Digital Computer Simulation of the Performance Small Solid Propellant Rocket Motors
0
Citation
0
Reference
10
Related Paper
Abstract:
Abstract : A mathematical model of a small solid propellant rocket was programmed for use with a Univac Solid State 90 digital computer by means of Fortran I and Fortran II. In addition to calculating the pressure-time and thrust-time transients, the program computes time-averaged pressure, thrust coefficient, thrust, flow rate, and burning rate, as well as total impulse and specific impulse. The report includes the derivation of equations, the method of solution, the program in Fortran I and Fortran II, an example solution compared with experiment, and a recommended procedure for use of the computer program in the design and development of a small solid propellant rocket motor.Keywords:
Solid-fuel rocket
Rocket (weapon)
Rocket propellant
Solid-fuel rocket
Rocket (weapon)
Cite
Citations (0)
Abstract Rocket engines that use solid propellants are widely used in the commercial space flight industry for powering orbital-class launch vehicles and small research rockets. Thrust and the specific impulse developed by a rocket engine are essential properties of a rocket propulsion system, and it specifies the overall performance of a rocket. These properties heavily influenced by the burn-rate properties of the solid propellants. One of the many methods to improve the burn rate of the solid propellant is the addition of metallic powders into the fuel-oxidizer matrix. This technique has been observed to enhance the burn rate of the solid propellants; several studies have concluded the same. On the other hand, these additives result in the release of metal oxides into the atmosphere and lead to a higher amount of environmental pollution. This paper summarizes the effects of adding metals and their concentrations on the burning properties of the solid propellants.
Solid-fuel rocket
Specific impulse
Burn rate (chemistry)
Solid fuel
Booster (rocketry)
Rocket (weapon)
Ammonium perchlorate
Cite
Citations (7)
A simple method, which had been proposed by the authors to compute grain burnback during the operation of a solid-propellant rocket motor, is revisited. The method uses a fixed grid, which is imposed on the propellant grain. The intersection of the moving solid-gas interface with the grid is tracked and the burning surface is described using straight lines to compute the burning surface area and the port area. The revised version allows a more accurate tracking of the propellant regression than in the original method. The precision of the procedure is greatly increased by recording both the position and inclination of the solid-gas interface with respect to the grid lines, and the grain geometry is described using straight lines and circular arcs. Coarser grids can be used for the same expected error and the corresponding computing time is reduced. Improvements include the capability of handling surface merging and spatially dependent burning rates.
Solid-fuel rocket
Position (finance)
Solid fuel
Tracking (education)
Interface (matter)
Rocket (weapon)
Cite
Citations (1)
There are two major groups in solid propellants, the composite propellant and the double base propellant, used for rockets. The famous “Pencil Rocket” developed by Prof. Itokawa of Tokyo Univ. used double base propellant, that is made from nitrocellulose and nitroglycerine. Recently, composite propellants are widely used for large-sized solid rocket motors, since that have good burning property, good mechanical property, processibility, higher stability and long shelf-life. In this paper, some characteristics of composite propellants are briefly introduced.
Solid-fuel rocket
Rocket (weapon)
Rocket propellant
Cite
Citations (0)
Solid-fuel rocket
Rocket (weapon)
Cite
Citations (1)
Report describes proposed solid-propellant rocket motor. Case of motor integrated with propellant and burns and produces thrust as propellant combustion proceeds outward. Propellant and case manufactured together. Proposed motor increases payload-weight capacity.
Solid-fuel rocket
Payload (computing)
Rocket (weapon)
Liquid-propellant rocket
Cite
Citations (0)
Storage of rocket motors loaded with composite solid propellant for long periods may change the propellant properties, thus causing failure and affecting the safety during launch. In this study, an accelerated aging assay was carried out, in order to predict the useful lifetime and to evaluate variations on the propellant properties with time by means of thermal analysis (TG/DSC). The aging temperatures used were 65°C, and samples were withdrawn after 3 months. Aging was also carried out at room temperature. There was significant variation in the activation energy of the solid propellant samples thermal decomposition in the two kinetic methods used – Ozawa or model-free isoconversional method and Kissinger method – during the aging period. There was significant decrease of enthalpy of aged propellant enthalpy causing changes in ballistics parameters of the solid propellant grain affecting the rocket's performance.
Solid-fuel rocket
Rocket propellant
Internal ballistics
Energetic material
Rocket (weapon)
Ballistics
Accelerated aging
Cite
Citations (1)
1. Abstract This paper deals with performance test results of a new solid composite propellant based on GAP and Hydrazinium Nitroformate (HNF). This propellant delivers about 3,5% 9,3% higher performance (c*) than the best existing composite solid rocket propellant. Characteristics of ingredients and propellant formulations are presented together with the test results which demonstrate the increased performance compared to conventional high-performance propellants based on Ammonium Perchlorate (AP). The test equipment is being described as well as estimates of losses which occur in the test motor. This allows to estimate the expected performance in full-size rocket motors.
Ammonium perchlorate
Solid-fuel rocket
Rocket propellant
Rocket (weapon)
Cite
Citations (11)
The aim of this research is to examine the effects of propellant properties such as: combustion temperature, propellant density, characteristic velocity, reference burning rate and burning rate pressure exponent on internal ballistic performance of solid rocket motors. A zero dimensional internal ballistic solver is developed and internal ballistic performance analyses of solid rocket motors having slotted cross section are performed. Thus, different internal ballistic results such as maximum combustion pressure, burning time, specific impulse and total impulse are determined. Finally, variation of these response variables according to solid propellant properties are determined constructing different response surfaces. Graphical results represented in this work makes easier to select solid propellants for a certain kind of geometrical configuration.
Specific impulse
Solid-fuel rocket
Internal ballistics
Burn rate (chemistry)
Internal pressure
Rocket (weapon)
Ballistics
Cite
Citations (0)