首页> 外国专利> METHOD FOR TEST RIG DEVELOPMENT OF LASER BEAM-CONTROLLED ROCKETS, MICRORANGE AND TEST RIG FOR ITS REALIZATION

METHOD FOR TEST RIG DEVELOPMENT OF LASER BEAM-CONTROLLED ROCKETS, MICRORANGE AND TEST RIG FOR ITS REALIZATION

机译：激光束控制火箭的试验台架开发方法，微范围及其实现的试验台架

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FIELD: tests.;SUBSTANCE: the rocket is installed on a test rig, the countdown graph is started, the power of the control signal is changed in proportion with the distance of the rocket to the target, and the external actions on the rocket in a real flight are simulated. The operation of the rocket control system and the parameters of the external actions are monitored, the serviceability of the system is determined according to the response of the rocket control system to the checked external actions. The microrange includes a test route, rocket and a test rig for development of the rocket. A guidance instrument is installed on the test route, a device for varying the control signal power in proportion with the distance to the rocket is installed between the guidance instrument and the rocket, and the rocket is positioned on the rig simulating the external actions on the rocket. The device for varying the control signal power is made in the form of optical filters of various penetrability or reflecting surfaces of various curvature that are installed on the shaft of the rotation drive. The rig has a device for installation of the rocket, base and a system for measurements and recording of the rocket parameters. The device for installation of the rocket is made in the form of a gas turbine, whose rotor is fastened on the rocket, and the stator is coupled to the base through a hinge providing for turning of the rotor in the horizontal plane, and an additional rotation assembly installed at a distance from the turbine. The fixed yoke of the additional rotation assembly is coupled through a hinge to the rod of a pendulum, whose axle is installed on the vertical guide of the base. The system for measurement and recording in addition has transducers of rocket attitude, spinning and rocket bank position electrically coupled to the recording system.;EFFECT: provided test rig development of laser beam-controlled rockets in the conditions simulating the real flight, the material for the analysis and repeated use being preserved.;6 cl, 4 dwg

机译：场：测试。;实质：火箭安装在测试台上，开始倒计时图，控制信号的功率与火箭到目标的距离成比例地变化，并且外部对火箭的作用模拟真实飞行。监视火箭控制系统的操作和外部动作的参数，根据火箭控制系统对所检查的外部动作的响应来确定系统的可使用性。微型射程包括测试路线，火箭和用于开发火箭的测试装备。在试验路线上安装了一个导向仪，在导向仪和火箭之间安装了一个用于根据与火箭的距离成比例地改变控制信号功率的装置，并且将火箭定位在钻机上，以模拟火箭上的外部动作。火箭。用于改变控制信号功率的装置由安装在旋转驱动器的轴上的具有各种渗透性的滤光器或具有各种曲率的反射面构成。该钻机具有用于安装火箭的装置，基座以及用于测量和记录火箭参数的系统。用于安装火箭的装置以燃气轮机的形式制成，其转子固定在火箭上，并且定子通过铰链连接到基座，该铰链用于使转子在水平面内旋转，并且附加地旋转组件安装在距涡轮机一定距离处。附加旋转组件的固定叉架通过铰链连接到摆杆，摆杆的轴安装在基座的垂直导轨上。用于测量和记录的系统还具有与记录系统电耦合的火箭姿态，旋转和火箭堆位置传感器。效果：在模拟真实飞行的条件下，提供了激光束控制火箭的试验台开发，其材料用于分析和重复使用得到保存; 6 cl，4 dwg

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公开/公告号RU2299475C2

专利类型
公开/公告日2007-05-20

原文格式PDF
申请/专利权人 GOSUDARSTVENNOE UNITARNOE PREDPRIJATIE KONSTRUKTORSKOE BJURO PRIBOROSTROENIJA;
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申请/专利号RU20050124072
发明设计人 LIKHTEROV VLADIMIR MOISEEVICH;ZAVALNJUK ANATOLIJ GAVRILOVICH;IVANOV SERGEJ NIKOLAEVICH;KOLOTILIN VLADIMIR IVANOVICH;KUZNETSOV VLADIMIR MARKOVICH;
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申请日2005-07-28
分类号G09B9/08;F41G3/26;F41J1/18;
国家 RU
入库时间 2022-08-21 20:30:38

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