Numerical investigation on regression rate and thrust regulation behaviors of a combined solid rocket motor with aluminum-based fuel

Zou, Xiangrui; Wang, Ningfei; Le, H. Q.; Bai, Tao; Xie, Kan

doi:10.1016/j.ast.2021.107102

Cited by 24 publications

(4 citation statements)

References 44 publications

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“…As a power device for aerospace vehicles, the solid rocket motor is widely utilized owing to its advantages of simplistic structure, high reliability, stable storage, and prompt launch [1,2]. The solid rocket motor utilizes solid propellant as fuel to generate a copious amount of high-temperature and high-pressure combustion products in the combustion chamber, which are subsequently accelerated and expanded by a Laval nozzle and expelled to form a plume, thus generating power [3].…”

Section: Introductionmentioning

confidence: 99%

Light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis

Yang,

Ye,

Qiang

et al. 2024

Propellants Explo Pyrotec

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The light transmittance measurement method, which is used to characterize smoke characteristic signal of solid rocket motor plume, can provide important reference for development and design of low smoke characteristic signal solid propellants and motors. The light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis is proposed in this paper. By using a 405 nm laser as the light source and a narrow‐band filter detection method, the influence of plume radiation on the measurement of light transmittance of solid rocket motor plume smoke can be minimized. Additionally, combined with the laser modulation spectrum analysis technology, the signal amplitude is selected by the laser modulation frequency to improve the signal‐to‐noise ratio of the signal. Compared with the laser constant current measuring mode, laser high‐frequency modulation measuring mode with spectrum analysis effectively improves the optical transmittance measurement accuracy. Based on this, a solid rocket motor plume smoke transmittance test system is developed to measure the plume smoke of standard test motors with different propellants and combustion chamber pressures. The results demonstrate that the system can effectively measure the light transmittance of the plume smoke. The light transmittance of solid rocket motor plume can be increased by reducing the aluminum content of solid propellant or increasing the pressure of the combustion chamber. Thus, this research provides an effective measuring tool for evaluating smoke concentration of solid rocket motor plume, which is beneficial to develop low smoke characteristic signal solid propellants and motors.

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Section: Introductionmentioning

confidence: 99%

Light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis

Yang,

Ye,

Qiang

et al. 2024

Propellants Explo Pyrotec

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“…A novel segregated fuel and oxidizer system (SFOS) was proposed by Los Alamos National Laboratory (LANL) in 2016 that separates the solid fuel and oxidizer in a cascade structure and provides high safety for the propulsion of small satellites [1]. Zou et al [2] proposed a segregated oxidizer/fuel solid motor (SOFSM) in 2021 that is shown in Figure 1. Different from the SFOSM system, both oxidizer and fuel in the SOFSM system are designed for self-sustained combustion.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Mixing Effect on Coupled Heat Release and Transfer Performance of a Novel Segregated Solid Rocket Motor

Liu,

Zhang,

Wang

et al. 2024

Aerospace

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The effect of mixing on coupled heat release and transfer performance of a novel segregated solid motor is numerically evaluated with a transient two-dimensional combustion model. The results show that vortex structures are formed and evolved in the combustion chamber. Quantitative calculation of the mixing effect shows the inhomogeneous distribution of oxidant and fuel species. The well-mixing area is located in a narrow belt-like coupled combustion region near the burning surface of the propellant. Heat transfer coefficient decreases greatly due to lower combustion reaction rate and enlarged flow channel area. Heat transfer coefficients near the two ends of the propellant grain are higher than other parts due to the influence of vortex mixing. Raising the inlet mass flow rate leads to enhanced mixing and heat transfer, which results in a lower temperature and regression rate of the propellant with combustion time. Temperature and oxidation rates of H2 and CO are unevenly distributed in the boundary layer of coupled combustion. Increasing the mass flux of inlet oxidizer gas leads to a higher combustion heat release rate. Therefore, the gas-phase temperature increases significantly. The heat release rate reaches the maximum near the ends of the propellant grain, where vortex mixing strengthens the coupled combustion process in the motor.

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“…Although Song et al [8] focused on calculating the transient flow characteristics within a solid rocket motor having a pintle nozzle, which has highly unsteady features, they used a common thrust force formula based on exit momentum and pressure in their studies, too. Other researches have been done in the field of transient phenomena in rocket engines [9][10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

Transient thrust behavior of low‐aspect‐ratio rocket propulsion systems**

Zanjani

Tahsini

2023

Propellants Explo Pyrotec

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In this work, the transient thrust force of the solid propellant rocket motor is numerically computed to illustrate the shortcomings of the common thrust formula in transient periods of operation. The internal ballistics of the solid rocket motor is simulated using the quasi one‐dimensional governing equations in which the finite volume method and the Roe′s scheme are utilized in calculation procedure. This is demonstrated that in transient operation of the propulsion systems, the common thrust formula may ignore some parts of physical phenomena because it has been derived based on steady state assumption, but there are some moving waves in transient operation in the combustion chamber which induce the fluctuations on the thrust force. So, the thrust‐time history must be computed by pressure force integration over the whole solid boundaries of the motor at any instant. The results show that such transient thrust behavior is more intense in low aspect ratio propulsion systems like small space thrusters.

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Numerical investigation on regression rate and thrust regulation behaviors of a combined solid rocket motor with aluminum-based fuel

Cited by 24 publications

References 44 publications

Light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis

Light transmittance measurement method of solid rocket motor plume based on laser modulation spectrum analysis

Evaluation of Mixing Effect on Coupled Heat Release and Transfer Performance of a Novel Segregated Solid Rocket Motor

Transient thrust behavior of low‐aspect‐ratio rocket propulsion systems**

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