说 明 本报告是DSR设计55-238的一部分。它是与NASA的载人宇宙飞船中心签定的合同NAS9-4065进行工作的。 本报告并不包括NASA认为不许可公布的部分内容。因此,仅涉及到设计思想的变化和意图。 摘 要 在本文中介绍了“阿波罗”的登月舱数字自动驾驶仪的设计原理。应用这些原理将使喷气控制系统喷嘴的起动次数最少,因而使喷气控制系统具有最大的可靠性和最小消耗燃料。惯性测量组合测量的平台角度将由最佳递推线性滤波器来处理,从而获得飞行器的定向角,飞行器的角速度和由于主发动机系统产生的飞行器扰动加速度。此滤波器的输出将指出飞行器在角度一角速度相平面上的位置,以及描绘飞行器运动的抛物线段的轨迹。用起动喷气控制 This report is part of DSR Design 55-238. It is working with the NASA’s Manned Spacecraft Center contract NAS9-4065. This report does not include sections that NASA believes are not to be released. Therefore, it only involves the change and intention of design idea. Abstract This article describes the design principle of Apollo’s lunar module digital autopilot. Applying these principles will minimize the number of starts for the jet control system nozzles, giving the jet control system maximum reliability and minimum fuel consumption. Inertial measurements The combined platform angle measurements will be processed by the best recursive linear filter to obtain the aircraft’s orientation angle, the angular velocity of the aircraft and the acceleration of the aircraft due to the main engine system. The output of this filter will indicate the position of the aircraft at the angular phase of the angular velocity and the trajectory of the parabolic segment depicting the movement of the aircraft. Start with jet control