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1.发明授权추력 벡터 제어(Ｔｈｒｕｓｔ Ｖｅｃｔｏｒ Ｃｏｎｔｒｏ ： ＴＶＣ) 비행체의 피치각 명령을 실시간으로 산출하기 위한 방법 및 이를 이용하는 유도 조정 장치 有权用于计算实时控制飞行器的俯仰指令的方法及其调节装置
公开(公告)号：KR101261240B1
公开(公告)日：2013-05-07
申请号：KR1020110107202
申请日：2011-10-19
Applicant: 국방과학연구소
Abstract: 본명세서는추력벡터제어(Thrust Vector Control: TVC) 방식을이용하는비행체의피치각(pitch angle) 명령을산출하기위한방법에있어서, 상기비행체에대한초기비행상태정보및 로켓의추력특성정보를입력정보로획득하는단계; 상기비행체에대한목표정점고도및 성형종료피치각에대한파라미터값을설정하는단계; 상기획득된입력정보및 상기설정된파라미터값을이용하여, 상기로켓분리후 상기비행체가목표정점고도에도달하기위한피치각성형구간을결정하는단계; 및상기결정된피치각성형구간및 상기성형종료피치각에기초하여, 상기비행체에대한피치각명령을산출하는단계를포함하여이루어진다.
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公开(公告)号：KR1020160070573A
公开(公告)日：2016-06-20
申请号：KR1020140177705
申请日：2014-12-10
Applicant: 국방과학연구소
Abstract: 본발명은유도탄의요격지점(Impact Point)을실시간으로예측할수 있는유도탄의요격지점실시간예측방법에관한것으로, 비행조건입력시유도탄의비행궤적을고려한비행거리를도출하는단계; 유도탄의비행속도를구간선형화하고잔여비행시간동안적분하여유도탄의비행속도를고려한비행거리를해석적으로도출하는단계; 상기도출된유도탄의비행궤적을고려한비행거리와유도탄의비행속도를고려한비행거리를연립하여요격지점관계식을도출하는단계; 상기도출된요격지점관계식의해를산출하는단계; 및상기산출된요격지점관계식의해를이용하여요격예상지점및 잔여비행시간을실시간예측하는단계;를포할수 있다.
Abstract translation: 本发明涉及实时预测导弹的影响点的方法。 该方法包括：在输入飞行条件时考虑到导弹的轨迹导出飞行距离的步骤; 考虑到导弹的飞行速度，通过对导弹的飞行速度进行线性化并将飞行时间整合为一个剩余飞行时间来分析导出飞行距离的步骤; 考虑到飞行速度，考虑到导弹的轨迹，组合飞行距离，得出冲击点相互作用公式的步骤; 计算派生冲击点相互作用公式的值的步骤; 以及通过使用冲击点相互作用公式的计算值来预测预期影响点和剩余飞行时间的步骤。 因此，本发明能够实现有效的中射。
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Patent Agency Ranking
公开(公告)号：KR1020140104245A
公开(公告)日：2014-08-28
申请号：KR1020130018196
申请日：2013-02-20
Applicant: 국방과학연구소
CPC classification number: G06T17/10 , G06T3/0031 , G06T7/277 , G06T2207/20076
Abstract: The present invention relates to a method for calculating an effective search area for a seeker to improve a lock-on-target (LOT) performance, which models a space area where a real target may exist into a three-dimensional ellipsoid considering a navigational error of an aircraft and a location error of a target, determines the size of the ellipsoid space area capable of maximizing the LOT probability of the seeker in the modeled three-dimensional ellipsoid space area, converts the determined three-dimensional ellipsoid space area into a two-dimensional effective search area within a viewing screen of the seeker, and determines whether a directing point of the seeker exists within the converted two-dimensional effective search area to verify the validity of seeker information, thereby reducing the probability of wrong lock-on-target by searching the target only in the determined effective search area when recognizing the target.
Abstract translation: 本发明涉及一种用于计算寻求者的有效搜索区域以改善锁定目标（LOT）性能的方法，其将真实目标可能存在的空间区域建模成三维椭圆体，考虑导航误差 的飞机和目标的位置误差，确定能够最大化建模的三维椭圆空间区域中的寻求者的LOT概率的椭球空间区域的大小，将确定的三维椭圆空间区域转换为二 在寻求者的观看屏幕内的维度有效搜索区域，并且确定寻求者的指向点是否存在于转换的二维有效搜索区域内以验证寻求者信息的有效性，从而降低错误锁定的概率， 在识别目标时，仅在确定的有效搜索区域中搜索目标。
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4.发明公开추력 벡터 제어(Ｔｈｒｕｓｔ Ｖｅｃｔｏｒ Ｃｏｎｔｒｏ ： ＴＶＣ) 비행체의 피치각 명령을 실시간으로 산출하기 위한 방법 및 이를 이용하는 유도 조정 장치 有权用于计算实时控制飞行器的俯仰指令的方法及其调节装置
公开(公告)号：KR1020130043007A
公开(公告)日：2013-04-29
申请号：KR1020110107202
申请日：2011-10-19
Applicant: 국방과학연구소
CPC classification number: F02K9/80 , G05D1/107 , G06F17/10 , G06F17/5009
Abstract: PURPOSE: A method for calculating a pitch angle command and an induction control device using the same are provided to operate the pitch angle command according to a flight condition of a flight vehicle by using sensor information. CONSTITUTION: An induction control device obtains initial flight condition information for a flight vehicle as input information(S110). The induction control device sets a parameter value for a target peak altitude for the flight vehicle and a deformation end pitch angle(S120). The induction control device determines a pitch angle deformation section after a rocket is separated(S130). The induction