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БЦ |
ИПМ |
K-100
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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
Events | Time, seconds since lift-off | Relative velocity, mps | Height, km | Latitude | Longitude |
Lift-off command | -2.80 | 0 | 0 | 46d02'22N | 63d01'58E |
Lift-off | 0.00 | 0 | 0 | 46d02'22N | 63d01'58E |
100% of 1st stage engines thrust | 1.60 | 7 | 0.008 | 46.04N | 63.03E |
Maximum velocity head | 66.00 | 459.5 | 11.2 | 46.10N | 63.03E |
2nd stage engine ignition | 118.94 | 1551.3 | 39.4 | 46.26N | 63.48E |
1st stage separation | 123.29 | 1677.9 | 42.5 | 46.29N | 63.55E |
Payload fairing separation | 185.00 | 2151.2 | 78.2 | 46.74N | 64.83E |
3rd stage engine ignition | 327.74 | 4349.3 | 119.5 | 48.36N | 70.06E |
2nd stage separation | 331.14 | 4417.6 | 120.6 | 48.41N | 70.24E |
Command on the payload separation | 583.29 | 7202.4 | 144.7 | 51.49N | 89.02E |
Payload (Block D-2 + spacecraft + adapter + lower casing + middle casing) separation | 583.42 | 7202.4 | 144.7 | 51.49N | 89.07E |
Middle casing separation | 638.42 | - | - | - | - |
1st ignition of the Block D-2 main engine's launching provision system(SOZ) | 643.42 | 7188.1 | 155.6 | 51.71N | 95.14E |
1st ignition of the Block D-2 main engine | 942.42 | 7175.3 | 166.0 | 48.07N | 123.87E |
75% of the Block D-2 main engine thrust; SOZ burn-out | 942.84 | 7191.9 | 165.9 | 48.06N | 123.91E |
Block D-2 main engine burn-out | 1038.94 | 7519.9(Vabs=7843.1) | 160.1 | 45.32N | 131.99E |
2nd ignition of the SOZ engine | 3833.81 | 7485.8 | 163.2 | 38.96S | 46.56W |
Payload entry into the Earth's shadow | 4032.00 | - | - | - | - |
2nd ignition of the Block D-2 main engine | 4132.81 | 7488.0 | 159.5 | 25.12S | 29.88W |
75% of the Block D-2 main engine thrust; SOZ burn-out | 4133.23 | 7488.1 | 159.5 | 25.09S | 29.86W |
SOZ separation | 4136.81 | 7502.5 | 159.5 | 24.92S | 29.69W |
Block D-2 main engine burn-out | 4661.98 | 10385.3 | 435.1 | 7.16N | 4.79W |
Block D-2/Mars-96 separation | 4678.04 | 10361.6(Vabs=10684.8) | 466.7 | 8.27N | 3.97W |
Spacecraft's low-level thrust engine ignition for providing of main engine burn | 4692.98 | 10337.0 | 497.9 | 9.30N | 3.20W |
Spacecraft's main engine burn | 4747.98 | 10237.5 | 626.8 | 12.96N | 0.41W |
75% of the spacecraft main engine thrust | 4750.68 | 10234.0 | 633.7 | 13.14N | 0.28W |
Command on spacecraft main engine burn-out | 4921.59 | 10384.2 | 1183.6 | 23.54N | 8.41E |
Insertion of the spacecraft on a trajectory tothe Mars | 4923.76 | 10379.7(Vabs=10702.9) | 1192.0 | 23.66N | 8.52E |
Spacecraft exit from the Earth's shadow | 6280.00 | - | - | - | - |
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.
Event | Date | Time, UTC | X, km | Y, km | Z, km | Vx, km/s | Vy, km/s | Vz, km/s |
BECO#1 | 16.11.96 | 21:06:13.696 | -3776.149 | 2646.729 | 4619.926 | -6.095322 | -4.131954 | -2.614969 |
SBME#2 | 16.11.96 | 21:57:45.562 | 5908.491 | -428.635 | -2756.298 | 2.781540 | 5.169820 | 5.152905 |
SOZS | 16.11.96 | 21:57:49.562 | 5919.556 | -407.933 | -2735.635 | 2.751391 | 5.181815 | 5.178972 |
BECO#2 | 16.11.96 | 22:06:36.732 | 6212.627 | 2669.722 | 862.110 | -1.802765 | 6.376021 | 8.402991 |
BSEP | 16.11.96 | 22:06:50.792 | 6186.508 | 2759.043 | 980.156 | -1.912021 | 6.328447 | 8.387033 |
SECO | 16.11.96 | 22:10:56.515 | 5499.815 | 4228.589 | 3021.075 | -3.614126 | 5.703135 | 8.289463 |
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.
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cодержание, дизайн, оформление, техническая поддержка:
Денис Тучин
Copyright 2002-2022
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