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1. 发明授权

KR101493755B1 적층식 단위케이스와 단면 마운트 구조의 회로기판을 구비한 내충격형 포탄비행제어장치 有权
标题翻译：炮弹弹射控制装置，具有电路板耐冲击和堆叠结构
公开(公告)号：KR101493755B1
公开(公告)日：2015-02-16
申请号：KR1020140094010
申请日：2014-07-24
申请人： 주식회사 풍산
发明人： 박장호 , 김재호 , 조창연 , 허준회
IPC分类号： F41G9/00 , F42B30/08 , F42B15/01
摘要： 내충격 구조의 단층회로판을 안착 고정한 단위케이스를 적층 결합한 포탄비행제어모듈 및 포탄비행제어장치가 개시된다. 단위 비행제어유닛은 소켓과 터미널에 필요한 관통공간을 제외하고는 전체적으로 고른 면지지 구조의 안착면을 갖는 단위케이스에 의해 단층회로판이 포 발사 충격에도 찌그러지지 않고 견딜 수 있으며, 회로간 적층공간을 메우는 몰딩제가 없어 압축 후 되툉김 현상이 발생되지 않는다.
제어유닛이 복수 개 적층된 제어모듈과 이를 하우징으로 수납 고정하는 제어장치는 납작한 원통형 용기모양의 단위케이스(30-n)와 원판형 단층회로판(20-n)가 반복 적층되는 과정에서 터미널과 소켓이 인접한 층 사이에서 서로 다른 위치에 마운트되면서 터미널(22-n)의 평면상 배열위치가 서로 겹치지 않도록 배열된다. 이 같은 구조에 의해 적층된 모든 회로판의 터미널은 바로 아래층의 안착면으로부터 지지받을 수 있어 발사충격에 의해 빠지거나 내려앉지 않는다. 이는 프로세서의 배치에도 응용되어 각 단층회로판의 프로세서들은 인접한 비행단위케이스 상에서 적층 방향으로 서로 겹치지 않도록 배열되어 무게 배분과 발열 배분에 기여한다.
摘要翻译：本发明公开了一种通过堆叠和联接耐冲击结构的单层电路板分别固定和固定的单元箱形成的炮弹的飞行控制模块，以及炮弹的飞行控制装置。单元飞行控制单元使得单层电路板能够耐受冲击的冲击，而不会被具有整体均匀的表面支撑结构的座面的单元壳体凹陷，除了插座和端子所需的通过空间，以及可以通过不要求填充电路之间的堆叠空间的成型材料来防止压缩后的回弹效应。具有堆叠在彼此顶部的多个控制单元的控制模块和用于将控制模块接收并固定在壳体中的控制装置被布置成使得端子的平面阵列位置在安装在不同位置时不能彼此重叠在将具有扁平圆筒形容器形状的单元壳体和盘形单层电路板重叠堆叠的过程中，端子和插座彼此相邻的层之间。通过该结构堆叠的所有电路板的端子可能不被每个端子正下方的层的座面支撑而被去除或折叠。这甚至适用于处理器的布置，以使得单层电路板的处理器在与每个处理器相邻的飞行单元壳体上的堆叠方向上彼此不重叠，从而有助于重量分布和热分布。

