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公开(公告)号：KR100672978B1
公开(公告)日：2007-01-22
申请号：KR1020050079609
申请日：2005-08-29
Applicant: 부산대학교 산학협력단
Abstract: A rotor head of an unmanned co-axial inversion vertical take-off and landing aircraft is provided to improve stability of the hovering by uniformly keeping the rotary surface of the upper rotor and to secure the whole reliability by properly inclining the lower rotor by a swash plate. A rotor head(100) of an unmanned co-axial inversion vertical take-off and landing aircraft comprises an upper rotor part(10) formed with a bell method to control the flying position of the fuselage; a lower rotor part(20) formed with a direct pitch control method to adjust the moving direction of the fuselage; a motor part(30) providing power to drive the rotation of the upper and lower rotor parts; and a transmission part(40) connected to transfer the power generated from the motor part to the upper and lower rotor parts. The upper rotor part contains an upper rotor head(11), a stabilizer weight(12), and a seesaw lever(13) connecting the upper rotor head and the stabilizer weight. The lower rotor part contains a lower rotor head(21), a swash plate(22), and a pitch arm(23) connecting the lower rotor head and the swash plate.
Abstract translation: 提供无人同轴反转垂直起降飞机的转子头，以通过均匀地保持上转子的旋转表面来提高盘旋的稳定性，并通过斜盘适当倾斜下转子来确保整体可靠性 盘子。 无人同轴反转垂直起降飞机的转子头（100）包括形成有用于控制机身的飞行位置的钟形法的上转子部分（10） 形成有用于调节机身的移动方向的直接俯仰控制方法的下转子部分（20）; 提供动力以驱动上下转子部分的旋转的马达部件（30）; 以及连接成将从电动机部产生的动力传递到上下转子部的传动部（40）。 上转子部分包括上转子头部（11），稳定器重物（12）和连接上转子头和稳定器重物的跷跷板杆（13）。 下转子部分包括下转子头部（21），斜板（22）和连接下转子头部和斜板的变桨臂（23）。
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公开(公告)号：KR101606325B1
公开(公告)日：2016-03-24
申请号：KR1020150120650
申请日：2015-08-27
Applicant: 부산대학교 산학협력단
Abstract: 본발명은국소(局所) 굽힘효과를이용한가변성형장치에관한것으로, 성형될판재를사이에두고상하로복수개의성형펀치를포함하되, 성형될판재를기준으로상하중 일측의각 성형펀치중심축이타측간의각 성형펀치의중심축사이에위치하도록성형펀치를배열하여국부적(국소) 굽힘효과를일으켜성형성을향상시키기위한 "국소굽힘효과를이용한가변성형장치"에관한것이다. 본발명에따르면, 상하로다수의성형펀치가배열되고, 각각의성형펀치는펀치헤드와, 내부나사산을가진중공형외부부재와, 상기외부부재에삽입체결되는외부나사산을가진내부부재를포함하며, 상기외부부재및 내부부재중 하나는상기펀치헤드에연결되고나머지하나는회전축에연결되며, 상기각각의성형펀치각각의회전축에맞물려토크를제공할수 있는하나이상의펀치조절모터를포함하며, 상기다수의성형펀치는상하로복수의행과복수의열에배열되고, 상기다수의성형펀치상하중 일측의성형펀치의중심축은이에대응하여마주보는타측의인접하는성형펀치의중심축간 사이에위치하므로성형시국부적굽힘이일어나서성형물의성형성이향상되는것을특징으로하는국소굽힘효과를이용한가변성형장치를제공한다.
Abstract translation: 本发明涉及一种使用局部弯曲效果的柔性成形装置和“使用局部弯曲效应的柔性成形装置”，其包括穿过要形成的板条板的多个成形冲头; 通过将成形冲头配置成使得成形冲头的中心轴在上板侧和下侧之间的板状板的上侧和下侧的中心轴线成为位于各成形冲头的中心轴线之间，从而提高成形能力 在上侧和下侧的另一侧。 根据本发明，多个成形冲头被上下配置。 每个成型冲头包括冲头，具有内螺纹的中空型外部构件和具有外螺纹的内部构件。 外部构件和内部构件中的一个连接到冲头，另一个连接到旋转轴。 每个成型冲头包括多个冲头控制马达，其能够通过与每个旋转轴线互锁来提供扭矩。 成形冲头以多行和多列的形式布置成上下。 由于成形冲头的上侧和下侧中的一个上的成形冲头的中心轴线位于相邻成形冲头的中心轴线的一侧的与成形冲头的中心轴线相反的另一侧 对应对应，局部弯曲发生在成型过程中; 从而提高成形能力。
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公开(公告)号：KR101309228B1
公开(公告)日：2013-09-23
申请号：KR1020130024711
申请日：2013-03-07
Applicant: 부산대학교 산학협력단
IPC: B21D5/08
Abstract: PURPOSE: A mold-less plate forming device with flexible forming rollers is provided to be proper to the small quantity batch production of plates by variously changing forming shapes and to prevent dimples and wrinkles. CONSTITUTION: A mold-less plate forming device (100) includes two forming rollers (101a, 101b) and a plurality of roller controlling members (103). The forming rollers are arranged to be vertically corresponded and can be bent at various curvatures. Each end portion of the roller controlling members is fixated to each forming roller, and the lengths of the roller controlling members can be adjustable. The curvatures of the forming rollers and an interval between the forming rollers are adjusted by the roller controlling member according to the lengths.
