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公开(公告)号：KR100517195B1
公开(公告)日：2005-09-27
申请号：KR1020020080744
申请日：2002-12-17
Applicant: 한국항공우주연구원
IPC: H02M3/28
CPC classification number: Y02B70/1491
Abstract: 본 발명은 영전압 천이(Zero-Voltage Transition) 펄스폭 변조(Pulse Width Modulation)방식의 DC-DC 컨버터에서 일반적으로 사용되는 강제 스위칭 방식의 보조 스위치를 소프트 스위칭 방식으로 스위칭 시키도록 하는 소프트 스위칭 방식의 보조 스위치를 갖는 영전압 스위칭 PWM 방식의 DC-DC 전력변환기에 관한 것이다.
이러한 본 발명은 영전압 천이 펄스폭 변조 방식의 직류-직류 컨버터에 있어서, 주 스위치와 필터 인덕터사이에 역저지 다이오드를 직렬 연결하고, 상기 주 스위치와 병렬 연결된 보조 스위치와 공진 인덕터 사이에 역저지 다이오드를 직렬 연결함으로써 이루어지는 것으로, 영전류 조건에서 스위칭하기 때문에 스위칭 손실이 제거되는 한편 주 스위치의 영전압 스위칭, PWM에 의한 일정 주파수 제어 등의 장점을 그대로 유지하여 DC-DC 컨버터의 전력변환 효율을 높일 수 있다.-
公开(公告)号：KR1020030018303A
公开(公告)日：2003-03-06
申请号：KR1020010051953
申请日：2001-08-28
Applicant: 한국항공우주연구원
IPC: G01F23/28
CPC classification number: G01F23/296 , G01D21/02 , G01H1/00
Abstract: PURPOSE: A rocket onboard sloshing measurement apparatus is provided to allow for a precise computer simulation by using the data obtained from the measurement through the use of an ultrasonic sensor and three-axis accelerometer. CONSTITUTION: A rocket onboard sloshing measurement apparatus comprises an ultrasonic sensor for measuring the amplitude of the fuel contained in a fuel tank for propeller to be mounted on a rocket; a three-axis accelerometer for measuring vibration of the fuel tank caused due to the sloshing of the fuel; a signal controller(3) for controlling signals in such a manner that signals output from the ultrasonic sensor and the three-axis accelerometer become suitable as an input to a remote measurement system; and a data processing unit(4) for converting an analog sensor signal output from the signal controller into a digital signal, and connecting the digital signal in serial or parallel to a PCM encoder which serves as a data processor of the remote measurement system.
Abstract translation: 目的：通过使用超声波传感器和三轴加速度计，通过使用从测量中获得的数据，提供火箭板上晃荡测量装置，以实现精确的计算机模拟。 构成：火箭机载晃动测量装置包括：超声波传感器，用于测量安装在火箭上的螺旋桨的燃料箱中容纳的燃料的振幅; 三轴加速度计，用于测量由于燃料晃动引起的燃料箱的振动; 用于以这样的方式控制信号的信号控制器（3），使得从超声波传感器和三轴加速度计输出的信号变得适合作为远程测量系统的输入; 以及数据处理单元（4），用于将从信号控制器输出的模拟传感器信号转换为数字信号，并将数字信号串行或并行连接到用作远程测量系统的数据处理器的PCM编码器。
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公开(公告)号：KR1020040054088A
公开(公告)日：2004-06-25
申请号：KR1020020080744
申请日：2002-12-17
Applicant: 한국항공우주연구원
IPC: H02M3/28
CPC classification number: Y02B70/1491
Abstract: PURPOSE: A zero-voltage PWM DC-DC power converter having an auxiliary switch of soft switching method is provided to remove a switching loss generated at the auxiliary switch and enhance power converter efficiency. CONSTITUTION: A zero-voltage PWM DC-DC power converter comprises a filter inductor(9), a main switch(1), a main diode(8), a filter capacitor(10), an auxiliary switch(2), a resonating inductor(3), a resonating capacitor(4), and inverse prevention diodes(5,6) connected in serial to the main switch and the auxiliary switch. The filter inductor is connected in serial to the main switch, the auxiliary switch, and the resonating capacitor. The main switch, the auxiliary switch, and the resonating capacitor are connected to each other in parallel. The inverse prevention diode(6) is connected in serial between the resonating inductor and the auxiliary switch.
