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公开(公告)号：WO2017086639A1
公开(公告)日：2017-05-26
申请号：PCT/KR2016/012711
申请日：2016-11-07
Applicant: 한국항공우주연구원
Inventor： 이융교
CPC classification number: B64C3/00 , B64C3/32 , B64C11/46 , B64C25/32 , B64D27/24 , B64D41/00 , B64D45/00 , B64F1/10
Abstract: 일 실시예에 따른 비행체는, 동체; 상면이 곡면으로 형성되고 상기 동체의 중앙으로부터 양쪽으로 뻗은 주익; 상기 주익의 상면에 구비되어 태양에너지를 전기에너지로 전환하는 태양 전지; 및 상기 주익 하부에 배치되어 상기 태양 전지에서 발생된 전기에너지를 저장하는 에너지 저장부;를 포함하고, 상기 태양 전지는 복수 개의 단위 태양 전지로 마련되어 상기 태양 전지의 효율이 향상되고, 상기 복수 개의 단위 태양 전지에서 출력된 전기에너지 또는 상기 에너지 저장부에 저장된 전기에너지에 의해 체공시간이 연장될 수 있다.
Abstract translation: 根据一个实施例的飞行物体包括主体; 具有弯曲上表面并从本体中心的两侧延伸的翼; 太阳能电池，所述太阳能电池设置在所述机翼的上表面上并将太阳能转换为电能; 以及设置在机翼下方并储存在太阳能电池中产生的电能的能量存储单元，其中太阳能电池设置有多个单元太阳能电池以提高太阳能电池的效率， 太阳能电池供电的时间可以通过从太阳能电池输出的电能或存储在能量存储单元中的电能来延长。
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公开(公告)号：WO2019050156A1
公开(公告)日：2019-03-14
申请号：PCT/KR2018/008313
申请日：2018-07-24
Applicant: 한국항공우주연구원
IPC: B60W30/02 , B60W40/105 , B60W50/14 , G01P13/02 , G01P5/02
Abstract: 차량용 주행 보조 장치에 연관되며, 차량의 주행안정성 유지되는 주행안정영역을 풍동시험 등을 통해 미리 지정하고, 차량의 일측에 부착되어 2차원 풍향 및 풍속을 측정하는 바람센서; 및 상기 차량의 주행속도와 상기 바람센서로부터 측정되는 풍향 및 풍속 정보를 이용하여 주행 안정성을 판단하는 프로세서를 포함한다.
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公开(公告)号：WO2016093389A1
公开(公告)日：2016-06-16
申请号：PCT/KR2014/012130
申请日：2014-12-10
Applicant: 한국항공우주연구원
CPC classification number: B64C3/26 , B64C3/185 , B64C3/187 , B64C39/02 , B64D47/00 , B64D2211/00 , H01L31/042 , H02S20/00 , H02S30/00 , Y02E10/50
Abstract: 본 발명은 비행체의 날개에 구비되는 태양광 패널장치와 이를 구비한 비행체 날개 및 비행체에 관한 것으로서, 더욱 상세하게는 태양광을 에너지로 변환할 수 있는 패널을 갖는 한편, 날개의 굽힘 하중이나 거동 등에 의해 패널이 파괴되지 않도록 하기 위한 비행체의 날개에 구비되는 태양광 패널장치와 이를 구비한 비행체 날개 및 비행체에 관한 것이다.
Abstract translation: 技术领域本发明涉及包括在飞行器机翼中的太阳能电池板装置，以及包括该飞行器机翼的飞行器机翼和飞行器，更具体地，涉及包括在飞行器机翼中的太阳能电池板装置和飞行器机翼 以及包括其的飞行器，其中太阳能电池板装置具有能够将太阳光转换为能量的面板，并且另外防止由于机翼的弯曲载荷或行为而损坏面板。
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公开(公告)号：KR1020100072668A
公开(公告)日：2010-07-01
申请号：KR1020080131144
申请日：2008-12-22
Applicant: 한국항공우주연구원
Inventor： 이융교
Abstract: PURPOSE: A natural laminar airfoil for a small jet is provided to enable passengers to cost-efficiently use a plane by reducing fuel consumption. CONSTITUTION: A natural laminar airfoil(200) for a small jet comprises a top surface and a bottom surface. The top surface is curved. The bottom surface is formed in the bottom of the airfoil. A maximum thickness ratio of the airfoil is 14~16%. The airfoil reduces drag by delaying the succession of air current from laminar flow to turbulence flow.
