On the Effectiveness of Using the Real Law of Solid Propellant Burning Rate As a Function of Solid Rocket Motor Pressure

2020 ◽  
Vol 56 (2) ◽  
pp. 172-180
Author(s):  
A. M. Lipanov ◽  
L. N. Kolesnikova ◽  
A. Yu. Leshchev
Keyword(s):  
Burning Rate ◽  
Solid Propellant ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
The Real ◽  
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.

scholarly journals A New Erosive Burning Model of Solid Propellant Based on Heat Transfer Equilibrium at Propellant Surface

2020 ◽  
Vol 2020 ◽  
pp. 1-9
Author(s):  
Yanjie Ma ◽  
Futing Bao ◽  
Lin Sun ◽  
Yang Liu ◽  
Weihua Hui
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Burning Rate ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Erosive Burning ◽  
Computational Data ◽  
And Performance ◽  
Solid Rocket ◽  
Propellant Surface

Erosive burning refers to the augmentation of propellant burning rate appears when the velocity of combustion gas flowing parallel to the propellant surface is relatively high. Erosive burning can influence the total burning rate of propellant and performance of solid rocket motors dramatically. There have been many different models to evaluate erosive burning rate for now. Yet, due to the complication processes involving in propellant and solid rocket motor combustion, unknown constants often exist in these models. To use these models, trial-and-error procedure must be implemented to determine the unknown constants firstly. This makes many models difficult to estimate erosive burning before plenty of experiments. In this paper, a new erosive burning rate model is proposed based on the assumption that the erosive burning rate is proportional to the heat flux at the propellant surface. With entrance effect, roughness, and transpiration considered, convective heat transfer coefficient correlation proposed in recent years is used to compute the heat flux. This allows the release of unknown constants, making the model universal and easy to implement. The computational data of the model are compared with different experimental and computational data from different models. Results show that good accuracy (10%) with experiments can be achieved by this model. It is concluded that the present model could be used universally for erosive burning rate evaluation of propellant and performance prediction of solid rocket motor as well.

NON-STATIONARY BEHAVIOR OF A SOLID PROPELLANT CHARGE FOR NOZZLELESS SOLID ROCKET MOTORS UNDER GAS-DYNAMIC LOAD

2021 ◽  
pp. 48-59
Author(s):  
I.G. Voropaeva ◽  
◽  
A.A. Kozulin ◽  
L.L. Min’kov ◽  
E.R. Shrager ◽  
...  
Keyword(s):  
Burning Rate ◽  
Solid Propellant ◽  
Solid Mechanics ◽  
Stokes Equations ◽  
Combustion Products ◽  
Conjugate Problem ◽  
Navier Stokes ◽  
Solid Rocket Motor ◽  
Propellant Charge ◽  
Solid Rocket

The numerical solution to a conjugate problem of an unsteady flow of combustion products in a flow path of the nozzleless solid rocket motor (SRM) and the oscillation of a solid propellant charge under the action of the forces directed from combustion products is considered. The Navier-Stokes equations for a compressible viscous gas are used to mathematically describe the flow of the combustion products. To model the charge oscillations, the equations of solid mechanics are applied, which take into account the propellant hyperelasticity. Pressure distributions and the propellant burning rate along the charge channel are presented for different models of the propellant burning rate. It is revealed that at the stage of SRM design, the use of the burning rate law, determined by pressure in the head of the combustion chamber, is more preferable in order to assess the internal ballistic characteristics. The solution to the conjugate problem shows that in the nozzleless SRM with the propellant having low Young's modulus, resonance can occur, which causes uncontrolled charge oscillations.

Design of a Solid Propellant Air Turbo Rocket for a Tactical Air-Launched Missile

2007 ◽  
Author(s):  
Fredrik Haglind ◽  
Henrik Edefur ◽  
Stefan Olsson
Keyword(s):  
Solid Propellant ◽  
Combined Cycle ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Gas Generator ◽  
Number Range ◽  
Solid Propellant Rocket ◽  
Solid Rocket ◽  
Novel Concept ◽  
Propellant Rocket

