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SECTION 9 ORBIT DATA - LAUNCH TRAJECTORY
--~-
SECTION 9 LAUNCH TRAJECTORY
91 MISSION PROFILE
IUE was launched by a three-stage Delta 2914 launch vehicle from Cape Kennedy
on January 26 1978 at l7h 36m OS206 GMT At an altitude of 89 nautical miles it was injected into a near-circular parking orbit with an inclination of 287 degrees After coasting for about 34 minutes the booster injected
the spacecraft into a transfer orbit with an argument of perigee of 2574 degrees Following injection into the transfer orbit the spacecraft orbit and attitude were determined from tracking and telemetry data The hydrazine reaction control system was then used to reorient the spacecraft into the apogee motor firing attitude About 22 minutes prior to the second apogee passage of the transfer orbit the apogee boost motor was fired to inject the satellite into a synchronous orbit with an eccentricity of 025
92 ORBITAL ELEMENTS
The parking orbit achieved was defined by the following parameters
Semi-major Axis 6542496 km Eccentricity 001871 Inclination 28728 deg Right Ascension of the Ascending Node 209185 deg Argument of Perigee 47791 deg Mean Anomaly 94746 deg Epoch 780126 l7h44m 59s 0 GMT
Following the period of coasting the spacecraft was injected into the parkshying orbit The orbital parameters were
Semi -major Axi s 29677 110 km Eccentricity 077946 Inclination 28710 deg Right Ascension of the Ascending Node 209170 deg Argument of Perigee 257010 deg Mean Anomaly 0662 deg
9-1
sEpoch 780126 18h 19m 500 GMT
Right Ascension 19647 deg
Declination -574 deg Spin Rate 6313 rpm
In the transfer orbit a maneuver was executed to reori ent the spin axis of the spacecraft from the injection attitude to the attitude necessary for firing the apogee boost motor (ABM) The subsequent orbital parameters were
Semi -major Ax s 29458648 km Eccentri city 077769 Inclination 28668 deg Right Ascension of the Ascending Node 208556 deg Argument of Perigee 257586 deg Mean Anomaly 236826 deg Epoch 780127 03h 30m 30 s0 GMT Right Ascension 2243 deg Declination 330 deg Spin Rate 6283 rpm
Prior to the firing of the apogee boost motor two attitude tOllcbup maneuvers were executed The firing of the ABM occurred on January 27~ 1978 at 14h 53m 54s GMT which placed the spacecraft in a drift orbit with an eastshyward drift rate of 0123 degrees per day The resuJting orbital parameters as evaluated were
Semi-major Axis 42085412 km Eccentricity 024180 Inclination 28672 deg Right Ascension of the Ascending Node 208435 deg Argument of Perigee 256658 deg Mean Anomaly 178836 deg Epoch 780127 14h 54m 10s0 GMT
Right Ascension 2225 deg Declination 338 deg Spin Rate 6292 rpm
9-2
Events following the apogee boost motor firings included a maneuver to reorient the spacecraft spin axis to a sun angle of 120 degrees and to reduce the spacecraft spin rate from 628 to 44 rpm
93 STATION ACqUISITION MANEUVERS
Due to the violation of a tracking constraint at NTTF the first station acquisition maneuver was performed at 01 h 54m 32s 0 on February 14 1978 with the objective of changing the eastward drift rate of 015 degrees per day to a westward drift rate of 005 degrees per day The predicted post-maneuver elements and the achieved post-maneuver elements are presented as evaluated at the Epoch of the maneuver
Predicted Achi eved Post-Maneuver Post-Maneuver
Semi-major Axis (km) 42169053 42166995 middot Eccentricity 02396278 02395886 Inclination (deg) 286330 286333 Node (deg) 2017397 2077482 Argument of Perigee (deg) 2573918 2573944 Mean Anomaly (deg) 37637 37765 Drift Rate (degday) 004909 W 002274 W
