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公开(公告)号：KR100679138B1
公开(公告)日：2007-02-05
申请号：KR1020050104663
申请日：2005-11-03
Applicant: 국방과학연구소
Abstract: A device for correcting load of six axes is provided to estimate the load transmitted to six axes as a correcting load to arrange coordinate axes again and to determine a correcting coefficient of a six-axes load measuring sensor. A device for correcting load of six axes includes a supporting frame(100) to place a six-axes load measuring sensor(110) thereon, a load adapter(120) placed on the six-axes load measuring sensor, an X-axis hydraulic actuator(130) to apply axial load to the load adapter in the X-axis direction, a Y-axis hydraulic actuator(140) to apply an axial load to the load adapter in the Y-axis direction, a Z-axis hydraulic actuator(150) to apply load to the load adapter in the Z-axis direction, at least one X-axis moment hydraulic actuator(160) to apply moment load to the load adapter in the Z-axis, at least one X-axis moment hydraulic actuator(170-1) to apply a moment load to the load adapter in the X-axis, and at least one Z-axis moment hydraulic actuator(170-2) to apply moment load to the load adapter in the Y-axis.
Abstract translation: 提供了一种用于校正六轴负载的装置，以估计传输到六个轴的负载作为校正负载，以再次排列坐标轴并确定六轴负载测量传感器的校正系数。 一种用于校正六轴负载的装置包括用于在其上放置六轴负载测量传感器（110）的支撑框架（100），放置在六轴负载测量传感器上的负载适配器（120），X轴液压 致动器130，用于沿X轴方向向负载适配器施加轴向负载; Y轴液压致动器140，用于沿Y轴方向向负载适配器施加轴向负载; Z轴液压致动器 （150），用于在Z轴方向上向负载适配器施加负载;至少一个X轴力矩液压致动器（160），用于在Z轴上施加力负载到负载适配器;至少一个X轴力矩 用于在X轴上向负载适配器施加力矩负载的液压致动器（170-1）以及用于在Y轴上向负载适配器施加力矩负载的至少一个Z轴力矩液压致动器（170-2） 。
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公开(公告)号：KR101268393B1
公开(公告)日：2013-05-28
申请号：KR1020130011738
申请日：2013-02-01
Applicant: 국방과학연구소
Abstract: PURPOSE: A hybrid propulsion engine is provided to supersonically discharge a subsonically combusted fuel-air using a tandem nozzle in order to lower the minimum operational Mach number of an engine to 2.0, thereby expanding the operational range of an entire dual ramjet. CONSTITUTION: A hybrid propulsion engine includes a main body(110), a complex combustor(130), a gas generator(140), and a variable flow path valve(142). The complex combustor continuously operates in a ramjet mode and in a scramjet mode. In the ramjet mode, a tandem nozzle chokes a subsonically combusted gas in the complex combustor in order to supersonically discharge the gas. In the scramjet mode, air flows in the gas generator so that the gas generator can pre-combust fuel and air which are to be combusted in the complex combustor. The variable flow path valve shuts off the gas generator in the ramjet mode. The variable flow path valve is open in the scramjet mode, and transfers the flow path of the air in order to make part of the air flowing into a hollow portion(111) flow into the gas generator. [Reference numerals] (150) Propeller control unit; (AA) Variable flow path valve opening signal; (BB) Tandem nozzle stop signal; (CC) Mach; (DD) Altitude
Abstract translation: 目的：提供一种混合动力推进发动机，以使用串联喷嘴对二次燃烧的燃料空气进行超声波排放，以将发动机的最小操作马赫数降至2.0，从而扩大整个双冲压喷气发动机的运行范围。 构成：混合动力推进发动机包括主体（110），复合燃烧器（130），气体发生器（140）和可变流路阀（142）。 复合燃烧器以冲压喷射模式和冲压喷射模式连续运行。 在冲压喷射模式中，串联喷嘴扼流在复合燃烧器中的二次燃烧气体，以便对气体进行超声波排放。 在冲压喷射模式中，空气在气体发生器中流动，使得气体发生器可以预先燃烧将在复合燃烧器中燃烧的燃料和空气。 可变流量阀在冲压喷气模式下关闭气体发生器。 可变流路阀以冲压模式打开，并且传送空气的流动路径，以使流入中空部分（111）的空气的一部分流入气体发生器。 （附图标记）（150）螺旋桨控制单元; （AA）可变流量开阀信号; （BB）串联喷嘴停止信号; （CC）马赫; （DD）海拔高度
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Patent Agency Ranking
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公开(公告)号：KR101357062B1
公开(公告)日：2014-02-03
申请号：KR1020120040871
申请日：2012-04-19
Applicant: 국방과학연구소
Abstract: 본 발명은 로켓 등의 추진체에서 연소가스를 발생시키는 가스 발생기의 노즐을 통해 배출되는 유량 및 추력을 조절하기 위하여 노즐의 출구 단면적을 가변시키는 노즐 크기 조절밸브를 제어하기 위한 가스 발생기의 비선형 제어방법에 관한 것으로서,
입력된 명령(11)과 상기 가스 발생기(10)의 실제 압력을 감지한 압력 감지신호(15)와의 차이를 계산하고, 여기에 제어 이득(13)을 적용하여 가스발생기(10)의 노즐목 크기 조절밸브 제어신호로 사용하되, 상기 제어 이득(13)은 상기 압력 감지신호(15)와 공간 추정기(16)에 의해 추정된 상기 가스발생기(10)의 내부 공간의 크기에 의해 연속적으로 변화하도록 한 것을 특징으로 한다.
이와 같이, 가스 발생기의 노즐에 설치된 노즐 크기 제어밸브를 조절하기 위한 신호를 생성할 때 압력 센서에 의한 피드백 신호값과 함께 내부 공간의 크기에 따른 제어이득 값을 반영하여 출력 신호값을 결정하게 되므로, 내부 공간의 크기 변화에 둔감한 높은 제어성능을 얻을 수 있음은 물론 이득 스케줄링 기법의 적용에 따라 신뢰성이 높아지게 된다.-
公开(公告)号：KR100830055B1
公开(公告)日：2008-05-19
申请号：KR1020070039935
申请日：2007-04-24
Applicant: 국방과학연구소
Abstract: A thrust stand is provided to improve operation with a simpler structure since an output measurement unit is distributed over a first fixing unit. A thrust stand includes an output measurement unit. The output measurement unit comprises a main thrust output measurement unit(310), a pitch-directional load measurement unit(320), and a yaw-directional load measurement unit(330). The main thrust output measurement unit consists of first and second units which are arranged in the front of a first fixing unit and measure load in a main thrust axis direction. The pitch-directional load measurement unit measures load in a pitch axis direction which is perpendicular to the main thrust axis. The yaw-directional load measurement unit measures load in a yaw axis direction which is perpendicular to the main and pitch thrust axes.
Abstract translation: 由于输出测量单元分布在第一定影单元上，提供了一种推力支架，以便以更简单的结构改善操作。 推力支架包括输出测量单元。 输出测量单元包括主推力输出测量单元（310），俯仰方向负载测量单元（320）和偏航方向负载测量单元（330）。 主推力输出测量单元由第一和第二单元组成，其布置在第一固定单元的前部并且在主推力轴方向上测量载荷。 俯仰方向负载测量单元测量与主推力轴垂直的俯仰轴方向的载荷。 偏航方向负载测量单元测量与主推力轴和俯仰推力轴垂直的偏航轴方向的负载。
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