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Anoop, P.
- Aerothermal Design, Qualification and Flight Performance
Abstract Views :254 |
PDF Views:96
Authors
Affiliations
1 Aeronautics Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 022, IN
1 Aeronautics Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 114, No 01 (2018), Pagination: 64-67Abstract
Reusable Launch Vehicle-Technology Demonstrator (RLV-TD) experiences severe thermal environment during its ascent as well as re-entry into the atmospheric regime. Structures should be designed to withstand this thermal load. Thermal environments were estimated for RLV-TD and depending on the peak heat flux and heat load, hot structure design for nose cap, wing, vertical tail and control surfaces was developed. Thermal protection system (TPS) using silica tile and flexible insulation was designed to protect the windward and leeward regions respectively. It is essential to verify and establish the design and also physically corroborate the actual thermal performance. Besides the design, the hot structures and TPS functionality as a system has to be qualified and thereby yield full confidence on the total performance during flight. To qualify the hot structures and TPS, various qualification tests were undertaken. The demonstration of their fly-ability and qualification under the combined effect of structural and thermal load was carried out successfully for all structures. This article provides details of aerothermal design of RLVTD and various qualification tests carried out. Comparison of the estimated structure temperatures with measured temperatures in flight shows the robustness of the design methodologies adopted.Keywords
Heat Flux, Reusable Launch Vehicle, Temperature, Thermal Protection System.Full Text
References
- Fay, F. A. and Riddell, F. R., Theory of stagnation point heat transfer in dissociated air. J. Aeronaut. Sci., 1958, 25(2), 73–85.
- Van Driest E. R., Turbulent boundary layer in compressible fluids. J. Aeronaut. Sci., 1951, 18(3), 145–160.
- Van Driest, E. R., Investigation of laminar boundary layer in compressible fluids using the cross method. NACA TN 2597, 1957.
- Beckwith, I. E. and Gallagher, J. J., Local heat transfer and recovery temperature on a yawed cylinder at a Mach number of 4.15 and at high Reynolds number, NASA-TR-R-104.
- Aerothermal Design of Crew Escape System
Abstract Views :167 |
PDF Views:74
Authors
K. S. Lakshmi
1,
M. Ram Prabhu
1,
Rishi Padmanabhan
1,
Ullekh Pandey
1,
M. Manirajan
2,
P. Anoop
1,
T. Sivamurugan
3,
B. Sundar
1,
M. J. Chacko
4
Affiliations
1 Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
2 Space Transportation System, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
3 Human Space Technology Group, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
4 Formerly GD, Aeronautics Entity, IN
1 Aeronautics Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
2 Space Transportation System, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
3 Human Space Technology Group, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
4 Formerly GD, Aeronautics Entity, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 110-115Abstract
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.Full Text
References
- Davidson, J. et al., Crew Exploration Vehicle ascent abort overview. In AIAA Guidance, Navigation and Control Conference and Exhibit, AIAA 2007-6590, Hilton Head, South Carolina, USA, 20–23 August 2007.
- Varghese, R. C., Prabhu, M. R., Anoop, P. and Sundar, B., Aerothermal design, analysis, thermo-structural testing and qualification of RLV-TD. J. Aerosp. Sci. Technol., 2017, 69(3A), 471–479.
- Van Driest, Turbulent boundary layer in compressible fluids. J. Aeronaut. Sci., 1951, 18(3), 145–160.
- Ram Prabhu, M, Pandey, U., Radhakrishnan, T. V. and Chacko, M. J., Integrated approach for spatial thermal mapping of radiative heat flux in base region of launch vehicles (IHMTC2015-374). In Proceedings of 23rd National Heat and Mass Transfer Conference, First International ISHMT-ASTFE Heat and Mass Transfer Conference, Thiruvananthapuram, 17–20 December 2015.
- Varghese, R. C., Prabhu, M. R., Anoop, P., Sundar, B., Chacko, M. J. and Raj, P. J., Thermal modeling of umbilical tower during lift off of a launch vehicle. J. Aerosp. Sci. Technol., 2018, 70(2), 77–84.
- NX-9.0 Thermal Solver TMG Reference Manual, 2013.