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公开(公告)号：KR100429005B1
公开(公告)日：2010-01-28
申请号：KR1020010006648
申请日：2001-02-10
Applicant: 국방과학연구소
IPC: C07F9/00
CPC classification number: F23G5/02 , F23G2200/00 , F23G2209/10
Abstract: PURPOSE: A method for disposing waste of toxic methylphosphonyl difluoride(DF) is provided to minimize waste and simplify total process using a single reaction group. CONSTITUTION: A method for disposing waste of methylphosphonyl difluoride comprises: a step of hydrolyzing the methylphosphonyl difluoride in neutral aqueous solution to generate methylphosphonic acid and hydrofluoric acid; a step of injecting water and distilling to separate and collecting hydrofluoric acid; a step of adding water to methylphosphonic acid having residual reaction group and liquid-incinerating; and a step of repeating the distillation step.
Abstract translation: 目的：提供一种处理有毒甲基膦酰基二氟化物（DF）废物的方法，以最大限度地减少废物，并简化使用单一反应组的总工艺。 构成：用于处理甲基膦酰基二氟化物废弃物的方法包括：在中性水溶液中水解甲基膦酰基二氟化物以产生甲基膦酸和氢氟酸的步骤; 注入水并蒸馏分离和收集氢氟酸的步骤; 向具有残留反应基团和液体焚烧的甲基膦酸中加入水的步骤; 和重复蒸馏步骤的步骤。
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公开(公告)号：KR101753681B1
公开(公告)日：2017-07-04
申请号：KR1020160090972
申请日：2016-07-18
Applicant: 국방과학연구소
CPC classification number: H04W28/0289 , H04B7/2643 , H04W28/0284 , H04W28/08 , H04W74/0816 , H04W84/18
Abstract: 본발명에따른분산호 수락제어방법은, 제1노드가자신이점유할수 있는일정홉(hop) 내비어있는 CTS 점유정보를판단하기위한프레임을수신하는 CTS 점유판단단계; 다른노드와충돌없이 CTS 점유에성공하는경우, 상기제1노드가자신의파이어링메시지를송신하는파이어링메시지송신단계; 상기파이어링메시지를수신한제2노드는상기파이어링메시지에상기제1노드가신규참여노드임을표시하는 JR플래그가 1로설정된경우, 상기제2노드는네트워크 ID 정보를통해로컬네트워크참여노드들의네트워크 ID 정보와일치하는지비교하는네트워크 ID 비교단계; 상기비교결과네트워크 ID가없거나다른네트워크 ID라면, 로컬네트워크참여노드의 CTS 점유구간에서신규노드 ID에대한 JR플래그를 1로설정하여파이어링메시지를방송하는제1파이어링메시지방송단계; 일정홉 내이웃노드범위내의참여노드수에대하여망 혼잡상태와연관된 NCS 플래그가 1로설정된비율이허용범위이내이면각 노드들이상기 JC 플래그를 1로설정하여파이어링메시지를방송하는제2파이어링메시지방송단계를포함한다.
Abstract translation: 根据本发明的分布式呼叫接纳控制的方法，所述CTS占有确定方法，包括：一个节点接收到空白帧内啤酒花（啤酒花）的时间表来确定可以它们占据CTS占用信息; 一个发射消息发送步骤，其中当CTS占用成功而不与另一个节点发生冲突时，第一节点发送它自己的发射消息; 所述第二节点接收的情况下JR标志的击发消息被设置为1，所述第二节点参与超过指示所述第一节点是新的参与节点到击发消息的网络ID信息的节点的本地网络 网络ID比较步骤，比较网络ID信息和网络ID信息; 比较，或者如果其他网络ID，广播消息JR标志用于在占用参与任命roseol 1的本地网络节点上的CTS区域的新的节点ID的第一烧成工序示出了击发消息的网络ID的结果; 一定跳频速率与所述网络拥塞状态相关联的相对于参与节点在相邻间的节点范围被设定为1的数量NCS标志内的公差第二击发消息发送到每个节点广播击发消息指定的JC标志1 roseol 和一个广播步骤。
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公开(公告)号：KR101273422B1
公开(公告)日：2013-06-11
申请号：KR1020110091127
申请日：2011-09-08
Applicant: 국방과학연구소
Abstract: 복수개의 광섬유 격자센서와 압전센서를 사용하여 항공기 운항 중에 항공기의 손상을 실시간으로 감시할 수 있도록 하여 항공기의 안전성을 보장할 수 있는, 항공기의 구조 건전성 감시 시스템을 제공한다.
