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公开(公告)号：WO2018230774A1
公开(公告)日：2018-12-20
申请号：PCT/KR2017/010798
申请日：2017-09-28
Applicant: 한국항공우주연구원
IPC: E04H9/02 , E04B1/98 , F16F7/12 , F16F15/023 , F16F15/067
CPC classification number: E04B1/98 , E04H9/02 , F16F7/12 , F16F15/023 , F16F15/067
Abstract: 본 발명은 복합재 튜브를 이용하여 진동 충격과 같은 반복적인 충격 에너지를 효과적으로 흡수하는 장치를 제공하는 것이며, 상기 구성에 의해서 복합재 튜브를 이용하여 인장, 압축 충격하중에 따른 충격 에너지를 효과적으로 흡수할 수 있으며, 이러한 충격 에너지 흡수장치를 건물에 적용하여 반복적인 지진에 대비할 수 있는 제진장치로 활용할 수 있는 유리한 효과가 발생한다.
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公开(公告)号：WO2016199979A1
公开(公告)日：2016-12-15
申请号：PCT/KR2015/009496
申请日：2015-09-09
Applicant: 한국항공우주연구원
Abstract: 가변두께를 갖는 주름형 완충부재가 개시되어 있다. 개시된 가변두께를 갖는 주름형 완충부재는 충돌에너지 작용면에 작용하는 충돌에너지 작용방향의 직각방향으로 주름면이 형성된 주름판을 포함하되, 상기 주름판은 좌굴 취약구간의 두께가 여타구간의 두께에 비해 두껍게 구성된 것을 특징으로 한다.
Abstract translation: 公开了一种具有可变厚度的波纹缓冲构件。 所公开的具有可变厚度的波纹状缓冲构件包括波纹板，波纹板具有沿垂直于应用于碰撞能量的方向的方向形成的波纹表面，该波纹表面被施加到碰撞能量施加表面，其中波纹板被构造成使得 易于屈曲的部分的厚度大于另一部分的厚度。
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公开(公告)号：KR1020110076267A
公开(公告)日：2011-07-06
申请号：KR1020090132931
申请日：2009-12-29
Applicant: 한국항공우주연구원
Abstract: PURPOSE: An airplane wing equipped with a surface deformation unit and an airplane including the same are provided to decrease drag by keeping the same shape as the surface of a wing when an airplane is on a cruise and to increase lift by being inhaled inward and generating vortex when an airplane takes off and landing. CONSTITUTION: An airplane including an airplane wing equipped with a surface deformation unit comprises an airplane wing(10), a pump, and a control unit. The airplane wing comprises a surface deformation unit(12) provided to an upper skin(11), a chamber, a chamber pressure measurement sensor, and an air pressure measurement sensor, wherein the surface deformation unit keeps flat at the same height as the upper skin according to the pressure inside the chamber to reduce drag acting on the airplane wing when an airplane is on a cruise, or is inhaled inward to generate vortex when an airplane takes off and landing.
Abstract translation: 目的：提供装备有表面变形单元和包括其的飞机的飞机机翼，以在飞机在巡航时保持与机翼表面相同的形状来减小阻力，并通过向内吸入并增加升力来增加升力 当飞机起飞和着陆时涡流。 构成：包括装备有表面变形单元的飞机机翼的飞机包括飞机机翼（10），泵和控制单元。 飞机机翼包括设置在上皮肤（11），腔室，腔室压力测量传感器和气压测量传感器的表面变形单元（12），其中表面变形单元保持与上部相同的高度 皮肤根据室内的压力，以减少当飞机在巡航时作用在飞机机翼上的阻力，或者当飞机起飞和降落时被向内吸入以产生涡流。
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公开(公告)号：KR101681598B1
公开(公告)日：2016-12-01
申请号：KR1020160080158
申请日：2016-06-27
Applicant: 한국항공우주연구원
IPC: B64F5/00 , G01M7/08 , G01M17/02 , G01M17/013
Abstract: 본발명의실시예에따른항공기용착륙장치의휠 회전장치는착륙장치(landing gear)의휠에접촉되어상기휠에회전력을전달하고, 회전축의중심을교차하는중심축을기준으로상기휠이접촉된위치에따라시계또는반시계방향으로회전되어상기휠에밀착되는회전지지부, 상기회전지지부를상하방향및 회전방향으로탄성지지하는탄성지지부, 그리고상기탄성지지부를지지하고, 상기탄성지지부의위치조절이가능한위치조절부를포함한다.
