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Harikrishnan, R.
- Development of Slow-Burning Solid Rocket Booster for RLV-TD Hypersonic Experiment
Abstract Views :308 |
PDF Views:96
Authors
Achutananda Parhi
1,
V. Mahesh
1,
Khadarvoli Kalluru
1,
S. Reshmi
1,
R. Harikrishnan
1,
V. M. Lakshmi
1,
J. Paul Murugan
1,
Renjith Kumar Reddy
1
Affiliations
1 Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 022, IN
1 Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 114, No 01 (2018), Pagination: 74-83Abstract
This article discusses the developmental challenges of the low-thrust, long-duration solid rocket motor for the launch of the experimental Reusable Launch Vehicle-Technological Demonstrator (RLV-TD). The main challenges were: (1) developing a motor case and subsystems with low inert mass; (2) design of an optimum nozzle such that the motor can have maximum specific impulse at atmospheric conditions, but with no flow separation at low operation pressures; (3) developing a slow-burning propellant (3 mm/s) to meet the mission requirements; (4) design of propellant grain for the motor so that it has long burning time, the vehicle experiences low dynamic pressure at the transonic regime, and the motor is without combustion instability; (5) developing necessary thermal protection system to take care of long-duration operations, and (6) developing the igniter to ensure the ignition of the motor, especially when easy ignition is difficult with slow-burning propellants and that there should be sufficient overlap of igniter functioning with motor initiation. Performance of the motor in flight indicated that the design met all the required criteria within the expected tolerance.Keywords
Burning Rate, Igniter, Motor Case, Performance Prediction, Solid Rocket Booster.Full Text
References
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- Design, Development, Static and Flight Tests of Reverse Flow Multiple Nozzle Solid Rocket Motor with High Burn Rate Propellant
Abstract Views :167 |
PDF Views:77
Authors
K. Sreejith
1,
Shailesh Prasad
1,
R. Bagavathiappan
1,
C. Prasanth
1,
R. Jeenu
1,
J. Paul Murugan
1,
Thomas Kurian
1,
N. Mansu
1,
R. Harikrishnan
1,
G. Levin
1,
V. Eswaran
1
Affiliations
1 Solid Propulsion and Research Entity, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
1 Solid Propulsion and Research Entity, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 116-121Abstract
The Vikram Sarabhai Space Centre, Thiruvananthapuram has developed a special purpose motor for Human Spaceflight Programme with four reverse flow nozzles, having cant angle of 149°, termed as Lowaltitude Escape Motor (LEM). This is a high-thrust short-duration motor having specific envelope constraints. New high burn rate propellant has been developed to achieve the specific mission requirements. In the design, emphasis has been given to smooth turning of internal flow, avoiding sharp edges and corners, to the specified cant angle. It has to satisfy the thermal as well as structural design requirements for the multiple nozzle openings provided, containing itself to minimum external projections and envelope. Since four ellipsoidal-shaped cut-outs from the chamber cause high stress concentrations, welding or some other joining methods are not preferable. The nozzle hardware has to be machined out of 15CDV6 steel forging with high precision. The motor is tested in the vertical mode in order to avoid exhaust gas hitting on the ground and getting deflected back to the motor. This calls for extensive thermal protection requirements for both test stand and motor subsystems. A solid rocket motor with four reverse flow nozzles has been designed, realized and twice static tested successfully. The intricacies involved in the development of LEM are presented in this article.Keywords
Launch Escape System, Manned Mission, Multiple Nozzles, Reverse Flow, Solid Rocket Motors.Full Text
References
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