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公开(公告)号：KR100882598B1
公开(公告)日：2009-02-12
申请号：KR1020070124478
申请日：2007-12-03
Applicant: 한국항공우주연구원
Abstract: A rotation angle compensation method of a drive nozzle is provided to measure the driving signal during TVC(Thrust Vector Control) accurately by comparing the inputted driving signal with the actual driving of the nozzle. A rotation angle compensation method of a drive nozzle comprises the steps of: determining an angle proportional factor and a slope proportional factor for correcting the mutual error about the input signal(S1); measuring yaw displacement and pitch displacement by using a displacement gauge(S2); producing yaw angle and pitch angle from the measured yaw and pitch displacement(S3); producing corrected yaw displacement angle and pitch displacement angle from the yaw angle and pitch angle by compensating the interaction between the displacement gauges with applying the angle proportional factor(S4); and producing yaw-corrected angle and pitch-corrected angle from the corrected yaw displacement angle and pitch displacement angle with applying the slope proportional factor(S5).
Abstract translation: 提供驱动喷嘴的旋转角补偿方法，通过将输入的驱动信号与喷嘴的实际驱动进行比较，精确地测量TVC（推力矢量控制）期间的驱动信号。 驱动喷嘴的旋转角度补偿方法包括以下步骤：确定用于校正与输入信号相关的相互误差的角度比例因子和斜率比例因子（S1）; 通过使用位移计（S2）测量偏航位移和俯仰位移; 从所测量的偏航和俯仰位移产生偏航角和俯仰角（S3）; 通过施加角度比例因子（S4）来补偿位移量规之间的相互作用，从偏航角和俯仰角产生校正的偏航位移角和俯仰位移角; 并且通过应用斜率比例因子从校正的偏航偏移角和俯仰位移角产生偏航校正角度和俯仰校正角度（S5）。
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公开(公告)号：KR100668805B1
公开(公告)日：2007-01-12
申请号：KR1020050127910
申请日：2005-12-22
Applicant: 한국항공우주연구원
CPC classification number: B64G1/26
Abstract: A method of arranging a shaft of a driving nozzle is provided to inject the satellite in the right orbit by initially corresponding the shaft to the fuselage shaft and minimizing the position error of the satellite launching body. A method of arranging a shaft of a driving nozzle is composed of a step(S110) of measuring the centers of the external diameter of the driving nozzle connection part, the driving nozzle neck, and the driving nozzle rear end; a step(S120) of calculating and correcting to be parallel with the driving nozzle shaft and the center shaft of the external diameter of the nozzle; and a step(S130) of correcting to correspond the driving nozzle shaft to the center shaft of the external diameter of the nozzle by measuring and calculating the parallel distance of the corrected driving nozzle shaft and the fuselage shaft.
Abstract translation: 提供一种布置驱动喷嘴的轴的方法，用于将卫星初始地对应于机身轴并将卫星发射体的位置误差最小化，将卫星注入右轨道。 布置驱动喷嘴的轴的方法由测量驱动喷嘴连接部分，驱动喷嘴颈部和驱动喷嘴后端的外径的中心的步骤（S110）组成; 计算和校正与喷嘴的外径的驱动喷嘴轴和中心轴平行的台阶（S120）; 以及通过测量和计算校正后的驱动喷嘴轴和机身轴的平行距离来校正驱动喷嘴轴与喷嘴外径的中心轴的步骤（S130）。
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公开(公告)号：KR1020100132851A
公开(公告)日：2010-12-20
申请号：KR1020090051651
申请日：2009-06-10
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A notch displacement gauge calibrator and a calibrating system using the same are provided to accurately measure displacement by calibrating a displacement gauge in a measuring system comprised of a displacement gauge and a measuring device. CONSTITUTION: A notch type displacement gauge calibrator includes a body(10), a micrometer holder(20), a displacement gauge holder(30), and a notch(40). The body includes a micrometer(200) and a displacement gauge. The micrometer holder has a penetration hole(21) through which the driving unit of the micrometer passes. The micrometer holder includes an extension unit(22) contacted with the body to be fixed to the body. The displacement gauge holder has a shape corresponding to the outer surface of the displacement gauge. The displacement gauge holder includes an extension unit(32) with the body. The notch receives the bottom of the outer surface of the displacement gauge.
Abstract translation: 目的：提供凹口位移计校准器和使用该位移计的校准系统，通过校准由位移计和测量装置组成的测量系统中的位移计，来精确地测量位移。 构成：凹口型位移计校准器包括主体（10），测微器支架（20），位移计保持器（30）和凹口（40）。 身体包括千分尺（200）和位移计。 千分尺支架具有穿孔（21），千分尺的驱动单元穿过该通孔。 千分尺保持器包括与身体接触以固定到身体的延伸单元（22）。 位移计保持器具有对应于位移计的外表面的形状。 位移计保持器包括具有主体的延伸单元（32）。 凹口接收位移计的外表面的底部。
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