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公开(公告)号：KR100759353B1
公开(公告)日：2007-09-17
申请号：KR1020060028496
申请日：2006-03-29
Applicant: 국방과학연구소
CPC classification number: G01K15/005 , B64D2045/0085 , G01K1/20 , G01K7/02 , G01K7/16 , G01K2007/163
Abstract: An apparatus for measuring flying object temperature with a compensation function and an apparatus for compensating temperature for a thermocouple for the same are provided to be suitable to the temperature of a flying object having the limitation of weight and size by being manufactured small and light. An apparatus for measuring flying object temperature with a compensation function includes a thermocouple, a wire unit(20), a junction unit(30), an RTD(Resistance Temperature Detector)(50), a remote measuring unit(80), and a calculating unit. The thermocouple is attached on a flying object to measure the temperature of the flying object. The wire unit of the thermocouple is extended from a temperature measuring point(10) of the thermocouple. The junction unit connects a general wire(40). The RTD is connected to a leading wire(60) of the RTD to measure the temperature of the junction unit. The remote measuring unit having a transmission function receives an output signal of the RTD and the output voltage of the thermocouple. The calculating unit calculates the temperature of the flying object where a measured error is compensated according increasing the temperature of the junction unit as the output signal of the RTD and the output voltage of the thermocouple.
Abstract translation: 通过补偿功能测量飞行物体温度的装置和用于补偿热电偶的温度补偿装置被设计成适合于通过制造小型和轻型而具有重量和尺寸限制的飞行物体的温度。 用于通过补偿功能测量飞行物体温度的装置包括热电偶，导线单元（20），接合单元（30），RTD（电阻温度检测器）（50），远程测量单元（80）和 计算单位。 热电偶连接在飞行物体上，以测量飞行物体的温度。 热电偶的导线单元从热电偶的温度测量点（10）延伸。 连接单元连接通用线（40）。 RTD连接到RTD的导线（60）以测量接合单元的温度。 具有发送功能的远程测量单元接收RTD的输出信号和热电偶的输出电压。 计算单元计算通过增加接合单元的温度作为RTD的输出信号和热电偶的输出电压来补偿测量误差的飞行物体的温度。
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公开(公告)号：KR101385451B1
公开(公告)日：2014-04-15
申请号：KR1020120144623
申请日：2012-12-12
Applicant: 국방과학연구소
Abstract: The present invention relates to an apparatus and method for controlling impact velocity of a flying object. The method for control impact velocity of a flying object according to an embodiment includes the steps of: when the combustion speed of the flying object is higher than a reference combustion speed at the time of the combustion termination of the flying object, decreasing the flying speed by lowering the flight altitude, thereby decreasing the impact velocity; and when the combustion speed of the flying object is lower than the reference combustion speed at the time of the combustion termination of the flying object, increasing the flying speed by raising the flight altitude, thereby increasing the impact velocity. [Reference numerals] (100) Combustion speed detecting unit; (200) Control unit
Abstract translation: 本发明涉及一种用于控制飞行物体的撞击速度的装置和方法。 根据实施例的用于控制飞行物体的撞击速度的方法包括以下步骤：当飞行物体的燃烧速度高于飞行物体燃烧终止时的参考燃烧速度时，降低飞行速度 降低飞行高度，从而降低冲击速度; 并且当飞行物体的燃烧速度低于飞行物体的燃烧终止时的基准燃烧速度时，通过提高飞行高度来提高飞行速度，从而提高冲击速度。 （附图标记）（100）燃烧速度检测单元; （200）控制单元
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公开(公告)号：KR1020110076419A
公开(公告)日：2011-07-06
申请号：KR1020090133121
申请日：2009-12-29
Applicant: 국방과학연구소
Abstract: PURPOSE: A nozzle device for rocket for reducing tip-off and a rocket launching method are provided to prevent the tip off phenomenon by slanting combustion gas from a launching time through a deflector for a specific duration. CONSTITUTION: A nozzle device for rocket for reducing tip-off comprises a nozzle body and a deflector(142). The nozzle body is arranged in one end of a rocket main body(110) and is connected to a combustion chamber(130). The nozzle body is formed with the central axis of the main body in parallel with a center axis. The deflector makes combustion gas lean toward the central axis in the launching of the main body. The deflector ejects burning gas after the launching of the main body to the direction in parallel with the central axis. The deflector is included of an ablation material which is worn away with the combustion gas.
