Table B.8.

Tsiolkovsky Rocket Equation Calculations for Phase D1

D1: Crew to Lunar Surface (LS)	Step1	Step2
Vehicle	DE2	n/a
Init Mass (mt)	19.46	n/a
Final Mass (mt)	11.66	n/a
Prop (mt)	7.80	n/a
Isp (s)	450.50	n/a
ΔV (km/s)	2.26	n/a
Margin (mt)	0.26	n/a
Margin (boil-off days)	5.7	n/a

To Lunar Surface.

DE2 Prop available in LLFPO = 8.06 mt after 21 days boil-off LOX/LH₂ (loss = 0.95 mt).

Initial Vehicle Mass = AE1 (8.4 mt), DE2 (10.56 mt), and Payload (crew = 0.4 mt, tools 0.1 mt).

AE1 dry mass (4.0 mt) includes 2 xEMU suits (0.38 mt): additional 2 xEMU suits in DE1 payload.

DE2 final propellant after descent to LS = 0.26 mt, or 5.7 LOX/LH₂ boil-off days.

Note: Tug2DE2 could be used to help DE2 deorbit DE1 (requires Tug2DE2 RPOD with AE1+DE2, then Tug2DE2 pushes to lower lunar orbit and separates, then DE2 completes landing).