-
-
公开(公告)号：KR101257877B1
公开(公告)日：2013-04-23
申请号：KR1020120119221
申请日：2012-10-25
Applicant: 국방과학연구소
Abstract: PURPOSE: A flying object with an integral wing is provided to minimize a drag force by smoothly forming the external skin of a flying object and to prevent damage from deformation due to heat using a coupling member. CONSTITUTION: A flying object with an integral wing comprises a body part, an operation wing, and a tail wing(40). The body part is extended in one way direction, and the operation wing is installed to be close to one end of the body part. An area of the tail wing is arranged in the other end of the body part, and comprises a nozzle assembly(410), an external skin(420), and a wing part(421). The nozzle assembly is formed in the inner side of the body part and discharges a combusted propellant to the outside.
Abstract translation: 目的：提供具有整体翼的飞行物体，以通过平滑地形成飞行物体的外部皮肤并且防止由于使用联接构件的热而引起的变形而损坏。 构成：具有整体翼的飞行物体包括主体部分，操作翼和尾翼（40）。 主体部分沿单向方向延伸，操作翼安装成接近身体部分的一端。 尾翼的区域布置在主体部分的另一端，并且包括喷嘴组件（410），外部皮肤（420）和翼部（421）。 喷嘴组件形成在主体部分的内侧，并将燃烧的推进剂排放到外部。
-
-
Patent Agency Ranking
公开(公告)号：KR101400237B1
公开(公告)日：2014-05-28
申请号：KR1020140016482
申请日：2014-02-13
Applicant: 국방과학연구소
IPC: B60R21/26 , B60R21/263 , B60R21/272
CPC classification number: B60R21/261 , B60R21/01512 , B60R2021/26017
Abstract: The present invention relates to an apparatus for controlling a smart airbag system using a dual chamber structure, comprising a gas generator which controls a flow of high temperature gas and sprays the high temperature gas when an accident occurs in consideration of the optimum expansion power of an airbag computed from passenger information; a gas chamber which receives the high temperature gas sprayed from the gas generator to inject the high temperature gas to the air bag; and a fluid chamber which converts the high temperature gas into low temperature gas by spraying a fluid to lower the temperature before the high temperature gas is introduced into the air bag.
Abstract translation: 本发明涉及一种用于控制使用双室结构的智能气囊系统的装置，包括气体发生器，其在发生事故时控制高温气体的流动并喷射高温气体，考虑到最佳的膨胀功率 乘客信息计算的气囊; 接收从气体发生器喷射的高温气体以将高温气体注入气囊的气室; 以及流体室，其通过喷射流体将高温气体转换成低温气体，以在将高温气体引入气囊之前降低温度。
-
公开(公告)号：KR1020130051770A
公开(公告)日：2013-05-21
申请号：KR1020110117106
申请日：2011-11-10
Applicant: 국방과학연구소
Abstract: PURPOSE: A four folding curved wing for a guided missile launched from a cylindrical torpedo tube is provided to secure high mobility by reducing static stability of the guided missile. CONSTITUTION: A four folding curved wing comprises a curved wing and a connection unit. The connection unit is equipped on a lower part of the curved wing and connects the curved wing to a guided missile to be rotated. The curved wing includes inner surface and outer surface forming a curved inner space. An upper part of the curved wing includes outer surface which is cut in a square shape around a central line connecting the upper end and the lower end of the curved wing.
Abstract translation: 目的：提供一个从圆柱形鱼雷管发射的导弹的四折弯曲翼，以通过降低导弹的静态稳定性来确保高度的移动性。 构成：四个弯曲的弯曲翼包括弯曲的翼和连接单元。 连接单元配备在弯曲翼的下部，并将弯曲的翼连接到导弹以旋转。 弯曲的机翼包括形成弯曲的内部空间的内表面和外表面。 弯曲翼的上部包括围绕连接弯曲翼的上端和下端的中心线切成正方形的外表面。
-
公开(公告)号：KR101793539B1
公开(公告)日：2017-11-03
申请号：KR1020160030475
申请日：2016-03-14
Applicant: 국방과학연구소
Abstract: 본발명은, 전개와고정을정밀하게구현할수 있는유도무기의접이식날개를제공한다. 본발명에의한접이식날개는, 유도무기의동체에고정되는제1단날개; 상기제1단날개에체결및 고정되며, 일방향톱니를구비한연결핀; 상기연결핀을수용하며, 연결핀을축으로회전하여전개되는제2단날개; 및상기제2단날개에수용되며, 상기일방향톱니를탄성력을가지고누르는걸림부를구비한멈추개를구비한다. 본발명은상기일방향톱니와상기걸림부의작용으로상기제2단날개의방향성있고정밀한회전을구현한다.
-
公开(公告)号：KR1020170106832A
公开(公告)日：2017-09-22
申请号：KR1020160030475
申请日：2016-03-14
Applicant: 국방과학연구소
Abstract: 본발명은, 전개와고정을정밀하게구현할수 있는유도무기의접이식날개를제공한다. 본발명에의한접이식날개는, 유도무기의동체에고정되는제1단날개; 상기제1단날개에체결및 고정되며, 일방향톱니를구비한연결핀; 상기연결핀을수용하며, 연결핀을축으로회전하여전개되는제2단날개; 및상기제2단날개에수용되며, 상기일방향톱니를탄성력을가지고누르는걸림부를구비한멈추개를구비한다. 본발명은상기일방향톱니와상기걸림부의작용으로상기제2단날개의방향성있고정밀한회전을구현한다.
Abstract translation: 本发明提供了一种能够精确地实施展开和固定的感应武器的可折叠机翼。 根据本发明的可折叠翼包括：固定到被引导武器的主体的第一端叶片; 固定并固定到第一端叶片并具有单向齿的连接销; 第二端部刀片容纳连接销，第二端部刀片通过旋转连接销而旋转; 以及容纳在第二端部叶片中并且具有用于利用弹力按压单向齿的闩锁部的止动器。 本发明通过单向齿和啮合部分的作用实现了第二端翼的定向和精确的旋转。
-
公开(公告)号：KR101364636B1
公开(公告)日：2014-02-20
申请号：KR1020110117106
申请日：2011-11-10
Applicant: 국방과학연구소
Abstract: 본 발명은 원통형 발사관에 사용될 수 있으며, 유도조종 성능이 우수하도록 롤링 모멘트를 줄이고 기동성을 향상시킨 유도탄을 위한 네 개의 접이식 곡면날개에 관한 것으로, 본 발명의 접이식 곡면날개의 일 실시예는, 곡면날개; 상기 곡면날개의 하부에 구비되어 상기 곡면형 날개를 회동가능하게 유도탄에 결합시키는 연결부;를 포함하고, 상기 곡면형 날개는 만곡된 내부를 형성하는 내부면과 외부면을 포함하고, 상기 곡면날개의 상단부는 곡면날개의 상단과 후단을 연결하는 중심선을 중심으로 외부면이 사각으로 절단되어 있는 것을 특징으로 한다.
-
-
-
-
-
-
-
Search Results
8
records
(took 0.02 seconds)