The second station acquisition maneuver was executed at 16 h 34m 13 s0 on July 24 1978 to avoid a violation of the tracking constraint at the VILSPA tracking site The predicted Post-Maneuver parameters and the achieved Post-Maneuver parameters are presented as evaluated at the epoch of the maneuver
Predicted Achieved Post-Maneuver Post-Maneuver
Semi -major Axi s (km) 4215444 4215217 Eccentri city 023966 023962 Inclination 28485 28482 Node 204319 204303 Argument of Perigee (deg) 260812 260808 Mean Anomaly 4756 4760 Drift Rate (degday) 013269E 016205E
9-3
Periodically subsequent maneuvers will be necessary to maintain the spaceshycraft in a position such that the tracking constraints will not be violated
9-4
u-Ishy~
u
r shy0
o ~
lLJ =gt
-I I
en QJ ~ J 0)
r-lJ
9-5
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
--~-
SECTION 9 LAUNCH TRAJECTORY
91 MISSION PROFILE
IUE was launched by a three-stage Delta 2914 launch vehicle from Cape Kennedy
on January 26 1978 at l7h 36m OS206 GMT At an altitude of 89 nautical miles it was injected into a near-circular parking orbit with an inclination of 287 degrees After coasting for about 34 minutes the booster injected
the spacecraft into a transfer orbit with an argument of perigee of 2574 degrees Following injection into the transfer orbit the spacecraft orbit and attitude were determined from tracking and telemetry data The hydrazine reaction control system was then used to reorient the spacecraft into the apogee motor firing attitude About 22 minutes prior to the second apogee passage of the transfer orbit the apogee boost motor was fired to inject the satellite into a synchronous orbit with an eccentricity of 025
92 ORBITAL ELEMENTS
The parking orbit achieved was defined by the following parameters
Semi-major Axis 6542496 km Eccentricity 001871 Inclination 28728 deg Right Ascension of the Ascending Node 209185 deg Argument of Perigee 47791 deg Mean Anomaly 94746 deg Epoch 780126 l7h44m 59s 0 GMT
Following the period of coasting the spacecraft was injected into the parkshying orbit The orbital parameters were
Semi -major Axi s 29677 110 km Eccentricity 077946 Inclination 28710 deg Right Ascension of the Ascending Node 209170 deg Argument of Perigee 257010 deg Mean Anomaly 0662 deg
9-1
sEpoch 780126 18h 19m 500 GMT
Right Ascension 19647 deg
Declination -574 deg Spin Rate 6313 rpm
In the transfer orbit a maneuver was executed to reori ent the spin axis of the spacecraft from the injection attitude to the attitude necessary for firing the apogee boost motor (ABM) The subsequent orbital parameters were
Semi -major Ax s 29458648 km Eccentri city 077769 Inclination 28668 deg Right Ascension of the Ascending Node 208556 deg Argument of Perigee 257586 deg Mean Anomaly 236826 deg Epoch 780127 03h 30m 30 s0 GMT Right Ascension 2243 deg Declination 330 deg Spin Rate 6283 rpm
Prior to the firing of the apogee boost motor two attitude tOllcbup maneuvers were executed The firing of the ABM occurred on January 27~ 1978 at 14h 53m 54s GMT which placed the spacecraft in a drift orbit with an eastshyward drift rate of 0123 degrees per day The resuJting orbital parameters as evaluated were
Semi-major Axis 42085412 km Eccentricity 024180 Inclination 28672 deg Right Ascension of the Ascending Node 208435 deg Argument of Perigee 256658 deg Mean Anomaly 178836 deg Epoch 780127 14h 54m 10s0 GMT
Right Ascension 2225 deg Declination 338 deg Spin Rate 6292 rpm
9-2
Events following the apogee boost motor firings included a maneuver to reorient the spacecraft spin axis to a sun angle of 120 degrees and to reduce the spacecraft spin rate from 628 to 44 rpm
93 STATION ACqUISITION MANEUVERS
