From: cdorrough@nortonconsultants.com   
      
   "John"  wrote in message   
   news:quSLc.357$V75.33@newsfe4-gui.ntli.net...   
   > "Jonathan A. Goff"  wrote...   
   > > What are the current options for cryogenic propellant transfer on orbit   
   > (assume   
   > > LOX temperatures, not LH2 temps)?  Has anyone actually succesfully   
   > demonstrated   
   > > this?  Are there any options that look reasonably from a   
   > cost/mass/reliability   
   > > point of view?   
   >   
   > Depends on how you do it. Answers below for fuel are just as applicable   
   for   
   > oxident.   
   >   
   > Tank. If you transfer the entire tank then it's easy. Think of it as a big   
   > LNG canister.   
   >   
   >    
      
   This is method is not as silly as it might sound either - this technique is   
   already used world-wide for transporting messy or difficult substances.   
      
   Basically, an ordinary tank, manufactured complete with cryogenic sheathing   
   where necessary, including "dry-break" couplings, safety vents and whatever   
   instrumentation you might need, is installed in a standard-size frame and   
   replaces the existing _tank module_ when delivered - the empty is sent back   
   for refilling.   
      
   They are called "isotainers"...  And I, for one, cannot see any reason why   
   you couldn't use a similar system for on-orbit refuelling (of course you'd   
   still need an EVA to install it).   
      
   Cameron:-)   
      
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