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1. 发明授权

KR101248417B1 발사 구속 장치가 불필요한 위성용 진동절연모듈 有权
标题翻译：空载启动和ON-ORBIT振动隔离器模块，无需启动锁定机构
公开(公告)号：KR101248417B1
公开(公告)日：2013-04-02
申请号：KR1020120128576
申请日：2012-11-14
申请人： 국방과학연구소
发明人： 이경주 , 오현웅 , 정석용 , 백철우
IPC分类号： B64G1/66 , F16F15/02
CPC分类号： B64G1/38 , B64G1/1021 , B64G2001/228 , B64G2700/24 , F16F15/02
摘要： PURPOSE: A vibration damping module for a satellite without a launching control device is provided to protect mission equipment of the satellite from impact applied in a launch environment and to damp minute vibration so that the mission equipment can be protected in an orbit environment. CONSTITUTION: A vibration damping module(1) for a satellite without a launching control device comprises a launch environment circuit breaker, an orbit environment circuit breaker, and a mounting block(10). The launch environment circuit breaker restricts impact and vibration transferred from a launch environment of the satellite. The orbit environment circuit breaker damps the high frequency of the vibration transferred from a device driven in an orbit environment to mission equipment. The mounting block integrates the launch environment circuit breaker and the orbit environment circuit breaker and fixes the mission equipment.
摘要翻译：目的：提供一种无发射控制装置的卫星减振模块，用于保护卫星任务设备免受发射环境中的冲击，并减轻微小振动，使任务设备能够在轨道环境中得到保护。构成：用于没有发射控制装置的卫星的减震模块（1）包括发射环境断路器，轨道环境断路器和安装块（10）。发射环境断路器限制从卫星的发射环境转移的冲击和振动。轨道环境断路器将从在轨道环境中驱动的设备转移到任务设备的高频振动器。安装块集成了发射环境断路器和轨道环境断路器，并修复了任务设备。

2. 发明授权

KR101445500B1 발사환경 진동저감 기능을 구비한 우주용 냉각기 미소진동 절연시스템 有权
标题翻译：具有启动振动衰减能力的空间冷却器微型振动隔离系统
公开(公告)号：KR101445500B1
公开(公告)日：2014-09-29
申请号：KR1020130110837
申请日：2013-09-16
申请人： 조선대학교산학협력단
发明人： 오현웅 , 권성철 , 전수현
IPC分类号： B64G1/22 , F16F15/02
CPC分类号： B64G1/22 , B64G1/66 , B64G2001/228 , F16F1/44 , F16F15/08 , B64G1/38 , B64G2700/24 , F16F15/02
摘要： A spaceborne cooler micro-vibration isolation system with capability of launch vibration attenuation according to the present invention comprises a fixated shaft having one end fixated and connected to a vibration generating source mounted on a satellite; a fixated shaft cover installed to wrap the fixated shaft in an axial direction; a displacement restraint block (20) through which a shaft body (32) of the fixated shaft cover (30) penetrates, forming an in-plane displacement restraint hole for preventing penetration of a shaft displacement restraint body (31) and having one side coming into contact with an end of the shaft displacement restraint body (31); a support bracket (10) coupled to the displacement restraint block (20) and including a head (11) forming a housing space for housing the shaft displacement restraint body (31) of the fixated shaft cover (30) therein and a left and right leg (13,14) extended to make a regular angle from the head (11); and a damper unit (40) including a string (45) installed on an outer side of the head (11) of the support bracket (10) to be radially arranged with respect to the shaft displacement restraint body (31) of the fixated shaft cover (30), wrapping the outer surface of the shaft displacement restraint body (31) in a circumferential direction and having a regular tensile force, and a damper part connected to the string (45) passing through a string penetration hole formed in the head (11) of the support bracket (10) for absorbing vibration generated at the fixated shaft (100).
摘要翻译：根据本发明的具有发射振动衰减能力的太空冷却器微型振动隔离系统包括固定轴，其一端固定并连接到安装在卫星上的振动发生源; 固定轴套，其安装成沿轴向包裹固定轴; 位置限制块（20），固定轴罩（30）的轴体（32）穿过该位移限制块，形成用于防止轴位移限制体（31）穿透并具有一侧的面内位移限制孔与所述轴位移限制体（31）的端部接触; 一个联接到位移限制块（20）的支撑托架（10），并包括形成用于将固定轴套（30）的轴位移限制体（31）容纳在其中的头部（11）和左右腿部（13,14）延伸成与头部（11）成一定角度; 以及阻尼单元（40），其包括安装在所述支撑托架（10）的头部（11）的外侧上的绳（45），以相对于所述固定轴的轴位移限制体（31）径向地布置盖体（30），沿圆周方向包绕轴位移限制体（31）的外表面并且具有规则的拉力;以及阻尼部分，连接到穿过形成在头部中的穿刺孔的绳（45）（10）的支撑架（11），用于吸收在固定轴（100）产生的振动。

