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Aerothermal Design of Crew Escape System


Affiliations
1 Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
2 Space Transportation System, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
3 Human Space Technology Group, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
4 Formerly GD, Aeronautics Entity, India
 

Crew safety holds highest priority in manned space missions. Crew Escape System (CES) intends to rescue the Crew Module (CM) which accommodates crew members in case of emergency abort situations. Pad Abort Test (PAT) demonstrates the functioning of CES during abort scenarios at the launch pad. CES pulls away CM from the launch pad using specially designed, quick-acting solid Escape Motors. CES-PAT vehicle is engulfed in hot exhaust plumes of these motors during its ascent, exposing the vehicle surfaces to severe thermal environments. Hence estimation of aerothermal heating levels and Thermal Protection System (TPS) design for CES-PAT vehicle structures are mission-critical. Thermal management of avionic packages housed inside CM is to be ensured for its safe functioning. This article highlights the different aerothermal environments experienced during CESPAT mission, design approaches adopted for estimating heating levels, TPS design and thermal management of avionic systems. Post-flight observations and assessment on aerothermal measurements during CES-PAT mission are also included. Aerothermal measurements confirmed the adequacy of the adopted design approach.

Keywords

Aerothermal Design, Crew Module, Heat Flux, Temperature, Thermal Protection System.
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  • Aerothermal Design of Crew Escape System

Abstract Views: 171  |  PDF Views: 74

Authors

K. S. Lakshmi
Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
M. Ram Prabhu
Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
Rishi Padmanabhan
Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
Ullekh Pandey
Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
M. Manirajan
Space Transportation System, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
P. Anoop
Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
T. Sivamurugan
Human Space Technology Group, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
B. Sundar
Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, India
M. J. Chacko
Formerly GD, Aeronautics Entity, India

Abstract


Crew safety holds highest priority in manned space missions. Crew Escape System (CES) intends to rescue the Crew Module (CM) which accommodates crew members in case of emergency abort situations. Pad Abort Test (PAT) demonstrates the functioning of CES during abort scenarios at the launch pad. CES pulls away CM from the launch pad using specially designed, quick-acting solid Escape Motors. CES-PAT vehicle is engulfed in hot exhaust plumes of these motors during its ascent, exposing the vehicle surfaces to severe thermal environments. Hence estimation of aerothermal heating levels and Thermal Protection System (TPS) design for CES-PAT vehicle structures are mission-critical. Thermal management of avionic packages housed inside CM is to be ensured for its safe functioning. This article highlights the different aerothermal environments experienced during CESPAT mission, design approaches adopted for estimating heating levels, TPS design and thermal management of avionic systems. Post-flight observations and assessment on aerothermal measurements during CES-PAT mission are also included. Aerothermal measurements confirmed the adequacy of the adopted design approach.

Keywords


Aerothermal Design, Crew Module, Heat Flux, Temperature, Thermal Protection System.

References





DOI: https://doi.org/10.18520/cs%2Fv120%2Fi1%2F110-115