Experimental Investigation on Throat Insert’s Thermal Shock Resistance Using C/C Composite in Solid Rocket Motor

Abstract:

To provide the test method for thermal shock resistance of throat insert material in rocket motor design, an experimental method with a SRM of scale down was developed to simulate the thermal load of full-size rocket motor’s throat insert. The test guaranteed the consistency of propellant、chamber pressure 、rate of ignition pressurization and the contour of the surface of throat insert with full-size rocket motor, and make a compromise of condition of throat insert at the same time. This method had well reappearance of the fracture failure of throat insert of a full-size rocket motor, which proved the feasibility of the test method to a certain extent. A comparison test for thermal shock resistance of two different composite materials was carried out. The experimental results indicate that two reserve C/C composite materials had good thermal shock resistance than three directions woven C/C composite material which used in the motor of failure, and the performance of carbon fabric pierced C/C composite material was better than no woven fabric pierced C/C composite material in some sort.

• Periodical: Advanced Materials Research (Volume 304)
• Pages: 169-174
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.304.169
• Online since: July 2011
• Authors: Xiang Geng Wei, Jiang Li, Jian Chen, Wei Jin
• Keywords: Scale Test, Solid Rocket Motor (SRM), Thermal Shock Resistance, Throat Insert

References

[1] Tian Si Peng, Tang Guo Jin, Li Daokui, Yuan Duancai: Gap design of solid rocket motor nozzle structures, Journal of Solid Rocket Technology, 2005, 26(5).

[2] Tian Sipeng, Tang Guojin, Li Dao Kui, Wufei: Analysis on Nozzle Structure Integrality of Solid Rocket Motors, Journal of Propulsion Technology, 2005, 28(3).

[3] Li Long, Zeng Bianrong, Li He Jun, etc: effect of thermal shock on the flexural strength of 2D-C/C composite, Kun Ming P.R. China, (2003).

[4] Xiang Shenghai, Zhang Ping, Li Shipeng, ect: An Analysis on Faults in the Nozzle Throat Insert of a Pulse, Journal of Beijing Institute of Technology, 2006, 26(5).

[5] Liu Zhanqin, Wang Dongfeng, Zhang Zhicheng, ect: Design and Validation of Small Proportion Model of Missile Engine's Flow Field, 2008, 25(8).

[6] Cheng Huier, Niu Lu: Simulation Research of Radiation Heat Transfer of Engine group by Model Nozzles, Journal of Propulsion Technology, 2001, 22(2).

[7] Wng Shuxian, Chen Linquan, Liu Yongquan: Experimental investigation on ablation properties of C/C throat-insert, Journal of Solid Rocket Technology, 2007, 30(2).

[8] Yang Sa, Li Jiang, Wang Wenbin, ect: Experimental investigation on Ablation Properties of C/C throat-insert, Journal of Solid Rocket Technology, 2009, 32(3).