Dynamic Identification of Nozzle Throat Diameter of a Solid Rocket Motor and Experimental Validation based on Micron-CT 3D Reconstruction

2020 ◽  
Author(s):  
Lin Sun ◽  
Chengbo Yu ◽  
Yu Zhao ◽  
Futing Bao ◽  
Yang Liu ◽  
...  
Keyword(s):  
3D Reconstruction ◽  
Experimental Validation ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Nozzle Throat ◽  
Dynamic Identification ◽  
Throat Diameter ◽  
Solid Rocket

scholarly journals Comparison Of Solid Rocket Motor Thrust Modulation Technique

2021 ◽  
Author(s):  
Clayton Edward Wozney
Keyword(s):  
Longitudinal Axis ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
The Novel ◽  
Solid Rocket Motor ◽  
Nozzle Throat ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Lower Chamber ◽  
Solid Rocket

The thrust profiles of solid rocket motors are usually determined ahead of time by propellant composition and grain design. Traditional techniques for active thrust modulation use a moveable pintle to dynamically change the nozzle throat diameter, increasing the chamber pressure and therefore thrust. With this approach, high chamber pressures must be endured with only modest increases in thrust. Alternatively, it has been shown that spinning a solid rocket motor on its longitudinal axis can increase the burning rate of the propellant and therefore the thrust without the resulting high chamber pressures. Building on prior experience modelling pressure-dependent, low-dependent and acceleration-dependent burning in solid rocket motors, an internal ballistic simulation computer program is modified for the present study where the use of the pintle nozzle and spin-augmented solid rocket motor combustion approaches, for a reference cylindrical-grain motor, are compared. This study confirms that comparable thrust augmentation can be gained at lower chamber pressures using the novel spin-acceleration approach, relative to the established pintle-nozzle approach, thus potentially providing a significant design advantage.

scholarly journals Comparison Of Solid Rocket Motor Thrust Modulation Technique

2021 ◽  
Author(s):  
Clayton Edward Wozney
Keyword(s):  
Longitudinal Axis ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
The Novel ◽  
Solid Rocket Motor ◽  
Nozzle Throat ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Lower Chamber ◽  
Solid Rocket

The thrust profiles of solid rocket motors are usually determined ahead of time by propellant composition and grain design. Traditional techniques for active thrust modulation use a moveable pintle to dynamically change the nozzle throat diameter, increasing the chamber pressure and therefore thrust. With this approach, high chamber pressures must be endured with only modest increases in thrust. Alternatively, it has been shown that spinning a solid rocket motor on its longitudinal axis can increase the burning rate of the propellant and therefore the thrust without the resulting high chamber pressures. Building on prior experience modelling pressure-dependent, low-dependent and acceleration-dependent burning in solid rocket motors, an internal ballistic simulation computer program is modified for the present study where the use of the pintle nozzle and spin-augmented solid rocket motor combustion approaches, for a reference cylindrical-grain motor, are compared. This study confirms that comparable thrust augmentation can be gained at lower chamber pressures using the novel spin-acceleration approach, relative to the established pintle-nozzle approach, thus potentially providing a significant design advantage.

Experimental validation of solid rocket motor damping models

2017 ◽  
Vol 10 (2) ◽  
pp. 213-230 ◽  
Author(s):  
Cristina Riso ◽  
Sebastiaan Fransen ◽  
Franco Mastroddi ◽  
Giuliano Coppotelli ◽  
Francesco Trequattrini ◽  
...  
Keyword(s):  
Experimental Validation ◽  
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.

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.

Sign in / Sign up

Export Citation Format

Share Document