3. 发明公开

KR1020110068032A 음향하중 저감 구조체 失效
标题翻译：消声减震结构
公开(公告)号：KR1020110068032A
公开(公告)日：2011-06-22
申请号：KR1020090124853
申请日：2009-12-15
申请人： 한국전자통신연구원
发明人： 최장섭
IPC分类号： B64G1/22 , B64G1/66
CPC分类号： G10K11/16 , B64G1/22 , B64G1/44 , B64G1/52 , B64G1/66 , B64G2001/228
摘要： PURPOSE: An acoustic load reduction structure is provided to prevent damage or breakdown of a thin film structure caused by an acoustic load. CONSTITUTION: An acoustic load reduction structure(100) comprises a substrate(10) and a tape structure(30). The tape structure is attached to one side of the substrate. The tape structure comprises an attachment part(25) attached to the substrate and a spacing part(21) which is separated from the substrate and has one or more vent holes(27).
摘要翻译：目的：提供声负荷降低结构，以防止由声负荷引起的薄膜结构的损坏或击穿。构成：声学负载减小结构（100）包括衬底（10）和带结构（30）。带结构附着在基片的一侧。带结构包括附接到基底的附接部分（25）和与基底分离并具有一个或多个通气孔（27）的间隔部分（21）。

4. 发明公开

KR1020100059576A 인공위성 태양전지판의 전개시험을 위한 무중력 상태 제공장치 失效
标题翻译：免费提供卫星太阳能电池板部署测试装置
公开(公告)号：KR1020100059576A
公开(公告)日：2010-06-04
申请号：KR1020080118398
申请日：2008-11-26
申请人： 한국항공우주연구원
发明人： 김홍배 , 이원범 , 김규선 , 최해진
IPC分类号： B64G5/00 , B64G7/00
CPC分类号： B64G7/00 , B64G1/443 , B64G2001/228
摘要： PURPOSE: A weightlessness offering apparatus for a deployment test for a solar panel of a satellite is provided to prevent the malfunction of a deploying apparatus for unfolding a solar panel attached to a satellite by enabling testing of the deploying apparatus on the ground. CONSTITUTION: A weightlessness offering apparatus for a deployment test for a solar panel of a satellite comprises a support(200) in which a satellite is installed, a fixed shaft(300) which is installed on the top of the support, a rotating shaft(400) which is installed on the fixed shaft, and a supporting unit(500) which is installed on the rotating shaft and supports the weight of a solar panel to implement a weightless state.
摘要翻译：目的：提供一种用于卫星太阳能电池板部署测试的失重提供装置，以通过使地面上的部署设备能够进行测试来防止用于展开附着在卫星上的太阳能电池板的展开装置的故障。构成：用于卫星太阳能电池板展开试验的失重提供装置包括安装有卫星的支撑件（200），安装在支架顶部的固定轴（300），旋转轴（ 400），以及支撑单元（500），其安装在旋转轴上并支撑太阳能电池板的重量以实现无重量状态。

