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Patent Agency Ranking
公开(公告)号：KR101338178B1
公开(公告)日：2013-12-09
申请号：KR1020130092063
申请日：2013-08-02
Applicant: 국방과학연구소
Abstract: The present invention relates to restriction release apparatus of a portable guided missile. Disclosed is the restriction release apparatus including a cooling gas container assembly, which provides gas used for cooling an explorer; a branch block, which distributes the gas to the explorer; and a restriction release device of a portable guided missile, which releases the restriction of the portable guided missile by using the pressure of the gas provided from the branch block.
Abstract translation: 本发明涉及便携式导弹的限制解除装置。 公开了一种包括提供用于冷却探险者的气体的冷却气体容器组件的限制释放装置; 一个分支块，将气体分配给探险者; 以及便携式导弹的限制释放装置，其通过使用从分支块提供的气体的压力来释放便携式导弹的限制。
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公开(公告)号：KR101338177B1
公开(公告)日：2013-12-09
申请号：KR1020130092062
申请日：2013-08-02
Applicant: 국방과학연구소
Abstract: The present invention relates to an apparatus for adjusting a control fin of a portable guided missile comprising: a control fin having a first through-hole formed in one side, and rotating on the first through-hole; a shaft coupled in a state where one side is received, and arranged inside a guided missile body; a hinge for connecting the control fin and the shaft through the second through-hole of the shaft and the first through-hole; a fixing fin penetrating a first fixing pin receiving hole formed on the hinge in a direction vertical to the axial direction of the hinge and a second fixing pin receiving hole formed on one side of the control fin in a direction different to the first through-hole so as to restrict the rotation of the control fin and the hinge; and an elastic member arranged on the shaft to rotate the control fin.
Abstract translation: 本发明涉及一种用于调节便携式导弹的控制翅片的装置，包括：控制翅片，其具有形成在一侧的第一通孔，并在第一通孔上旋转; 在一侧被接收的状态下联接并布置在导弹体内部的轴; 用于通过所述轴的第二通孔和所述第一通孔连接所述控制翅片和所述轴的铰链; 固定翅片，其穿过形成在所述铰链上的垂直于所述铰链的轴向的方向上的第一固定销接收孔;以及第二固定销容纳孔，其形成在所述控制翅片的与所述第一通孔不同的方向上的一侧 以限制控制翅片和铰链的旋转; 以及设置在所述轴上以使所述控制翅片旋转的弹性构件。
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公开(公告)号：KR101529514B1
公开(公告)日：2015-06-17
申请号：KR1020140062467
申请日：2014-05-23
Applicant: 국방과학연구소
Abstract: 본발명은, 냉각가스가유입되는제1 유로와연소가스가유입되는제2 유로를구비하는몸체부, 적어도일부가상기제1 유로내부로삽입되는가스관을구비하고내부에상기냉각가스가충전되는가스공급부, 추진제를연소시켜발생되는상기연소가스를상기제2 유로내부로유입시키는착화부, 및상기제1 및제2 유로를구획하고상기연소가스에의해가압되어슬라이드가능하게구성되며상기슬라이드이동에의해상기제1 유로내부로삽입된상기가스관의적어도일부를절단하도록형성되는전단부를포함하고, 상기냉각가스에상기제2 유로내부의불순물이혼합되는것을방지하기위하여상기냉각가스가상기절단된가스관을통하여상기제1 유로로흐를수 있도록, 상기전단부는제1 및제2 유로를격리시킨상태를유지하며슬라이드이동되는것을특징으로하는냉각가스공급장치.
Abstract translation: 本发明涉及一种用于供应冷却气体以阻止冷却气体的流路中的污染物流入的装置，更具体地，涉及一种能够防止污染物流入冷却气体的流路的冷却气体的装置， 将流路中的污染物排放到外面。 该装置包括：主体部，其具有冷却气体流过的第一流路和燃烧气体流过的第二流路; 气体充填部，其具有将至少一部分插入到所述第一流路中的气体管，并将内部的冷却气体充电; 以及点燃部，其燃烧所述推进剂并将所述燃烧气体送入所述第二流路; 将第一流路和第二流路分割的剪切部构造为能够由燃烧气体的压力而滑动，并且，通过该第一流路和第二流路的运动而切断插入第一流路的气体配管的至少一部分 滑动，其中剪切部分通过滑动而移动，同时保持第一流动通道和第二流动通道彼此分离，使得第二流动通道中的污染物不会与冷却气体混合，并且冷却气体将流入第一流动通道 通过切割气管。
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公开(公告)号：KR101338156B1
公开(公告)日：2013-12-06
申请号：KR1020130105471
申请日：2013-09-03
Applicant: 국방과학연구소
Abstract: The present invention provides a portable ejection deice for a guided missile. The present invention includes a first cylindrical surface; a housing including an extended surface extended from one end of the first surface by being curved towards the outside of a cylinder; and a connection ring assembly connecting the portable guided missile and the housing. The connection ring assembly unit includes a body in which a groove in which the extended surface inserted is formed on one end, wherein the one end forms a free end and the other end forms a fixed end by being connected to the housing; a spring applying elasticity to the body by being arranged between a first surface and the connection ring body; and a fixing pin of which one end faces the first surface by passing through the body.
Abstract translation: 本发明提供一种用于导弹的便携式喷射罩。 本发明包括第一圆筒形表面; 壳体，其包括从所述第一表面的一端朝向圆柱体的外侧弯曲的延伸表面; 以及连接便携式导弹和壳体的连接环组件。 连接环组件单元包括其中在一端形成有延伸表面插入的槽的主体，其中一端形成自由端，另一端通过连接到壳体形成固定端; 弹簧通过布置在第一表面和连接环体之间而对身体施加弹性; 以及通过穿过本体而使其一端面向第一表面的固定销。
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公开(公告)号：KR101356554B1
公开(公告)日：2014-01-29
申请号：KR1020130095894
申请日：2013-08-13
Applicant: 국방과학연구소
Abstract: The present invention relates to a deploying and folding structure of a wing used for controlling a position and a posture of a guided missile during a flight. The guided missile includes a plurality of wings used for controlling the posture and the position of the guided missile during the flight. The deploying and folding structure of the wing of the guided missile includes a hinge which is a rotary axis of the wing by being included on one end of the wing; a spring providing a rotatory force to the wing while the wing is rotated; and a hinge body in which the wing, the spring, and the hinge are assembled. The deploying and folding structure of the wing of the guided missile is characterized by deploying and folding the wing by rotating the same around the hinge once.
Abstract translation: 本发明涉及一种用于在飞行中控制导弹的位置和姿势的机翼的展开和折叠结构。 导弹包括用于控制飞行中导弹的姿势和位置的多个翼。 导弹翼的展开和折叠结构包括一个铰链，它是翼的旋转轴线，它包括在机翼的一端; 弹簧在机翼旋转时向机翼提供旋转力; 以及铰接体，其中机翼，弹簧和铰链组装在其中。 导弹翼的展开和折叠结构的特点是通过围绕铰链旋转一次来展开和折叠机翼。
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