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首页> 外国专利> METHOD FOR FORMING A TEAM CONTROL missiles, rotates an angle of heel CONTROL missiles, METHOD OF MEASUREMENT angle of heel on a rocket, gyroscopic angle meter roll, METHOD FOR FORMING sine and cosine signals on a rocket, rotate angle of heel, and sine-cosine shaper CONTROL SYSTEMS Missiles

METHOD FOR FORMING A TEAM CONTROL missiles, rotates an angle of heel CONTROL missiles, METHOD OF MEASUREMENT angle of heel on a rocket, gyroscopic angle meter roll, METHOD FOR FORMING sine and cosine signals on a rocket, rotate angle of heel, and sine-cosine shaper CONTROL SYSTEMS Missiles

机译：形成团队控制导弹的方法，旋转后跟控制导弹的角度，测量火箭上的后跟角度的方法，陀螺仪角度计滚动，在火箭上形成正弦和余弦信号的方法，后跟的旋转角度和正弦值余弦整形器控制系统导弹

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FIELD: physics; control.;SUBSTANCE: group of inventions relates to rocket control systems. The method of generating control commands involves measuring the banking angle of the rocket, which is generated in form of a signal in an n-bit Gray code, which is converted to a binary number having n bits, logic levels of which generate a multi-step approximation of sine-wave and cosine-wave signals, and rocket control commands on the heading and pitch, respectively, are generated from the decoded received signals. The rocket control system includes a gyroscopic device for measuring the banking angle, an XOR logic circuit, a control command converter and a second steering gear. The method of measuring the banking angle involves generating additional sequences of logic levels which form a number in an n-bit Gray code, which is converted to a binary n-bit number which corresponds to the measured value of the banking angle of the rocket. The gyroscopic device for measuring the banking angle further includes LED-photodiode pairs placed on the housing of the gyroscope and separated by raster. The method involves generating sine and cosine signals for generating control commands thereto, wherein a binary number in parallel form is generated in form of an n-bit number. The rocket control system includes a sine-cosine generator of M number setting devices and a digital inverter circuit.;EFFECT: high efficiency of generating control commands for rocket control systems.;8 cl, 6 dwg
机译：领域：物理学;物质：一组发明涉及火箭控制系统。生成控制命令的方法包括测量火箭的倾斜角，该倾斜角以n位格雷码的信号形式生成，该信号被转换为具有n位的二进制数，其逻辑电平生成一个从解码后的接收信号分别生成正弦波和余弦波信号的逐步逼近，以及分别在航向和俯仰上的火箭控制命令。火箭控制系统包括用于测量倾斜角的陀螺仪设备，XOR逻辑电路，控制命令转换器和第二转向器。测量倾斜角的方法包括生成逻辑电平的附加序列，这些逻辑电平序列形成一个n位格雷码的数字，该数字被转换为二进制n位数字，该二进制n位数字对应于火箭倾斜角的测量值。用于测量倾斜角的陀螺仪设备还包括放置在陀螺仪的壳体上并被光栅隔开的LED-光电二极管对。该方法包括产生正弦和余弦信号以产生对其的控制命令，其中以n位数字的形式产生并行形式的二进制数。火箭控制系统包括一个由M个数字设定装置组成的正弦余弦发生器和一个数字逆变器电路;效果：高效地生成了火箭控制系统的控制命令; 8 cl，6 dwg

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