Talk:Titan (rocket family)
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Titan 4 payload to GTO is about 13000kg, not 5800kg. That's the GEO payload. --Rnbc 00:07, 2005 Jun 16 (UTC)
Are you sure???
The current owners of the Titan line (Lockheed-Martin) decided to extend their Atlas family of rockets instead of the more expensive Titans, along with joint ventures to sell launches on the Proton and the new Delta IV class of medium and heavy-lift launch vehicles.
- But Delta IV prodused by Boeing. Lockheed-Martin produsing Atlas rockets. Is that a mistake? TestPilot 00:52, 20 January 2006 (UTC)
The link to the IUS infromation at Boeing is:
Cost of propellants
"The high cost of Hydrazine and Nitrogen Tetroxide proved too much" - this cannot be true. The cost of propellant is on the order of 1% of all costs associated with the launch. The toxicity and fire hazard of said components is most likely were more important in that decision.
does someone have infor to include on the Titan accident. A maintenance guy droped a wrench down the silo, this burst the fuel tank and threw the war head miles away causing an emergency search to recover the warhead. Saltysailor (talk) 14:42, 8 June 2008 (UTC)
Weaponized version of Titan III
I've read in a couple places that Titan III was considered for use as a heavy fractional orbital bombardment system, as in the following quote: "TheTitan 3A was basically a Titan II with an upper stage, but all subsequent launchers have stemmed from theTitan 3B configuration, which added a pair of large strap-on solid boosters. This was also seen as apotential weapons system, especially for FOBS and other special payloads, but development of aweaponized version did not go ahead." This is from a document found online titled "U.S. Nuclear Missiles: History and Guide to Resources." Has anyone seen anything similar, with verifiable sourcing? It might make a good addition to this page. Sacxpert (talk) 07:22, 28 October 2011 (UTC)
For Titan III, it says, “Their maximum payload mass was about 7,500 lb (3,000 kg).” This is inconsistent. 7,500 lb is about 3400 kg, while 3000 kg is about 6600 lb.--Solomonfromfinland (talk) 06:03, 19 July 2013 (UTC)
Number of first stage engines
This article is listed at [[Talk:LR-87#Affected articles as one of those affected by the proposal at Talk:LR-87#Consensus? to treat all variants of the LR-87 as a single engine with two nozzles. Please raise any objections to this there.
Required edits done . Neither of these sentences really assume the number of nozzles either way, but they could be taken that way. The edits are more of the nature of clarification than correction. Given the history of this particular question, it's important to be clear. Andrewa (talk) 16:33, 27 March 2014 (UTC)