Challenges in CES/CM Separation Dynamics Analysis

Abstract

In any manned spaceflight, safety of the crew is of paramount importance. A Crew Escape System (CES) is needed to ensure the safety of crew in case of exigencies during atmospheric ascent (1st stage flight) as well as launch pad abort. In normal missions, once the performance of second stage is confirmed, the CES is separated from the launch vehicle. In abort missions, the Crew Escape System along with Crew Module (CM) is separated from the falling vehicle first followed by the separation of CES from crew module after attaining safe altitude. As a part of critical technology for human space flight program, an abort test from launch pad (CES-PAT) was planned. In this flight test, after attaining altitude of about 2.5 km, CES gets separated from CM. This separation is achieved using a single Crew Escape Jettisoning motor (CJM). During the atmospheric region, the aerodynamics characteristics of separating crew module and CES are essential for the design of safe separation. This paper brings out the results of design and analysis made to predict the separation of CES fairing from CM. Subsequently from the flight data analysis it is evidenced that the separation performance was normal and collision free and as per predication.