Capsule Abort Recontact Simulation

A study is performed to ascertain the validity of the use of inviscid and viscous simulation methods to predict the axial and normal forces during a launch abort scenario for manned space flight vehicles. The proximity drag character of the Apollo launch escape vehicle (LEV) was studied in detail in a wind tunnel during the Apollo program. Simulation results obtained during the present effort are compared to the Apollo era wind tunnel experiments. The validated simulation techniques are applied to assess the possibility of recontact between the crew capsule and the service module after a launch abort is initiated. The natural extension of the method is to assess the risk associated with the new Crew Launch Vehicle’s escape system.