Satellite Interrogator Database Satellite Information
@DATABASE AREA DESCRIPTIONS:
1- INTDES           International Designation
2- NAME             Satellite Common Name
3- CATNMBR               Satellite Catalog Number
4- COUNTRY               Country of ownership
5- LDATE            Launch Date
6- LSITE            Launch Site
7- ORBIT            Orbital Period
8- INCLINE               Inclination of the Spacecraft
9- APOGEE           Apogee of the Spacecraft
10- PERIGEE              Perigee of the Spacecraft
##
@HISTORY - U.S. POLAR ORBITING AND GEOSTATIONARY WEATHER SATELLITE
1-  The first U.S. weather satellite was launched on April 1, 1960,
TIROS 1.
2-  Weather satellite series ( POLAR ORBITING AND GEOSTATIONARY
SERIES ), TIROS, NIMBUS, ESSA, ATS, ITOS, TIROS-N (NOAA A-H ).
GOES.
Select the name of the Satellite Series for more information
@TIROS SERIES:   ( Television Infrared Observation Satellite )
Orbit: Polar 470 NMI
First launched April 1, 1960
Last of the series launched July 2, 1965
TIROS 1 through 10
270 lbs. total weight
42" X 19" Cylindrical in shape
Systems:  Low-resolution TV camera ( f 1.5 lens ) and
High resolution TV cameras ( f 1.8 lens )
the onboard systems did not change much during
this series except for lens types and Vidicon
tubes.
@NIMBUS SERIES: ( NIMBUS is Latin for cloud )
First launched August 28, 1964
Last of the series launched October 1978
NIMBUS 1 through 7
912 lbs. total weight to over 2000 lbs in later
satellites in the series
57" X 118 " 132" across the solar panels
Hexagonal main section
Systems:  This spacecraft was the first of the APT
( Automatic Picture Transmission)
AVCS ( Vidicon camera system ) for
daytime observations, HRIR ( High resolution
infrared radiometer ) for night time
observations.
@ESSA SERIES:   ( U.S. Environmental Science Services
Administration) also known as TOS ( TIROS
Operational Satellites ) from ESSA-3 on
Orbit: Polar 400 NMI
First launched February 3 1966
Last of the series launched February 26, 1969
ESSA 1 through 9
305 lbs to 320 lbs
22" X 42 " cylindrical 18- sided polygon
Systems:  APT, AVCS similar to the NIMBUS series
spacecraft
@ATS SERIES:    ( Applications Technology Satellites )
Orbit: Geostationary  2047 NMI
First launched on December 7, 1986
Last of the series launched May 30, 1974 with
ATS series satellites were the first
Geostationary weather satellites and carried
other experiments not weather related.
ATS 1 through 6
815 lbs to 3090 lbs on ATS-6
56" X 72" cylindrical
Systems:  Spin Scan Cloud Camera ( SSCC ) This satellite
returned the first photo of the earth covering
nearly the entire full disk (Stationary View)
on December 9, 1966
@ITOS SERIES:   ( Improved TIROS Operational System )
First launched on January 23, 1970
Last of the series launched on July 26, 1976
ITOS-1 through H ( NOAA 1 through 5 )
682 lbs to 750 lbs
40" X 48" with 14' solar panels, rectangular
Systems:AVCS, APT FPR ( Flat plate radiometer )
SPM ( Solar proton monitor)
@TIROS-N SERIES ( Television Infrared Observation Satellite )
First launched October 13, 1978 ( NOAA-6 )
Last of the series launched May 15, 1991
The NOAA class of satellite is the current
satellite in NOAA's polar orbiting program.
NOAA 6 through 12
3097 lbs
74" X 146" cylindrical in shape with a large
solar array at one end
Systems:  APT, AVHRR ( Advanced Very High Resolution
Radiometer ) SAR ( Search and Rescue ) SBVUV
( Solar Backscatter Ultraviolet Spectral
Radiometer ) MSU ( Microwave Sounding Unit )
SSU ( Stratospheric Sound Unit )
TIROS-N Notes:
APT transmissions are carried out on the 137 Mhz
band.  APT provides the direct read out user with
Visual spectrum daylight images of 4 Km resolution
along with normally 1 other channel of Infrared
spectral data.  Night time imaging provides two
channels of Infrared data.  HRPT ( High Resolution
Picture Transmission ) of 1.1 Km resolution is
available to the direct read out user on 1700 Mhz.
