Cpropepweb an online computer program to calculate propellant performance in rocket engines. One of the goals of rocket engine hotfire testing is to directly evaluate engine performance for the purpose of validating analytical design. Theoretical analysis of a rotating two phase detonation in a. A computational program is developed to design the motor system structure, to predict the interior ballistics and the ballistic trajectory. Investigation of particle size effects on aluminized. This is done by coupling to a simplified inviscid flow model the fuel. Volume i of this report describes the engineering analysis which was used in developing this computer program. A mathematical and numerical model for the analysis of hybrid. A flexible, modular, fully automated, solid rocket motor performance prediction program has been developed. Except for the nonzero velocity in the oombustor, the oonditions of the analysis are the same as for the ideal rocket motor. David harris, moira todd, mackenzie humble, martin locklin. Nov 19, 2011 in this study, a twostage variable thrust and nontoxic 98%hphtpb hybrid rocket motor vthrm is designed and applied in a sounding rocket, and the design parameters of the motor are analyzed and optimized. The hybrid rocket performance code hrpc, programmed in matlab, is.
Preliminary prediction of srm performance can be achieved using numerical simulation of its internal ballistics 1 2. Initially, the model is designed as a simplistic ballistics model capable of predicting the pressure and thrust generated by a rocket motor from a given set of. Design and geometrical analysis of propellant grain. One of the goals of rocket engine hotfire testing is to directly evaluate engine performance for the purpose of validating analytical design parameters or flight worthiness. Xxx general the terrierorion rocket system is a two stage spin stabilized rocket system which utilizes a terrier mk 12 mod 1 or mk70 for the first stage and an improved orion motor for the second stage.
Nasa has given the solid propellant performance prediction and analysis. A mathematical and numerical model for the analysis of. Design tool for liquid rocket engine thermodynamic analysis is a computer program to predict the performance of the liquidpropellant rocket engines. Aluminum oxide particle size for solid rocket motor performance prediction. Procedures recommend by the jannaf performance standardization working group for liquid rocket engine performance prediction are presented. Richard nakkas experimental rocketry web site solid rocket motor theory propellant grain propellant grain the propellant utilized in amateur experimental rocket motors may be simple in composition, being comprised of two main constituents fuel and an oxidizer.
Subscale rocket enginemotor design, development and performance analysis manish mehta1, c. In this study, grain burnback analysis for 3d grain. Limit amplitude, triggering, and mean pressure shift article pdf available in physics of fluids 199 september 2007 with 275 reads. Parametric study and performance analysis of hybrid rocket. Model rocket project for aerospace engineering course. Jannaf rocket engine performance prediction and evaluation. There are two main factors need to be considered in the design selection and fabrication which are performance or processability and mechanical strength. Although in our basic model we introduced provides deep insight into the dynamics of the. The main objective of this technical paper is to demonstrate a capability which can predict the linear stability in a solidpropellant rocket motor using approximate stability analysis result which is based on. Casper college and ncsd students used the software to.
Technology development now focuses on determining how to ignite the engine in. In order to contribute in the understanding of solid propellant rocket engines, this work analyses the basic functioning of this type of motor and simulates its performance in the experimental rocketry field. Solid rocket motor performance prediction software is widely used to understand the ballistics internal flow of a solid motor. The solid performance program, spp12 is the latest version of the jannaf standard for performance predictions of solid propellant rocket motors srms. Good agreement is observed based on design prediction analysis and test data. Pdf out of various mode of failure of rocket motor, material failure is the main cause of concern. This work discusses the parameters which influence the performance of this motor. In this study, grain burn back analysis for 3d star grain geometries for solid rocket motor was investigated c. Based upon this the performance of the solid propellant rocket motor the design is done by considering the loads that are going to act on the solid rocket motor casing. Performance analysis of the ideal rocket motor, by martin summerfield. These codes have been integrated and modified, as required.
