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数字姿态控制系统已用来控制探测火箭有效载荷的姿态。数字姿态控制系统包括:三轴单框架惯性平台,通用数字计算机,电池,活门驱动器,以及与优质导引敏感器(如星光跟踪器和太阳探测器)相连接的系统输入/输出电子设备。数字姿态控制系统安装在有效载荷舱内,利用反作用控制系统,就可完成全部机动控制。这种机动可用数字计算机模拟和编程序。用惯性平台作为系统误差敏感元件,数字姿态控制系统在典型的探测火箭发射环境下,将使有效载荷定向在所要求的惯性姿态的±20弧分内。按惯性指向方式,在惯性运动期间,数字姿态控制系统的漂移率每分钟小于2弧分。当导引敏感器和数字姿态控制系统一起使用时,有效载荷的绝对惯性姿态,如导引敏感器测得的那样,将被控制在±1弧分范围内。在工作期间,数字姿态控制系统极限周值将小于±5弧分。
The digital attitude control system has been used to control the attitude of the rocket payload. Digital attitude control systems include three-axis, single-frame inertial platforms, universal digital computers, batteries, shutter drives, and system input / output electronics connected to premium guidance sensors such as star trackers and solar detectors. Digital attitude control system installed in the payload compartment, the use of reaction control system, you can complete all of the motor control. This type of maneuver can be simulated and programmed using digital computers. Using the inertial platform as the system error sensing element, the digital attitude control system will orient the payload within ± 20 arc minutes of the desired inertial attitude under a typical launch condition of the probe. By inertial pointing, the drift of the digital attitude control system is less than 2 arc minutes per minute during inertial motion. When a guidance sensor is used with a digital attitude control system, the payload’s absolute inertial attitude, as measured by the guidance sensor, will be controlled within ± 1 arcmin. During work, the digital attitude control system limit cycle will be less than ± 5 arc minutes.