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Evolution of Crew Escape System Configuration


Affiliations
1 Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, India
 

The Crew Escape System (CES) is used for safe return of crew in case of any malfunctioning of a launch vehicle during ascent, specially in the atmospheric phase of flight. In the present case, as no active control is employed, the aerodynamic stability of CES is essential for safe return of crew in case of any emergency during ascent phase. While finalizing the shape of CES, besides stability, other aerodynamic parameters like acoustic, thermal, structural load, etc. need to be analysed. Based on detailed studies using CFD, a conical-shaped CES has been finalized. This article discusses the challenges involved in aerodynamic shaping of CES and different parameters studied while finalizing the configuration.

Keywords

Aerodynamic Coefficients, Crew Escape System, Launch Vehicle, Static Margin, Stability.
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  • Evolution of Crew Escape System Configuration

Abstract Views: 347  |  PDF Views: 149

Authors

Juluri Sreenivasulu
Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, India
Sanjoy Kumar Saha
Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, India
M. M. Patil
Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, India
V. Ashok
Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, India

Abstract


The Crew Escape System (CES) is used for safe return of crew in case of any malfunctioning of a launch vehicle during ascent, specially in the atmospheric phase of flight. In the present case, as no active control is employed, the aerodynamic stability of CES is essential for safe return of crew in case of any emergency during ascent phase. While finalizing the shape of CES, besides stability, other aerodynamic parameters like acoustic, thermal, structural load, etc. need to be analysed. Based on detailed studies using CFD, a conical-shaped CES has been finalized. This article discusses the challenges involved in aerodynamic shaping of CES and different parameters studied while finalizing the configuration.

Keywords


Aerodynamic Coefficients, Crew Escape System, Launch Vehicle, Static Margin, Stability.

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DOI: https://doi.org/10.18520/cs%2Fv120%2Fi1%2F96-104