Liquid Rocket Engines for Spacecraft Pressure-Fed Propulsion Systems Training

Liquid Rocket Engines for Spacecraft Pressure-Fed Propulsion Systems Training

Introduction:

Liquid Rocket Engines for Spacecraft Pressure-Fed Propulsion Systems Training Course Description

Liquid Rocket Engines have been used to propel Earth orbiting satellites and deep space interplanetary missions for the last five decades.
This three-day course provides in-depth treatment of the fundamental concepts and technologies of modern spacecraft liquid propellant rocket engines. The course focuses on scientific and engineering foundations of pressure- fed, monopropellant, bipropellant, dual mode, and secondary combustion augmented thrusters for satellite orbit-raising and station-keeping operations. Thruster analyses; design; ground testing; flight operations; and lessons learned will be discussed in detail. Interactions of thrusters with the propulsion subsystem, and interfaces of the propulsion subsystem with other subsystems of spacecraft as they relate to the spacecraft overall design and operations will be discussed. The extensive set of course notes provides a concise reference for understanding virtually all aspects of modern spacecraft liquid thruster technologies.

Liquid Rocket Engines for Spacecraft Pressure-Fed Propulsion Systems TrainingRelated Courses:

Duration:3 days

Skills Gained:

• Fundamentals of
• Rocket Propulsion and Rocket Engines
• Flow-Pressure drop of liquids and gases in thruster valves and injector orifices
• Heat transfer in thrusters
• Developing thruster specification requirements
• Thruster Design and Analysis
• Developing thruster ground hot-fire test matrix
• Thruster hot-fire testing
• Thruster test data analysis
• Thruster flight and in-orbit operations
• Thruster EOL operation for optimum propellant life technical issues involved in the successful planning, design, development, fabrication, deployment and operation of space systems

Customize It:

With onsite Training, courses can be scheduled on a date that is convenient for you, and because they can be scheduled at your location, you don’t incur travel costs and students won’t be away from home. Onsite classes can also be tailored to meet your needs. You might shorten a 5-day class into a 3-day class, or combine portions of several related courses into a single course, or have the instructor vary the emphasis of topics depending on your staff’s and site’s requirements.

Course Content:

Introduction: Course Overview: History of liquid rocket engines; Evolution of liquid propellant rocket engines from Second World War

Rocket Engine Fundamentals and Definitions: Thrust, Impulse, Specific impulse, Impulse-bit, Thrust coefficient, Characteristic exhaust velocity, Catalytic decomposition, Combustion stoichiometry, Mixture ratio, Adiabatic flame temperature

Monopropellant Rocket Engines: Hydrogen peroxide (H2O2) thrusters, Hydrazine (N2H4) thrusters, Catalytic decomposition reactions, Catalyst degradation mechanisms (catalyst bed voids, Catalyst bed poisoning)

Early Bipropellant Rocket Engines: Early N2H4 / Nitric acid and Aerozine-50 / NTO bipropellant thrusters

Current Bipropellant Rocket Engines: Disilicide-coated Columbium and Ir/Re chamber, hypergolic MMH/NTO orbit raising thrusters (100-lbf to 900-lbf class) and orbit maintenance thrusters (2-lbf to 25-lbf class)

Future Dual Mode Rocket Engines: Disilicide-coated Columbium and Ir/Re chamber, hypergolic N2H4/NTO orbit raising thrusters (100-lbf class) and Platinum chamber orbit maintenance thrusters (5-lbf class)

Secondary Combustion Augmented N2H4/NTO Thruster (SCAT): Nickel chamber, ability to operate in both mono- and bipropellant modes

Bipropellant / Dual Mode Thruster Valves: Solenoid and Torque motor valves; Pressure actuated valves, Arc Suppressors, Valve testing (open/close response time; actuation cycles; flow-pressure drop, back-pressure relief feature, leakage, power, pull-in and drop-out voltage

Bipropellant / Dual Mode Thruster Injectors: Showerhead, Platelet and Pintle injectors, Radiatively- and Regeneratively cooled injectors, Injectors for fuel film cooled (FFC) chambers), Rupe number, D/V “contact” time, Injector core momentum angle, oxidizer versus fuel lead Hydraulic Flip Injector coupling to combustion chamber and its effects on dribble volume and post-firing thermal soakback, Oxidizer Boiling, FORP ZOT, Thermal stresses, Deposits, Injector water-flow testing for stream quality and pressure drop

Bipropellant/ Dual Mode Thruster Combustion Chamber Chamber materials and coatings, Chamber l/d ratio, Combustion instability, Thrust chamber burn-thru

Nozzles: Straight conical and bell-shaped nozzle configurations

Thruster Analyses: Steady state and pulse-mode performance, Startup & shutdown transients, Tail-off impulse, Thruster thermal analyses, Oxidizer boiling in injector orifices, Post-firing thermal soakback

Thruster Ground Hot-Fire Testing: Test cell vacuum (vacuum pumps versus steam jet ejectors), Vertical versus Horizontal (nozzle-down) firing, Propellant saturation techniques, propellant temperature conditioning techniques, thrust measurement system, Pulse-mode flow measurement techniques, Oxidizer/fuel biasing, Propellant, valve and injector temperatures, Chamber temperature measurement, single species depletion, Data acquisition system (instrumentation response and data sampling rate), Propellant feed system flow-?P, Propellant feed system coupling, Developing test matrix, Test facility error analysis

Spacecraft Flight Operations: Propulsion flight telemetry Propellant tank/ feed line pressures and temperatures, Valve and injector temperatures, Spacecraft dynamics parameters, Water hammer upon thruster valve closure, Single propellant species operation, Spacecraft end-of-life (EOL) de-orbit strategies

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Time Frame: 0-3 Months4-12 Months

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