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Wang L.-W.,China Aerospace Science and Technology Corporation | Chen L.-Q.,China Aerospace Science and Technology Corporation | Liu Y.-Q.,Xian Aerospace Composites Material Institute | Wu Y.,China Aerospace Science and Technology Corporation
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2015

A nozzle boundary-layer control system was introduced. This design can reduce the temperature of nozzle throat surface and the mass fractions of the oxidizing species in the combustion products due to the formation of a low-temperature fuel-rich boundary-layer. A parametric study of the effect of injection angle, geometric orientation, temperature and mass on the nozzle boundary-layer system was carried out using an axisymmetric model. A comparison of the decrease of nozzle surface temperature and concentrations of oxidizing species near nozzle surface under different parametric conditions was conducted. The change regulation of nozzle surface temperature and concentrations of oxidizing species near nozzle surface under different parametric conditions was elaborated. Finally, the effectiveness of nozzle boundary-layer control system on mitigating the influence factors of throat erosion was demonstrated. ©, 2015, Journal of Solid Rocket Technology. All right reserved.


Chen L.-Q.,China Aerospace Science and Technology Corporation | Wang L.-W.,China Aerospace Science and Technology Corporation | Liu Y.-Q.,Xian Aerospace Composites Material Institute | Zheng K.-B.,China Aerospace Science and Technology Corporation | Wu Q.,China Aerospace Science and Technology Corporation
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2014

A nozzle boundary-layer control system was introduced to reduce solid rocket motor nozzle erosion. This design not only reduces the temperature of nozzle throat surface but also reduces the mass fractions of the oxidizing gaseous species such as H2O, CO2 and OH in the combustion products, thus reducing the chemical attack on the nozzle throat surface. This paper gives an research status of this method at home and abroad in theoretical and experimental aspects. The effectiveness of this design for mitigating nozzle erosion was introduced in theoretical aspect, which can reduce nozzle erosion by more than 80%. In experimental aspect, the effectiveness of this system was demonstrated, and this method can achieve zero erosion rate. Research status of this method was summarized, and future work was analyzed.


Song M.,Xian Aerospace Composites Material Institute | Fu L.,Xian Aerospace Composites Material Institute
Materials China | Year: 2013

Composites with silicone carbide matrix and coatings have been widely used in aerospace field, due to fheir high properties of being resistant to oxidation, high temperature resisting, wear-resisting, corrosion-resisting and thermal endurant. As a kind of polymer precursor, polycarbosilane can be used to prepare silicone carbide coatings and silicone carbide matrix via polymer pyrolysis in circumstances of high temperature. Synthesizing methods, structures and properties of polycarbosilane are summarized in this article. Applications of silicone carbide fibers, surface/interface coatings of silicone carbide for resisting oxidation, silicone carbide matrix composites original from polycarbosilane are meanwhile included.Oxidation and ablation resisting properties of C/C composites clad with SiC coating are raised, service life are extended. Flexural strength and fracture toughness of C/SiC composite fabricated by CVI+PIP process are attained to be 643 MPa and 20.94 MPa·m1/2 respectively.Composites with silicone carbide matrix and coatings have been widely used in aerospace field, due to fheir high properties of being resistant to oxidation, high temperature resisting, wear-resisting, corrosion-resisting and thermal endurant. As a kind of polymer precursor, polycarbosilane can be used to prepare silicone carbide coatings and silicone carbide matrix via polymer pyrolysis in circumstances of high temperature. Synthesizing methods, structures and properties of polycarbosilane are summarized in this article. Applications of silicone carbide fibers, surface/interface coatings of silicone carbide for resisting oxidation, silicone carbide matrix composites original from polycarbosilane are meanwhile included.Oxidation and ablation resisting properties of C/C composites clad with SiC coating are raised, service life are extended. Flexural strength and fracture toughness of C/SiC composite fabricated by CVI+PIP process are attained to be 643 MPa and 20.94 MPa·m1/2 respectively.


Song M.-L.,Xian Aerospace Composites Material Institute | Tian W.,Xian Aerospace Composites Material Institute | Yan L.-S.,Xian Aerospace Composites Material Institute | Cui H.,Xian Aerospace Composites Material Institute | Zhang Q.,Xian Aerospace Composites Material Institute
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2014

Composites with silicone carbide matrix and coatings have been used widely in aerospace due to its high properties of oxidation protection and thermal endurance. As a kind of polymer precursor, polycarbosilane can be used to prepare silicone carbide matrix composites via polymer pyrolysis in circumstances of high temperature. Structures and properties and PIP-SiC matrix composites of polycarbosilane were summarized. Results show that C/C-SiC dual matrix composites combine the features of high operation temperature of C/C and good oxidation resistance of C/SiC composites. The integrated mechanical and ablation resistance properties of C/C-SiC composites are improved with increasing PIP-SiC content. The flexural and the tensile strength of 3D C/C-SiC composites by means of "CVI+PIP" process reach 468.4 MPa and 348.6 MPa. The linear and mass ablation rate of oxygen-acetylene under 600 s are 0.0017 mm/s and 0.000 6 g/s respectively.

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