SAR ( Search And Rescue ) is a cooperative project
between various nation and provide data collection of
distress signal on 121.5 Mhz., 243 Mhz. and 406 Mhz.
ELT's ( Emergency Locator Transmitters) EPIRB
( Emergency Position Indicating Radio Beacons)
These transmitters are located on aircraft and ships
at sea.  Should a transmitter become active the data
recorded by the satellite contains user coded
information along with the location of the signal.
This data is the transmitted to ground stations who
notify rescue teams in the affected area.  This
system has to date found many downed aircraft and
provided locations of ships at sea that are in
trouble.
@GOES SERIES: ( Geostationary Operational Environmental
Satellite )
Geostationary 22,300 NMI
First launched October 16, 1975
Last of the series launched in 1987
GOES 3 through 7
1841 lbs
81" X 123" cylindrical in shape with solar
panels bonded to the entire exterior surface
Systems:  VISSR ( Visible/Infrared spin scanner
radiometer ( VAS ) WEFAX ( Weather Facsimile )
NMC ( National Meteorological Charts )
GOES NOTES:    The current GOES satellite is GOES-7.  This
platform is dying and plans for a new GOES-NEXT
are well under way with GOES 8 launched in April of 1994
Meteosat and the U.S. Government have worked out a lease
program for the use of a METS satellite which has been
moved over to provide western hemisphere coverage should
GOES-7 fail.  The MET satellite is now transmitting
normal WEFAX data to U.S. Ground stations. Due to on
board instruments on the MET series spacecraft VAS
transmissions are not available.
@OTHER METEOROLOGICAL SATELLITES
METEOR SERIES: ( Russian near earth observation satellites )
Meteor 2 series: Provide regular APT over the United
Meteor 3 series: Provide regular APT Visual and IR
FengYun Series: Chinese polar orbiting providing APT Visual
and IR along with HRPT data. The FengYun
series spacecraft have been plagued with
many problems with their instrumentation
and do not transmit on a regular basis.
Okean series:   Russian, ocean observation series numbered
1 through 3.  Transmit 3 types of APT
Visual, IR, Side Looking Radar.  This series
has not been heard from in this hemisphere in
over a year now, although reports from the UK
indicate that they are turned on over the
north pole during European passes.
COSMOS series:  Cosmos 1602 is the only known satellite
in the series transmitting APT.  This series
of satellite transmit APT in the same form as
the Okean series spacecraft.  Not much is
known about these transmissions. This spacecraft
has not been heard from since 1990.
GOMS series:    Russia is now building a Geostationary
platform for launch sometime next year.
This spacecraft will provide them with
data similar to our GOES series.  This
platform will also double as a communications
satellite.
GMS series:     Japan has placed into orbit their version of
our GOES Geostationary satellite. This satellite
provide them with WEFAX data.
METEOSAT series:Placed into orbit by the European Space Agency,
this spacecraft provides Europe with WEFAX data.
INSAT series:   Indian Geostationary satellite, Transmitting
WEFAX and doubles as a communications satellite.
@NORAD/NASA 2-LINE SATELLITE DATA
NORAD maintains general perturbation element sets on all resident
space objects.  These element sets are periodically refined so as to maintain
a reasonable prediction capability on all space objects. In turn, these
element sets are provided to users.
Space related telephone BBS around the country are posting current
Keplerian data.  The most recent element sets received from NASA/Goddard
Space Flight Center for several categories of satellites: Amateur Radio,
Earth Resources, Manned Spacecraft, Navigation, Weather, and NASA's 30 Day
Specials(which contain objects launched within the last 30 days and are often
easy to spot visually).  More specifically, these include the following
satellites or satellite series: OSCAR, Radio Sputnik, UOSAT, Cosmos, LandSat,
SeaSat 1, SPOT, Mir, Salyut 7, Soyuz, LDEF, US Space Shuttle, NAVSTAR (GPS),
GOES, Meteor, and NOAA.