control device calculates a pitch angle command for the flight vehicle based on the pitch angle deformation section and the deformation end pitch angle(S140). Initial flight condition information includes flight altitude, rising speed, and a pitch angle. Rocket thrust characteristic information includes the thrust size of the rocket and the burning time of the rocket. [Reference numerals] (AA) Start; (BB) End; (S110) Inputting initial flight condition information and rocket thrust feature information; (S120) Setting a target peak altitude and deformation end pitch angle; (S130) Setting a pitch angle deformation section; (S140) Calculating a pitch angle command;
Abstract translation: 目的：提供一种用于计算俯仰角指令的方法和使用其的感应控制装置，以通过使用传感器信息根据飞行器的飞行状况来操作俯仰角命令。 构成：感应控制装置获取作为输入信息的飞行器的初始飞行状态信息（S110）。 感应控制装置设定用于飞行车辆的目标峰值高度的参数值和变形结束俯仰角度（S120）。 感应控制装置在火箭分离后确定俯仰角变形部（S130）。 感应控制装置基于俯仰角变形部和变形结束俯仰角来计算飞行用车辆的俯仰角指令（S140）。 初始飞行条件信息包括飞行高度，上升速度和俯仰角。 火箭推力特征信息包括火箭的推力尺寸和火箭的燃烧时间。 （附图标记）（AA）开始; （BB）结束; （S110）输入初始飞行情况信息和火箭推力特征信息; （S120）设定目标峰值高度和变形端部俯仰角度; （S130）设定俯仰角变形部; （S140）计算俯仰角指令;
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公开(公告)号：KR101257688B1
公开(公告)日：2013-04-24
申请号：KR1020110116623
申请日：2011-11-09
Applicant: 국방과학연구소
Abstract: PURPOSE: A method and an apparatus for computing the thrust diagram of a rocket are provided to predict the thrust characteristic of the rocket in real time. CONSTITUTION: A method for computing the thrust diagram of a rocket is as follows: a step for preprocessing to analyze the characteristic of nominal thrust(S110); a step for storing data in the preprocessing step(S120); a step for measuring thrust acceleration in a linearization section(S130); a step for estimating the combustion time of the rocket by using the combustion time of the nominal thrust, the coefficient of a linear approximate function, and the thrust acceleration(S140); and a step for computing the thrust diagram of the rocket based on a nominal thrust diagram and the estimated combustion time of the rocket(S150). [Reference numerals] (AA) Start; (BB) End; (S110) Performing a pre-process for analyzing the characteristics of nominal thrust; (S120) Storing data obtained through the pre-process; (S130) Measuring an acceleration in a linearization section of nominal thrust diagram; (S140) Estimating a rocket combustion time; (S150) Computing a rocket thrust diagram;
Abstract translation: 目的：提供一种用于计算火箭推力图的方法和装置，用于实时预测火箭的推力特性。 构成：计算火箭推力图的方法如下：预处理分析名义推力特性的步骤（S110）; 用于在预处理步骤中存储数据的步骤（S120）; 用于测量线性化部分中的推力加速度的步骤（S130）; 通过使用公称推力的燃烧时间，线性近似函数的系数和推力加速度来估计火箭的燃烧时间的步骤（S140）; 以及基于标称推力图和火箭的估计燃烧时间来计算火箭的推力图的步骤（S150）。 （附图标记）（AA）开始; （BB）结束; （S110）进行名义推力特性分析的预处理; （S120）存储通过预处理获得的数据; （S130）测量标称推力图的线性化部分的加速度; （S140）估计火箭燃烧时间; （S150）计算火箭推力图;
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公开(公告)号：KR101444656B1
公开(公告)日：2014-09-24
申请号：KR1020130018196
申请日：2013-02-20
Applicant: 국방과학연구소
Abstract: 본 발명은 표적 포착성능 향상을 위한 탐색기의 유효 탐색영역 산출방법에 관한 것으로, 비행체의 항법오차와 표적의 위치오차를 고려하여 실제 표적이 존재할 수 있는 공간영역을 3차원 타원체로 모델링하고, 상기 모델링된 3차원 타원체 공간영역에서 탐색기의 표적 포착확률을 최대화할 수 있는 타원체 공간영역의 크기를 결정한 후 상기 결정된 3차원 타원체 공간영역을 탐색기 시야 화면내의 2차원 유효탐색영역으로 변환하여, 상기 변환된 2차원 유효탐색영역내에 탐색기의 지향점이 존재하는지 판단하여 탐색기 정보의 유효성을 검증함으로써 표적 인식시 상기 결정된 유효 탐색영역에서만 탐색을 수행함으로써 표적 오포착 확률을 줄일 수 있는 효과가 있다.
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公开(公告)号：KR101658464B1
公开(公告)日：2016-09-22
申请号：KR1020140177705
申请日：2014-12-10
Applicant: 국방과학연구소
Abstract: 본발명은유도탄의요격지점(Impact Point)을실시간으로예측할수 있는유도탄의요격지점실시간예측방법에관한것으로, 비행조건입력시유도탄의비행궤적을고려한비행거리를도출하는단계; 유도탄의비행속도를구간선형화하고잔여비행시간동안적분하여유도탄의비행속도를고려한비행거리를해석적으로도출하는단계; 상기도출된유도탄의비행궤적을고려한비행거리와유도탄의비행속도를고려한비행거리를연립하여요격지점관계식을도출하는단계; 상기도출된요격지점관계식의해를산출하는단계; 및상기산출된요격지점관계식의해를이용하여요격예상지점및 잔여비행시간을실시간예측하는단계;를포할수 있다.
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