Difference between revisions of "Rocket Engines"
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(Created page with " =Technology Roadmap Sections and Deliverables= ==Roadmap Overview== ==Design Structure Matrix (DSM) Allocation==") |
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==Design Structure Matrix (DSM) Allocation== | ==Design Structure Matrix (DSM) Allocation== | ||
==Roadmap Model Using OPM== | |||
==Figures of Merit== | |||
===Tsiolkovsky Rocket Equation (m/s)=== | |||
Δv = ve*ln(m0/mf) | |||
ve = effective exhaust velocity | |||
m0 = initial total mass including fuel and oxidizer | |||
mf = final mass without fuel and oxidizer | |||
===Specific Impulse (s)=== | |||
Isp = ve/g0 | |||
ve = average exhaust speed along the axis of the engine (either at sea level or vacuum) | |||
g0 = standard gravity in m/s2 | |||
===Net Thrust (N)=== | |||
Fn = M*Ve | |||
M = exhaust gas mass flow | |||
Ve = effective exhaust velocity | |||
===Thrust-to-weight ratio (N/kg)=== | |||
TTW = Net Thrust (N)/m (kg) | |||
m = dry mass of the engine | |||
Revision as of 16:14, 7 October 2019
Technology Roadmap Sections and Deliverables
Roadmap Overview
Design Structure Matrix (DSM) Allocation
Roadmap Model Using OPM
Figures of Merit
Tsiolkovsky Rocket Equation (m/s)
Δv = ve*ln(m0/mf) ve = effective exhaust velocity m0 = initial total mass including fuel and oxidizer mf = final mass without fuel and oxidizer
Specific Impulse (s)
Isp = ve/g0 ve = average exhaust speed along the axis of the engine (either at sea level or vacuum) g0 = standard gravity in m/s2
Net Thrust (N)
Fn = M*Ve M = exhaust gas mass flow Ve = effective exhaust velocity
Thrust-to-weight ratio (N/kg)
TTW = Net Thrust (N)/m (kg)
m = dry mass of the engine