2. 发明授权

KR101389351B1 유도형 탄의 조종날개 구동토크 측정방법 및 그 장치 有权
标题翻译：扭矩传感方法和控制方式的设计
公开(公告)号：KR101389351B1
公开(公告)日：2014-04-25
申请号：KR1020130142999
申请日：2013-11-22
申请人： 주식회사 풍산
发明人： 박장호 , 김재호 , 조창연
IPC分类号： G01L3/02 , G01L5/00 , F42B35/00
摘要： Disclosed are a torque sensing method and apparatus for a control wing of a guide type munition, in which a control wing 100 is fixed to a first jig, and a wing surface of a control wing is clamped and fixed by using a second jig to measure a driving torque of the control wing by using a torque meter 23 coaxially connected to a rotation shaft of the second jig. An oscillograph for displaying a voltage signal generated by a twist due to a difference between a first rotation motion and a second rotation motion in real-time and a digital indicator 17 for converting the voltage signal into a torque value to display the converted torque valve are connected to the torque meter 23 through a wire, and the digital indicator 17 operates to sense a peak value of the torque value, thereby displaying the sensed peak value as a fixed value. The rotation motion of the torque meter 23 is converted into a reciprocation motion by a crank 30 and a connecting rod 31, and the reciprocation motion is converted into a third rotation motion including an oscillation motion and then is transmitted into the fly wheel 40. The ply wheel has inertial resistance with respect to the oscillation to apply various resistant forces to the control wing. In this process, since an external force similar to a force in an actual flying situation is applied, a motor driving controller may transmit realistic driving torque and rotation rate information to a wing motor on the basis of the applied external force. The present invention may practically measure the driving torque of the control wing in various kinds of guide type munitions. The results measured through the above-described processes may largely help optimization in design of the guide type munition as well as selection of a required specification and a reduction gear ratio. [Reference numerals] (AA) Wing module/reduction gear; (BB) Wing root
摘要翻译：公开了一种用于导向型弹药的控制翼的转矩传感方法和装置，其中控制翼100固定到第一夹具，并且控制翼的翼面通过使用第二夹具夹紧和固定来测量通过使用同轴连接到第二夹具的旋转轴的扭矩计23来控制翼的驱动扭矩。用于显示由于第一旋转运动和第二旋转运动之间的差异而实际产生的电压信号的示波器和用于将电压信号转换成转矩值以显示转换的转矩阀的数字指示器17，通过线连接到扭矩计23，并且数字指示器17操作以感测扭矩值的峰值，从而将感测到的峰值显示为固定值。扭矩计23的旋转运动通过曲轴30和连杆31转换为往复运动，并且往复运动转换成包括振动运动的第三旋转运动，然后传递到飞轮40中。帘布轮具有相对于振动的惯性阻力，以对控制翼施加各种抵抗力。在该过程中，由于施加与实际飞行情况下的力类似的外力，电动机驱动控制器可以基于所施加的外力将真实的驱动转矩和转速信息传递给翼型电动机。本发明可以实际测量各种导向型弹药中的控制翼的驱动扭矩。通过上述过程测量的结果可能在很大程度上有助于优化导向型弹药的设计，以及选择所需规格和减速比。（标号）（AA）机翼模块/减速机; （BB）翼根

3. 发明授权

KR101911831B1 전원활성화용 고전류 스위치 有权
公开(公告)号：KR101911831B1
公开(公告)日：2018-10-25
申请号：KR1020160172492
申请日：2016-12-16
申请人： 주식회사 풍산
发明人： 김재호 , 조창연 , 박장호 , 김진원 , 허준회 , 서일원 , 정필규 , 임현준
IPC分类号： F41G9/00 , F42B15/01 , F42C11/00
摘要： 스위치커버, 스위치회로기판, 및스위치몸체가결합구로결합된전원활성화용고전류스위치에있어서, 상부에위치한스위치커버와상기스위치커버하부의접촉부가포함된스위치회로기판은상기접촉부에실린더형실린더형스프링핀이구비되고; 상기스위치회로기판하부에는스위치몸체가위치하며, 상기스위치몸체의내부홈에삽입되어압축및 팽창가능한수단이구비된원통형의접촉핀; 상기접촉핀과평행하여위치한원통형의스터드핀과상기스터드핀 하부오목부에위치한스터드스프링; 및상기접촉핀과스터드핀의사이에위치하는볼을포함하는것을특징으로하는전원활성화용고전류스위치를제공한다.

