LUNAR EXPEDITION PLAN
LUNAR EXPEDITION PLAN
LUNAR EXPEDITION PLAN
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4.2.1 2<br />
c." 'ControlSystem"***' TJ5<br />
(1) Aerodynamic 600<br />
(2) Attitude 175<br />
d. Environmental Control 1530<br />
(1) Equipment Cooling 138<br />
(2) Structure Cooling 9^0<br />
(3) Cryogenic Storage ^52<br />
e. Landing Gear 700<br />
f. Instruments & Displays 200<br />
g. Electric Pover system 600<br />
h. Guidance & Navigation 400<br />
1. Communi cations 250<br />
J. Furnishing & Equipment 850<br />
(1) Seats fc Restraints 225<br />
(£) Decompression Chamber 175<br />
(3) Equipment Compartment 300<br />
(k) Miscellaneous 150<br />
k. life Support hoo<br />
1. Crew (3 men) 800<br />
m. Radiation 1200<br />
n. Abort System 3000<br />
Present re-entry and recovery techniques are outgrovths<br />
of the ballistic missile program utilising ballistic re-entry<br />
and parachute recovery. 3hey are not compatible vlth the<br />
velocities associated with re-entry from the moon, vlth controlled<br />
landing, or vith manned operation. Present engineering<br />
data associated vith high speed re-entry is not adequate for<br />
vehicle design.<br />
4.2.1.3<br />
A development-test program is required to obtain<br />
generalized data on re-entry phenomena and to test scale models<br />
WDIAR-B-456<br />
TMt tacmmmM anfalM taferRBtlan oHactlnj taa notional aah*M at ** Unitrf Slorti wiHlT* Hit naonhnj of tha Eipiannv* lovl, Tltk<br />
II. U.&X-, ftcttm 713 and TW. •*• trmiinliiiaa ar r***Ja1IeB af vliicli )n any Mannar ta an vnaafheiiiad awa h prohibited or la*.<br />
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