5. 发明授权

KR101384135B1 비접착식 진동저감장치 有权
标题翻译：使用非粘合弹性体的振动减少装置
公开(公告)号：KR101384135B1
公开(公告)日：2014-04-17
申请号：KR1020130151390
申请日：2013-12-06
申请人： 한국항공우주연구원
发明人： 김대관 , 최홍택
IPC分类号： F16F15/04 , F16F15/08
CPC分类号： F16F15/08 , B64G2001/228 , F16M11/22 , F16M2200/08
摘要： The present invention relates to a non-adhesive type vibration reduction device comprising a support, a body, and an elastomer. The elastomer is connected in a non-adhesive way without using an adhesive so that the non-adhesive type vibration reduction device reduces detachment and damage caused by the degradation of adhesive strength. The body (300) includes an upper wall (310); a lower wall (320) separated from the upper wall (310) at a fixed distance; a second groove unit (340) formed on the inner surface of the upper wall (310) and the lower wall (320) to be concave; and a connection unit (33) connecting the upper wall (310) and the lower wall (320).
摘要翻译：本发明涉及一种包括支撑体，主体和弹性体的非粘合型减振装置。弹性体以非粘合方式连接而不使用粘合剂，使得非粘合型减振装置减少由粘合强度降低引起的剥离和损坏。主体（300）包括上壁（310）; 与所述上壁（310）以固定距离分离的下壁（320）; 形成在所述上壁（310）和所述下壁（320）的内表面上以形成凹面的第二凹槽单元（340）以及连接上壁（310）和下壁（320）的连接单元（33）。

6. 发明授权

KR101295886B1 음향하중 저감 구조체 失效
标题翻译：降低声学负载的结构
公开(公告)号：KR101295886B1
公开(公告)日：2013-08-12
申请号：KR1020090124853
申请日：2009-12-15
申请人： 한국전자통신연구원
发明人： 최장섭
IPC分类号： B64G1/22 , B64G1/66
CPC分类号： G10K11/16 , B64G1/22 , B64G1/44 , B64G1/52 , B64G1/66 , B64G2001/228
摘要： 본 발명은 음향 하중 저감 구조체를 제공한다. 이 구조체는, 기판과 부착되는 부착부와, 상기 기판으로부터 이격되며 적어도 하나의 통기구멍이 형성된 이격부를 포함하는 테이프 구조체를 가진다. 이로써 상기 부착부의 탄성작용과 상기 이격부와 상기 기판 사이에 형성되는 공기층의 완충 작용으로 음향 하중을 저감시킬 수 있다. 또한 상기 통기구멍을 통해 공기의 유입이 가능하여 공기압의 변화에 따른 테이프 부착부의 분리를 방지할 수 있다.
음향하중, 캡톤 테이프

7. 发明公开

KR1020110074082A 유연 블레이드와 전기유변유체를 포함하는 중합체를 이용한 우주비행체 탑재체 진동절연시스템 失效
标题翻译：使用包括电流变流体的柔性刀片和弹性体的SPACECRAFT PAYLOAD振动隔离系统
公开(公告)号：KR1020110074082A
公开(公告)日：2011-06-30
申请号：KR1020090130945
申请日：2009-12-24
申请人： 한국항공우주연구원
发明人： 박종석
IPC分类号： B64G1/38 , F16F15/18 , B64G1/66
CPC分类号： B64G1/38 , B64G2001/228 , B64G2700/24 , F16F15/18
摘要： PURPOSE: A vibration isolation system for spacecraft payload using flexible blades and an elastomeric unit including electro-rheological fluid is provided to show optimal vibration damping effect according to the condition of the spacecraft since an elastomeric unit and electro-rheological fluid are used together. CONSTITUTION: A vibration isolation system for spacecraft payload using flexible blades and an elastomeric unit including electro-rheological fluid comprises a support unit(10), an upper plate unit(20) and a vibration absorbing unit(30). The support unit is fixed to the spacecraft and supports the payload of the spacecraft. The upper plate unit is installed on the upper end of the support unit. The vibration absorbing unit is mounted on the top of the upper plate unit. The vibration absorbing unit comprises a connecting unit(31), a V-shaped blade(33) and a variable damping elastomeric unit(32). Each end of the connecting unit is fixed to each of both ends of the upper plate unit and the payload is mounted on the top of the connecting unit.
摘要翻译：目的：提供使用柔性叶片和包括电流变流体的弹性单元的航天器有效载荷的隔振系统，以根据航天器的状况显示出最佳的减振效果，因为弹性单元和电流变流体一起使用。构成：使用柔性叶片和包括电流变流体的弹性单元的用于航天器有效载荷的隔振系统包括支撑单元（10），上板单元（20）和振动吸收单元（30）。支撑单元固定在航天器上并支撑航天器的有效载荷。上板单元安装在支撑单元的上端。振动吸收单元安装在上板单元的顶部。振动吸收单元包括连接单元（31），V形叶片（33）和可变阻尼弹性体单元（32）。连接单元的每个端部固定到上板单元的两端中的每一端，并且有效载荷安装在连接单元的顶部。

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