4. 发明授权

KR101449738B1 복수 폭발분리장치들의 전단파괴 작동에 의한 발사체 분리구조 有权
标题翻译：多种爆破剪切装置的射弹分离结构
公开(公告)号：KR101449738B1
公开(公告)日：2014-10-10
申请号：KR1020140094000
申请日：2014-07-24
申请人： 주식회사 풍산
发明人： 박장호 , 김재호 , 조창연
IPC分类号： F42B15/36 , B64G1/64
CPC分类号： F42B15/36 , F15B15/19
摘要： Disclosed is a projectile separation structure in which a shear pin (22) buried in a main body is inserted into a side surface of a body of a stud (20) inserted into the main body (11) and fastened to a separation unit (12) to detach the separation unit (12) by breaking the shear pin (22) with explosive hit of a pyroactuator (30). The stud (20) may be disposed to support a first external force, which is a great force applied to the separation unit (12), and the shear pin (22) may be disposed to support a second external force, which is a small force applied in a direction different from that of the first external force. The pyroactuator (30) selectively breaking the shear pin supporting the small force may control the hitting force by the size of a clearance (35) formed between a hit cover (31) and the stud (20) or by the volume of a chargeable space (36) formed between the hit cover (31) and gunpowder (32). The above devices can be disposed at predetermined intervals in the shape of a ring around the circumference of a clear space (16) of the main body, and the amount of charged gunpowder (32), the clearance (35), and the chargeable space (36) can be independently controlled for each of the devices. Accordingly, even when the inertial mass of the separation unit is topically increased, a projectile can be separated without distracting a flight trajectory of the projectile or the detachment trajectory of the separation unit only by simply adjusting a hitting force of a specific pyro separation device without changing the entire structure.
摘要翻译：公开了一种抛射物分离结构，其中埋在主体中的剪切销（22）插入插入主体（11）的螺柱（20）的主体的侧表面中，并紧固到分离单元（12））通过用热致动器（30）的爆炸撞击破坏剪切销（22）来分离分离单元（12）。螺柱（20）可以被设置成支撑施加到分离单元（12）的很大的力的第一外力，并且剪切销（22）可以被设置成支撑第二外力，第二外力是小的施加在与第一外力不同的方向上的力。选择性地破坏支撑小力的剪切销的热致动器（30）可以通过在撞击盖（31）和螺柱（20）之间形成的间隙（35）的尺寸或者可充电空间的体积来控制击打力（36）形成在击打盖（31）和火药（32）之间。上述装置可以以围绕主体的透明空间（16）的圆周的环形的形状以及带电火药（32），间隙（35）和可充电空间（36）可以独立地控制每个设备。因此，即使当分离单元的惯性质量局部增加时，也可以通过简单地调整特定热分离装置的击打力而不会分散抛射体的飞行轨迹或分离单元的分离轨迹，而不会改变整个结构。

