Talk:Titan IIIC

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General Characteristics ordered wrongly?

The 'General Characteristics' is ordered by value:

E.g.

Power plant
Stage 1: --
Stage 2: --

Should it be ordered by:

Stage 1
Power plant: --

Engine: --

Scruce (talk) 12:49, 26 January 2012 (UTC)[reply]

I'm not sure about all this "order stuff" but first it should be recognized that a Titan III C had a Stage Zero which were the two UTCSD 120 inch diameter segmented (five segments plus forward and aft closures) solid rocket motors. They used nitrogen tetroxide as the "injectant" to deflect the exhaust plume to accomplish steering. The NTO was injected through 24 electro-mechanical valves (per motor), divided into 6 valves per "quadrant". These motors used PBAN propellant which was basically synthetic rubber, aluminum powder fuel and ammonium percholorate oxidizer. Stage One was ignited at altitude as the SRMs approached burnout. Stage One used an Aerojet LR 87 engine (consisting of 2 "sub-assemblies", hence the two nozzles) which burned hypergolic propellants (Aerozine 50 and nitrogen tetroxide). This engine had separate pumps for each sub-assembly and each propellant for a total of four pumps. The two turbine outputs were fed through a gear boxes to the pumps. Turbine outpur was something like 25,000 horsepower. The expansion ratio for these engines was slightly greater than if they had been ignited at sea level. Stage Two used an Aerojet LR91 engine with the same propellants as Stage One. The turbine/pump arrangement was similar to the Stage One with only one "sub-assembly". the expansion ratio for this engine was 40:1. For weight savings the nozzle had an ablative extension that was attached when the Launch Vehicle was erected at the launch site. The Upper Stage for the Titan III C was called Transtage. It used two Aerojet LR 138 engines with the same propellants as the other liquid stages. This Stage was unique in several ways; first, the propellant tanks were side by side instead of "stacked", second the engines gimbaled at the throat, not the head end (the injector end). The Guidance from the early 1970's until the next configuration Titan was introduced was a Delco Carousel set consisting of a gyro package and the Flight Control Computer. This particular configuration Titan Launch Vehicle was capable of a complete mission to GEO, unlike others that needed the spacecraft to have an AKM to circularize at the final synchronous orbit.

Number of first stage engines

There is a discussion at Talk:LR-87#Number of nozzles and Talk:LR-87#Affected articles that affects this article. Please discuss it there. Andrewa (talk) 23:41, 17 March 2014 (UTC)[reply]

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.

If no objections are received, the proposal will in due course take effect in this article. Andrewa (talk) 08:23, 26 March 2014 (UTC)[reply]

SRM used without defining it

The abbreviation SRM is used several times without first defining it. What does SRM abbreviate? Rv8 (talk) 10:27, 13 July 2015 (UTC)[reply]

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Edited Launch History

Instead of having "Successful" replaced with {{{{Success}}}} so it will turn green. Also did if there was a failure or a partial failure.

Like this
Success

If disagree with edits, please revert them. 04:12, 7 February 2019 (UTC)