The Lunar Lander

The Lunar Lander

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Spacecraft Summary Weight Statement
Configuration: Apollo Lunar Module			Mass Property Section				Date: January 1969

Code	System (U.S. Custom: lbs & ft)	Item Or Module								Craft
		A		B	C	D		E	F	M
1	Aerodynamic Surface
2	Body Surface	1,042		978						2,020
3	Induced Envir. Prot.	342		328						670
4	Lnch Recov & dkg	50		480						530
5	Main Propulsion	469		1,113						1,582
6	Orient Control	344		13						357
7	Prime Power Source	369		573						942
8	Power Conv. & Dist.	464		67						531
9	Guidance & Navigation	78		43						121
10	Instrumentation	128		7						135
11	Communication	111		13						124
12	Environmental Control	291		97						388
13	Reserved Equipment	610		331						941
14	Personnel Provisions	98		53						151
15	Crew Sta. & Control	239		3						242
16	Range Safety & Abort
Subtotal Dry weight		4,635		4,099						8,734
17	Personnel
18	Cargo
19	Ordnance	26		26						52
20	Ballast
21	Residual Prop. & Serv. Item	120		270						390
Subtotal Inert Weight		4,781		4,395						9,176
22	Residual Prop. & Serv. Item
23	In flight losses	693		326						1,019
24	Thrust Decay Propellant
25	Full Thrust Propellant	4,979		17,334						22,313
26	Thrust Prop Buildup
27	Pre-ignition Losses


Total Gross Weight		10,453		22,055						32,508
Design Envelope (ft³)		750		850
Pressure Volume (ft³)		250
Design Envelope Surface Area (ft²)		550		550
Pressurized Surface Area(ft²)

Design g Max
Design Power Max (KW)
Design No. Man/Days										2/2

From the "Fundamental Techniques of Weight Estimating and Forcasting for Advanced Manned Spacecraft and Space Stations" by Willie Heineman, Jr.; NASA TN D-6349

A = Ascent Stage

B = Descent Stage

M = Manned Spacecraft

Early lunar lander technology, Leg operation

The Lunar Lander

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