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公开(公告)号：KR1020090057848A
公开(公告)日：2009-06-08
申请号：KR1020070124608
申请日：2007-12-03
Applicant: 국방과학연구소
Abstract: An apparatus for measuring dynamic stiffness and a controlling method thereof is provided to facilitate assembly and disassembly by installing a driving shaft and a part supporting the driving shaft separately with a cylinder part. An apparatus(1) for measuring dynamic stiffness comprises: a dynamic stiffness driver(20) applying the torque to a test object; a torque sensor(51,52) measuring the torque applied in the dynamic stiffness driver; and a flexible coupling(30) formed of flexible material to compensate for the alignment error between shafts. The flexible coupling is connected between the dynamic stiffness driver and the test object(10). The flexible coupling delivers the driving force of the dynamic stiffness driver to the test object. The dynamic stiffness driver comprises: a driving shaft(22); a pair of connecting rods in which one end is connected to the driving shaft through a pin and the other end is connected to a piston; and a servo valve(11) applying the differential power to the connecting rod.
Abstract translation: 提供一种用于测量动态刚度的装置及其控制方法，以便通过将驱动轴和支撑驱动轴的部分与气缸部分分开地安装来方便组装和拆卸。 一种用于测量动态刚度的装置（1）包括：将动力刚度驱动器（20）施加到测试对象上; 扭矩传感器（51,52），测量施加在所述动态刚度驱动器中的扭矩; 以及由柔性材料形成的柔性联轴器（30），以补偿轴之间的对准误差。 柔性联轴器连接在动刚度驱动器和测试对象（10）之间。 柔性联轴器将动态刚度驱动器的驱动力提供给测试对象。 动力刚度驱动器包括：驱动轴（22）; 一对连杆，其一端通过销与驱动轴连接，另一端与活塞连接; 以及向所述连杆施加所述差动力的伺服阀（11）。
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公开(公告)号：KR101062230B1
公开(公告)日：2011-09-06
申请号：KR1020070124608
申请日：2007-12-03
Applicant: 국방과학연구소
Abstract: 본 발명은 동적 강성 측정 장치 및 그의 제어 방법에 관한 것으로, 구동축과 토크센서를 일체화시킴으로써 컴팩트한 구동기를 갖는 동적 강성 측정 장치를 제안한다. 또한, 유압 토크 제어 서보 시스템과 유압 날개구동장치의 모델링을 바탕으로 토크제어 시스템이 갖는 근본적인 한계를 극복하고, 구현이 간단하면서도 강력한 토크 제어 기법을 제안한다.
동강성, 이중귀환, 벨로우즈, 푸시푸시-
公开(公告)号：KR101408078B1
公开(公告)日：2014-06-18
申请号：KR1020140025737
申请日：2014-03-04
Applicant: 국방과학연구소
Abstract: The present invention relates to an apparatus and a method for adjusting a zero-point error of a guided missile control fin. The apparatus according to an embodiment of the present invention includes a zero-point error inspection unit sending a position command to adjust a position of a control fin to zero degree by a drive controller controlling the control fin of the guided missile, measuring the zero-point error of the control fin in the state in which the position of the control fin is maintained at zero degree according to the position command, and receiving an axis of the control fin for the zero-point adjustment; a control fin position adjusting unit verifying whether the axis of the control fin for the zero-point adjustment coincides with a reference axis of the guided missile; a zero-point adjustment unit sending, to the drive controller, the zero-point adjustment command with respect to the axis of the control fin to be zero-point adjusted, and receiving the result of the zero-point adjustment command from the drive controller; and a zero-point error verifying unit sending a position command to adjust the position of the control fin to zero degree to the drive controller, and measuring each position error between the position of the control fin and a reference axis of the guided missile in the state in which the position of the control fin is maintained at zero degree according to the position command.
Abstract translation: 本发明涉及一种用于调整导弹控制鳍片的零点误差的装置和方法。 根据本发明的实施例的装置包括零点错误检查单元，其通过控制导弹的控制翅片的驱动控制器发送用于将控制翅片的位置调整为零度的位置命令， 根据位置指令将控制翅片的位置保持在零度的状态下控制翅片的点误差，并且接收用于零点调整的控制翅片的轴线; 控制翅片位置调整单元，用于验证用于零点调整的控制翅片的轴线是否与导弹的参考轴线重合; 零点调整单元向驱动控制器发送相对于控制翅片的轴为零点调整的零点调整命令，并且从驱动控制器接收零点调整命令的结果 ; 以及零点误差验证单元发送位置指令以将控制翅片的位置调整为零度到驱动控制器，并且测量控制翅片的位置与导弹的参考轴之间的位置误差 控制翅片的位置根据位置指令保持在零度的状态。
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