These elements are be maintained in ASCII format in the file.  Data
for each satellite will consist of three lines in the following format:
AAAAAAAAAAA
1 NNNNNU NNNNNAAA NNNNN.NNNNNNNN +.NNNNNNNN +NNNNN-N +NNNNN-N N NNNNN
2 NNNNN NNN.NNNN NNN.NNNN NNNNNNN NNN.NNNN NNN.NNNN NN.NNNNNNNNNNNNNN
Line 1 is a eleven-character name. Lines 2 and 3 are the standard
Two-Line Orbital Element Set Format identical to that used by
NASA and NORAD.  The format description is:
Line 2
Column     Description
----------------------
01-01     Line Number of Element Data
03-07     Satellite Number
10-11     International Designator (Last two digits of launch year)
12-14     International Designator (Launch number of the year)
15-17     International Designator (Piece of launch)
19-20     Epoch Year (Last two digits of year)
21-32     Epoch (Julian Day and fractional portion of the day)
34-43     First Time Derivative of the Mean Motion (rev/day^2)
or Ballistic Coefficient (Depending of ephemeris type)
45-52     Second Time Derivative of Mean Motion (Blank if N/A)
54-61     BSTAR drag term if GP4 general perturbation theory was
used.  Otherwise, radiation pressure coefficient.
63-63     Ephemeris type
65-68     Element number
69-69     Check Sum (Modulo 10)
(Letters, blanks, periods = 0; minus sign = 1;
plus sign = 2)
Line 3
09-16     Inclination [Degrees]
18-25     Right Ascension of the Ascending Node [Degrees]
27-33     Eccentricity (decimal point assumed)
35-42     Argument of Perigee [Degrees]
44-51     Mean Anomaly [Degrees]
53-63     Mean Motion [Revs per day]
64-68     Revolution number at epoch [Revs]
All other columns are blank or fixed.
Example:
NOAA 6
1 11416U          86 50.28438588 0.00000140           67960-4 0  5293
2 11416  98.5105  69.3305 0012788  63.2828 296.9658 14.24899292346978
Note that the International Designator fields are usually blank,
as issued in the NASA Prediction Bulletins.  All epochs are UTC.
Satellites will be ordered by their NASA Catalog Number.  The
data file will be updated as soon as possible after receipt of
new element sets or whenever element sets are received for the
Space Shuttle.
@MEAN CLASSICAL ELEMENTS
Five independent quantities called "orbital elements" are
sufficient to completely describe the size, shape and orientation
of an orbit. A sixth element is required to pinpoint the position
of the satellite along the orbit at a particular time. The
classical set of six orbital elements are defined as:
1. a, semi-major axis, a constant defining the size of
the conic orbit.
2. e, eccentricity, a constant defining the shape of the
conic orbit.
3. i, inclination, the angle between the Z axis, i.e.
like the North Pole, and the angular momentum vector,
h = R X V, i.e. the vector R crossed with the vector V.
4. ê, longitude of the ascending node, the angle, in the
fundamental plane, between the Greenwich Prime
Meridian and the point where the satellite crosses the
fundamental plane in a northerly direction, (ascending
node).  This angle is measured counterclockwise when
viewed from the north side of the fundamental plane.
5. w, argument of periapsis, the angle, in the plane of
the satellite's orbit, between the ascending node and
the periapsis point, measured in the direction of the
satellite's motion.
6. T, time of periapsis passage, the time when the
satellite was at periapsis.
6a. Sometimes the time of periapsis passage is replaced
by the true anomaly, v, the angle, in the plane of
the satellite's orbit, between perigee and the
position of the satellite at the particular time, t0,
called the epoch.
* (To convert from T to v)
v = (360 deg) * t0 / T
6b. The NASA/NORAD element sets include the right
ascension of the ascending node (RAAN) instead of the
longitude of the ascending node but the conversion is
between the two is not hard to do.
Elements used for study
Mir
1 16609U          90272.82451929  .00046194  00000-0  56285-3 0  9636
2 16609  51.6113 162.6955 0026137 101.1206 259.2727 15.59612888264453
From the example 2-line elements for Mir the epoch is;
9-29-1990 @ 19.78846296 UTC (19h 47m 18.4666s).
The GST for that date and time is 305.1334 deg..
From the elements the RAAN is 162.6955 deg..
Therefore:
Longitude = RAAN - GST
-142.4379 = (162.6955 - 305.1334)
The sharp reader will notice that the NORAD elements do NOT
include the semi-major axis, a. It is possible to calculate the
semi-major axis with the data in a NORAD elements set. The
approach would be;
1. Convert the mean motion into degrees per second.
and calculate the time to complete one orbit, this
will be called the period.
2. Using the period and the earth's gravitational
constant, mu, the semi-major axis can be calculated.
