THE SATURN LAUNCH VEHICLE AND ITS GUIDANCE AND CONTROL (GC) SYSTEM

摘要

The purpose of this paper is to describe the SATURN Launch Vehicle that successfully launched the manned APOLLO spacecraft into Earth orbit and thence onto a trans-lunar trajectory to the moon. It will then describe the SATURN G&C system that enabled this to occur. Using a "building block" approach, the NASA Marshall Space Flight Center (MSFC), under the direction of Wemher von Braun, achieved 33 successful launches out of 33 attempts. This included: 1. Ten unmanned SATURN Ⅰ "multiple engine development flights," seven of which were orbital; 2. Ten orbital SATURN IB "APOLLO hardware development flights," five of which were manned; and 3. Thirteen manned APOLLO Saturn Ⅴ missions, seven of which were lunar. This is the only major rocket development program ever to be completed without a catastrophic in-flight failure. The SATURN Ⅴ, with its 34.7-million N (7.5-million pounds) of thrust in its first stage, lofted 96,000 kg (212,000 lb) of payload into Low Earth Orbit [213 km (115 nautical miles)]. The SATURN 3rd stage then went on to place a 48,500 kg (107,350 lb) payload onto a trans-lunar trajectory. This paper will describe how NASA MSFC was successful in developing and implementing this system. It will describe the SATURN G&C system, including its genesis and associated trade studies. The techniques will be described to show how this feat was accomplished: engineering leadership; the extensive "building block approach; and the integrated design analysis, simulations, and testing.