Acoustic pressure oscillation effects on mean burning rates of plateau propellants
TL;DR: In this paper, the effects of acoustic pressure oscillations on mean burning rates of non-aluminized and aluminized propellants which exhibit low pressure exponent index (n) in the burning rate trends were investigated.
About: This article is published in Combustion and Flame.The article was published on 2021-04-01. It has received 4 citations till now. The article focuses on the topics: Chamber pressure & Sound pressure.
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TL;DR: In this paper, a numerical model was developed to capture the regression rate and simulate the combustion process of combined solid rocket motor by combining the Navies-Stokes equations with turbulence and gas-solid coupling models.
12 citations
TL;DR: Experiments have been carried out to investigate the effect of cowl length variation on performance characteristics of a single expansion ramp nozzle as mentioned in this paper, and the performance parameters were estimated for different cowl lengths.
Abstract: Experiments have been carried out to investigate the effect of cowl length variation on performance characteristics of a single expansion ramp nozzle. The performance parameters were estimated for ...
6 citations
TL;DR: In this article , the authors used the laser Doppler velocimetry technique to measure the velocity of the particles which are emerging out from the propellant burning surface in the gas phase zone under steady-state to determine the mean burning rate of aluminized solid propellant and double base propellant in the pressure range of 1-5 MPa.
Abstract: The main focus of this study is to utilize the laser Doppler velocimetry technique to measure the velocity of the particles which are emerging out from the propellant burning surface in the gas phase zone under steady-state to determine the mean burning rate of aluminized solid propellant and double base propellant in the pressure range of 1-5 MPa. The steady-state experiments are conducted under the high mean chamber pressure with the incorporation of a servomechanism feedback system to maintain the relative distance between the laser probe volume and the propellant regression surface. It is clear from the literature that only limited work has been reported on the LDV of solid propellants and hardly there is any work reported on characterizing aluminized solid propellants at high mean chamber pressure using the LDV technique, which has high spatial and temporal resolution features. A high-pressure window bomb with multiple optical access and coupled with a feedback actuation system serves the purpose of visualizing the propellant burning with the help of a camera and allowing the laser beam to align over the propellant surface. The actuation system is operated under two modes, viz., open loop and closed loop mechanism. The combustion photography is performed up-to-the mean chamber pressure of 5 MPa to compare the data with that of the LDV. It can be concluded that the LDV of solid propellant has shown promising results for the aluminized propellant and double base propellant burning rate estimation under steady-state combustion for high mean chamber pressure.
16 Jul 2021
TL;DR: In this article, the first-order measurement device represented by thermocouple and the second-order sensor represented by pressure sensor are analyzed and the relationship between the measurement error and the natural frequency is derived.
Abstract: Dynamic response characteristics of the sensors have an important effect on the accuracy of measurement results. Relevant studies about the dynamic response characteristics of sensors are carried out, which are mainly concern with the first-order measurement device represented by thermocouple and the second-order measurement device represented by pressure sensor. For temperature measurement with thermocouple, the theoretical expression of time constant and the corresponding relationship between measurement error and time constant are derived. For the pressure sensor, the corresponding relationship between the measurement error and the natural frequency is derived also. Formulas obtained in this paper can be used as the guideline for sensor selection and measurement error estimation.
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Book•
01 Jan 1963
TL;DR: In this paper, the authors defined and defined the fundamentals of solid propellant rocket propulsion systems, including propulsion system design, propulsion system parameters, and propulsion system performance analysis, as well as propulsion system testing.
Abstract: Classification definitions and fundamentals nozzle theory and thermodynamic relations flight performance chemical rocket propellant performance analysis liquid propellant rocket engine fundamentals liquid propellants thrust chambers combustion of liquid propellants turbopumps, engine design, engine controls, calibration, integration and optimization solid propellant rocket fundamentals solid propellants combustion of solid propellants solid rocket components and motor design hybrid propellant rockets thrust vector control selection of rocket propulsion systems rocket exhaust plumes electric propulsion rocket testing.
2,366 citations
Book•
01 Jan 1993
TL;DR: The main families and use of solid propellants, A. Davenas as mentioned in this paper, B. Gondouin, B. Zeller, and H. Austruy.
Abstract: Section headings: Foreword, A. Davenas. Propulsion elements for solid rocket motors, R. Lucas. Solid propellant grain design, B. Zeller. Prediction and measurement of specific impulse, J-P. Bac. Solid propellant combustion and internal ballistics of motors, B. Gossant. Plume, signal interference and plume signature, G. Prigent. Structural analysis of propellant grains, B. Gondouin. Safety characteristics of solid propellants and hazards of solid rocket motors, J. Brunet. The main families and use of solid propellants, A. Davenas. Double base propellants, H. Austruy. Composite propellants, A. Davenas. Advanced energetic binder propellants, R. Couturier. Propellants for integral rocket ramjet systems, C. Perut. Thermal insulations, liners and inhibitors, J-M. Tauzia. Future of solid rocket propulsion, A. Davenas. 60 illus approx.
198 citations
Book Chapter•
01 Jan 1992
TL;DR: In this paper, the authors define specific heat of particle material as follows: C = specific heat, Cv = mass fraction of particles, Cm = p^/pg Cp = mass-averaged specific heat.
Abstract: a = speed of sound, Eq. (23) Ab = defined in Eq. (92b) An = defined in Eq. (58) Anij = defined in Eq. (75) Bn = defined in Eq. (58) Bnij = defined in Eq. (75) C = specific heat of particle material Cm = mass fraction of particles, Cm = p^/pg Cp — mass-averaged specific heat, Eq. (20) Cv = mass-averaged specific heat, Eq. (20) Dni = defined in Eq. (75) e0 = stagnation energy, gas phase El = defined in Eq. (47b) Eni = defined in Eq. (75) ("&} = time-averaged energy / defined in Eq. (42) /! defined in Eq. (52b)
147 citations
TL;DR: In this article, nano-aluminium particles of ∼50nm size, produced at this laboratory, are added to composite solid propellants based on ammonium perchlorate and hydroxyl-terminated poly-butadiene binder that exhibit plateau burning rate trends and those including burning rate catalysts.
145 citations
TL;DR: In this paper, the non-steady burning of solid propellants was investigated both theoretically and experimentally, with attention to combustion instability, transient burning during motor ignition, and extinction by depressurization.
Abstract: : Non-steady burning of solid propellants was investigated both theoretically and experimentally, with attention to combustion instability, transient burning during motor ignition, and extinction by depressurization. The theory is based on a one-dimensional model of the combustion zone consisting of a thin gaseous flame and a solid heat up zone. The non-steady gaseous flame behavior is deduced from experimental steady burning characteristics; the response of the solid phase is described by the time-dependent Fourier equation. Solutions were obtained for dynamic burning rate, flame temperature, and burnt gas entropy under different pressure variations; two methods were employed. First, the equations were linearized and solved by standard techniques. Then, to observe nonlinear effects, solutions were obtained by digital computer for prescribed pressure variations. One significant result is that a propellant with a large heat evolution at the surface is intrinsically unstable under dynamic conditions even though a steady-state solution exists. Another interesting result is that the gas entropy amplitude and phase depend critically on the frequency of pressure oscillation and that either near-isentropic or near-isothermal oscillations may be observable. Experiments with an oscillating combustion chamber and with a special combustor equipped for sudden pressurization tend to support the latter conclusion. (Author)
138 citations