Abort Separation of Launch Escape System Using Aerodynamic Interference

摘要

Three configurations (A, B-l, and B-2) of a capsule-shaped abort system using aerodynamic interference were studied by computational fluid dynamics and experiment. Specifically, the effects of the abort separation distance on the flowfield and interference were investigated based on static and dynamic simulations at M = 3.0. The results are summarized as follows: 1. As a preliminary evaluation of this abort system, the proximity aerodynamics analysis was made on the present abort system. When the abort separation distance is small, the two-dimensional axisymmetric case can be used to simulate the real three-dimensional (3-D) scenario. 2. Only drag force is produced on the capsule of model A; thus, abort separation cannot be boosted. By contrast, the model B series has negative drag force (thrust force), in which supersonic aerodynamic interference contributes to the abort process. 3. The effect of a fence disappears when h/D > 0.6, and drag force (negative thrust) is produced when h/D > 0.8. Consequently, the capsule moves backward after the capsule attains a maximum separation distance of 2.05 and 2.23 for models B-l and B-2, respectively. However, the capsule has no possibility of recontacting with the rocket, because the smaller the separation distance becomes, the stronger the flow interference becomes. 4. The present abort system can be used as an auxiliary equipment of an escape system such as that used in the Apollo-shaped space transportation system at the initial stage of the abort separation. In addition, the present study will lead to the next study, in which a 3-D and six-degrees-of-freedom scenario will be carried out to examine the 3-D abort characteristics after the initial stage of the abort separation.