Abstract translation: 目的：提供一种具有柔性成型辊的无模板成型装置，适用于通过各种变化的成形形状进行小批量批量生产，并防止凹坑和皱纹。 构成：无模板制版装置（100）包括两个成形辊（101a，101b）和多个辊控制件（103）。 成形辊被布置为垂直对应并且可以以各种曲率弯曲。 辊控制构件的每个端部固定到每个成形辊，并且辊控制构件的长度可以是可调节的。 成形辊的曲率和成形辊之间的间隔由辊控制部件根据长度进行调节。
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公开(公告)号：KR1020130005503A
公开(公告)日：2013-01-16
申请号：KR1020110066941
申请日：2011-07-06
Applicant: 부산대학교 산학협력단
Abstract: PURPOSE: An apparatus for helicopters to land is provided to automatically inject fuel, and to replace a battery by positioning the helicopter at a tight position. CONSTITUTION: An apparatus for helicopters to land comprises a landing strip(10), a pair of vertical alignment units(20,20') and a pair of horizontal alignment units(30,30'). The pair of vertical alignment units is installed at both sides of the landing strip, and arranges the vertical position of the helicopter. The pair of the horizontal alignment units is installed at both front and rear sides of the landing strip, and arranges the horizontal position of the helicopter. The pair of vertical alignment units comprises vertical alignment blocks, vertical alignment bars, and driving units. The pair of vertical alignment units comprises horizontal alignment blocks, a horizontal alignment bar(32), and the driving unit. The driving unit moves the horizontal alignment bar back and forth.
Abstract translation: 目的：提供用于直升机着陆的装置，以自动喷射燃料，并通过将直升机定位在紧密位置来更换电池。 构成：用于直升机降落的装置包括着陆条（10），一对垂直对准单元（20,20'）和一对水平对准单元（30,30'）。 一对垂直对齐单元安装在着陆带的两侧，并排列直升机的垂直位置。 一对水平对准单元安装在着陆带的前后两侧，并布置直升机的水平位置。 一对垂直对准单元包括垂直对准块，垂直对准条和驱动单元。 一对垂直对准单元包括水平对准块，水平对准杆（32）和驱动单元。 驱动单元来回移动水平对准杆。
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Patent Agency Ranking
公开(公告)号：KR1020130005501A
公开(公告)日：2013-01-16
申请号：KR1020110066938
申请日：2011-07-06
Applicant: 부산대학교 산학협력단
Abstract: PURPOSE: An unmanned aerial vehicle is provided to reduce manufacturing costs and purchasing costs by simultaneously reconnoitering as an unmanned aerial vehicle and an unmanned vehicle with one body. CONSTITUTION: An unmanned aerial vehicle comprises a body(10), multiple fixed blades(20-1,20-2,20-3,20-4), rotors(30-1,30-2,30-3,30-4), movable blades(40-1,40-2,40-3,40-4), and wheels(50-1,50-2,50-3,50-4). The multiple fixed blades are installed on the body. The rotors are respectively installed on the fixed blades and tilts at each different angle according to a flying mode, a vertical take-off and landing mode, and a driving mode. The movable blades are respectively installed on the rotors, are unfolded in the flying mode, and are folded in the vertical take-off and landing mode and the driving mode. The wheels are respectively installed on the rotors, are used as a landing gear in the flying mode, and are used as a driving wheel in the driving mode.