(equations used)
xn_s = (mean motion * 360)/86400
per  =  360/xn_s
a    = ((per^2 * mu)/(4*ã^2))^(1/3)
mu = 3.986012E+14 m^3/sec^2.
The starting point for the study of motion of one body orbiting
another, such as an artificial satellite about the earth, is
always the two-body problem; i.e., two point masses attracted to
each other according to Newton's Law of Universal Gravitation,
the inverse square law. The solution is well-known; the two
bodies move about each other in conic sections. For bounded
motions, such as those of an earth satellite, this conic is
either a circle or an ellipse.
The problem can be formulated in different ways, but is always
convenient to chose a coordinate system with the origin centered
at one of the bodies. The position of the second body then can
be specified, for example, by giving its initial Cartesian
position and velocity coordinates and then integrating the
equations of motion to find the future positions and velocities.
The Cartesian system is not the most convenient one in which to
represent the motion because an analytic solution cannot be
obtained and the integrations must be done numerically.
By adopting a polar coordinate system, one is able to effect an
analytic solution referred to above which can be specified in
terms of six constants of motion; five orbital elements,
a,e,i,w,ê and the time of pericenter passage T. The last
constant can be, and usually is, replaced by the mean anomaly M
which is a linear function of time. This is a very convenient way
to specify the initial position and velocity of a satellite and
it also allows an easy visualization of the motion. The position
and velocity of the satellite at any future time can be
specified in terms of these six constants, a,e,i,w,ê,M and
time.
In realistic applications, such as artificial satellites about
the earth, there are forces acting on the satellite in addition
to the inverse square force although this is the dominate one.
Other gravitational forces are due to distant bodies such as the
moon and sun but the principal additional gravitational forces
are due to the non-sphericity of the earth. All of the
gravitational forces are conservative and can be represented by
a potential function. In addition to these extra gravitational
forces, there are non-conservative forces such as atmospheric
drag. All of these forces other than the inverse square force
are called perturbations. The prediction of motion considering
these additional forces is called Perturbation Theory.
The orbital elements, constant for pure two-body motion, become
slowly varying functions of time when the perturbations are
considered. Differential equations describing the time rates of
change of the elements are called the Lagrange Planetary
Equations, LPE and can be found in any standard book on
celestial mechanics. Considering conservative forces only, which
can be represented by a potential function, the part of the
potential other than the two-body part is conventionally called
the disturbing function, represented by R, and the LPE are:
.
a = 2 / n a * ( ëR / ëM )
e = (-(1-eý)^« / naýe)*ëR/ëw+(1-eý/naýe)*ëR/ëM
i = cot i/(naý(1-eý)^« * ëR/ëw - ëR/(ëênaý(1-eý)«)
w = (1-eý)^« * ëR / naýeëe - cot i * ëR/(naý(1-eý)^«)*ëi)
ê = ëR/(naý sin i *(1-eý)^«) * ëi)
M = n - 2ëR/naëa - 1-eý * ëR/(naýe * ëe).
* where ë is the partial derivative
starting from the very simple representation of the gravitational
potential between two point masses of magnitude m0 and mi
separated by distance r as;
V = -G * (m0 * mi)/r
one can, by applying this to a satellite of mass m0 and to every
infinitesimal mass point mi of the earth and integrating over the
whole earth, arrive at the following potential function for the
earth;
ì                   n ì              n    m
V=-æ/r(1-ä JnPn (sinë)(re/r)^ +ä ä Jnm (re/r)^  Pn^ (sinë)cos(m(à-à))).
n=2                     n=2m=1                             mn
The first term is the one giving pure two-body motion and the
additional terms are the perturbing terms. The first sum, zonal
harmonics, represents the flattening and other distortions
relative to the equator and the second sum, tesseral harmonics,
represents the non-uniformity of the earth in longitude. If, as
is frequently done, one assumes that the earth possesses
rotational symmetry, then the second sum vanishes. The neglect of
the second sum usually produces no noticeable effects except in
the case of geosynchronous satellites. Then one must consider
those terms which cause slow long-period drifts of the
geosynchronous position.
For close earth satellites one can usually take about three terms
from the first sum and get very accurate results; even the first
term alone will produce very satisfactory results in most cases
for short-time periods.
The Jn are constants which depend on the mass distribution in the
earth and are deduced from analysis of observed satellite
motions.
-3
J2 = 1.082616 X 10
-6
J3 = -2.53881 X 10
J4 = -1.65597 X 10  .