5. 发明授权

KR101374309B1 포탄발사식 관측자탄의 비행제어 장치 및 방법 有权
标题翻译：航空观测子系统飞行控制的方法和装置
公开(公告)号：KR101374309B1
公开(公告)日：2014-03-12
申请号：KR1020130142998
申请日：2013-11-22
申请人： 주식회사 풍산
发明人： 박장호 , 김재호 , 조창연 , 한유근
IPC分类号： F42B15/08 , F42B15/01
CPC分类号： F42B12/365 , B64D17/34 , H04N5/2257
摘要： Disclosed are an flight control device of an observation submunition with a cannonball-firing type, which is rotated and decelerated by a deceleration wing (23) and a drag chute (27) after being discharged from a complete round (10) and is equipped with a propulsion motor (121), a handling motor (127), and a parafoil (130), and a control method thereof. The device is equipped with a GPS receiver, which detects the location information on a system of material points, and multiple sensors, which detect the position information on a six-axis coordinate system, in order to collect location information and position information and then integrate and process the information on its own. Sensors, which detect a six-axis position, are arranged, being isolated from the protrusion standing motion and rotational vibration (fluttering) motion of a propulsion device. Therefore, the device can not only perform flight algorithm, which minimizes power consumption, but also construct an autonomous control system of the observation submunition capable of maintaining altitude and performing pattern flight. Also, it is possible to allocate extra power to an observation module and an induced flight control module, so it is possible to achieve the observation submunition (100) with more excellent observation skills and duty performing capability.
摘要翻译：公开了一种具有炮弹式观察子弹药的飞行控制装置，其在从完整圆（10）排出后由减速翼（23）和拖曳滑槽（27）旋转和减速，并配备推进电动机（121），搬运用电动机（127）以及石蜡炉（130）及其控制方法。该装置配备有GPS接收器，其检测物料点系统上的位置信息，以及多个传感器，其检测六轴坐标系上的位置信息，以便收集位置信息和位置信息，然后集成并自行处理信息。检测六轴位置的传感器布置成与推进装置的突起立起运动和旋转振动（振动）运动隔离。因此，该装置不仅可以执行最大限度降低功耗的飞行算法，而且可以构建能够维持高度和执行模式飞行的观察子弹药的自主控制系统。此外，可以向观察模块和诱导飞行控制模块分配额外的功率，因此可以实现具有更好的观察技能和作业执行能力的观察子弹药（100）。

6. 发明授权

KR101443677B1 입력각도량에 따라 동기가속구간과 센서리스제어구간이 결합된 회전각도를 출력하는 포탄 날개구동장치 및 그 구동제어방법 有权
标题翻译：通过同步加速和无传感驱动组合旋转角度输出的方法和装置的方法和装置
公开(公告)号：KR101443677B1
公开(公告)日：2014-09-23
申请号：KR1020140094024
申请日：2014-07-24
申请人： 주식회사 풍산
发明人： 박장호 , 김재호 , 조창연
IPC分类号： F42B10/60 , F42B10/14 , F42B10/66
CPC分类号： F42B10/64 , B64C13/50 , F42B15/01
摘要： Disclosed are a wing driving device for a launched shell outputting a rotation angle in which a synchronized acceleration section and a sensorless control section are combined according to an input angle amount, and a driving method for same. According to the present invention, half of a supply voltage is set as a value compared to a terminal voltage in view of a specific high-load operating condition in controlling a brushless DC motor for shell manipulation wing driving where it is difficult to mount a rotation angle detection sensor. In this manner, a comparison operation is performed in a PWM signal ON section for ZCP detection. By an integrated control mechanism in which a position controller, a speed controller, and a current controller are configured to be serially connected, a manipulation wing position command input angle is divided into an early stage synchronized acceleration section and a following constant speed section for respectively performing a synchronized acceleration stage and a sensorless driving stage. Accordingly, a sufficient driving speed and a sufficient positional accuracy of the manipulation wing required for shell guide fly can be satisfied at the same time even without the rotation angle detection sensor with less durability.
摘要翻译：公开了一种用于输出旋转角度的推进壳体的翼驱动装置及其驱动方法，其中同步加速部分和无传感器控制部分根据输入角度量组合。根据本发明，考虑到在控制用于外壳操纵翼驱动的无刷直流电动机的特定的高负荷运行条件下，将电源电压的一半设置为与端子电压相比的值，其中难以安装旋转角度检测传感器。以这种方式，在用于ZCP检测的PWM信号ON部分中进行比较操作。通过其中位置控制器，速度控制器和电流控制器被串联连接的集成控制机构，操作翼位置指令输入角分别被分为早期同步加速部分和下一个恒定速度部分执行同步加速阶段和无传感器驱动阶段。因此，即使没有耐久性较差的旋转角检测传感器，也能够同时满足壳导向翼所需的操纵翼的足够的行驶速度和充分的位置精度。

