PERFORMANCE EVALUATION OF FLEX NOZZLE ABLATIVE LINERS BY CONDUCTING SOLID ROCKET MOTOR GROUND FIRING TEST
Keywords:
Solid rocket motor, Ablative liners, Firing test, Structural membersAbstract
The Rocket motor assembly with their different sub systems should be done with utmost care because these have to withstand very high operating pressures upto 80 bar, high temperatures of 3200K and velocity of gases. The erosion resistance is one of the key attributes of Composite ablative liners. The reasons for minimizing erosion rate of ablative liner will enhance the performance of the liner. The Flex Nozzle ablative liners are used to protect the nozzle structural members from the severe thermal environment in solid rocket nozzles. For this purpose, ablative composite liners made up of Phenolic resin matrix combined with reinforcement material like Rayon Carbon fabric, E-glass and silica fabric are extensively used.The nozzle ablative liners are made with carbon phenolic prepregs by tape winding process.Nozzle ablative liners are manufactured by using the optimized process parameters and these liners are assembled to the structural members of the flex nozzle assembly. The char, erosion, virgin thickness are measured and checked against the predictions.
Downloads
References
ASTM E285-08, “Standard Test Method for Oxyacetylene Ablation Testing of Thermal Insulation Materials”, ASTM International, 100 Barr Harbor Drive, West Conshohocken, PA, US.
Toshio Ogasawara and Takashi Ishikawa, Tetsuya Yamada Rikioyokota, Masayoshi Itoh and shigeruNogi (2002), “Thermal response and ablation characteristics of carbon fiber reinforces composite with novel silicon containing polymer MSP”, Journal of composite Materials Vol. 36 (02), 143-157.
Marcus LuizPontarolli (2006), “Ablative carbon phenolic composites additivated with carbon nano particles”, Thesis Masters in physics and chemistry of Aerospace Materials at the Technological Institute of Aeronautics, ITA, Sao Jose dos coampos, sao Paulo State, Brazil.
Patton R D, Pittman CU, Wang L; Hill J R and Day A (2002), “Ablation, mechanical and thermal properties of vapor grown carbon fiber/phenolic matrix composites”, International Journal of Composites: Part A vol.33, 243- 251.
Pulci G, Tirillo J, Marra F, Fossati F, Bartuli C and Valente, T (2010), “Carbon-phenolic ablative materials for re-entry space vehicles: manufacturing and properties”, International Journal of Composites Part A Vol. 41, 1483- 1490.
Yang W H and Tarng Y S (1998), “Design optimization of cutting parameters for turning operations based on the Taguchi method”, Elsevier Journal of Material processing Technology, Vol. 84, 122-129.