The Pn (sin ë) are Legendre polynomials of index n and are even
functions of sin ë for n even and odd functions for n odd. The J2
term describes the flattening of the earth and the J3 term the
so-called pear shape. J2, which is three orders of magnitude
larger than J3, gives rise to secular changes in the elements w,
ê, and M while J3 gives rise to long_period oscillations in e and w.
In general, even harmonics cause long-period and secular changes
in the elements, and odd harmonics cause long-period
oscillations.
Short-period oscillations can result from all terms; but since J2
is so much larger than the other coefficients, generally only the
J2 short-period terms are considered. Secular terms are those
which monotonically increase or decrease with time. For first
order solutions this change with time is linear. Long-period
terms are those which oscillate with a period of typically one to
two months, and short-period terms are those which oscillate with
a period of one orbital period or some rational fraction of it.
To finish formulating the problem, the disturbing function is
expressed in terms of the orbital elements and then the
appropriate partial derivatives are taken and substituted into
the LPE. One then has a coupled set of first order non-linear
ordinary differential equations. Because they are non-linear, they
can be solved only by various approximation methods. The usual
method is to assume that the solutions can be represented in some
type of power series expansion in a small parameter and arrive at
sets of approximation equations which can be a close
representation of the real motion, at least over short-time
periods.
The complete solution consists of the sum of the secular terms,
short-period terms, and the long-period terms; i.e.,
a    = a  +  a  +  a
osc    s     sp    lp
@MODELS FOR PROPAGATION OF NORAD ELEMENT SETS
NORAD maintains general perturbation element sets on all
resident space objects.  These element sets are periodically
refined so as to maintain a reasonable prediction capability on
all space objects.  In turn, these element sets are provided to
users.
The most important point to be noted is that not just any
prediction model will suffice.  The NORAD element sets are "mean"
values obtained by removing periodic variations in a particular
way.  In order to obtain good predictions, these periodic
variations must be reconstructed (by the prediction model) in
exactly the same way they were removed by NORAD.  Hence,
putting NORAD element sets into a different model (even though
the model may be more accurate or even a numerical integrator)
will result in degraded predictions.
All space objects are classified by NORAD as near-Earth (period
less than 225 minutes) or deep-space (period greater than or
equal 225 minutes). Depending on the period, the NORAD element
sets are automatically generated with the near-Earth or deep-
space model.
@TELEPHONE BBS's-Obtaining Current Keplerian Data
The following telephone BBS's post current Keplerian data as it becomes
available.
MAPS-NET BBS                            The Barter Board
Hampstead, Maryland                      Baltimore, Maryland
SYSOP: Charles Davis                    SYSOP: Thom LaCosta
410-239-4247                            410-239-4247
24 Hours, 2400/9600/14.400              24 Hours, 2400/9600/14.400
8bit NO parity 1 stop                   8Bit NO parity 1 Stop
Celestial RCP/M                         Datalink RBBS System
Fairborn, Ohio                          Dallas Remote Imaging Group (DRIG)
SYSOP: Dr, T.S. Kelso                   Dallas, Texas
513-427-0674                            SYSOP: Dr. Jeff Wallach
24 Hours, 9600/2400/1200                214-394-7438
8 Bit NO parity 1 stop                  24 hours, 14.400/9600/2400/1200
8 bit NO parity 1 stop.
RPV BBS
Rancho Palos Verdes, Ca.
SYSOP: Dave Ransom Jr.
310-541-7299 or 310-544-8977
24 hours, 14.400/9600/2400/1200 baud,
To obtain the elements from the DATALINK BBS and MAPS-NET BBS, (with
the least amount of trouble), just dial up the BBS and login. The
next step is to step is to type "D", for download and then type
" BULLET90 " as the file to download, open an ZMODEM file transfer
mode with your telecommunications software.  (The file name is
always called BULLET90 ) This will transfer the  NASA 2-line
elements to a file on the users computer. The downloading of
BULLET90 should take about 2 minutes at 2400 baud.
NOTE
Files downloaded from other BBS's other than DATALINK will have some
characters at the top of the  file that will need to be removed with
a word processor ( PC-Write, Edlin etc. works very well).
The keplerian data must be saved in a pure ASCII file format. Saving
the Data in and ASCII format insures that all of the data will be
read into your tracking program with out errors.
EXAMPLE: CURRENT ELEMENT SET 123  <- Remove this data
@NASA BBS - OBTAINING ELEMENTS
The following is a partial extract from the notice sent out by
the NASA Goddard Space Flight Center's Orbital Information Group.
