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Exploring the Unknown: Selected Documents in ... - The Black Vault

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<strong>Explor<strong>in</strong>g</strong> <strong>the</strong> <strong>Unknown</strong> 533<br />

lunar rendezvous approach conta<strong>in</strong>s a number of features which tend to raise <strong>the</strong><br />

schedule confidence level; <strong>the</strong> most impor tant of <strong>the</strong>se are:<br />

(a) <strong>The</strong> Apollo vehicle, <strong>the</strong> lander, and <strong>the</strong> rendezvous experiment can<br />

all proceed on an <strong>in</strong>dependent parallel basis, thus avoid<strong>in</strong>g schedule con flicts;<br />

fur<strong>the</strong>r, <strong>the</strong> overall development is simplified because each vehicle has only a<br />

s<strong>in</strong>gle function to perform.<br />

(b) <strong>The</strong> lunar rendezvous approach permits complete system development<br />

to be done with C-l, which will be available and well developed, and makes <strong>the</strong><br />

entire C-3 picture exceptionally clean and simple, thus result<strong>in</strong>g <strong>in</strong> a m<strong>in</strong>imum<br />

cost program.<br />

In amplification of <strong>the</strong>se general remarks, <strong>the</strong> follow<strong>in</strong>g specific<br />

conclusions are drawn from <strong>the</strong> technical studies which are summarized <strong>in</strong> <strong>the</strong><br />

body of this report:<br />

A. Mission Approach and Schedul<strong>in</strong>g:<br />

1. <strong>The</strong> lunar rendezvous method requires only a s<strong>in</strong>gle C- 3 or C-4 launch<br />

vehicle. Earth orbital weights required for various system arrange ments are summarized<br />

<strong>in</strong> figure 1. (See also tables VI and VII later <strong>in</strong> <strong>the</strong> text.) [not provided]<br />

2. <strong>The</strong> lunar rendezvous method schedules <strong>the</strong> first land<strong>in</strong>g <strong>in</strong> March 1966.<br />

3. <strong>The</strong> lunar rendezvous method does not require that <strong>the</strong> Apollo vehicle<br />

be compromised because of land<strong>in</strong>g considerations.<br />

4. <strong>The</strong> lunar rendezvous method allows <strong>the</strong> land<strong>in</strong>g vehicle configura tion to<br />

be optimized for land<strong>in</strong>g.<br />

5. <strong>The</strong> lunar rendezvous method requires only C-l boosters for com plete<br />

system deve1opment.<br />

[2]<br />

6. <strong>The</strong> lunar rendezvous method provides for complete lander checkout<br />

and crew tra<strong>in</strong><strong>in</strong>g <strong>in</strong> <strong>the</strong> lunar land<strong>in</strong>g, lunar launch, and rendezvous dock<strong>in</strong>g<br />

operations on <strong>the</strong> actual vehicle.<br />

B. Fund<strong>in</strong>g:<br />

<strong>The</strong> lunar rendezvous method results <strong>in</strong> a program cost which will be less<br />

than <strong>the</strong> cost of o<strong>the</strong>r methods for <strong>the</strong> follow<strong>in</strong>g reasons:<br />

1. Requires fewer (20 to 40 percent) large boosters than o<strong>the</strong>r programs.<br />

2. Requires no Nova vehicles.<br />

3. Requires less C-3 or C-4 vehicles than o<strong>the</strong>r programs.<br />

4. Programs most flights on best-developed booster (C-1).

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