Ultrasonic testing of solid propellant rocket motors (With a plastic lining between propellant and case)
0
Citation
0
Reference
10
Related Paper
Keywords:
Solid-fuel rocket
Rocket (weapon)
This chapter discusses all the aspects of interior ballistic calculations for solid propellant-based rockets. The thermo-chemical calculations for a theoretical assessment of propellant energetics have been elaborated. The mathematical formulations for characteristic velocity and specific impulse, and their physical significance with respect to rocket motors, have been enumerated. An example is given at the end of the chapter to understand the utility of various concepts for rocket propulsion and appreciate the design of rocket propellants for mission requirements.
Specific impulse
Solid-fuel rocket
Rocket (weapon)
Rocket propellant
Energetics
Characteristic velocity
Cite
Citations (0)
Solid-fuel rocket
Rocket (weapon)
Rocket propellant
Liquid-propellant rocket
Cite
Citations (15)
A generalised model of burning of a solid rocket propellant based on kinetics of propellant hasbeen developed. A complete set of variables has been formed after examining the existing models.Buckingham theorem provides the functional form of the model, such that the existing models are thesubcases of this generalised model. This proposed model has been validated by an experimental data.
Solid-fuel rocket
Rocket (weapon)
Cite
Citations (3)
An advanced facility and corresponding method for real-time detecting exhaust plume of rocket motors have been established. In order to determine the experiment conditions of detecting the plumes using this new facility and method, the electro-magnetic wave transmittances of plumes of rocket motors loaded with four types of solid propellants respectively, were measured. The experimental results indicate that this new technique can be used to characterize signatures of various types of propellants with satisfactory repeatability and accuracy.
Solid-fuel rocket
Rocket (weapon)
Repeatability
Rocket propellant
Cite
Citations (1)
Classification Definitions and Fundamentals Nozzle Theory and Thermodynamic Relations Heat Transfer Flight Performance Thermo-Chemical Rocket Propellant Performance Analysis Liquid Propellant Rocket Engine Fundamentals Liquid Propellants Combustion of Liquid Propellants Liquid Propellant Rocket Engine Systems and Components Solid Propellant Rocket Fundamentals Solid Propellants Combustion of Solid Propellants Solid Propellant Components and Motor Design Hybrid Propellant Rockets Thrust Vector Control Selection of Rocket Propulsion Systems Rocket Exhaust Plumes Rocket Testing.
Liquid-propellant rocket
Solid-fuel rocket
Rocket (weapon)
Rocket engine nozzle
Rocket propellant
Rocket engine
Cite
Citations (356)
The paper gives a way of internal ballistics design of nozzleless rocket motors,then analyses the effect of propellant motors' structure parameter to the performance of solid propellant rocket motor,and gives the research conclusion.
Solid-fuel rocket
Internal ballistics
Rocket (weapon)
Ballistics
Rocket propellant
Cite
Citations (0)
A one-dimensional model is formulated to simulate the interior ballistics of a solid propellent rocket motor, considering the mass, momentum and energy conservation equations, applied to a control volume. The model describes the transient ignition process, flame spreading and complete grain burning. The suitable selection of the numerical method allows an efficient solution, resulting in a very low computational cost that permits the use of a personal computer. Three steps are considered for modeling the ignition transient: induction, flame spreading and combustion chamber filling. The igniter is modeled by an assumed mass flow rate function, with time as the independent variable. For flame spreading calculation, the conservation equations are combined with a heat transfer model, which considers convection from the igniter gases and conduction through the propellant grain. In this way, the grain surface temperature evolution is calculated using a one-dimensional solution to the transient heat conduction equation. Flame spreading is evaluated using a critical temperature of the grain surface: each element of grain surface is assumed to start burning when its calculated temperature reaches the critical value. An outstanding feature of this model is the changing boundary conditions downstream of the nozzle. Initially, at the start of the ignition process, the zero-flow boundary conditions are set, simulating the nozzle plug. Later, when the plug expulsion pressure is achieved, the boundary conditions change to subsonic outflow. Finally, when the critical pressure is reached in the combustion chamber, boundary conditions turn into supersonic flow. Instability associated with the initial low Mach number flow is solved using an artificial diffusion term. Also included is the blowing effect of the gases generated on the propellant surface on the friction coefficient, and burning rate correlation considering erosive burning.
Internal ballistics
Solid-fuel rocket
Cite
Citations (0)
In order to increase pay loads in missile systems, research work in the domain of rocket propellants concentrates on conquering new, high-energy compositions providing a greater volume specific impulse. A short survey of rocket propellant development up to present days is followed by the most recent achievements in enhancing energy characteristics of existing compositions and in conquering completely new compositions of high-energy solid rocket propellants. .
Rocket (weapon)
Specific impulse
Solid-fuel rocket
Rocket propellant
High energy
Liquid-propellant rocket
Cite
Citations (0)
A φ0.8mm micro-solid propellant rocket array thruster for simple attitude control of a 10kg class micro-spacecraft was tested in vacuum. The micro-thruster uses boron/potassium nitrate propellant (NAB), because NAB has ignition temperature as low as 500°C, and easily start to burn in vacuum. For a half of the rockets, an ignition aid (RK) was also loaded. Ignition was succeeded in vacuum with NAB + RK and NAB. The maximum impulse thrust of 4.6 × 10-4 Ns, which is approximately a half of our requirement, was obtained with NAB. Compared to NAB, NAB + RK generated lower impulse thrust. The success rate of ignition was as low as 30%, although RK was used. These results suggest that RK has no benefit for the ignition of NAB, and other kinds of ignition aid should be found.
Solid-fuel rocket
Rocket (weapon)
Arcjet rocket
Rocket propellant
Cite
Citations (11)
Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.
Solid-fuel rocket
Rocket (weapon)
Spacecraft design
Space vehicle
Cite
Citations (6)