@article{WANG2024, 
author = {Ge WANG and Zhibang WANG and Fuqi WANG and Ben GUAN and Limin WANG and Haoran NING},
title = {Numerical study on quasi-one-dimensional internal ballistics of throttling segregated fuel-oxidizer systems},
year = {2024},
journal = {Acta Aeronautica et Astronautica Sinica},
volume = {45},
number = {7},
pages = {129111},
keywords = {solid rocket motor, segregated fuel-oxidizer system, quasi-one-dimensional internal ballistics, thrust regulation, performance regulation mechanism},
url = {https://www.sciopen.com/article/10.7527/S1000-6893.2023.29111},
doi = {10.7527/S1000-6893.2023.29111},
abstract = {A predictive unsteady quasi-one-dimensional internal ballistic numerical model and a set of performance regulation mechanism formulas are established for throttling segregated fuel-oxidizer systems. The numerical model considers combustion gas injection, wall friction, and propellant surface regression, using a finite-rate chemical reaction model to describe the non-equilibrium process. With this model, performance parameters and internal flow parameter distributions of the throttling segregated fuel-oxidizer system can be well demonstrated.Results show that, adjustment of the throat radius of the throttle valve from 2.89 mm to 1.65 mm increases the thrust of the system from 105.09 N to 432.18 N, by 411.25% from the original thrust, verifying the regulation capability of the throttling segregated fuel-oxidizer system. During the dynamic operation of the throttle valve, the system experiences anti-regulations. Faster actuation of the valve leads to larger anti-regulation amplitude and shorter response period of the performance parameters. Analysis of the influencing factors of performance regulation reveals that the increase of propellant pressure index and the decrease of nozzle throat radius both contribute to the improvement in performance regulation ability of the throttling segregated fuel-oxidizer system. Accordingly, a new arrangement of throttling segregated fuel-oxidizer system with an adjustable nozzle is proposed. Simulation of this arrangement suggests that, for a specified thrust adjustment ratio, reducing the nozzle throat radius can effectively alleviate the pressure level of the fuel-rich combustion chamber of the system, thus providing more feasible performance regulation schemes for the system operation.}
}