Traditionally, air-launched missiles are powered by a turbojet engine, rocket motor or a ramjet engine. A novel concept that may offer advantages over these concepts is the Air Turbo Rocket (ATR), which is a combined cycle engine, featuring a cycle where the turbine is isolated from the core engine flow entirely and powered by a separate gas generator. This paper is aimed at assessing the suitability of the solid propellant ATR as power source for a tactical air-launched missile. The ATR cycle is designed to achieve optimum performance, and a suitable solid propellant is selected. In addition, a turbojet and a solid rocket motor are designed for the same requirements, and the performances of these three engine concepts are compared. The ATR offers high thrust to weight and thrust to frontal area weight ratios, throttleability, and a wide speed-altitude operating envelope. The calculations suggest that, provided that the afterburning cooling issues can be solved, it would be reasonable to design the ATR such that a stoichiometric fuel/air mixture is obtained in the afterburner. For the Mach number range evaluated here, the ATR may offer advantages over the turbojet and the solid propellant rocket motor.

scholarly journals Fluid-structure interaction considerations for solid rocket motor internal ballistics modeling

2021 ◽  
Author(s):  
Giovanni Montesano
Keyword(s):  
Burning Rate ◽  
Combustion Instability ◽  
Three Dimensional ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Fluid Structure ◽  
Dimensional Finite Element ◽  
Solid Rocket ◽  
Model Components ◽  
Three Dimensional Finite Element

A study of the numerical modeling and prediction of nonlinear unsteady combustion instability within the combustion chamber of a solid rocket motor (SRM) is the main objective. The numerical model consists of a three-dimensional finite-element representation of a cylindrical-grain motor, coupled to a quasi-one-dimensional internal ballistic flow (IBF) model, where a quasi-steady rapid kinetic rate burning rate algorithm is used to model the propellant combustion and regression. Fluid-structure-combustion interaction subroutines are also employed to control the simulated motor firings and the data transferred between the fluid, structure and burning rate model components. Results illustrating the significant effects of structural vibrations on the burning rate and consequently the IBF are shown and compared to experimental data. Modeling considerations are illustrated, giving insight into the physical phenomena of SRM combustion instability.

Star Grain Regression under Spin Induced Acceleration Effect

2011 ◽  
Vol 110-116 ◽  
pp. 451-456 ◽  
Author(s):  
Hlaing Tun Soe ◽  
Hong Jun Xiang
Keyword(s):  
Solid Propellant ◽  
Rocket Motor ◽  
Spin Effect ◽  
Geometrical Approach ◽  
Operating Pressure ◽  
Solid Rocket Motor ◽  
Solid Propellant Rocket ◽  
Solid Rocket ◽  
Propellant Rocket ◽  
Propellant Surface

Spinning is used in some of solid rocket motors to increase the flight trajectory precision or for stability requirements. The angular acceleration due to the spin effect increases the burning rate of solid propellant and changes the motor performance by increasing the operating pressure and decreasing the burning time. So it is important to know the grain regression taken place in the solid propellant rocket motor in the acceleration field. In this study, we represent the grain regression analysis of two-dimensional axis-symmetric star grain configuration of the solid propellant rocket motor under spin induced acceleration effect to study how the spin affects on the internal ballistics of the solid rocket motor. Grain regression is done by two methods - geometrical approach and numerical approach. The burning rates on the propellant surface are different with its radial distance, acceleration vector angle and surface slope when the rocket is spinning. With the different burn rates on the propellant surface, the propellant surface perimeter and port area are computed by using the numerical method, and the results are compared with that of constant burn rate.

scholarly journals Parameters Affecting the Erosive Burning of Solid Rocket Motor

2018 ◽  
Vol 153 ◽  
pp. 03001
Author(s):  
Almostafa Abdelaziz ◽  
Liang Guozhu ◽  
Anwer Elsayed
Keyword(s):  
Burning Rate ◽  
High Energy ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Time Curve ◽  
Rocket Motors ◽  
Erosive Burning ◽  
Pressure Time ◽  
Burning Propellant ◽  
Solid Rocket

Increasing the velocity of gases inside solid rocket motors with low port-to-throat area ratios, leading to increased occurrence and severity of burning rate augmentation due to flow of propellant products across burning propellant surfaces (erosive burning), erosive burning of high energy composite propellant was investigated to supply rocket motor design criteria and to supplement knowledge of combustion phenomena, pressure, burning rate and high velocity of gases all of these are parameters affect on erosive burning. Investigate the phenomena of the erosive burning by using the 2’inch rocket motor and modified one. Different tests applied to fulfil all the parameters that calculated out from the experiments and by studying the pressure time curve and erosive burning phenomena.

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