7. 发明授权

KR101374307B1 포탄발사식 관측자탄 및 이를 이용한 관측방법 有权
标题翻译： CANNON发射机观测子系统及其观测方法
公开(公告)号：KR101374307B1
公开(公告)日：2014-03-12
申请号：KR1020130142988
申请日：2013-11-22
申请人： 주식회사 풍산
发明人： 김재호 , 박효환 , 이영기 , 박장호 , 조창연
IPC分类号： F42B15/08 , F42B12/00
CPC分类号： F42B12/365 , B64D17/00 , F42B12/58 , H04N5/2257
摘要： Disclosed are a propulsion device storage unit (112) where a propulsion device, which can be projected and stood by rotation movement, is stored; a middle cover plate (113), which fixes the propulsion device storage unit to be rotated; an observation submunition (100), which includes a flight control circuit arranged below the middle cover plate; and an observation method using the same. The present invention relates to an unmanned aerial unit with a cannonball firing-type, which is designed to be fitted to various air observation missions, such as natural disaster exploration, military reconnaissance, and battle damage assessment (BDA). The present invention successfully achieves a motor paragliding method for rapidly developing the unmanned aerial unit and making the unit reach a target area after the unit is developed and discharged in deceleration from a complete round, thereby maintaining an effective observation height for a long time by making the aerial unit endure turning flight. An operation motor (127), which has the roles of a specific vertically-protruding rotation supporter and a fixing jaw thereof, enables a large-caliber propeller with more than maximum diameter of the observation submunition (100) to be mounted, thereby maintaining real turning flight skills for pulling a parafoil and moving the parafoil forwards. Therefore, the operation motor can largely extend effective observation time.
摘要翻译：公开了一种推进装置存储单元（112），其中可以投射并通过旋转运动站立的推进装置被存储; 中间盖板（113），其固定所述推进装置存储单元以旋转; 观察子弹药（100），其包括布置在中间盖板下方的飞行控制电路; 以及使用其的观察方法。本发明涉及一种具有炮弹射击型的无人驾驶飞行器，其设计适用于各种空中观察任务，如自然灾害勘测，军事侦察和战斗伤害评估（BDA）。本发明成功地实现了一种用于快速开发无人驾驶飞行器的马达滑翔伞方法，并且在单元从整体减速开始后排出到目标区域之后，通过制造长时间保持有效的观察高度，空中单位忍耐转身飞行。具有特定的垂直突出的旋转支撑件和固定爪的作用的操作马达（127）能够安装具有观察子弹药（100）的最大直径的大口径螺旋桨，从而保持实际转动飞行技能拉扯parafoil和向前移动parafoil。因此，操作电机可以大大延长有效的观察时间。

8. 发明授权

KR102036526B1 발사체의 날개전개장치 有权
公开(公告)号：KR102036526B1
公开(公告)日：2019-10-25
申请号：KR1020180064598
申请日：2018-06-05
申请人： 주식회사 풍산
发明人： 조창연 , 서송원 , 박장호 , 정필규 , 임현준
IPC分类号： F42B10/14 , B64C3/56 , B64C3/14

9. 发明授权

KR102163426B1 가속도를 이용한 가속도 센서의 이격거리 산출 방법 및 컴퓨터 프로그램 有权
公开(公告)号：KR102163426B1
公开(公告)日：2020-10-07
申请号：KR1020190055556
申请日：2019-05-13
申请人： 주식회사 풍산
发明人： 허준회 , 서일원 , 김재호 , 박장호
IPC分类号： G01C21/10 , F42B10/00 , G06F17/10 , G01P15/00

10. 发明授权

KR102085916B1 활공날개 수납전개장치 有权
公开(公告)号：KR102085916B1
公开(公告)日：2020-03-06
申请号：KR1020180148584
申请日：2018-11-27
申请人： 주식회사 풍산
发明人： 박현묵 , 박장호 , 조창연
IPC分类号： F42B10/14 , F42B10/38 , B64C3/56

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