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公开(公告)号：KR100921573B1
公开(公告)日：2009-10-12
申请号：KR1020070136930
申请日：2007-12-24
Applicant: 한국항공우주연구원
Abstract: 비행선 또는 기구는 부유상태를 유지하도록 다수개의 연결선에 연결되는데, 본 발명은 비행선 또는 기구에 연결된 연결선 간의 장력이 균등하게 유지되도록 하는 비행선 또는 기구의 장력 조절장치에 관한 것이며, 또한 비행선 또는 기구의 장력 조절장치를 이용한 비행선 또는 기구의 위치 조절방법에 관한 것이다.
도르래, 힌지축, 회전축, 장력, 회전, 비행선, 기구, 기낭-
Patent Agency Ranking
公开(公告)号：KR1020090069084A
公开(公告)日：2009-06-29
申请号：KR1020070136930
申请日：2007-12-24
Applicant: 한국항공우주연구원
Abstract: A tension control device for an aerostat or balloon and a method for adjusting the location of an aerostat or balloon are provided to maintain uniform tension acting on a connection line connecting the tether cable and the patch attached to the air bladder of the aerostat. A tension control device for an aerostat or balloon comprises a first tension control unit(831) and a second tension control unit(832). The first tension control unit loosens a second connection line(502) connected to the aerostat or balloon when pulling a first connection line(501) connected to the aerostat or balloon and pulls the second connection line when loosening the first connection line so that the tension of the first and second connection lines is balanced. The second tension control unit loosens a fourth connection line(504) connected to the aerostat or balloon when pulling a third connection line(503) connected to the aerostat or balloon and pulls the fourth connection line when loosening the third connection line so that the tension of the third and fourth connection lines is balanced.
Abstract translation: 提供了一种用于空气净化器或气球的张力控制装置和用于调节空气净化器或气囊的位置的方法，以保持作用在连接系绳电缆和连接到空气稳定器的气囊的贴片的连接线上的均匀张力。 用于空气净化器或气囊的张力控制装置包括第一张力控制单元（831）和第二张力控制单元（832）。 当拉动与空气稳定器或气球连接的第一连接线（501）时，第一张力控制单元松开连接到空气稳定器或气球的第二连接线（502），并且当松开第一连接线时拉动第二连接线，使得张紧 的第一和第二连接线是平衡的。 当拉动与空气稳定器或气球连接的第三连接线（503）时，第二张力控制单元松开连接到空气稳定器或气球的第四连接线（504），并且当松开第三连接线时拉动第四连接线，使得张紧 的第三和第四连接线是平衡的。
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公开(公告)号：KR1020160071697A
公开(公告)日：2016-06-22
申请号：KR1020140179178
申请日：2014-12-12
Applicant: 한국항공우주연구원
IPC: B64C1/34
CPC classification number: B64C1/34
Abstract: 일실시예에따른이동체내부의공간을보호하기위한충격흡수장치는, 이동체의하부에적용가능한프레임; 상기프레임의상부에배치되는지지판; 상기프레임과지지판사이에배치되고순간적으로팽창가능한에어백; 상기프레임의하측에배치되는충격감지센서; 및상기충격감지센서가충격을감지하는경우, 상기에어백을순간적으로팽창시키는작동기;를포함할수 있다.