Abstract translation: 目的：提供一种具有软开关方式的辅助开关的零电压PWM DC-DC电源转换器，以消除辅助开关产生的开关损耗，提高功率转换器的效率。 构成：零电压PWM DC-DC电力转换器包括滤波电感器（9），主开关（1），主二极管（8），滤波电容器（10），辅助开关（2），谐振 电感器（3），谐振电容器（4）和反向防止二极管（5,6），其串联连接到主开关和辅助开关。 滤波电感串联连接到主开关，辅助开关和谐振电容器。 主开关，辅助开关和谐振电容器彼此并联连接。 反相二极管（6）串联连接在谐振电感器和辅助开关之间。
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公开(公告)号：KR100372607B1
公开(公告)日：2003-02-17
申请号：KR1020000034669
申请日：2000-06-23
Applicant: 한국항공우주연구원
IPC: H03M5/02
Abstract: PURPOSE: A PCM coder mounted on a rocket is provided to fully carry out sampling rating requested by each sensors on sending aviation performance data and observation onto the earth ground and to simplify its construction. CONSTITUTION: A controller U6 generates a control signal initiating A/D conversion after obtaining a significant time to follow an original signal for a selected signal and acts to control a sampling rate in the whole signals data, and produce a channel signal Ao, An of an analog multiplex U1 to apply signals for sensors S1-Sn to an A/D converter U2, so that signal lines are connected with the output of the sensor corresponded to the input of the analog multiplex at a ratio of 1:1. To adjust a bit rate of the sending signal, the serial and parallel converter(U3) is supplied with a clock and parallel load signals and produces a continuous serial bit stream data in accordance with 1 bit output by a clock input after latching A/D converted signals to the converter. A coder convertor U4 converts an input NRZ-L code into BIΦ-L. A band width sent signal is reduced by passing a cut-off frequency half times more than the bit rate through a low band passage filter U5.
Abstract translation: 目的：提供安装在火箭上的PCM编码器，以充分执行每个传感器要求的采样率，以便将航空性能数据和观测结果发送到地面并简化其结构。 构成：控制器U6在获得显着的时间后，产生一个启动A / D转换的控制信号，以跟随所选信号的原始信号，并用来控制整个信号数据中的采样率，并产生一个信道信号Ao，An 一个模拟多路复用器U1，用于将传感器S1-Sn的信号加到A / D转换器U2上，使得信号线与对应于模拟多路复用器的输入的传感器的输出以1：1的比率连接。 为了调整发送信号的比特率，串行和并行转换器（U3）提供有时钟和并行加载信号，并根据在锁存A / D之后由时钟输入输出的1位产生连续的串行比特流数据 转换后的信号到转换器。 编码器转换器U4将输入的NRZ-L码转换成BI＆amp; Phi; -L。 带宽发送信号通过经过低频带通过滤波器U5的比特率超过半个截止频率而减小。
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Patent Agency Ranking
公开(公告)号：KR1020020005196A
公开(公告)日：2002-01-17
申请号：KR1020000034669
申请日：2000-06-23
Applicant: 한국항공우주연구원
IPC: H03M5/02
CPC classification number: H03M7/3053 , H03M9/00 , H03M2201/192
Abstract: PURPOSE: A PCM coder mounted on a rocket is provided to fully carry out sampling rating requested by each sensors on sending aviation performance data and observation onto the earth ground and to simplify its construction. CONSTITUTION: A controller U6 generates a control signal initiating A/D conversion after obtaining a significant time to follow an original signal for a selected signal and acts to control a sampling rate in the whole signals data, and produce a channel signal Ao, An of an analog multiplex U1 to apply signals for sensors S1-Sn to an A/D converter U2, so that signal lines are connected with the output of the sensor corresponded to the input of the analog multiplex at a ratio of 1:1. To adjust a bit rate of the sending signal, the serial and parallel converter(U3) is supplied with a clock and parallel load signals and produces a continuous serial bit stream data in accordance with 1 bit output by a clock input after latching A/D converted signals to the converter. A coder convertor U4 converts an input NRZ-L code into BIΦ-L. A band width sent signal is reduced by passing a cut-off frequency half times more than the bit rate through a low band passage filter U5.
Abstract translation: 目的：提供安装在火箭上的PCM编码器，以完全执行每个传感器要求的发送航空性能数据和观测到地面上的采样等级，并简化其构造。 构成：控制器U6在获得用于跟随所选信号的原始信号的有效时间之后产生启动A / D转换的控制信号，并且用于控制整个信号数据中的采样率，并产生信道信号Ao，An 用于将传感器S1-Sn的信号施加到A / D转换器U2的模拟多路复用器U1，使得信号线与以1：1的比率对应于模拟多路复用的输入的传感器的输出连接。 为了调整发送信号的比特率，串行和并行转换器（U3）提供时钟和并行负载信号，并在锁存A / D后根据时钟输入产生1位输出的连续串行位流数据 转换信号转换器。 编码器转换器U4将输入的NRZ-L码转换成BIΦ-L。 通过将截止频率通过低频带通过滤波器U5通过比比特率的一半倍减小带宽发送信号。
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公开(公告)号：KR1020020005195A
公开(公告)日：2002-01-17
申请号：KR1020000034668
申请日：2000-06-23
Applicant: 한국항공우주연구원
IPC: G06F19/00
Abstract: PURPOSE: A shock data acquisition system is provided to measure a shock which occurs during a flight, obtain lot of data for a short time in synchronization with time at which an event is generated for effectively using a telemetry channel when transmitting on the ground, store the data in a memory of a launching unit and transmit a sequentially obtained data on the ground based on a sync signal for thereby increasing an efficiency of a telemetry channel and simplifying a data process. CONSTITUTION: A sensor(U1) receives a static current of a static current resource(S1). A computation amplifier(U2) accurately amplifies a signal sensed by the impact sensor(U1). An A/D converter(U3) converts an output signal of the computation amplifier(U2) into a digital signal value. A RAM(U4) temporarily stores a digital data converted by the A/D converter(U3). A controller(U5) obtains a data when an event occurs and outputs a stored data when a converted data is requested by the other system. When an event generation signal(EVENT) is detected, the controller(U5) controls the A/D converter(U3) and the RAM(U4). The data is converted into a digital data by the A/D converter(U3) based on an impact degree of 10,000Sample/Sec which is generated by the sensor(U1) for a certain time(800mS). The stored impact data is transmitted on the ground at 200Sample/Sec in synchronization with a ground transmission signal(Sync).
