Official name: 	Mars-96
Launch Date: 	16 Nov 1996
Launch Time: 	20:48:52.795 UTC
Launch Place: 	Baykonur
Launcher: 	Proton-K + Block D-2

Flight Profile Timeline

Launch Profile Overview

1 - Booster phase
2 - Block D-2 1st burn
3 - Block D-2 2nd burn
4 - Spacecraft main engine burn

Map of Launch Ground Track

 1  - Payload (Block D-2 + spacecraft + adapter + lower casing + middle casing) 
      separation.
 2  - 1st ignition of the Block D-2 main engine launch provision  sistem (SOZ).
 3  - 1st ignition of the Block D-2 main engine.
 4  - Block D-2 main engine burn-out.
 5  - 2nd ignition of the SOZ engine.
 6  - 2nd ignition of the Block D-2 main engine.
 7  - Block D-2 main engine burn-out.
 8  - Block D-2/Mars-96 separation. 
 9  - Spacecraft's  low-level  thrust  engine  ignition  for providing of main 
      engine burn.
10 - Spacecraft's main engine burn.
11 - Spacecraft's main  engine  burn-out.  Insertion  of  the  spacecraft on a 
     trajectory to the Mars.

Event State Vectors For Satellite Observers

Nominal post-launch events vectors for satellite observers
( for Nov 16, 20:48:52.752 launch opportunity)

Events are:
Block D-2 main engine cut-off #1 (BECO #1) after 1st burn. Parking orbit vector.   
150.9x166.0, 51.56 deg, 87.477 min

Start of the Block D-2 main engine 2nd burn (SBME#2).                              
152.8x166.3, 51.56 deg, 87.497 min

SOZ motors separation from the Block D-2 (SOZS). Orbit vector for two SOZ motors.  
157.7x206.5, 51.56 deg, 87.988 min

Block D-2 main engine cut-off #2 (BECO #2) after 2nd burn.                         
652.1x308244.5, 51.76 deg, 7 d 10 h 28 min

Mars-96 spacecraft separation from the Block D-2 (BSEP). Block D-2 orbit vector.   
660.0x309325.9, 51.76 deg, 7 d 11 h 23 min

Mars-96 spacecraft main engine cut-off (SECO). Hyperbolic escape trajectory vector.

Reference  coordinate  frame  is  J2000 inertial reference system ( +Z2000  is 
normal to the Mean Earth Equator of Epoch J2000; +X2000  is  parallel  to  the 
Mean Earth Vernal Equinox of Epoch  J2000; +Y2000  completes  the right-handed 
system), where the Epoch of J2000 is the Julian Ephemeris Date 2451545.0.

For those who would like to use B1950 vector a single transformation matrix is 
presented. It can  be  used  to  convert  from  B1950  based  ephemeris  to  a 
corresponding J2000  based  one  and  vice  versa. B1950 is inertial reference 
system ( +Z1950 is normal to the Mean Earth Equator  of Epoch B1950; +X1950 is 
parallel to the Mean Earth Vernal Equinox of Epoch B1950; +Y1950 completes the 
right-handed system), where the Epoch of B1950  is  the  Julian Ephemeris Date 
2433282.423357

   | 0.9999256791774783 -0.0111815116763724 -0.0048590038154553 |
A= | 0.0111815116959975  0.9999374845751042 -0.0000271625775175 |
   | 0.0048590037714450 -0.0000271704492210  0.9999881946023742 |

X_J2000=A *X_B1950
X_B1950=AT*X_J2000

where X, Y, Z either X, Y, Z coordinates or Vx, Vy, Vz velocity components.

Determining of the Block D-2 Decay Point

2nd  ignition of the Block D-2 didn't took place due  to  some  reasons  which 
should be determined by a special group. Mass of the Block D-2 with fuel after 
separation  of  the spacecraft was around 14300 kg (dry mass 1900 kg), mass of 
the spacecraft was 6825 kg. According to the Block D-2 timing diagram the fuel 
remaining  had  to be  venting in case of the spacecraft separation. Since the 
spacecraft SEPARATED from the Block D-2, mass of the Block had been decreasing 
during  next  few  orbits. This  fact  had  been indirectly confirmed with the 
estimations  of  ballistic coefficient during orbit determinations from ground 
stations measurements on first 5 orbits.

Following  trajectory  measurements  were  received  from   tracking  stations 
operated by the Russian Military Space Forces (time is DMV = UTC + 3h,
date is Nov 17):


Orbit #
Tracking Station
Measurement Time Frame
1
OKIK-13 (Ulan-Ude)  
00:00:18 - 00:01:04
1
OKIK-15 (Ussuriysk) 
00:04:29 - 00:07:32
2
OKIK-7  (Barnaul)   
01:25:00 - 01:31:56
2
OKIK-12 (Kolpashevo)
01:24:00 - 01:30:56
2
OKIK-13 (Ulan-Ude)  
01:30:55 - 01:34:50
3
OKIK-14 (Schyolkovo)
02:50:42 - 02:55:15
3
OKIK-12 (Kolpashevo)
02:55:00 - 03:01:25
3
OKIK-7  (Barnaul)   
02:55:00 - 03:02:28
4
OKIK-14 (Schyolkovo)
04:21:18 - 04:26:27
5
OKIK-14 (Schyolkovo)
05:52:20 - 05:56:32


After  processing  of  these  trajectory measurements following orbital  state 
vectors were obtained in the KIAM Ballistic Center:



Orbit #
Date,YY/MM/DD
Time,DMV
X,km
Y,km
Z,km
Xdot,km/s
Ydot,km/s
Zdot,km/s
Sb
2
96/11/17 
01:05:43.704
6436.67871
-1158.67024
0.00000
0.769719878
4.30816688 
6.11272204
0.0070
3
96/11/17 
02:33:11.533
5516.60475
-3511.32538
0.00000
2.34547607 
3.69521432 
6.11329747
0.0076
4
96/11/17 
04:00:38.616
3773.98632
-5339.68742
0.00000
3.57133794 
2.53066138 
6.11349014
0.0086
5
96/11/17 
05:28:05.088
1468.61989
-6370.54634
0.00000
4.26493244 
0.988508105
6.11400563
0.0103



Orbit #
Nodal period,min
Incl,deg
Hmin,km
Hmax,km
2
87.4635
51.5516
143.64
169.61
3
87.4525
51.5525
143.39
168.87
4
87.4427
51.5518
142.89
168.25
5
87.4274
51.5493
142.45
167.24


Note. Heights are counted above the Earth's ellipsoid surface.