Abstract translation: 目的：提供一种用于小型飞机的天然层状翼型，以使乘客能够通过降低燃料消耗来成本有效地使用飞机。 构成：用于小射流的天然层状翼型件（200）包括顶表面和底表面。 顶面是弯曲的。 底面形成在翼型的底部。 翼型件的最大厚度比为14〜16％。 机翼通过延迟从层流到湍流的气流的连续性来减小阻力。
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公开(公告)号：KR1020090069090A
公开(公告)日：2009-06-29
申请号：KR1020070136936
申请日：2007-12-24
Applicant: 한국항공우주연구원
Inventor： 이융교
IPC: B64G1/24
CPC classification number: B64G1/24 , B64G1/14 , B64G1/62 , B64G2001/245
Abstract: A space shuttle and a reentry attitude control of the space shuttle at low earth orbit are provided to secure stability of the space shuttle attitude reentering the low earth orbit without additional device. A space shuttle comprises a body(100), a nozzle(200) applying a propulsion force to the body, a rudder causing a yaw action in the body, a main wing(300) which is composed of a leading end(310) and a trailing end(320) with a first mounting groove(322) and attached to the body, an elevon which is mounted on the first mounting groove and moves to vary the attack angle, a tail boom(500) formed on the outer end of the main wing trailing end, and a canard(700) which is mounted apart from the main wing on the front side of the body and moves to vary the attack angle.
Abstract translation: 提供了在低地球轨道上的航天飞机的航天飞机和重入姿态控制，以确保重新进入低地球轨道的航天飞机姿态的稳定性，而无需额外的装置。 航天飞机包括主体（100），向主体施加推进力的喷嘴（200），在主体中引起偏航动作的方向舵;主翼（300），其由前端（310）和 具有第一安装槽（322）并附接到主体的后端（320），安装在第一安装槽上并移动以改变攻角的升降板，形成在外壳上的尾梁（500） 主翼尾端以及与身体前侧上的主翼分离安装的猫（700），并移动以改变攻角。
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Patent Agency Ranking
公开(公告)号：KR1020140079641A
公开(公告)日：2014-06-27
申请号：KR1020120148186
申请日：2012-12-18
Applicant: 한국항공우주연구원
Inventor： 이융교
IPC: B64C3/00 , H01L31/042
CPC classification number: Y02E10/50 , B64C3/32 , B64D2211/00 , H01L31/0445 , H02S10/40 , Y02E10/52
Abstract: The present invention provides a photovoltaic cell wing of an unmanned aerial vehicle, which comprises wing frame units installed on both sides of a fuselage, respectively; multiple photovoltaic films adhering to the upper parts of the wing frame units; and thermoplastic films attached to the wing frame units to wrap around the wing frame units and the photovoltaic films. According to the present invention, thermoplastic films are attached to wrap around the wing frame units and the photovoltaic films after attaching the photovoltaic films to the wing frame units of the unmanned aerial vehicle, where no adhesion surfaces are formed on the photovoltaic films and the thermoplastic films, thereby preventing deformation of wings even if the photovoltaic films are deformed. In addition, the photovoltaic films are installed inside the thermoplastic films to prevent power cables of the photovoltaic films from protruding outside, thereby preventing drag of the photovoltaic cell wing from increasing.