Interested users should write to the address given and request
access to the RBBS; include your full name and address with your
request.
The NASA OIG RBBS has four lines operating in rotation. A modem
and software is required to download data. The RBBS operates at
2400/1200/300 baud. You MUST write for access and password; you
cannot call and log on without having first received that
information by mail from NASA OIG!
******************
* IMPORTANT NOTE *
Note that the format used on RBBS for two-line orbital elements
is slightly different from that required by programs like
TRAKSAT, INSTANTRAK, and SDSTRAK.  Several programs are "in process"
to simplify conversion to the standard format and  are posted on
the above listed BBS's . One such program is called ORBITEL and can
be found and ELEMAN.ZIP.
For some time the Orbital Information Group's Reports and
Information Dissemination (RAID) section has been developing an
electronic bulletin board as a way to reduce our cost of
providing orbital elements to users worldwide, in addition to
providing mail users with an around-the-clock way to obtain the
latest two-line element set iteration.
Development and enhancement of the electronic bulletin board is
completed, and activation was on September 16, 1991. The official
name of the RAID Bulletin Board System is RBBS. Effective
immediately, ALL USERS ARE ENCOURAGED TO USE THE RBBS INSTEAD OF
THE MAIL SERVICE.
Those who use the service and find it serves their needs or is an
acceptable alternative to the slower and more costly mail
service, should advise us to drop them from mail distribution.
This may be done by advising the RBBS SYSOP or by sending a
letter. Users may not continue to use the RBBS and to receive
mail service.
The RBBS permits users of our NASA Prediction Bulletins and Two-
line Orbital Elements (TLE's) access to the latest element set
provided to us, avoiding the mail delay, in addition to allowing
a user the flexibility of accessing the two-line element set of
choice. One may obtain the latest two-line element set iteration
around-the-clock from anywhere in the world, via telephone modem.
Correspondence regarding this service should be sent to:
NASA Goddard Space Flight Center
Project Operations Branch/513
Attn: Orbital Information Group
Greenbelt, MD  20771
USA
The RBBS is updated with revised TLE's on the following schedule:
Monday       TLE's revised between 12:00 GMT Friday and 12:00 GMT
Monday.
Wednesday    TLE's revised between 12:00 GMT Monday and 12:00 GMT
Wednesday.
Friday       TLE's revised between 12:00 GMT Wednesday and 12:00 GMT
Friday.
Should a holiday fall on a day that the RBBS is scheduled to be
updated with the latest TLE's, updating will be done on the next
Monday through Friday working day.
@VISUAL SIGHTING OF SPACECRAFT
Below is a list of some satellites that are "good hunting" for
the optical users. (First timers should look for the smallest
magnitude satellites, i.e., Mir, Kvant-1, HST.)  Use of your
tracking program along with current Keplerian data is a must
when looking for visible satellites.
Norad      Vis     Satellite Name
ID#        Mag*
00694      3.0     Atlas Centaur 2
01001      3.3     Transtage 3
01359      3.3     Transtage 4
03598      3.0     OAO 2 R/B
04597      3.3     Cosmos 374 R/B
04622      3.3     Cosmos 375 R/B
04786      1.9     Cosmos 382
04966      2.3     Cosmos 398
05994       .9     Pageos
06155      3.0     OAO 3 R/B (Copernicus R/B)
06212      2.7     1972-076A Radcat
06779      3.0     IntelSat 4 F-3 R/B
08074      1.6     Pageos 1 DEB (Pageos H)
10967      3.0     SeaSat 1
12054      2.4     Cosmos 1220
12069      3.0     FltSatCom 4 R/B
12363      3.0     Comstar 4 R/B
12445      3.0     IntelSat 5-2 R/B
12465     -1.6     Cosmos 1271 R/B
12497      3.0     IntelSat 5-1 R/B
13007      3.0     IntelSat 5-3 R/B
15423      2.5     KH 11-6
15772      2.9     Cosmos 1656 R/B(4)
16182      2.5     Cosmos 1697 R/B
16609      -.4     Mir Space Station
16615      3.2     Spot 1 R/B
16910      2.8     EGP/JAS-1 R/B
17358      2.9     Cosmos 1603 R/B(4)
17369      3.3     Cosmos 1818
17528      3.1     MOS-1 R/B
17590      2.5     Cosmos 1833 R/B
17845      -.4     Kvant-1 (part of Mir)
17974      2.5     Cosmos 1844 R/B
18187      3.3     Cosmos 1867
18441      2.5     KH 11-7
19120      2.5     Cosmos 1943 R/B
19274      3.3     Okean 1
19460      3.3     USA 32
19461      3.3     USA 32 R/B
19625      2.5     KH 11-8
19650       .7     Cosmos 1980 R/B
19671      1.8     Lacrosse
19911      2.7     Delta Star
20147      2.4     Cosmos 2033
20261      3.3     In-Cosmos 24
20322      1.8     Cosmic Background Explorer
20335      -.4     Kvant-2 (part of Mir)
20443      3.1     Spot 2 R/B