본 발명에 따른 항공기의 구조 건전성 감시 시스템은 항공기 날개의 변형을 감지하는 변형감지부; 상기 항공기 날개에 가해지는 충격을 감지하는 충격감지부;
상기 항공기 날개와 동체의 연결부분에 설치되며, 균열 및 볼트 풀림을 감지하는 손상감지부; 및 상기 변형감지부로부터 신호를 받고, 상기 충격감지부로부터 신호를 받고, 상기 손상감지부로부터 신호를 받아서, 상기 변형 또는 충격이 크거나 균열 및 볼트 풀림이 발생하면 항공기의 운항을 중지시키고, 상기 변형 또는 충격이 작거나 균열 및 볼트 풀림이 발생하지 않으면 항공기의 운항을 계속시키는 제어부;를 포함한다.-
Patent Agency Ranking
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公开(公告)号：KR1019940003467B1
公开(公告)日：1994-04-22
申请号：KR1019910020518
申请日：1991-11-18
Applicant: 국방과학연구소
IPC: C03C14/00
Abstract: The SiC whisker reinforced crystallized glass composite is produced by (a) homogeneously mixing and dispersing the high purity silica colloid and the boehmite colloid disperse system and silicon carbide whisker disperse system by inducing the heterointeraction between particles with zeta potentials, (b) adding the salts of metals(lithium, magnesium) to the mixture for homogeneous dispersion, (c) preparing the composite powder by gelation and dry process, (d) sintering the composite powder. The other sol-gel process for composite powder comprises (a') gelation by adding SiC whisker disperse system to sol prepared by hydrolytic condensation of metallic alkoxide compound(silicon or aluminum alkoxide) for the high purity composite powder, (b') sintering this composite powder.
Abstract translation: SiC晶须增强结晶玻璃复合材料通过（a）通过诱导具有ζ电位的颗粒之间的异质相互作用，均匀混合和分散高纯度二氧化硅胶体和勃姆石胶体分散体系和碳化硅晶须分散体系，（b）加入盐 的金属（锂，镁）混合均匀分散，（c）通过凝胶化和干法制备复合粉末，（d）烧结复合粉末。 复合粉末的其他溶胶 - 凝胶法包括（a'）通过将SiC晶须分散系统加入到通过金属醇盐化合物（硅或铝醇盐）水解缩合制备的溶胶中用于高纯度复合粉末的凝胶化，（b'）烧结该 复合粉末。
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公开(公告)号：KR1020130075065A
公开(公告)日：2013-07-05
申请号：KR1020110143263
申请日：2011-12-27
Applicant: 국방과학연구소
Abstract: PURPOSE: A method for monitoring the structural stability of an aircraft is provided to monitor damage to an aircraft caused by a flying load or shock load in real-time by using multiple lattice sensors and piezoelectric sensors. CONSTITUTION: A method for monitoring the structural stability of an aircraft is as follows. The deformation of aircraft wings and shock applied to the aircraft wings is sensed (S11). The size of the sensed deformation and the position of the shock are stored (S12). If the size of the deformation is more than a first reference value, the flying of an aircraft is stopped. If the size of the deformation is less than a second reference value, the flying of the aircraft is continued. If the size of the deformation is between the first and second reference values, the flying of the aircraft is stopped when cracks and bolt loosening are sensed. And the flying of the aircraft is continued when cracks and bolt loosening are not sensed (S13). [Reference numerals] (S11) First step of sensing the deformation of aircraft wings and shock applied to the aircraft wings; (S12) Second step of confirming and storing the size of the deformation and the position of the shock; (S13) Third step of stopping the flying of an aircraft if the size of the deformation is more than a first reference value, continuing the flying of the aircraft if the size of the deformation is less than a second reference value, stopping the flying of the aircraft if cracks and bolt loosening are sensed, and continuing the flying of the aircraft if cracks and bolt loosening are not sensed; (S14) Fourth step of precisely inspecting damages to the deformation position, the connection portion of the aircraft wings and an aircraft body, and/or the shock position
Abstract translation: 目的：提供一种用于监测飞机结构稳定性的方法，通过使用多个格子传感器和压电传感器来实时监测由飞行载荷或冲击载荷引起的飞机损坏。 构成：监测飞机结构稳定性的方法如下。 感测到飞机机翼的变形和飞机机翼的冲击（S11）。 存储感测变形的大小和冲击的位置（S12）。 如果变形的尺寸大于第一参考值，则停止飞行器的飞行。 如果变形的尺寸小于第二参考值，则继续飞行。 如果变形的尺寸在第一和第二参考值之间，则当感测到裂纹和螺栓松动时，飞行器的飞行停止。 当感觉到裂缝和螺栓松动时，飞机继续飞行（S13）。 （S11）检测飞机机翼的变形和应用于飞机机翼的冲击的第一步骤; （S12）确认并存储变形的大小和冲击位置的第二步骤; （S13）如果变形的尺寸大于第一参考值，则停止飞行器飞行的第三步，如果变形的尺寸小于第二参考值，继续飞行的飞行，停止飞行 如果感觉到裂缝和螺栓松动，飞机如果没有感觉到裂缝和螺栓松动，继续飞行; （S14）精确检查对变形位置的损害的第四步骤，飞机机翼和飞机机身的连接部分和/或冲击位置
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