Boeing capsule vs Lockheed lifting body CEV<br /><br />I'm sort of surprised at all the heat over capsules vs lifting bodies. If anything, I would think the most controversial aspect of the Lockheed CEV is the way it combines the equivalent of the command module and the service module into a single vehicle.<br /><br />The NASA requirements for the CEV is (among other things) the ability for direct return from Lunar orbit to Earth while keeping under 20 tons launch mass. From the cutaway views of the Lockheed CEV available it looks like the fuel for direct return is there. My WAG for the Lockheed CEV is 18 tons mass including 6 tons of stored rocket propellent.<br /><br />As far as the relative merits of the Lockheed design, yes the lifting body would have a higher development risk, but I think it would pay off in lower flight risk compared a capsule. For direct return to Earth, the superior crossrange of a lifting body would be a great advantage over a capsule. Unlike a spacecraft lingering in LEO, zipping in from the moon permits only one chance at reentry. And as for the lack of volume efficiency of a lifting body, the cylindrical + boxy shape Lockheed selected doesn't look much less efficient than the cone + cylinder shape of the Apollo CSM.<br /><br />I don't know what shape the Boeing design will take, but I have another WAG. Since Grumman and Boeing are partnered, with Grumman taking the lead for spiral one, I'm basing my guess on some artwork from Grumman material. The Boeing CEV is going to be nothing much more than a 4 man Soyuz, with the same solar power arrangement, the same orbital module, re-entry module, service module configuration and the same launch shroud.<br /><br />Not that there's anything wrong with that. The Soyuz is a very efficient design, much more efficient than Apollo ever was. So the Boeing design should encompass the virtues of light weight and conservative design.<br /><br />Bottom line on CEV -- Boeing's lightweight and low cost desig