After  5th  orbit  Block  D-2  was  not in  sight from Russian ground tracking 
stations till Nov 17 evening (orbit 13). But chemical batteries had discharged
and  active  communications  was  not  restored.  Since this time tracking was 
provided with radar sensors operated by the Russian Space Surveillance  Center 
(SSC).  After  processing  own  measurements  SSC  obtained  following orbital 
vectors  which  were  sent  to MCC  (Mission Control Center in Korolev, Moscow 
region)  and  KIAM  Ballistic  Centers.  These  vectors  (EFG)  were  used for 
determinations of the Block D-2 decay point.


Orbit #
Date,YY/MM/DD
Time,DMV
X,km
Y,km
Z,km
Xdot,km/s
Ydot,km/s
Zdot,km/s
16
96/11/17 
21:28:22.710
5106.34876
 4053.78557
0.00000
-2.73248068 
3.43154666
6.12314340
17
96/11/17 
22:55:27.261
6256.55898
 1823.86391
0.00000
-1.23401630 
4.21132099
6.12413927
18
96/11/18 
00:22:28.021
6479.14440
-670.612883
0.00000
 0.446578435
4.36694295
6.12567753
19
96/11/18 
01:49:23.527
5742.84087
-3059.69335
0.00000
 2.06111927 
3.87972026
6.12945473
20
96/11/18 
03:16:12.092
4161.22493
-4985.83041
0.00000
 3.37653115 
2.82194186
6.13704676


NASA Goddard Space Flight Center Orbital Information Group (OIG) had providing 
TLE's  from U.S. Space Command for public access during all the day of Nov 17. 
Here is all TLE sets for the Block D-2 (ID 1996-064A, SpaceCom #24656).

1 24656U 96064A   96322.22419506  .05925615  12441-4  10000-3 0    27
2 24656  51.5257  15.7496 0011754 195.8405 163.9890 16.47046585    59

1 24656U 96064A   96322.46689235  .03446689  12560-4  48899-4 0    39
2 24656  51.5251  14.3524 0010353 193.1058 166.9712 16.48166778    97

1 24656U 96064A   96322.52750717  .03882494  12559-4  51023-4 0    40
2 24656  51.5241  14.0069 0009452 194.5731 165.5032 16.48693178   109

1 24656U 96064A   96322.58809741  .03869138  12586-4  47202-4 0    53
2 24656  51.5213  13.6508 0007694 204.7974 155.2667 16.49286694   113

1 24656U 96064A   96322.70920078  .05053773  12602-4  47595-4 0    61
2 24656  51.5372  12.9538 0007989 202.1388 157.9001 16.50809267   134

1 24656U 96064A   96322.76971714  .06024909  12616-4  48562-4 0    71
2 24656  51.5319  12.6052 0008703 210.0700 150.0408 16.51737766   145

1 24656U 96064A   96322.83017895  .06882682  12657-4  47869-4 0    85
2 24656  51.5193  12.2621 0007930 221.3916 138.6508 16.52761788   154

1 24656U 96064A   96322.83017941  .06646711  12657-4  46654-4 0    90
2 24656  51.5194  12.2673 0007622 218.1526 141.8966 16.52721283   151

1 24656U 96064A   96322.89062639  .07626927  12682-4  45415-4 0   102
2 24656  51.5229  11.9148 0007504 214.7640 145.3413 16.53844783   160

1 24656U 96064A   96322.89061285  .11793689  12720-4  64686-4 0   118
2 24656  51.5221  11.9148 0006904 225.0514 135.0329 16.54450754   164

1 24656U 96064A   96322.89060726  .11535862  12720-4  63566-4 0   121
2 24656  51.5231  11.9144 0006875 225.2180 134.8300 16.54419645   169

1 24656U 96064A   96323.01130778  .13328068  12842-4  45328-4 0   133
2 24656  51.4998  11.2010 0005797 231.1092 129.2833 16.58057739   180


Taking into account all available orbital information following decay data was
calculated. These data was agreed between SSC, MCC and KIAM.

Atmosphere entry point:          Nov 18, 01:13 UTC, 42.2 S, 161.3 E
Splashdown point:                Nov 18, 01:20 UTC, 50.9 S, 168.1 W
Uncertainty of splashdown point: from 01:10 UTC, 33.0 S, 147.2 E to 01:24 UTC, 50.2 S, 140.7 W

It  should  be  noted  that  uncertainty of splashdown point time and position 
caused by (in order of the uncertainty value decreasing):
  - absence  of ground  stations  for making of direct measurements in zone of 
    event;
  - uncertainty of the Block D-2 atmospheric decay model;
  - uncertainty of atmosphere dencity, pressure and winds velocity  models for 
    altitude from 120km to sea level;
  - errors of orbit determinations.

Few orbits prior to natural decay estimation for the  Block D-2  landing point 
was  in  Central  Australia and only two orbits priot to the decay event point 
closed to presented above was obtained.