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Prasath, M.
- Aerodynamic Design, Characterization and Flight Performance of RLV-TD
Abstract Views :270 |
PDF Views:100
Authors
G. Vidya
1,
K. Manokaran
1,
V. R. Ganesan
1,
M. Prasath
1,
Sundeepkumar Epuri
1,
P. Balasubramanian
1,
C. Babu
1,
B. Venkatasubrahmanyam
1,
Priyankar Bandyopadhyay
1
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: 48-63Abstract
Complete aerodynamic design and characterization of ascent as well as descent phases of Reusable Launch Vehicle-Technology Demonstrator (RLV-TD) have been obtained through thousands of wind tunnel tests, flow simulations using various computational fluid dynamic codes and tailor-made engineering codes. The evolution of the ascent and descent designs, aerodynamic characterization and flight performance is presented in this article. The flight data comparison of aerodynamic coefficients, control surface loads, pressure distribution and external acoustic levels with preflight data is good and therefore, providing confidence in using the ground-based data generation techniques along with defined dispersion bands. Some of the minor deviations in the performance observed in flight were resolved/understood in the post-flight analysis, whereas few effects observed in flight need further understanding.Keywords
Aerodynamic Design and Characterization, Ascent and Descent Phases, Flight Performance, Reusable Launch Vehicle, Wing Body.References
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- Vidya, G. et al., Aerodynamic design, characterization and parameter estimation of RLV-TD from flight data. J. Aerosp. Sci. Technol., 2017, 69(3A), 423–439.
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- Flush Air Data Sensing System
Abstract Views :315 |
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.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.
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- 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).