Abstract translation: 根据一个实施例，用于保护移动物体的内部空间的减震装置可以包括：能够施加到移动物体的下部的框架; 布置在所述框架的上部的支撑板; 安放在所述框架和所述支撑板之间并且瞬时膨胀的气囊; 布置在所述框架的下侧的冲击检测传感器; 并且当震动检测传感器检测到震动时，操作者即时地将气囊膨胀。
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公开(公告)号：KR1020140087523A
公开(公告)日：2014-07-09
申请号：KR1020120157909
申请日：2012-12-31
Applicant: 한국항공우주연구원
Inventor： 박일경
Abstract: The present invention relates to an aircraft structure having an impact energy absorbing structure capable of minimizing impact energy transmitted to a room inside a fuselage in an emergency landing situation by including a layer supporting member made of impact energy absorbing materials, and capable of stably fixing a layer separation unit combining member including a body unit and a connection unit of a layer separation unit as the layer separation unit combining member is made of metal materials.
Abstract translation: 本发明涉及具有冲击能量吸收结构的飞行器结构，该冲击能量吸收结构能够通过包括由冲击能量吸收材料制成的层支撑构件来最小化在紧急着陆情况下传递到机身内部的房间的冲击能量，并能够稳定地固定 层分离单元组合构件由金属材料制成，其包括主体单元和作为层分离单元组合构件的层分离单元的连接单元。
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公开(公告)号：KR101341372B1
公开(公告)日：2013-12-13
申请号：KR1020130098266
申请日：2013-08-20
Applicant: 한국항공우주연구원
Inventor： 박일경
IPC: B64C1/14
Abstract: The present invention relates to an aircraft including a capsule type mounting cockpit, capable of changing a fuselage by forming a body unit and a flight unit to be able to be separated and only changing a body unit as necessary and of reducing impact transmitted to the body unit by forming an impact fuse and an impact absorbing member in a connection member of a connection unit formed between the body unit and the flight unit.
Abstract translation: 本发明涉及一种包括胶囊型安装驾驶舱的飞机，其能够通过形成身体单元和飞行单元来改变机身以能够分离，并且仅在必要时改变身体单元并且减少传递到身体的冲击力 通过在形成在主体单元和飞行单元之间的连接单元的连接构件中形成冲击保险丝和冲击吸收构件。
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公开(公告)号：KR101271485B1
公开(公告)日：2013-06-05
申请号：KR1020110141420
申请日：2011-12-23
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A morphing wing for an aircraft is provided to deform trailing edge structure because an actuating linkage connected to a trailing edge is operated by a linear actuator. CONSTITUTION: A morphing wing(1) for an aircraft comprises an undeformable wing structure part(200), a linear actuator(300), an actuating linkage, an upper skin(510), a lower skin(520), and a deformable skin(600). The undeformable wing structure is formed in the opposite side of a trailing edge(100). The linear actuator is positioned in one side of the linear actuator to deform the structure of the trailing edge. The actuator linkage is connected between the linear actuator and the trailing edge to implement a linear motion. The upper and lower skins form top and bottom surfaces arranged between the undeformable wing structure part and the trailing edge and are bent upward and downward according to the motion direction of the actuator linkage. The deformable skin is positioned between the upper skin and the trailing edge and is tensed or compressed.
Abstract translation: 目的：为了使后缘结构变形，提供了用于飞行器的变形翼，因为连接到后缘的致动连杆由线性致动器操作。 构成：用于飞机的变形翼（1）包括不可变形的翼结构部分（200），线性致动器（300），致动连杆，上皮（510），下皮（520）和可变形的皮肤 （600）。 不可变形的翼结构形成在后缘（100）的相对侧。 线性致动器定位在线性致动器的一侧以使后缘的结构变形。 致动器联动装置连接在线性致动器和后缘之间以实现线性运动。 上表皮和下表面形成布置在不可变形翼结构部分和后缘之间的顶表面和底表面，并且根据致动器连杆机构的运动方向向上和向下弯曲。 可变形的皮肤位于上皮和后缘之间，并被拉紧或压缩。
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