In order to contribute in the understanding of solid propellant. The main objective of this technical paper is to demonstrate a capability which can predict the linear stability in a solid propellant rocket motor using approximate stability analysis result which is based on spatial and temporal averaging of the equations for twophase flow. Metalized fuel hybrid rocket motor parametric study ah. In this study, a twostage variable thrust and nontoxic 98%hphtpb hybrid rocket motor vthrm is designed and applied in a sounding rocket, and the design parameters of the motor are. The aim of the present paper is to expose the performance simulation of a small sounding rocket that operates with a solid propellant motor. In this study, grain burnback analysis for 3d grain geometries was investigated. A critical analysis of solid rocket motor thrust augmentation using beamed power sean hammerland1 and barry cornella2 university of colorado at colorado springs, colorado springs, co 80933 with the.
Casper college and ncsd students used the software to design the q class motor used in the pathfinder rocket launch left. A model rocket is a small rocket designed to reach low altitudes e. Solid rocket motor performance analysis and prediction nasa sp8039 william h miller on. The terrier motor is 18 inches in diameter and is configured with 2. Modifications of the model for metal flame erosion and nozzle ablation. Theoretical analysis of hydrides in solid and hybrid rocket propulsion. Marshall technical reports server nasa space vehicle. Propellant tradeoff analysis for upper stage solid rocket motors performance.
Parametric study and performance analysis of hybrid rocket motors with doubletube configuration. Xxx general the terrierorion rocket system is a two stage spin stabilized rocket system which utilizes a terrier mk 12 mod 1 or mk70 for the first stage and an improved orion. Total reliance on correlations of firing data is undesirable, however, as their. The physical phenomena which govern the overall efficiency of a solid rocket motor are quite numerous and complex. Before that, the researcher has focus on the fundamental of solid rocket motor for designing and fabricating. This is volume 2 of a threepart report which describes a computer program for the prediction of solid propellant rocket motor performance. Prediction of longitudinal combustion instability in a solid. A critical analysis of solid rocket motor thrust augmentation using beamed power sean hammerland1 and barry cornella2 university of colorado at colorado springs, colorado springs, co 80933 with the efficiencies of current launch systems reaching their chemical limit, there is a need to investigate improved methods of placing payloads into orbit. The program, which has been given the acronym spp is based on six preexisting computer. An analysis is conducted to evaluate the influence of the growing injector holes.
Design and optimization of variable thrust hybrid rocket. A comprehensive empirical study investigates the performance of the proposed algorithm yielding satisfactory results. Theoretical analysis of a rotating two phase detonation in a rocket motor iwu shen t. The performance prediction of the solid rocket motor can be achieved easily if the burn back steps of the grain are known.
In the present work we develop a simplified model of the coupling of the hybrid combustion process with the complete unsteady flow, starting from the injector assembly and ending with the nozzle. Analysis of solid rocket motor grain design, ballistics, and combustion performance description spp consists of a series of modules that are integrated to provide a method to predict the average delivered performance, as well as mass flow, pressure, thrust, and impulse as functions of time. A computer program for the prediction of solid propellant. The program was validated through the comparison of predicted and measured performance parameters for a smallscale hybrid test motor. An informal history of liquid rocket propellants pdf. A theoretical and experimental comparison of aluminum as. We also study the motion of a flexible inhibitor and its effect on the gas flow near a joint slot in a section of a typical large solid rocket motor. The computer program described is referred to as the spp program. Space vehicle design criteria solid rocket motor performance analysis and prediction comment on this post cancel reply your email address will not be published. Solid propellant rocket motor performance prediction computer. The computer program described is referred to as the spp. The results of research aimed at improving the predictability of internal ballistics performance of solid propellant rocket motors srms including thrust imbalance between two srms firing in parallel are presented. Nasasp8039, solid rocket motor performance analysis and prediction, nasa space vehicle design criteria chemical propulsion, nasa washington, dc, united states, may, 1971, pp.
Solid rocket motor failure prediction modification of model. The motor guide automatically finds motors that fit into your rocket and does a quickanddirty flight simulation to give you an idea of how they would work. Design of solid rocket motor becomes an exigent task when accounting for chamber design, nozzle design, ballistic performance calculations as well as grain geometry and regression. I am submitting herewith a thesis written by derek damon farrow entitled a theoretical and experimental comparison of aluminum as an energetic additive in solid rocket. Kovarik3 nasa marshall space flight center, huntsville, alabama 35812 aaron dufrene4 and nathan solly5 cubrc inc. New rocket propellant and motor design offer high performance and safety.
