A note on rocket performance comparison through impulse and thrust coefficients
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Specific impulse
Rocket (weapon)
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Abstract : The focus of this SBIR project was to develop and adapt existing computational methodologies for three-dimensional comprehensive analysis of ejection seat aerodynamics, including rocket plume effects. This Phase I study (6 months) focused on analyzing ejection seat rocket propulsion systems and developing techniques to solve for rocket plume flows within the ejection seat environment. Various methods were investigated for prescribing boundary and initial conditions for the seat rockets. The selected method utilizes a model that prescribes 3D nozzle exit boundary profiles extracted from detailed rocket nozzle calculations. Also, a multi-domain gridding method that allows for many-to-one interface meshing was developed and tested for efficient and accurate rocket plume resolution within the 3D ejection seat computational environment. Basic rocket plume model validations were made to a jet-in-axial and jet-in-crossflow problems. Excellent agreement was obtained for the jet-in-axial flow and reasonable agreement was obtained for the jet-in-crossflow. Validations were also performed for the Pintle Escape propulsion system rockets. Good agreement with test data was obtained for thrust levels obtained for various pintle positions. 3D ejection seat with rocket power calculations were also made to demonstrate the feasibility of the approach and the potential use of the model.
Rocket (weapon)
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The nozzle geometry affects the performance achieved by a solid propellant rocket motor to a great extent. In order to improve the development of a small home made solid propellant rocket motor these effects on performance from the nozzle geometry need to be understood. This thesis project involves the design of a small solid propellant rocket motor with materials readily available to a hobby rocket enthusiast. A specific investigation is then carried out into the effects that nozzle geometry has on the thrust and impulse performance of the rocket motor. The thrust-time profiles of the rocket motors are achieved by conducting a static firing in a cantilever beam thrust measuring apparatus. A secondary study is also done on these different nozzle geometries using computation fluid dynamics simulations to determine the predicted thrust performance. This also gives the advantage of visualizing the entire flow field and assists in identifying the features that drive the differences in performance. Overall this project develops a high performance nozzle geometry for use on a small home made solid propellant rocket motor as well as outlining various engineering issues involved with the development of a solid propellant rocket motor.
Solid-fuel rocket
Specific impulse
Rocket engine nozzle
Rocket (weapon)
Rocket propellant
Liquid-propellant rocket
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The thrust vector test of liquid rocket engine on satellite is a high and new technology.Based on the characteristics and measuring requirements of the thrust vector of the liquid rocket engine,the thrust parameter definition is elaborated and then the rotating table test principle and calculation method is introduced in this paper.
Liquid-propellant rocket
Rocket engine
Rocket (weapon)
Rocket engine nozzle
Table (database)
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Rocket (weapon)
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A numerical model for analysis of thermal and mechanical loads of a rocket motor has been developed. This model of a solid propellant motor corresponds to a short range, fast lunch and cruise type missile. It has been elaborated using the Finite Element Method (FEM) incorporated into commercial Comsol/M code. The experimental data on the thrust profile have been utilised to develop proper initial and boundary conditions for forgoing numerical calculations. The studies have been focused on the temperature and stress evolution within the case and nozzle section of the rocket engine. A special attention has been paid to the graphite insert of the rocket motor throat. The performed analyses proved effectiveness of the modelling methodology that will be applied to investigations of the modified motor performance.
Rocket engine
Rocket (weapon)
Rocket engine nozzle
Solid-fuel rocket
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Prediction of large rocket nozzle material performance using semiempirical technique, noting mathematical models for internal and external heat and mass transfer
Rocket (weapon)
Rocket engine nozzle
Solid-fuel rocket
Performance Prediction
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The effect of operation pressure on the specific impulse of tactical missile solid motors is analyzed from several factors, such as characteristic velocity, thrust coefficient, impulse coefficients of the chamber and nozzle. Two examples are provided for verifying the analyzed result. Finally, some suggestions and design principles are given for reference to relevant engineering design.
Specific impulse
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Rocket engine
Liquid-propellant rocket
Solid-fuel rocket
Rocket engine nozzle
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Specific impulse
Solid-fuel rocket
Rocket engine nozzle
Rocket (weapon)
Liquid-propellant rocket
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evaluating multidisciplinary optimization procedure. A multidisciplinary analytic model of a linear aerospike rocket nozzle has been developed; this model includes predictions of nozzle thrust, nozzle weight, and effective vehicle gross-liftoff weight. The contour of the aerospike nozzle has been designed for maximum thrust at one design condition. The aerospike geometry (length, base height, surface contour) and the structural (dimensions like tube radii and thickness) design parameters are computed to satisfy a structural constraints (displacement, stress and buckling). An Design optimization formulation has been implemented with a goal of minimizing gross-liftoff weight (GLOW). For this thrust and nozzle wall pressure calculations were made using CFD and were linked to structural FEA for determining nozzle weight and structural integrity. Calculations for specific impulse and engine thrust to weight ratio are executed to determine optimum vehicle liftoff weight. The Multidisciplinary analysis was integrated with an optimization procedure that allowed investigation of Multidisciplinary feasible strategy. This MDO result are compared with the separate aerodynamics & structural optimized design which shows the comparatively improvement over individual results. The Rocketdyne-developed F-1 engine is the most powerful single-nozzle liquid-fueled rocket engine ever flown. The RD-170 produces 11% more and the RD-171produces 20% greater thrust using a cluster of four combustion chambers and four nozzles. The M-1 rocket engine was designed to have more thrust, however it was only tested at the component level. The F-1 was a liquid-fueled rocket motor, burning RP-1 (kerosene) as fuel, and using liquid oxygen (LOX) as the oxidizer. Therefore I had take F1 as the reference engine.
Multidisciplinary design optimization
Specific impulse
Rocket (weapon)
Rocket engine
Solid-fuel rocket
Rocket engine nozzle
Optimal design
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