Abstract translation: 目的：提供一种冲击数据采集系统，用于测量飞行中发生的冲击，与发生事件的时间同步，获取大量数据，以便在地面上传输时有效使用遥测通道，存储 发射单元的存储器中的数据，并且基于同步信号在地面上发送顺序获得的数据，从而提高遥测通道的效率并简化数据处理。 构成：传感器（U1）接收静态电流资源的静态电流（S1）。 计算放大器（U2）精确地放大由冲击传感器（U1）感测的信号。 A / D转换器（U3）将计算放大器（U2）的输出信号转换为数字信号值。 RAM（U4）临时存储由A / D转换器（U3）转换的数字数据。 当事件发生时，控制器（U5）获取数据，并且当其他系统请求转换的数据时，输出存储的数据。 当检测到事件发生信号（EVENT）时，控制器（U5）控制A / D转换器（U3）和RAM（U4）。 基于由传感器（U1）产生的一定时间（800mS）的10,000Sample / Sec的影响程度，通过A / D转换器（U3）将数据转换成数字数据。 存储的冲击数据与地面传输信号（Sync）同步地以200Sample / Sec在地面上传输。
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公开(公告)号：KR102252061B1
公开(公告)日：2021-05-14
申请号：KR1020190106643
申请日：2019-08-29
Applicant: 한국항공우주연구원
Abstract: 트랜스폰더(transponder)가이용되는위치추적시스템을시험하는장치가개시된다. 이장치는궤도정보수신부, 거리정보생성부, 응답-지연시간설정부, 제어부, 및비교분석부를포함한다. 궤도정보수신부는시험대상궤도의정보를수신한다. 거리정보생성부는시험대상궤도의시간(t)에따른거리인제1 거리(d1(t))의정보를생성한다. 응답-지연시간설정부는, 시간(t)에따른상기제1 거리(d1(t))에대응하여, 시간(t)에따른트랜스폰더의응답-지연시간(Td(t))을설정한다. 제어부는, 궤도정보수신부, 거리정보생성부, 응답-지연시간설정부, 및트랜스폰더를구동한다. 비교분석부는, 위치추적시스템에의하여감지된시간(t)에따른측정거리를수신하고, 제1 거리(d1(t))와측정거리를상호비교하면서위치추적시스템을시험한다.
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公开(公告)号：KR1020120069793A
公开(公告)日：2012-06-29
申请号：KR1020100131091
申请日：2010-12-21
Applicant: 한국항공우주연구원
IPC: F42C21/00
Abstract: PURPOSE: A portable inspection apparatus for verifying detonation of an EBW(Explosive BridgeWire) driving device is provided to safely perform an inspection test instead of the EBW. CONSTITUTION: A portable inspection apparatus for verifying detonation of an EBW(Explosive BridgeWire) driving device comprises a CVR(Current Viewing Resistor)(10), a unit(20) for detecting a peak current value, a unit(30) for detecting a rising time, a comparison/determination unit(40), and a result detection unit(50). The CVR is connected to the positive pole(+) and negative pole(-) of the EBW driving unit. The unit for detecting the peak current value detects the peak current(Ipk) of an EBW. The unit for detecting the rising time detects the rising time(Tr) of the EBW. The comparison/determination unit compares the detected current and time with a peak current critical value and a time critical value. The result detection unit detects the result of the comparison/determination unit.
Abstract translation: 目的：提供用于验证EBW（爆炸桥线）驱动装置的爆震的便携式检查装置，以安全地执行检查试验而不是EBW。 构成：用于验证EBW（爆炸桥线）驱动装置的爆震的便携式检查装置包括CVR（电流检测电阻器）（10），用于检测峰值电流值的单元（20），用于检测 上升时间，比较/确定单元（40）和结果检测单元（50）。 CVR连接到EBW驱动单元的正极（+）和负极（ - ）。 用于检测峰值电流值的单元检测EBW的峰值电流（Ipk）。 用于检测上升时间的单元检测EBW的上升时间（Tr）。 比较/确定单元将检测到的电流和时间与峰值电流临界值和时间临界值进行比较。 结果检测单元检测比较/确定单元的结果。
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