Mission Parameters Components Steered Planar ODL Combiner s/c 1821kg 182.1 Combiner Propellant △WRTm)=056 Collector S/C 871Kg 87.1k Collector Delay Lines 0.34R0 Collector Propellant AV/(n Ro Tfe)=1.55 Spacecraft Mass estimates from For each spacecraft initial Deep Space 3 (DS3)design · Determine△∨ Tfo 5 years Propellant mass from Rocket equation Ro=500 m(DS3-1000 m baseline) Place odl on collector s/c m Ease of operation mo-Propellant Mass(kg) Lower overall dry mass and nd-Spacecraft Dry Mass(kg) therefore, lower system mass sp -Specific impulse( sec) g-Earth's gravity (9.81 m/sec) Space Systems Laboratory Massachusetts Institute of TechnologySpace Systems Laboratory Massachusetts Institute of Technology Mission Parameters Mission Parameters Components Steered Planar ODL Combiner S/C 182.1 kg 182.1 kg Combiner Propellant - ∆V/(n2RoTlife) = 0.56 Collector S/C 87.1 kg 87.1 kg Collector Delay Lines - 0.34Ro Collector Propellant ∆V/(n2RoTlife) = 1.55 - Spacecraft Mass estimates from initial Deep Space 3 (DS3) design • Tlife = 5 years • Ro = 500 m (DS3 - 1000 m baseline) For each spacecraft • Determine ∆V • Propellant mass from Rocket equation 1 V exp −⎟⎟⎠⎞ ⎜⎜⎝⎛ ∆ = m I g md sp p mp - Propellant Mass (kg) md - Spacecraft Dry Mass (kg) Isp - Specific impulse (sec) Place ODL on Collector S/C • Ease of operation • Lower overall dry mass and therefore, lower system mass g - Earth’s gravity (9.81 m/sec)