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Sivamurugan, T.
- Aerothermal Design, Qualification and Flight Performance
Abstract Views :255 |
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.
- Flush Air Data Sensing System
Abstract Views :313 |
PDF Views:103
Authors
N. Shyam Mohan
1,
M. Jayakumar
1,
T. Sivamurugan
1,
K. C. Finitha
1,
S. B. Vidya
1,
Jayanta Dhoaya
1,
N. Remesh
1,
M. Prasath
1,
Shashi Krishna
1,
Aisha Sidhique
2
Affiliations
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
2 Liquid Propulsion Systems Centre, Indian Space Research Organisation, Bengaluru 560 008, IN
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
2 Liquid Propulsion Systems Centre, Indian Space Research Organisation, Bengaluru 560 008, IN
Source
Current Science, Vol 114, No 01 (2018), Pagination: 68-73Abstract
Flush air data sensing system (FADS) forms a mission-critical subsystem in re-entry vehicles. It makes use of surface pressure measurements from the nose cap of the vehicle for deriving air data parameters such as angle of attack, angle of sideslip, Mach number, etc. of the vehicle. These parameters are used by the flight control and guidance systems, and also assist in the overall mission management. The overall system engineering of FADS, including selection of pressure transducers, tubing size, port geometry, FADS algorithm and associated processing electronics along with the integration scheme is addressed in this article. Details of the qualification tests carried out in wind tunnel for end-to-end verification of the entire FADS system are covered in brief. Majority of the tests were carried out in a low-speed wind tunnel at a wind speed of 65 m/s (Mach number 0.2). The flight performance of FADS is also discussed in this article.Keywords
Angle of Attack, Flushed Air Data System, Hypersonic Flight Vehicles, Subsonic, Wind Tunnel.Full Text
References
- Whitmore, S. A., Cobleigh, B. R. and Haering, E. A., Design and calibration of the X-33 flush air data sensing system (FADS). NASA/TM-1998-206540, Research Engineering, NASA Dryden Flight Research Centre, January 1998, pp. 1–32.
- Ellsworth, J. C. and Whitmore, S. A., Re-entry air data system for a suborbital spacecraft based on X-34 design. AIAA Paper 2007-1200.
- Ellsworth, J. C. and Whitmore. S. A., Simulation of a flush air data system for transatmospheric vehicles. J. Spacecraft Rockets, 2008, 45(4).
- Larson, T. J. and Siemers. P. M., Use of nose cap and fuselage pressure orifices for determination of air data for Space Shuttle Orbiter below supersonic speeds. NASA TP-1643, 1980.
- Larson, T. J., Whitmore, S. A., Ehernberger, L. J., Johnson, J. B. and Siemers, P. M., Qualitative evaluation of a flush air data system at transonic speeds and high angles of attack. NASA TP-2716, 1987.
- Rajeshkumar, G. V. et al., Calibration of air data systems using numerical simulation of supersonic flow over blunt forebody. In 20th National Convention of Aerospace Engineers, 29–30 October 2006, Trivandrum.
- Rajesh Kumar, G. V., Harish, C. S., Swaminathan, S. and Madanlal, Development of a flush air data system for a winged body re-entry vehicle. In 2nd European Conference for Aerospace Sciences (EUCASS), Belgium, France, 2007.
- Siemers, P. M., Paul, M., Henry, W. and Martin. W. H., Shuttle entry air data system (SEADS) – flight verification of an advanced air data system concept. AIAA paper 88-2104, 1988.
- Whitmore, S. A., Moes, T. R. and Larson. T. J., Preliminary results from a subsonic high angle of attack flush air data sensing (HI-FADS) system. Design, calibration and flight Test evaluation. NASA TM-101713, 1990.
- Whitmore, S. A., Davis, A. R. and Fife, M. J., Flight demonstration of a real time flush air data sensing (RT-FADS) system. AIAA Paper 94-3433, August 1995.
- Remesh, N., Jayakumar, M., Finitha, K. C., Abhay Kumar, Shyam Mohan, N. and Swaminathan, S., Pressure measurement sensitivity studies on a reusable launch vehicle (RLV) flush air data sensing system (FADS). In Proceedings of National Conference on Space Transportation Systems, Opportunites and Challenges (STS 2011).
- Flight Performance of Crew Escape System during Pad Abort Condition
Abstract Views :233 |
PDF Views:90
Authors
Affiliations
1 Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 022, IN
2 Human Space Flight Centre, Indian Space Research Organisation, Bengaluru 560 054, IN
1 Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 022, IN
2 Human Space Flight Centre, Indian Space Research Organisation, Bengaluru 560 054, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 81-88Abstract
As a prologue to the Gaganyaan project, ISRO successfully test fired one of the critical and essential technologies for human space flight, i.e. Crew Escape System (CES) Pad Abort Test on 5 July 2018. This is a strategically important flight as a part of various qualification tests that ensures emergency escape measure to quickly pull the Crew Module (CM) along with the astronauts to a safe distance from the launch vehicle in case of any eventuality. CES along with CM weighing of 12.6 tonnes lifted-off at 07.00 h from the Sounding Rocket Complex Launch Pad, Sriharikota. The vehicle was taken to an altitude of 3 km using a specially developed solid motor with multiple reverse flow and scarfed nozzles with 10 g acceleration. Around 330 sensors on-board were used to measure its performance. The data obtained ensured that the adopted design philosophy and approaches such as CM reorientation, aerodynamic data with jet-on environment, mission sequences, performance of special solid motors, deceleration system, etc. were in order. This provides more confidence to progress to the next level of demonstration as a part of Gaganyaan.Keywords
Crew Escape System, Crew Module, Flight Performance, Pad Abort.Full Text
- 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.