Static test data from the first six space shuttle srms is analyzed using a computer program previously developed for this purpose. It is an accurate and reliable software package for predicting the motor chamber pressure as a function of time and the corresponding thrust levels. Based upon this the performance of the solid propellant rocket motor the design is done. The results of research aimed at improving the predictability of internal ballistics performance of solidpropellant rocket motors srms including thrust imbalance between two srms firing in parallel are. A computational tool for predicting hybrid rocket motor. A critical analysis of solid rocket motor thrust augmentation.
I am submitting herewith a thesis written by derek damon farrow entitled a theoretical and experimental comparison of aluminum as an energetic additive in solid rocket motors with thrust. Based upon this the performance the design is done by undertaking the loads that are acting on the solid rocket motor casing. An integrated approach for optimization of solid rocket motor. The method used was solid modeling of the propellant grain for predefined intervals of burnback. This work studies problems through simulations and tests. The stability history of a rocket motor during burning can be showed along the time. Both the static motor and flight motors were successful. Comprehensive theoretical and experimental investigations on parameters that affect the performance of hybrid motor have been carried out.
For this reason the prediction of solid rocket motor delivered performance has, historically, been empirically oriented. The hybrid rocket performance code hrpc, programmed in matlab, is segregated into two individual models. The program, which has been given the acronym spp is based on six preexisting computer codes. Introduction detailed 3d simulation of solid rocket motors requires. The university of michigan department of aerospace engineering ann arbor, michigan 48104 prepared for national aeronautics and space administration nasa lewis research center grant ngl 23005336 r. A theoretical and experimental comparison of aluminum as an. Variability in the performance of compositepropellant rocket motors. A mathematical and numerical model for the analysis of hybrid rocket motors. Solid propellant rocket motor performance prediction computer program spp analysis of solid rocket motor grain design, ballistics, and combustion performance. We also study the motion of a flexible inhibitor and its effect on the gas flow near a joint slot in. Marshall maintains current software versions an important capability for both ballistic design and analysis.
Fischbach, and joseph majdalanib department of mechanical, aerospace and. Solidpropellant rocket motor internal ballistics performance. Theoretical analysis of a rotating two phase detonation in. The university of michigan department of aerospace engineering ann arbor, michigan. The new rocket fuel and motor design adds a higher degree of safety by separating the fuel from the oxidizer.
A mathematical and numerical model for the analysis of hybrid rocket motors marius stoiadjeska,1,a. Solid rocket motor health management etdp ishm work for fy07. Subscale rocket enginemotor design, development and performance analysis manish mehta1. Variability in the performance of compositepropellant. Abstract design and analysis of propellant grain configurations for determination of the grain geometry which is an important and critical step in the design of solid propellant rocket motors, because accurate calculation of grain geometrical properties plays a vital role in performance prediction. The s olid rocket motor belongs to the family of the rocket engine thrust achieved by mass ejection and its history can be considered both ancient and recent. Solid rocket motor performance analysis and prediction nasa. Modeling of chamber flowfield of solid rocket motors. Solid propellant rocket motor performance prediction. A structural analysis is performed to verify the structural integrity of the solid rocket motor at certain working temperature. Abstract design and analysis of propellant grain configurations for determination of the grain geometry which is an important and critical step in the design of solid propellant rocket motors. High speed aerodynamics and jet propulsion, vol xii jet propulsion engines, liquid rocket engines chapter, pages 439460, princeton university press, 1959.
Prediction of longitudinal combustion instability in a. Solid rocket motor failure prediction introduction. As before, the subscripts i, c, th, and e refer to states at the injector end of the combustor, the hot end of the combustor, the nozale throat, and the nozzle exit. This work studies a doubletube hybrid rocket motor to improve regression rate. While there were many small rockets produced after years of research and experimentation, the first modern model rocket, and, more importantly, the model rocket motor, was designed in 1954 by orville carlisle, a licensed pyrotechnics expert, and his brother robert, a model airplane enthusiast. The spp12 nozzle module analyzes and summarizes the performance loss mechanisms into four categories. Fischbach, and joseph majdalanib department of mechanical, aerospace and biomedical engineering, university of tennessee utsi.