in the lower part of a body of the aircraft so that an operator can position the aircraft to a preferable position. In addition, the aircraft is equipped with a solar panel to enable a long time flight for astronomical observation, and the movement speed of the aircraft can be controlled to enable safe take-off and landing.

Abstract translation: 本发明涉及可再生性高的用于天文观测的飞机。 飞机有一个氦气球，可以自由地从氦气储罐充放电氦气。 飞机控制程序控制飞行器的高度和方向以及响应于程序操作的螺旋桨，其设置在飞行器的主体的下部，以便操作人员将飞行器定位在优选的位置。 另外，飞机配备了太阳能电池板，可以长时间飞行进行天文观测，可以控制飞机的移动速度，从而实现安全起飞和降落。

公开(公告)号：KR101436595B1

公开(公告)日：2014-09-01

申请号：KR1020130115585

申请日：2013-09-27

Applicant: 세안이엔씨 주식회사 ,  주식회사 한진중공업 ,  박철수

Inventor： 박철수 ,  윤한봉 ,  조남희

IPC: H02G1/04 ,  H02G11/02 ,  H02B7/06 ,  B66D1/12 ,  B64B1/06

CPC classification number: H02G1/04 ,  B64B1/06 ,  B64C2201/022 ,  B66D1/12 ,  H02B7/06 ,  H02G11/02

Abstract: The present invention relates to a cable installing device configured to comprise a flying unit for flying between transmission towers; an unwinding drum rotatably mounted on the flying unit; a messenger wire wound on the outer peripheral surface of the unwinding drum; a speed sensor unit for measuring the speed of the flying unit; a rotating unit for rotating the unwinding drum in order to untie the messenger wire from the unwinding drum; and a control unit for controlling the rotating unit so as to adjust loosening speed of the messenger wire with respect to the unwinding drum depending on the speed of the measured flight unit via the speed sensor unit. The cable installing device according to the present invention, for installing the messenger wire to the power transmission tower by carrying the messenger wire through the flying unit flying therebetween, can save the labor and time required for work without requiring harvesting operations.

Abstract translation: 电缆安装装置技术领域本发明涉及一种电缆安装装置，其被配置为包括用于在传输塔之间飞行的飞行单元; 可旋转地安装在飞行单元上的退绕滚筒; 缠绕在退绕鼓的外周表面上的信使线; 用于测量飞行单元的速度的速度传感器单元; 旋转单元，用于旋转展开滚筒，以便从展开滚筒解开信使线; 以及控制单元，其用于控制​​旋转单元，以便根据所测量的飞行单元经由速度传感器单元的速度来调节消息线相对于退绕滚筒的松动速度。 根据本发明的电缆安装装置，用于通过将信使线穿过飞行单元而将信使线安装到输电塔上，可以节省工作所需的劳动和时间，而不需要收割操作。

公开(公告)号：KR1020080028845A

公开(公告)日：2008-04-01

申请号：KR1020080015151

申请日：2008-02-20

Applicant: 양원동

Inventor： 양원동

IPC: H02S10/40 ,  F24J2/52 ,  H02S40/38 ,  H01L31/073

CPC classification number: H02S10/40 ,  B64C2201/022 ,  F17C2270/0192 ,  H02S40/32 ,  H02S40/38 ,  H02S40/44

Abstract: A photovoltatic power generation system attached to a hot-air balloon is provided to obtain easily electric power by moving freely a power generation system. A balloon includes an envelope, a basket part(300), and an envelope fixing member(140). The envelope is formed to receive hot air and gas. The basket part is formed to load men or products. The envelope fixing member is formed to fix the envelope and the basket part by using a ribbon or a screw belt member. The balloon includes a solar cell generating part(240,480,640) consisting of solar cell modules for absorbing solar light. The electric power generated by the solar cell generating part is stored in a storage battery through a charge controller(400), an inverter(420), and a generating electric power transmission line(660).

Abstract translation: 提供安装在热气球上的光电发电系统，通过自由地发电发电系统来获得容易的电力。 气球包括一个信封，一个篮子部分（300）和一个信封固定件（140）。 信封形成为接收热空气和气体。 篮子部分形成为装载男士或产品。 信封固定部件形成为通过使用带或螺丝带部件固定信封和筐部。 该气囊包括由吸收太阳光的太阳能电池组件组成的太阳能电池产生部分（240,480,640）。 由太阳能电池产生部产生的电力通过充电控制器（400），逆变器（420）和发电电力传输线路（660）存储在蓄电池中。

公开(公告)号：KR1020040039117A

公开(公告)日：2004-05-10

申请号：KR1020020067879

申请日：2002-11-04

Applicant: 한국항공우주연구원

Inventor： 이상종 ,  김태식 ,  이해창 ,  염찬홍

IPC: B64C13/16

CPC classification number: B64B1/00 ,  B64C2201/022 ,  B64C2201/141 ,  B64D43/00 ,  G05D1/102

Abstract: PURPOSE: An automatic take-off and landing system for a large-class unmanned airship is provided to easily perform a takeoff and a landing under the self decision. CONSTITUTION: An elevator(102), a rudder(103), and flight control surface actuators(104,107) for handling the large-class unmanned airship over 40m in size are mounted to a vertical tail(105) and a horizontal tail(106). An automatic take-off and landing system for a large-class unmanned airship comprises a propeller(108) generating a thrust; a tilting system for handling the thrust direction; a speedometer for measuring the speed; a GPS(Global Positioning System) receiver(110), a GPS antenna(111), and a laser altimeter(112) for taking the position and height information; and an inertial navigation sensor(113).

Abstract translation: 目的：提供大型无人飞艇的自动起飞和着陆系统，以便在自我决定下轻松进行起飞和着陆。 构成：用于处理尺寸超过40m的大型无人飞艇的电梯（102），方向舵（103）和飞行控制表面致动器（104,107）安装到垂直尾部（105）和水平尾部（106） 。 用于大型无人飞艇的自动起飞和着陆系统包括产生推力的螺旋桨（108） 用于处理推力方向的倾斜系统; 用于测量速度的速度计; GPS（全球定位系统）接收器（110），GPS天线（111）和用于获取位置和高度信息的激光高度计（112） 和惯性导航传感器（113）。