20491      3.1     MOS-1B R/B
20516      2.0     USA 53
20523      3.0     IntelSat 6-3
20525      2.4     Cosmos 2060
20580      -.8     Hubble Space Telescope (HST)
20625      2.5     Cosmos 2082 R/B
20635      -.4     Kristall Module (part of Mir)
20638      3.2     ROSAT
20683      3.2     Gamma
20765      2.4     Cosmos 2096
20963      2.0     USA 67 (STS-38 Payload)
20985      2.4     Cosmos 2107
21015      2.5     Cosmos 2112 R/B
21065      2.4     Cosmos 2122
21147      1.8     Lacrosse 2
21148      2.9     Lacrosse 2 R/B
21213      2.2     Almaz 1 radar spacecraft
21225      2.8     Gamma Ray Observatory (GRO)
21311      -.4     Soyuz TM-12 (part of Mir)
21610      3.1     ERS-1 R/B
21638     -1.1     STS-43 (landed)
21653      3.0     Intelsat-6
21662      -.4     Progress M9 (part of Mir)
21700     -1.1     STS-48 (landed)
* This magnitude is an approximation, it assumes 75% illumination
of the satellite and 900 Km slant range.
@SOURCE
This is the source of the payload.  Usually, the source of the payload is
the same as the source of the launch, but not always.  For instance, the US
launches payloads for many other countries and organizations (e.g., NATO or
ESA).
ARGENT        Argentina
AUSTRL        Australia
BRAZIL        Brazil
CANADA        Canada
CZECH         Czechoslovakia
ESA           European Space Agency
ESRO          European Space Research Organization
FRANCE        France
FR/FRG        France/Federal Republic of Germany
FRG           Federal Republic of Germany
IMSO          International Maritime Satellite Organization
INDIA         India
INDNSA        Indonesia
ISRAEL        Israel
ITSO          International Telecommunications Satellite Organization
ITALY         Italy
JAPAN         Japan
KOREA         Korea
LUXEMB        Luxemburg
MEXICO        Mexico
NATO          North Atlantic Treaty Organization
NETH          Netherlands
PAKIST        Pakistan
PORTUG        Portugal
PRC           People's Republic of China
SAUDI         Saudi Arabia
SPAIN         Spain
SWEDEN        Sweden
THAI          Thailand
UK            United Kingdom
US            United States of America
USSR          Russia
@LSITE
This refers to the launch site from which the object was launched.  As of
today, there are currently 18 launch sites around the world.  The codes
and their meanings are:
AFETR         Air Force Eastern Test Range, Florida, USA
(Cape Canaveral)
AFWTR         Air Force Western Test Range, California, USA
(Edwards Air Force Base)
CHINA         Chinese Launch Complex, PRC, China
(Xchang)
FRGUI         French Guiana
(French Guiana)
HGSTR         Hammaguira Space Track Range
KSCUT         Kagoshima Space Center - University of Tokyo
(Japan)
KYMSC         Kapustin Yar Missile and Space Complex
(Russia)
PLMSC         Plesetsk Missile and Space Complex
SCMTR         Shangchengtze Missile Test Range, PRC
(China)
SRILR         Sriharikota Launching Range
(India)
SNMLP         San Marco Launch Platform, Indian Ocean
(Kenya)
TANSC         Tanegashima Space Center
TYMSC         Tyuratam Missile and Space Center, Kazakhstan
WLPIS         Wallops Island
(Virginia, USA)
WOMRA         Woomera
(Australia)
WUZLF         Wuzhai Launch Facility, PRC
XICLF         Xi Chang Launch Facility, PRC
YAVNE         Yavne Launch Facility
(Israel)
@ORBIT(s)
EARTH ORB             Earth Orbit (Geocentric)
SOLAR ORB             Solar Orbit (Heliocentric)
LUNAR ORB             Lunar Orbit (Selenocentric)
MARS ORBT             Mars Orbit  (Areocentric)
VENUS ORB             Venus Orbit
BARYCNTRC             Barycentric Orbit
SS ESCAPE or SSET     Solar System Escape Trajectory
CENM                  Current Elements Not Maintained
ELNA                  Elements Not Available
@SEARCH
Record: 000001                                                          05/26/9
ÚÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ¿
³             Satellite Data Base View Menu            ³
³------------------------------------------------------³
³                                                      ³
³        International:  1963 001A                     ³
³        Catalog Number:   521                         ³
³        Satellite:      SPUTNIK 25                    ³
³        Country Owner:  USSR                          ³
³        Launch Date:    04 JAN 63                     ³
³        Launch Site:    TYMSC                         ³
³Decay     Orbital Period Inclination  Apogee  Perigee ³
³05 JAN 63      88.0         64.6         189     165  ³
ÀÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÙ
EDIT/VIEW:  Delete   Edit   Find   Goto   Locate
Next-record   Previous-record   Return
FINDING SOMETHING
Let's assume we want to find a satellite with the name of TIROS.
