An Introduction to Rocket

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Presentation transcript:

An Introduction to Rocket MAE 4316: Propulsion An Introduction to Rocket Propulsion Systems

Types of launch vehicle propulsion systems Lesson Topics Some math Thrust, Impulse, Isp Types of launch vehicle propulsion systems Design considerations Launch Trajectories The Big Picture

Launch Trajectory

Rocket Propulsion MATH Take notes…

Liquid Rocket Engines A liquid rocket engine is a system that uses completely liquid propellants to produce thrust Advantages High Isp Throttle-able Stop and restart Reusable High density Isp (compared to gas storage) Disadvantages Low Thrust (compared to solids) Complex Cryogenic storage of propellants Safety

Liquid rocket engines are used for Launch vehicles Bipropellant systems Fuel Oxidizer Generates enough thrust Relatively high storage density High Isp allows reasonable propellant mass for ΔV required

Liquid Rocket Components

Solid Rocket Motors A solid rocket motor is a system that uses solid propellants to produce thrust Advantages High thrust Simple Storability High density Isp Disadvantages Low Isp (compared to liquids) Complex throttling Difficult to stop and restart Safety

Solid Rocket Motors Solid rocket motors are used for Launch vehicles High thrust (high F/W ratio) High storage density Ballistic Missiles Propellant storability Excellent aging Quick response storability high F/W ratio)

Solid Rocket Motor Components

Hybrid Propulsion Systems A hybrid propulsion system is one in which one propellant is stored in liquid (or gaseous) state while the other is stored in solid phase. Solid Propellant / Liquid (or gas) Oxidizer Most Common Solid Oxidizer / Liquid Propellant Less Common

Hybrid Advantages SAFETY: Literally no possibility of explosion Controllable Throttle Stop / Re-start Safe exhaust products Higher Isp than solids Higher density Isp than liquids Lower complexity than liquids Lower inert mass fraction than liquids

Hybrid Disadvantages More complex than solids Lower Isp than liquids Lower density Isp than solids Lower combustion efficiency than either liquids or solids O/F variability Poor propellant utilization Higher inert mass fraction than solids

Hybrid Schematic

Nuclear Thermal Propulsion (NTP) Nuclear Propulsion Nuclear Thermal Propulsion (NTP) System that utilizes a nuclear fission reactor Energy released from controlled fission of material is transferred to a propellant gas Fission Absorption of neutrons in a fuel material Excitation of nucleus causes fuel atoms to split Two new nulcei on average (Fission Fragments) High KE from release of nuclear binding energy Usually radioactive 1 to 3 free neutrons Necessary to keep reaction going Critical if each fission events leads to another Can be absorbed by reactor material or leak from reactor

Nuclear Propulsion ADVANTAGES High Isp (2-10x that of chemical systems) Low Specific Mass (kg/kW) High Power Allows High Thrust High F/W Use of Any Propellant Safety Reduced Radiation for Some Missions

A Nuclear/Chemical Comparison One gram of U-235 can release enough energy during fission to raise the temperature of 66 million gallons of water from 25oC to 100oC. By contrast, to accomplish the same sort of feat by burning pure octane, it would require 1.65 million gallons of the fuel

Nuclear Propulsion DISADVANTAGES: Political Issues Social Issues Low Technology Readiness Level (Maturity) Radiation issues (Shielding) High Inert Mass

Nuclear Propulsion Schematic Propellant Tank: Similar to tanks discussed for liquid propulsion systems. Tank can also be used as a radiation shield. Turbopump: Provides high pressure propellants to the heat exchange region of the propulsion system. Warm gas from regeneratively cooled nozzle drives the turbines. Radiation Shield: Protects the payload from radiation from the reactor by absorbing or reflecting neutrons and gamma rays.

Design Considerations Why does the Space Shuttle look the way it does?

Launch Trajectory

Launch Trajectory

The Big Picture Ballistic missiles and launch vehicles need large amounts of ΔV As inefficient as rockets are (low Isp), they are currently the only means by which high velocities (hypersonic) can be easily obtained