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Patil, M. M.
- Industry-Institute Partnership:Success Stories
Abstract Views :165 |
PDF Views:0
Authors
V. M. Thorat
1,
M. M. Patil
1
Affiliations
1 College of Engineering, Malegaon (BK), (Maharashtra), IN
1 College of Engineering, Malegaon (BK), (Maharashtra), IN
Source
Journal of Engineering Education Transformations, Vol 12, No 3 (1999), Pagination: 33-38Abstract
The Industry - Institute Interaction is a must for the effective utilization of resources from both the sides to increase their respective efficiency, productivity and quality. The feelings, which are, at several occasions, expressed that much less has been effective in this connection are offset by certain success stories proving the effectiveness of this interaction. This paper elaborates these contents with examples.
- Evolution of Crew Escape System Configuration
Abstract Views :226 |
PDF Views:105
Authors
Affiliations
1 Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, IN
1 Aeronautics Entity, Vikram Sarabhai Space Centre, Department of Space, ISRO Post, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 96-104Abstract
The Crew Escape System (CES) is used for safe return of crew in case of any malfunctioning of a launch vehicle during ascent, specially in the atmospheric phase of flight. In the present case, as no active control is employed, the aerodynamic stability of CES is essential for safe return of crew in case of any emergency during ascent phase. While finalizing the shape of CES, besides stability, other aerodynamic parameters like acoustic, thermal, structural load, etc. need to be analysed. Based on detailed studies using CFD, a conical-shaped CES has been finalized. This article discusses the challenges involved in aerodynamic shaping of CES and different parameters studied while finalizing the configuration.Keywords
Aerodynamic Coefficients, Crew Escape System, Launch Vehicle, Static Margin, Stability.Full Text
References
- McCarthy, J. F., Ian Dodds, J. and Crowder, R. S., Development of the Apollo Launch Escape System. J. Space Craft, 1968, 5(8), 927– 932.
- Ashok, V. and Babu, T. C., Parallisation of Navier–Stoke code on a cluster of workstations. In Proceedings of the 6th International High Performance Computing Conference. Lecture Series in Computer Science, Springer Verlag, 1999.
- Balu, R., Babu, T. C., Ashok, V., Pradeep Kumar and Das, D., Development of low cost parallel computing platform for CFD applications. In Third AeSI Annual CFD Symposium, 11–12 August 2002.
- Sreenivasulu, J. et al., CFD analysis of a Launch vehicle with reverse flow nozzles – a validation study. Int. J. Aerospace Innov., 2013, 5(1).
- Sreenivasulu, J. et al., CFD analysis over a rocket configuration with and without canard. In 12th Annual CED Symposium, Bangalore, 11–12 August 2010.
- Aftosmis, M. J. and Rogers, S. E., Effects of jet-interaction on pitch control of a launch abort vehicle. AIAA Paper 2008-1281.
- Sreenivasulu, J. et al., Flow field analysis over a typical rocket with and without jet. In 10th Asian Symposium on Visualization, SRM University, Chennai, India, 1–5 March 2010.
- Sreenivasulu, J. et al., Aerodynamic analysis of a rocket configuration with grid fin. In Proceedings of the 37th National and 4th International Conference on Fluid Mechanics and Fluid Power, IIT Madras, Chennai, India, 16–18 December 2010.
- Onset Separation Aerodynamics of Crew Module from Crew Escape System
Abstract Views :232 |
PDF Views:98
Authors
Affiliations
1 Wind Tunnel Data Division, and Synthesis Group, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
2 Aerodynamic Design and Synthesis Group, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
3 Cryo and Semicryo Subsystem Test Facilities, ISRO Propulsion Research Complex, Mahendragiri 627 133, IN
4 Department of Aerospace Engineering, Indian Institute of Science, Bengaluru 560 012, IN
1 Wind Tunnel Data Division, and Synthesis Group, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
2 Aerodynamic Design and Synthesis Group, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
3 Cryo and Semicryo Subsystem Test Facilities, ISRO Propulsion Research Complex, Mahendragiri 627 133, IN
4 Department of Aerospace Engineering, Indian Institute of Science, Bengaluru 560 012, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 105-109Abstract
Aerodynamic characteristics of Crew Module (CM) during its separation from the Crew Escape System (CES) are essential to carry out separation dynamics analysis for confirming collision-free separation. As CM is at the base of CES, it has to clear the complex wake flow that prevails in the aft region. A 1 : 10-scale wind tunnel model is tested at 45 m/s freestream velocity in Indian Institute of Science, Bengaluru lowspeed tunnel. The interaction of CM with the base flows is studied for different attitude conditions in terms angle of attack, longitudinal and lateral movements. Results indicate that CM is recovered from forebody influence beyond X/D = 2, and it experiences reverse flow till it moves to X/D = 1.4D. Stability characteristics of CM are also analysed.Keywords
Aerodynamics, Crew Models, Crew Escape System, Stability Characteristics, Wind Tunnel.Full Text