Abstract translation: 目的：提供一种用于减少脱落的火箭喷嘴装置和一种火箭发射方法，以通过将燃烧气体从发射时间通过偏转器倾斜一段特定持续时间来防止倾倒现象。 构成：用于减少倾倒的用于火箭的喷嘴装置包括喷嘴体和偏转器（142）。 喷嘴主体配置在火箭主体（110）的一端，与燃烧室（130）连接。 喷嘴体与主体的中心轴线平行于中心轴线形成。 导流板在主体的发射中使燃烧气体朝向中心轴线倾斜。 导向器在主体发射到与中心轴线平行的方向后喷射燃烧气体。 包括与燃烧气体一起磨损的消融材料的偏转器。
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Patent Agency Ranking
公开(公告)号：KR101108981B1
公开(公告)日：2012-02-09
申请号：KR1020090133121
申请日：2009-12-29
Applicant: 국방과학연구소
Abstract: 본 발명은 로켓용 노즐장치, 이를 구비하는 로켓 및 로켓 발사방법에 관한 것으로, 연소실로부터 분출되는 연소가스의 유동을 안내하며 로켓 본체의 발사시에 자중에 의한 모멘트를 보상하도록 형성되는 노즐장치에 있어서, 로켓 본체의 일단부에 배치되고 상기 연소실과 연결되며 상기 본체의 중심축과 평행하게 형성되는 노즐 몸체, 및 상기 본체의 발사시에 상기 연소가스를 상기 중심축에 대하여 편향시키고 상기 본체의 발사 후에 상기 연소가스를 상기 중심축과 평행한 방향으로 분출시키도록 상기 노즐 몸체의 내주에 형성되고 상기 연소가스에 의하여 마모되는 삭마재료(削磨材料, ablative material)로 이루어지는 편향부를 포함하는 로켓용 노즐장치를 제공한다. 이에 의하여 본 발명은 로켓의 경사발사시 발생하는 팁오프(tip-off) 현상을 완화 또는 방지한다.
로켓, 로켓용 노즐장치, 팁오프 현상, 삭마재료-
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公开(公告)号：KR100851889B1
公开(公告)日：2008-08-13
申请号：KR1020070065628
申请日：2007-06-29
Applicant: 국방과학연구소
IPC: B64G1/22
Abstract: A nozzle for a rocket having a separator is provided to improve thrust efficiency by gradually increasing a non-symmetric thrust since the separator is abraded according to the increment of a fly height. A nozzle(110) for a rocket having a separator includes a shrink unit(111), a nozzle throat(113), and a diffusion expansion unit(112). One end of the shrink unit is connected to a combustion chamber and a cross-section of the shrink unit decreases in a direction of extending from the combustion chamber. The nozzle throat is connected to the other end of the shrink unit. The separator is mounted on an inner surface of the diffusion expansion unit. The separator generates a symmetric separation movement to control the balance between the pressure of an output terminal of the diffusion expansion unit and an external atmosphere of the diffusion expansion unit according to an altitude. The separator is made of an ablative material abraded according to the increment of a fly height.
Abstract translation: 提供一种具有隔板的火箭喷嘴，以通过逐渐增加非对称推力来提高推力效率，因为分离器根据飞行高度的增量而磨损。 用于具有分离器的火箭的喷嘴（110）包括收缩单元（111），喷嘴喉部（113）和扩散扩展单元（112）。 收缩单元的一端连接到燃烧室，并且收缩单元的横截面在从燃烧室延伸的方向上减小。 喷嘴喉部连接到收缩单元的另一端。 分离器安装在扩散扩展单元的内表面上。 分离器产生对称分离运动，以根据高度来控制扩散扩展单元的输出端子的压力与扩散扩展单元的外部气氛之间的平衡。 分离器由根据飞行高度的增量磨损的烧蚀材料制成。
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