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公开(公告)号：KR1020140045692A
公开(公告)日：2014-04-17
申请号：KR1020120111740
申请日：2012-10-09
Applicant: 한국항공우주연구원
Abstract: The present invention relates to a damping control system based on internal pressure which can adjust the area of an orifice to be opened according to the internal pressure of a shock absorber of a landing gear. The damping control system adjusts the area of the orifice, through which oil passes, according to variations in the internal pressure, and includes a cylinder, a piston and an orifice-area adjusting member. The cylinder contains gas and oil therein. The piston has a main body containing oil in a hollow portion thereof, and reciprocating in the cylinder, and a slide portion connected to the main body and having a cross-sectional area smaller than the inner wall of the cylinder. The slider portion contains oil in the hollow portion thereof, and is provided with at least one orifice. The orifice-area adjusting member reciprocates along the slide portion. The oil in the cylinder and the oil in the piston move through the orifice according to variations in the internal pressure of the cylinder and the piston.
Abstract translation: 本发明涉及一种基于内部压力的阻尼控制系统，其可以根据起落架的减震器的内部压力来调节要打开的孔口的面积。 阻尼控制系统根据内部压力的变化调整油通过的孔口的面积，并且包括缸体，活塞和孔口面积调节构件。 气瓶内含有气体和油。 活塞具有在其中空部分中含有油的主体，并且在气缸中往复运动，以及与主体连接并具有小于气缸内壁的横截面积的滑动部分。 滑块部分在其中空部分中包含油，并且设置有至少一个孔口。 孔口面积调节构件沿滑动部分往复运动。 气缸中的油和活塞中的油根据气缸和活塞的内部压力的变化而移动通过孔口。
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公开(公告)号：KR1020110067289A
公开(公告)日：2011-06-22
申请号：KR1020090123821
申请日：2009-12-14
Applicant: 한국항공우주연구원
Abstract: PURPOSE: An auxiliary landing gear of a helicopter is provided to increase the survival rate of an operator by preventing intrusion of the auxiliary landing gear into a cockpit in a crash. CONSTITUTION: An auxiliary landing gear of a helicopter comprises a moving unit(100), a moving unit coupling frame(200), and a support link member. The moving unit coupling frame has a buffer unit(210). One end of the moving unit coupling frame is located inside the lower body of the helicopter so that the moving unit coupling frame can be moved to the rear side of the helicopter. The other end part of the moving unit coupling frame is coupled with the moving unit. The support link member is coupled between the moving unit coupling frame and the lower body of the helicopter in order to prevent the moving unit coupling frame from being moved to the rear side, and the support link member is broken by an impact over a specific level.
Abstract translation: 目的：提供直升机的辅助起落架，以通过防止辅助起落架在碰撞中侵入驾驶舱来提高操作员的存活率。 构成：直升机的辅助起落架包括移动单元（100），移动单元联接框架（200）和支撑连杆构件。 移动单元耦合框架具有缓冲单元（210）。 移动单元联结框架的一端位于直升机的下部主体内，使得移动单元联接框架可以移动到直升机的后侧。 移动单元联接框架的另一端部与移动单元联接。 支撑连杆构件联接在移动单元联接框架和直升机的下部主体之间，以防止移动单元联接框架移动到后侧，并且支撑连杆构件因特定水平的冲击而损坏 。
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公开(公告)号：KR1020150064339A
公开(公告)日：2015-06-11
申请号：KR1020130148937
申请日：2013-12-03
Applicant: 한국항공우주연구원
IPC: B64C17/02
CPC classification number: B64C17/02
Abstract: 본발명은항공기의날개중심을기준으로좌측에형성되는제1회전수단; 항공기의날개중심을기준으로우측에형성되는제2회전수단; 항공기의날개중심하부또는상부에형성되는제3회전수단; 상기제1회전수단, 상기제2회수단및 상기제3회전수단에폐루프를형성하며체결되는감김회전부재; 상기제3회전수단을회전시키는구동수단; 및상기제1회전수단및 상기제2회전수단사이에위치된상기감김회전부재에결합되고, 상기구동수단의정역회전에따라항공기의날개중심을기준으로좌우로이송되며, 소정의무게를갖는중량부재;를포함하는항공기의롤링제어장치에관한것으로써, 특히, 무게중심이동을통한항공기의롤링제어장치에관한것이다.
Abstract translation: 本发明涉及一种用于飞行器的滚动控制装置，其包括：形成在飞行器的翼的中心周围的左侧的第一旋转装置; 围绕飞行器的翼的中心的右侧形成的第二旋转装置; 第三旋转装置，形成在飞机的翼的中心的下部或上部; 联接成在所述第一旋转装置中形成闭环的第二旋转构件，所述第二旋转装置和所述第三旋转装置; 驱动装置，使第三旋转装置旋转; 以及联接到放置在第一旋转装置和第二旋转装置之间的卷绕旋转构件的配重构件，其根据驱动装置的往复旋转水平地绕飞行器的翼的中心传递并且具有预定的重量。 具体地说，本发明涉及一种通过重心运动的飞机的滚动控制装置。
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公开(公告)号：KR1020160077703A
公开(公告)日：2016-07-04
申请号：KR1020140187924
申请日：2014-12-24
Applicant: 한국항공우주연구원
IPC: B64C17/04
CPC classification number: B64C17/04
Abstract: 본발명은항공기의피치를제어하기위한것으로서특히날개부일 측에배치되는파드에웨이터를항공기전후방향이송시켜항공기구조물의변형이심하게발생하더라도피치를용이하게제어할수 있는웨이트이동방식의항공기피치제어장치및 방법에대한것이다.
Abstract translation: 本发明涉及一种使用重量移动方法的飞机的俯仰控制装置和方法，该方法能够容易地控制飞机的俯仰，即使飞行器结构通过在布置在翼的一侧的垫中传递重物而过度变形 部分在飞机的纵向方向。
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