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Remesh, N.
- 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.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).
- Mission Design, Preflight and Flight Performance and Observations for Pad Abort Test
Abstract Views :215 |
PDF Views:86
Authors
Jayanta Dhaoya
1,
N. Remesh
1,
C. Ravikumar
1,
P. Bhanumathy
1,
A. K. Anilkumar
1,
Abhay Kumar
1,
V. Ashok
1
Affiliations
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
1 Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 89-95Abstract
Abort system is initiated to take the Crew Module (CM) away from the launch vehicle in case of an emergency at lift-off or at any point of time after launch for a mission with crew onboard. Crew Escape System (CES)-based abort is carried out from launch pad and during the atmospheric phase of ascent flight. The design and operation of CES play a crucial role in providing abort capability for escape from launch vehicle and return of the crew back to Earth during critical phase of ascent flight. CES motors are used to pull CM away from the launch vehicle during this mode of abort. Mission simulation and analysis is necessary for the design of CES-based abort mission and for its configuration. This article discusses the mission design, challenges faced during the design and strategies formulated towards the successful execution of Pad Abort Test.Keywords
Abort System, Flight Performance, Launch Vehicle, Mission Design.Full Text
References
- Hyle, C. T. et al., Abort Planning for Apollo mission. In AIAA 8th Aerospace Sciences Meeting, AIAA-70-0094, 1970.
- Davidson, J. et al., Crew exploration vehicle ascent abort overview, AIAA-2007-6590. In AIAA Guidance, Navigation and Control Conference, August 2007.
- Davidson, J. et al., Orion crew exploration vehicle launch abort system guidance and control analysis overview. In AIAA Guidance, Navigation and Control Conference, AIAA 2008-7148, August 2008.
- Dhaoya, N. et al., Mission design and trajectory simulation for CES. In Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2015), 3–5 December 2015, Trivandrum, India, Paper id CP 89.