Rocket Groups

Rocket Groups - – Energy conversion equipment...

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
CHEMICAL vs. ELECTRIC ROCKET PROPULSION CHEMICAL Always thermal Energy / propellant initially together Energy source is combustion Energy limited Best propellants, Ue ~ 4,500 m/s Isp ~ 100-500 s Thrust ~ 0.1 N-10 MN Propellant and Energy decrease with time High Thrust, Low Isp, High mdot, Fast a o , Short t burn Thrust independent of t burn t burn ~O(seconds) Earth to orbit missions, low V ELECTRIC Some are thermal (resistojet, arcjet) Some are non-thermal (ion, hall effect, MPD) Energy source / propellant separate initially Energy source onboard or external Solar, Nuclear
Background image of page 1
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: – Energy conversion equipment onboard (heavy) • ‘Unlimited energy’ – Very high Ue (10,000-100,000 m/s) – Isp ~ 1,000-10,000 s – Thrust ~ μ N-N • Propellant decreases with time • Energy remains constant with time • Low Thrust, High Isp, Low mdot, Slow a o , Long t burn – Thrust inversely proportional to t burn – t burn ~O(days-months-years) • Station keeping, deep space exploration, high ∆ V Origin of Thrust: Eject Stored Mass Backwards → Use Reaction Force to Propel Vehicle Rocket Equation is Always True...
View Full Document

This note was uploaded on 02/17/2012 for the course CHEM 212 taught by Professor Staff during the Fall '10 term at Rutgers.

Ask a homework question - tutors are online