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一、序 言 登月舱的主要制导系统会有高性能的数字控制计算机,惯性测量组合和其它导航敏感元件,并能履行飞船稳定自动驾驶仪和控制系统的职能。过去,稳定和控制的功能通常是由含有角度和速率陀螺的模拟式系统来完成。最初的登月舱制导和控制系统具有在图1中所表示的结构形式。主要的制导系统和辅助制导系统,以及宇航员的所有数据都经过模拟式自动驾驶仪放大送到主发动帆的支架伺服系统和喷气控制系统中去（但仅在交换调头时,宇航员可通过模拟人自动驾驶仪直接操纵喷气控制系统的喷嘴来进行分离）。所提供的主要制导系统必须
I. INTRODUCTION The main guidance system for the lunar module will be a high-performance digital control computer, inertial measurement assembly and other navigation-sensitive components and will perform the functions of a spacecraft stabilized autopilot and control system. In the past, the function of stability and control was usually done by an analog system with angle and rate gyros. The original lunar module guidance and control system has the structure shown in FIG. 1. The main guidance and guidance aids, as well as all the data for the astronauts, are amplified by an analog autopilot into the main launch cradle servo and jet control system (but only as long as the interchange is being made) Simulator autopilot directly manipulates the jet control system’s nozzles for separation). The main guidance system provided must be