LSC Room 103, LCCV, UPRCV

I just came across a set of faxed pages that apparently relate to
discussions that were going on in late April - early May 1987
about USG/USAF/NRO heavy lift requirements and how to satisfy them.
There's a fair amount of interesting, if somewhat disjointed,
material pertaining to projected launch rates, mission (24 - hour
period polar orbit was one of them), etc.

However, three or so questions:

The fax header on most of the pages (some have none) says "LSC ROOM
103" and is timestamped May 5, 1987. I'm guessing that LSC might
be "Lockheed Space Center".

Any old Lockheed hands around who might know what Room 103 was?
(I'll be so disappointed if it was just the mailroom.)

One page -- I'd further guess it's from a Lockheed document --
talks about existing and projected/proposed heavyish launch
vehicles and follows below the line. Insights into what LCCV and
UPRCV were supposed to be are solicited. I could imagine the LCCV
is an ancestor of Atlas V, but only a remote one.

These may be little more than examples of the infinite series
of SLV designs that have been done over the years, but they
were put forth in what seems to be a somewhat serious context.


------------------------------------

021A2/5.1.2.1.1/P1/MG 4:31 PM April 30, 1987

5.1.2.1.1.2 Specific Descriptions

Existing Launch Vehicles Group

Titan IV

[snip]

STS (Shuttle I)

[snip]

New Launch Vehicles Group

LCCV - The LCCV is an all expendable system for use in the
early '90s. It is a two-stage, series burn configuration and uses
a new methane/liquid-oxygen engine in the first stage with a
modified SSME In the second (core) stage. The core stage design
is jointly determined by the UPRCV, where it is used as the second
stage with a propulsion/avionics (P/A) module, and the LCCV
requirements in order to establish a common stage between the two
vehicles. A single engine is employed in the core stage fuselage.
Vehicle design reliability is .98. The vehicle profile, weights
and performance summary are shown in Figure 5.1.2.1-3.

[Alas, Figure 5.1.2.1-3 was not included.]

UPRCV - The UPRCV is a partially reusable, series-burn system
with an expected initial operational capability (IOC) In the late
'90s. It consist [sic] of two stages. The flyback booster stage
is twin-bodied (wing sections link the two fuselage sections)
whose design is jointly determined by the Shuttle II and UPRCV
requirements in order to have a common stage for these two
vehicle applications. The core stage is almost identical to the
LCCV (common core), with the exception of a reusable P/A module
using a LOX/LH2 engine (modified SSME). The booster engines use
LOX/CH4 and are designed for a life of 100 missions with two
overhauls. The booster stage will support an engine-out condition
without mission failure. The booster has turbojet cruise engines
contained in the forward wing to provide a limited crossrange
capability along with a single go-around capability prior to
landing. Booster recovery is automated with ground override
capability available for emergencies. Booster life is 200
missions. The entire vehicle has a mission reliability of .996.
The vehicle profile, weights and performance summary are shown
in Figure 5.1.2.1-4.

[Alas, 5.1.2.1-4 was not included.]