{'fraction_non_alphanumeric': 0.016283524904214558, 'fraction_numerical': 0.0038314176245210726, 'mean_word_length': 5.698717948717949, 'pattern_counts': {'":': 0, '<': 0, '<?xml version=': 0, '>': 0, 'https://': 0, 'lorem ipsum': 0, 'www.': 0, 'xml': 0}, 'pii_count': 0, 'substrings_counts': 0, 'word_list_counts': {'cursed_substrings.json': 0, 'profanity_word_list.json': 0, 'sexual_word_list.json': 0, 'zh_pornsignals.json': 0}}
Mars Pathfinder cruise stage/entry vehicle separation dynamics

Prior to atmospheric entry, the Mars Pathfinder flight system will separate its entry vehicle from its cruise stage, and establish the entry conditions for a passive and unconventional entry, descent, and landing approach. This paper summarizes a separation dynamics analysis conducted to demonstrate that the cruise separation system design is viable and ensure that adequate design margins exist with the effects from parameter uncertainty included. Enhanced by the Monte Carlo technique, the separation analysis predicts the statistical bounds of separation velocity, entry attitude error, and a subset of critical clearances with 99 percent confidence. These statistical bounds are used to assess the performance of the current cruise separation hardware design under worst-case conditions. The results indicate that the current design satisfies the separation requirements, provided drag forces in the cable cutter barrel are less than approximately 18 N per cutter. (Author)