Analysis of Ablative Performance of C/C Composite Throat Containing Defects Based on X-ray 3D Reconstruction in a Solid Rocket Motor

2015 ◽  
Vol 32 (4) ◽  
Author(s):  
Wei-Hua Hui ◽  
Fu-Ting Bao ◽  
Xiang-Geng Wei ◽  
Yang Liu
Keyword(s):  
3D Reconstruction ◽  
Axial Direction ◽  
Ablation Rate ◽  
Carbon Composite ◽  
Rocket Motor ◽  
Reconstruction Method ◽  
Maximum Relative Error ◽  
Solid Rocket Motor ◽  
X Ray ◽  
Solid Rocket

AbstractIn this paper, a new measuring method of ablation rate was proposed based on X-ray three-dimensional (3D) reconstruction. The ablation of 4-direction carbon/carbon composite nozzles was investigated in the combustion environment of a solid rocket motor, and the macroscopic ablation and linear recession rate were studied through the X-ray 3D reconstruction method. The results showed that the maximum relative error of the X-ray 3D reconstruction was 0.0576%, which met the minimum accuracy of the ablation analysis; along the nozzle axial direction, from convergence segment, throat to expansion segment, the ablation gradually weakened; in terms of defect ablation, the middle ablation was weak, while the ablation in both sides was more serious. In a word, the proposed reconstruction method based on X-ray about C/C nozzle ablation can construct a clear model of ablative nozzle which characterizes the details about micro-cracks, deposition, pores and surface to analyze ablation, so that this method can create the ablation curve in any surface clearly.

scholarly journals Solid Rocket Motor Design Using Hybrid Optimization

2012 ◽  
Vol 2012 ◽  
pp. 1-9 ◽  
Author(s):  
Kevin Albarado ◽  
Roy Hartfield ◽  
Wade Hurston ◽  
Rhonald Jenkins
Keyword(s):  
Hybrid Approach ◽  
Optimal Solution ◽  
Solution Space ◽  
Axial Direction ◽  
Pattern Search ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Thin Sections ◽  
Solid Rocket

A particle swarm/pattern search hybrid optimizer was used to drive a solid rocket motor modeling code to an optimal solution. The solid motor code models tapered motor geometries using analytical burn back methods by slicing the grain into thin sections along the axial direction. Grains with circular perforated stars, wagon wheels, and dog bones can be considered and multiple tapered sections can be constructed. The hybrid approach to optimization is capable of exploring large areas of the solution space through particle swarming, but is also able to climb “hills” of optimality through gradient based pattern searching. A preliminary method for designing tapered internal geometry as well as tapered outer mold-line geometry is presented. A total of four optimization cases were performed. The first two case studies examines designing motors to match a given regressive-progressive-regressive burn profile. The third case study studies designing a neutrally burning right circular perforated grain (utilizing inner and external geometry tapering). The final case study studies designing a linearly regressive burning profile for right circular perforated (tapered) grains.

Effect of combustion gas mass flow rate on carbon/carbon composite nozzle ablation in a solid rocket motor

Carbon ◽  
2012 ◽  
Vol 50 (4) ◽  
pp. 1554-1562 ◽  
Author(s):  
Li-na Peng ◽  
Guo-qiang He ◽  
Jiang Li ◽  
Lei Wang ◽  
Fei Qin
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Carbon Composite ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Combustion Gas ◽  
Solid Rocket

scholarly journals Burning Rate Enhancement Analysis of End-Burning Solid Propellant Grains Based on X-Ray Real-Time Radiography

2020 ◽  
Vol 2020 ◽  
pp. 1-9
Author(s):  
Wei Xianggeng ◽  
Bo Tao ◽  
Wang Pengbo ◽  
Ma Xinjian ◽  
Lou Yongchun ◽  
...  
Keyword(s):  
Burning Rate ◽  
Real Time ◽  
Solid Propellant ◽  
Burning Surface ◽  
Rocket Motor ◽  
Operating Pressure ◽  
Solid Rocket Motor ◽  
X Ray ◽  
The Real ◽  
Solid Rocket

Unexpected pressure rise may occur in the end-burning grain solid rocket motor. It is generally believed that this phenomenon is caused by the nonparallel layer combustion of the burning surface, resulting in the increase of burning rate along the inhibitor. In order to explain the cause of this phenomenon, the experimental investigation on four different end configurations were carried out. Based on the X-ray real-time radiography (RTR) technique, a new method for determining the dynamic burning rate of propellant and obtaining the real-time end-burning profile was developed. From the real-time images of the burning surface, it is found that there was a phenomenon of nonuniform burning surface displacement in the end-burning grain solid rocket motor. Through image processing, the real-time burning rate of grain center line and the real-time cone angle are obtained. Based on the analysis of the real-time burning rate at different positions of the end surface, the end face cone burning process in the motor working process is obtained. The closer to the shell, the higher the burning rate of the propellant. Considering the actual structure of this end-burning grain motor, it is speculated that the main cause of the cone burning of the grain may be due to the heat conduction of the metal wall. By adjusting the initial shape of the grain end surface, the operating pressure of the combustion chamber can be basically unchanged, so as to meet the mission requirements. The results show that the method can measure the burning rate of solid propellant in real time and provide support for the study of nonuniform combustion of solid propellant.

Thermochemical Erosion of Hafnium Carbide Modified Carbon/Carbon Composite Throat in a Small Solid Rocket Motor

2011 ◽  
Vol 26 (4) ◽  
pp. 427-432 ◽  
Author(s):  
Xue-Tao SHEN ◽  
Ke-Zhi LI ◽  
He-Jun LI ◽  
Tao FENG ◽  
Lei-Lei ZHANG ◽  
...  
Keyword(s):  
Carbon Composite ◽  
Rocket Motor ◽  
Hafnium Carbide ◽  
Solid Rocket Motor ◽  
Solid Rocket

Ablation of the carbon/carbon composite nozzle-throats in a small solid rocket motor

Carbon ◽  
2011 ◽  
Vol 49 (4) ◽  
pp. 1208-1215 ◽  
Author(s):  
Ke-Zhi Li ◽  
Xue-Tao Shen ◽  
He-Jun Li ◽  
Shou-Yang Zhang ◽  
Tao Feng ◽  
...  
Keyword(s):  
Carbon Composite ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket

3D Reconstruction of Solid Rocket Motor Based on CT Images

2013 ◽  
Vol 711 ◽  
pp. 652-658
Author(s):  
Zhi Gao Xu ◽  
Chun An Ai ◽  
Jing Ma ◽  
Xiang Bin Li
Keyword(s):  
3D Reconstruction ◽  
Detection Efficiency ◽  
3D Visualization ◽  
Rocket Motor ◽  
Surface Rendering ◽  
Solid Rocket Motor ◽  
Internal Defects ◽  
Visualization Toolkit ◽  
Angle Of View ◽  
Solid Rocket

A 3D visualization model of Solid Rocket Motor is established based on CT slice data using visualization toolkit. The 3D reconstruction system of flaw for Solid Rocket Motor is presented. The system has the function of volume rendering, surface rendering and slice showing for solid Rocket Motor. The results of tests show that vivid 3D internal defects images of Solid Rocket Motor are achieved. Technician can inspect details of internal defects from different angle of view and can quickly and exactly estimate the quality status of SRM. The detection efficiency is greatly improved.

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