Simply choose F for find...you'll see a selection of search index names
SET INDEX:  1-INTDES  2-NAME  3-CATNMBR  4-COUNTRY  5-LDATE  6-LSITE  7-ORBIT
8-INCLINE  9-APOGEE  10-PERIGEE
Since we are attempting to find the Name TIROS, select number 2, and then
enter TIROS as the name.  SATINIT will find the first name that matches
TIROS and display the information for you. At the bottom of the screen you'll
see:
You may then select 'N' for the next TIROS, P for the previous TIROS or any
of the other commands available.
LOCATING ITEMS
SATINIT has a very flexible location system.. With it, you can locate a
satellite that matches a series of criteria you select.  SATINIT makes use
of Xbase logic for all the searches.
Lets assume you want to locate ALL satellites that were launched in
April of 1960.  The launch date field lists the launch date in the following
format, DD MMM YY,  So satellites launched in APRril of 1960 would have an
entry of the day's digits, then APR, then 60.
To locate the above, simply choose L from the edit menu.  You will then
see the matrix on the next page.
ÚÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ¿ÚÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ¿
³  #. Field       ³³  #. Operators         ³
ÃÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ´ÃÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ´
³  1. intdes      ³³  1. Equal             ³
³  2. catnr       ³³  2. Not equal         ³
³  3. name        ³³  3. Greater than      ³
³  4. source      ³³  4. Greater or equal  ³
³  5. launch      ³³  5. Less than         ³
³  6. lsite       ³³  6. Less or equal     ³
³  7. decay       ³³  7. Contains          ³
³  8. period      ³³  8. Is Contained in   ³
³  9. inc         ³ÃÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ´
³ 10. apogee      ³³  {C} = Connectors     ³
³ 11. perigee     ³³ÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ³
³ 12.             ³³  ' ' = <exit>         ³
³ 13.             ³³  'A' = .AND.          ³
³ 14.             ³³  'O' = .OR.           ³
ÀÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÙÀÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÙ
Enter FIELD #
ÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄÄ
Since we are looking for a launch date, we select field 5(launch), and since
we want ALL launches in april of 1960, we would select 7 (contains) then
APR 60 as a value. Press ENTER when you have defined your last condition.
We have now told SATINIT to locate ALL satellites launched in APR of 60.
Satinit will write the search conditons as follows:
("APR 60"$UPPER(A->launch))
This search criteria will be saved for later use.
In another example, we could look for NON-US satellites launched from
AFETR (Cape Canaveral).  We would select field 6 (LSITE) and enter AFETR as
the site...then we select A for the logical AND...then select field 4
(SOURCE) and enter US as the value, then select 2 for Not Equal. Finally,
press enter to finish your selection.  Satinit will write the search
conditions as follows:
(UPPER(A->lsite)="AFE").AND.(UPPER(A->source)<"US")
REPORTS
The same logic can be used to create custom reports...AND Satinit stores
your search crteria...allowing you select a complicated search at any time.
While viewing a report on-screen, you may press the ESC key.  You will
be asked if you want to go backwards in the report, continue or quit.
You may add, delete or modify any of the criteria listed in the location
database.