| T.R | Title | User | Personal
Name | Date | Lines |
|---|
| 417.1 | Names change? | SKYLAB::FISHER | Burns Fisher 381-1466, ZKO3-4/W23 | Wed Mar 23 1988 12:07 | 8 |
| Is anyone else surprised/confused at the names of the launch vehicles?
I had always believed that "Kosmos", "Vostok", "Soyuz", "Molinya",
etc were the names of payloads. Then suddenly a week or 2 ago I
started seeing these names attributed to boosters as well. Were
these names really considered to be boosters in the West for a long
time, or is it new?
Burns
|
| 417.2 | RE 417.1 | GAMERA::HUGHES | | Wed Mar 23 1988 15:10 | 32 |
| You are right that they are now applying payload names to launch
vehicles. This appears to done by the Glavkosmos organisation to give
the launchers 'sexy names' (sure beats Space Transportation System).
They have usually used the most well known payload name as the launch
vehicle name, although I don't know where Tsyklone came from. In the
case of Kosmos, it is meaningless as they call most everything Kosmos.
The DoD uses a simple number scheme, e.g. SL-4 is the Soyuz launch
vehicle, but it is based upon the time when the LV was first noticed by
the DoD. Fairly meaningless.
I prefer a scheme devised by the late Dr Sheldon for the Library of
Congress, of the form
X-n-x
where X sginifies the first stage(s), usually derived from a
weapon system
n indicates the version or generation of the upper stage
x indicates any added escape or manouvering stage
In this system, the Soyuz is the A-2. The A indicates it is derived
from the original Soviet heavy ICBM. The 2 indicates that the upper
stage is the second type to be used on the A booster. The Salyut
launcher is the D-1, the variant used to launch geosynch satellites is
the D-1-e since it has a transfer stage to carry the bird from parking
orbit.
Some time ago, I put together a list that correlated the letter series,
the DoD numbers and the Glavkosmos names. If there is interest, I can
type it in (no promises as to when).
gary
|
| 417.3 | Energia and Proton specs | VERGA::KLAES | Quo vadimus? | Wed Feb 23 1994 15:19 | 49 |
| Article: 83340
From: [email protected] (Dennis Newkirk)
Newsgroups: sci.space,sci.space.tech
Subject: Energia/Proton Specs
Date: Tue, 22 Feb 1994 16:25:24 GMT
Organization: Motorola
Sender: [email protected] (Net News)
From the International Reference Guide to Space Launch Systems
by Syeven Isakowitz, AIAA, 1991 ed. ISBN 1563470020, and Interavia 1992-3
Energia
Gross weight core 905000 kg + 4 x 350000 kg
Propellant core 820000 kg + 4 x 320000 kg
RD-170 Isp 309-337 s (Interavia 308-336)
RD-0120 Isp 354-452 s (Interavia 455)
Proton
1st
Gross 455600 kg
Propellant 410200 kg
Isp 285-316 s (Interavia 317)
2nd
Gross 165500 kg
Propellant 150000 kg
Isp 316 s (Interavia 327)
3rd
Gross 55600 kg
Propellant 50000 kg
Isp 316 s (Interavia 325)
4th (Block-D)
Gross 17650-19950 kg
Propellant 15000-17300 kg
Isp 351.8 s (Interavia 352 using Sintin)
Propellant difference on the Block-D must be due to the different
propellants reportedly used. LOX/Kerosene or the hydrocarbon Sintin
which I have yet to see explained.
Dennis Newkirk ([email protected])
Motorola, Land Mobile Products Sector
Schaumburg, IL
|
| 417.4 | RE 417.3 | VERGA::KLAES | Quo vadimus? | Thu Feb 24 1994 17:06 | 50 |
| Article: 83367
Newsgroups: sci.space
From: (Sidney M. Earley)
Subject: Re: Energia/Proton Specs
Sender: [email protected] (News Admin)
Organization: Martin Marietta Astronautics
Date: Wed, 23 Feb 1994 20:32:49 GMT
In article <[email protected]>,
[email protected] (Dennis Newkirk) wrote:
> (previous data deleted...)
>
> 4th (Block-D)
> Gross 17650-19950 kg
> Propellant 15000-17300 kg
> Isp 351.8 s (Interavia 352 using Sintin)
>
> Propellant difference on the Block-D must be due to the
> different propellants reportedly used. LOX/Kerosene or
> the hydrocarbon Sintin which I have yet to see explained.
>
> Dennis Newkirk ([email protected])
> Motorola, Land Mobile Products Sector
> Schaumburg, IL
I'd like to pass on some Block DM upper stage (Proton Launch Vehicle)
data provided to us by NPO Energia.
Propellant Load 15050 kg
Dry Mass w/ Equipment Bay 3350 kg
Dry Mass w/o Equipment Bay 2600 kg (payload must provide GN&C)
Engine Performance (LOX is the oxidizer)
Fuel Thrust (lbs) Isp(sec)
Synthin 19400 361
Naphtyl 18740 352
Fuel Characteristics
Fuel Description Density @ 20 deg C (g/cc)
Synthin Synthentic hydrocarbon 0.851
of the cyclopropane row
Naphtyl Product of oil fractions 0.836
----------------------------------------------------------------------
Sidney M. Earley | Martin Marietta Astronautics
Senior Systems Engineer | P.O. Box 179
(303) 977-8815 | Denver, CO 80201
----------------------------------------------------------------------
|