Abstract translation: 本发明提供了一种无人飞行器的光伏电池翼，其分别安装在机身两侧的翼架单元; 多个光伏膜粘附在机架单元的上部; 以及附着在翼架单元上的热塑性薄膜以围绕翼框单元和光伏薄膜。 根据本发明，在将光伏膜附着到无人驾驶飞行器的翼架单元上之后，将热塑性薄膜附着在机翼框架单元和光伏薄膜上，其中在光伏薄膜和热塑性塑料上没有形成粘附表面 膜，从而即使光伏膜变形，也防止机翼变形。 此外，光伏膜安装在热塑性薄膜的内部，以防止光伏薄膜的电力电缆向外突出，从而防止光伏电池翼的阻力增加。
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公开(公告)号：KR100648466B1
公开(公告)日：2006-11-27
申请号：KR1020050117935
申请日：2005-12-06
Applicant: 한국항공우주연구원
Abstract: A bank control system for an airship is provided to control bank of the airship by varying the position of a gondola of the airship and changing the center of the gravity of the airship to achieve the optimum bank angle for more solar energy. In a bank control system for an airship, a rail(30) is horizontally installed inside a gasbag(11) or on the outer peripheral surface of lower part of the gas bag. A wheel generates the bank in the airship by horizontally moving a gondola(20) connected to the rail. A wheel driving part(40) is connected to the wheel and drives the wheel. And a wheel driving controller is electrically connected to the wheel driving part and controls the wheel driving part.
Abstract translation: 提供飞艇的银行控制系统，通过改变飞艇的吊舱的位置并改变飞艇的重心以实现更多太阳能的最佳银行角度来控制飞艇的银行。 在飞艇的岸上控制系统中，导轨（30）水平地安装在气囊（11）内或气囊下部的外周表面上。 通过水平移动与轨道连接的吊舱（20），轮子在飞艇中产生岸。 车轮驱动部分（40）连接到车轮并驱动车轮。 并且车轮驱动控制器电连接到车轮驱动部件并且控制车轮驱动部件。
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公开(公告)号：KR1020030050310A
公开(公告)日：2003-06-25
申请号：KR1020010080723
申请日：2001-12-18
Applicant: 한국항공우주연구원
IPC: B64C39/00
CPC classification number: B64B1/58 , B64C39/02 , B64C2201/022
Abstract: PURPOSE: An envelope structure is provided to prevent the sudden inclination of helium and the large change of a helium volume ratio by a simple structure. CONSTITUTION: A front partition(2) and a rear partition(3) divide the inside of a plane(1) to three parts. Separating films(7,8,9) are installed in the center of the front partition and the rear partition. A front helium envelope(4), a middle helium envelope(5) and a rear helium envelope(6) are divided in the upper part and a front air envelope(10), and a middle air envelope(11) and a rear air envelope(12) are divided by the separating films. Thereby, the sudden inclination of helium and the large change of a helium volume ratio are prevented.
Abstract translation: 目的：提供一种包络结构，通过简单的结构防止氦的突然倾斜和氦体积比的大的变化。 构成：前隔板（2）和后隔板（3）将平面（1）的内部分成三部分。 分隔膜（7,8,9）安装在前隔板和后隔板的中心。 前氦气封（4），中氦气囊（5）和后氦气囊（6）被分成上部和前部气囊（10），中部空气气囊（11）和后部空气 信封（12）被分离膜分隔。 从而防止氦的突然倾斜和氦体积比的大的变化。
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公开(公告)号：KR101867434B1
公开(公告)日：2018-06-15
申请号：KR1020170097963
申请日：2017-08-02
Applicant: 한국항공우주연구원
CPC classification number: B64D45/00 , B64C39/024 , B64D2045/0085 , G01L5/12
Abstract: 본발명은압력센서를이용한상승풍및 와류고리상태감지장치에관한것으로더욱상세하게는프로펠러의회전으로인하여형성되는후류의압력을측정하는압력센싱부및 상기압력센싱부로부터인가받은신호를처리하여상기비행체의하부로부터의상승풍의속도또는상기비행체가와류고리상태에진입하는것을판단하는비행조종컴퓨터를포함하여구성되며, 비행체의제자리비행및 수직하강비행에있어적절한상황대처를가능하게하는압력센서를이용한상승풍및 와류고리상태감지장치에관한것이다.
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