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original post by propulsion-engineering â» retirednavylookingforwork […]
engineerscientist 03
objective position in propulsion engineering focusing on design, analysis, and operation of spacecraft, launch vehicles, and their components while improving tools and enhancing engineering capability to increase efficiency, …
comment on bending mars by agatadev » comment on bending mars by …
original post by propulsion-engineering â» after june 2008 amaesi exminations, bishnujee’s message … […]
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original post by propulsion-engineering â» kerala […]
aircraft propulsion
aircraft propulsion is an engineering textbook written for students in aerospace and mechanical engineering. the book covers aircraft gas turbine engine and rocket propulsion from its basic principles to more advanced treatments in …
Section titles include design, formulas, general theory (resistance and slip, efficiency, strength of blades, etc.), pattern-making and molding issues, machining and finishing of blade surfaces, and concludes with a brief section on repairs by welding.
This text provides an introduction to the fundamentals of gas turbine engines and jet propulsion for aerospace or mechanical engineers. The book contains sufficient material for two sequential courses i propulsion (advanced fluid dynamics) an introductory course in jet propulsion and a gas turbine engine components course. The text is divided into four parts introduction to aircraft propulsion; basic concepts and one-dimensional/gas dynamics; analysis and performance of air breathing propulsion systems; and analysis and design of gas turbine engine components.
This is the Sixth Edition of the leading textbook on rocket propulsion for courses in aerospace engineering. It covers the basic physical principles of rocket propulsion such as nozzle thermodynamics, heat transfer, flight performance, and fuel chemistry. It also includes the design rationale of components such as nozzles, fuel chambers, structures, and control systems. All rocket types are covered, i.e., liquid, solid, hybrid fueled, and electric propulsion systems.
Rocket propulsion options for small-scale Mars missions are presented and compared, particularly for the terminal landing maneuver and for sample return. Mars landing has a low propulsive Äv requirement on a ~1-minute time scale, but at a high acceleration. High thrust/weight liquid rocket technologies, or advanced pulse-capable solids, developed during the past decade for missile defense, are therefore more appropriate for small Mars landers than are conventional space propulsion technologies. The advanced liquid systems are characterized by compact lightweight thrusters having high chamber pressures and short lifetimes. Blowdown or regulated pressure-fed operation can satisfy the Mars landing requirement, but hardware mass can be reduced by using pumps. Aggressive terminal landing propulsion designs can enable post-landing hop maneuvers for some surface mobility. The Mars sample return mission requires a small high performance launcher having either solid motors or miniature pump-fed engines. 