Abstract translation: 目的：提供无人驾驶飞行器，通过作为无人驾驶飞行器和一体式无人驾驶飞机同时侦察，降低制造成本和采购成本。 构成：无人驾驶飞行器包括主体（10），多个固定叶片（20-1,20-2,20-3,20-4），转子（30-1,30-2,30-3,30- 4），可动叶片（40-1,40-2,40-3,40-4）和轮（50-1,50-2,50-3,50-4）。 多个固定刀片安装在车身上。 转子分别安装在固定刀片上，并根据飞行模式，垂直起飞和着陆模式以及驾驶模式在每个不同的角度倾斜。 可动刀片分别安装在转子上，以飞行模式展开，并以垂直起降模式和驾驶模式折叠。 车轮分别安装在转子上，用作飞行模式的起落架，并用作驾驶模式下的驱动轮。
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公开(公告)号：KR1020090124820A
公开(公告)日：2009-12-03
申请号：KR1020080051236
申请日：2008-05-30
Applicant: 부산대학교 산학협력단
Abstract: PURPOSE: A stretch sheet molding apparatus including a plurality of forming punches is provided to support large pressure at any thickness of sheet and a stretch sheet molding method using the apparatus is also provided. CONSTITUTION: A stretch sheet molding apparatus comprises a plurality of forming punches(1), one or more forming jigs(2), and one or more hydraulic presses. The forming punches are arranged beneath of a sheet(5). The forming jigs are fixed to the end of the sheet. The hydraulic presses apply a tensile force to the forming jigs.
Abstract translation: 目的：提供包括多个成形冲头的拉伸片材成型装置，以在任何厚度的片材上支撑大的压力，并且还提供使用该装置的拉伸片材模制方法。 构成：拉伸片成型装置包括多个成形冲头（1），一个或多个成形夹具（2）和一个或多个液压机。 成形冲头布置在片材（5）的下方。 成型夹具固定在片材的端部。 液压机对成形夹具施加张力。
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公开(公告)号：KR100602708B1
公开(公告)日：2006-07-20
申请号：KR1020050070359
申请日：2005-08-01
Applicant: 부산대학교 산학협력단
Abstract: 본 발명은 수직 이착륙 비행 장치의 초경량 착륙장치에 관한 것으로, 무게를 최소화하면서도 안정적인 착륙이 가능하고 생산과 조립이 용이한 착륙장치를 제공하기 위하여, 수직 이착륙 비행 장치의 착륙장치에 있어서, 수직 이착륙 비행 장치의 본체와 결합 고정되는 중앙부를 기준으로 2개 이상의 궁(弓)형 몸체가 교차하도록 결합되고, 궁형 몸체는 대칭되는 수직 이착륙 비행 장치의 본체가 안착되는 안착부, 소정 각도로 하향 절곡된 절곡부 및 지면과 접촉하는 착륙부로 구성되는 것을 특징으로 한다.
수직 이착륙 비행 장치, 헬리콥터, 경량, CFRP, 동축반전 로터Abstract translation: 本发明涉及一种用于垂直起降装置的超轻型着陆装置，更具体地涉及一种能够稳定着地同时使重量最小化并且易于生产和组装的着陆装置， 拱形体包括座位部分和座位部分，座位部分上安装有对称的垂直升降装置的主体，座位部分上以预定角度向下弯曲的弯曲部分 以及与地面接触的着陆部分。
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公开(公告)号：KR101968415B1
公开(公告)日：2019-04-11
申请号：KR1020170116607
申请日：2017-09-12
Applicant: 부산대학교 산학협력단 , 주식회사 파워엠엔씨
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公开(公告)号：KR101918439B1
公开(公告)日：2018-11-13
申请号：KR1020180003903
申请日：2018-01-11
Applicant: 부산대학교 산학협력단
Abstract: 본발명은안정적인비행수행하이브리드무인항공기에관한것으로서, 보다상세하게는수직비행시측풍으로인한외란의간섭을최소화하면서자세유지를용이하게하고수평비행시비행안정성을높기위한안정적인비행수행하이브리드무인항공기에관한것이다. 본발명의일실시예에따른안정적인비행수행하이브리드무인항공기는유선형으로마련되는동체부와, 상기동체부의중심부양옆으로마련되는메인날개부와, 상기메인날개부를가로지르는형태로, 상기동체부의진행방향을기준으로양측면에평행하게마련되는바(bar) 형태의로터지지부와, 지면에수직한회전축이형성되는로터(rotor)가상기로터지지부에마련되어상기동체부를부양하는양력을발생시키는메인로터부와, 지면과평행한회전축이형성되는로터가상기동체부의전면에마련되어상기동체부의추진력을발생시키는추진로터부와, 상기동체부후측에서신축(伸縮)되는동체신축부, 및상기동체신축부의후방에마련되는꼬리날개부를포함하고, 수직이착륙시상기동체신축부는상기동체부내로삽입되어상기동체신축부의진행방향길이를감축시키고상기꼬리날개부의횡단면이일(一)자형을유지하여안정적인양력을발생시키며, 수평비행시상기동체신축부는상기동체부내에서인출되어상기동체신축부의진행방향길이를증가시키고상기꼬리날개부의횡단면이브이(V)형상으로조정하여항속거리를향상시킨다.
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