Integrated Back-Pack Maneuvering Unit Propulsion Study and Exhaust Plume Heating Analysis

摘要

Two technical problems related to the Astronaut Maneuvering Unit are treated. The problems are: (1) heating associated with the impingement of the rocket exhaust on space suit surfaces, and (2) the performance of inert heated gases as propellants. Methods for predicting rocket exhaust heating rates in space are presented and results are compared with test data. Effects of plume heating of an H2O2 monopropellant exhaust from a typical motor placement is summarized. The results obtained from several heated gas propellant tests are reported and compared to theoretically predicted performance. The analytical and experimental techniques utilized are discussed in detail. The refrigerants, Freon 115 and Freon C318 show the highest density impulse and lowest weight. Freon 115 is recommended for use due to the lower storage temperature required. (Author)