论文部分内容阅读
“阿波罗”指挥舱和指挥舱/登月舱飞行器推力矢量控制用的数字自动驾驶仪是由麻省理工学院仪表试验室研制的,这个飞行器的俯仰和偏航是通过将火箭发动机安装在常平架上的办法来控制,而飞行器的横滚则通过点燃控制系统的喷气发动机来控制。 喷气发动机点火用的较简单的相平面开关逻辑线路可以控制飞行器的横滚。但是,对俯仰和偏航的控制,由于飞行器的弹性振动,燃料的晃动,推力不重合以及控制回路的交联影响等一系列问题,需要更精心的设计。 本文阐述了用于研制俯仰和偏航自动驾驶仪的设计途径和分析方法。这种设计具有很多重要的特点,如由宇宙航行员控制的高-低带宽工作状态,时变增益,多种取样速率,用可清除系数实现滤波的广义滤波器,推力不重合校正回路以及双增益控制回路。 本文还说明了这些自动驾驶仪的工作特点和实现方法,并分析了它们的稳定性和控制特性。
Apollo Command and Command / Lunar Module The digital autopilot used for thrust vector control was developed by the MIT Instrumentation Laboratory and was pitched and yawed by installing the rocket engine at Changping Aircraft approach to control, and aircraft roll through the ignition control system of the jet engine to control. The simpler phase-switching logic used for firing a jet engine controls the roll of the aircraft. However, the control of pitch and yaw requires more careful design due to a series of problems such as the elastic vibration of the aircraft, the fluctuation of the fuel, the misalignment of the thrust and the influence of the cross-linking of the control loop. This article describes the design approaches and analysis methods used to develop pitch and yaw autopilots. This design has many important features such as high-low bandwidth operation under the control of a space pilot, time-varying gain, multiple sample rates, generalized filters with filter-cleanable coefficients, thrust mismatch correction loops, and dual Gain control loop. This article also illustrates the working characteristics and implementation methods of these autopilots, and analyzes their stability and control characteristics.