Due to the violation of a tracking constraint at NTTF the first station acquisition maneuver was performed at 01 h 54m 32s 0 on February 14 1978 with the objective of changing the eastward drift rate of 015 degrees per day to a westward drift rate of 005 degrees per day The predicted post-maneuver elements and the achieved post-maneuver elements are presented as evaluated at the Epoch of the maneuver
Predicted Achi eved Post-Maneuver Post-Maneuver
Semi-major Axis (km) 42169053 42166995 middot Eccentricity 02396278 02395886 Inclination (deg) 286330 286333 Node (deg) 2017397 2077482 Argument of Perigee (deg) 2573918 2573944 Mean Anomaly (deg) 37637 37765 Drift Rate (degday) 004909 W 002274 W
The second station acquisition maneuver was executed at 16 h 34m 13 s0 on July 24 1978 to avoid a violation of the tracking constraint at the VILSPA tracking site The predicted Post-Maneuver parameters and the achieved Post-Maneuver parameters are presented as evaluated at the epoch of the maneuver
Predicted Achieved Post-Maneuver Post-Maneuver
Semi -major Axi s (km) 4215444 4215217 Eccentri city 023966 023962 Inclination 28485 28482 Node 204319 204303 Argument of Perigee (deg) 260812 260808 Mean Anomaly 4756 4760 Drift Rate (degday) 013269E 016205E
9-3
Periodically subsequent maneuvers will be necessary to maintain the spaceshycraft in a position such that the tracking constraints will not be violated
9-4
u-Ishy~
u
r shy0
o ~
lLJ =gt
-I I
en QJ ~ J 0)
r-lJ
9-5
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
SECTION 9 LAUNCH TRAJECTORY
91 MISSION PROFILE
IUE was launched by a three-stage Delta 2914 launch vehicle from Cape Kennedy
on January 26 1978 at l7h 36m OS206 GMT At an altitude of 89 nautical miles it was injected into a near-circular parking orbit with an inclination of 287 degrees After coasting for about 34 minutes the booster injected
the spacecraft into a transfer orbit with an argument of perigee of 2574 degrees Following injection into the transfer orbit the spacecraft orbit and attitude were determined from tracking and telemetry data The hydrazine reaction control system was then used to reorient the spacecraft into the apogee motor firing attitude About 22 minutes prior to the second apogee passage of the transfer orbit the apogee boost motor was fired to inject the satellite into a synchronous orbit with an eccentricity of 025
92 ORBITAL ELEMENTS
The parking orbit achieved was defined by the following parameters
Semi-major Axis 6542496 km Eccentricity 001871 Inclination 28728 deg Right Ascension of the Ascending Node 209185 deg Argument of Perigee 47791 deg Mean Anomaly 94746 deg Epoch 780126 l7h44m 59s 0 GMT
Following the period of coasting the spacecraft was injected into the parkshying orbit The orbital parameters were
Semi -major Axi s 29677 110 km Eccentricity 077946 Inclination 28710 deg Right Ascension of the Ascending Node 209170 deg Argument of Perigee 257010 deg Mean Anomaly 0662 deg
9-1
sEpoch 780126 18h 19m 500 GMT
Right Ascension 19647 deg
Declination -574 deg Spin Rate 6313 rpm
In the transfer orbit a maneuver was executed to reori ent the spin axis of the spacecraft from the injection attitude to the attitude necessary for firing the apogee boost motor (ABM) The subsequent orbital parameters were
Semi -major Ax s 29458648 km Eccentri city 077769 Inclination 28668 deg Right Ascension of the Ascending Node 208556 deg Argument of Perigee 257586 deg Mean Anomaly 236826 deg Epoch 780127 03h 30m 30 s0 GMT Right Ascension 2243 deg Declination 330 deg Spin Rate 6283 rpm
Prior to the firing of the apogee boost motor two attitude tOllcbup maneuvers were executed The firing of the ABM occurred on January 27~ 1978 at 14h 53m 54s GMT which placed the spacecraft in a drift orbit with an eastshyward drift rate of 0123 degrees per day The resuJting orbital parameters as evaluated were
Semi-major Axis 42085412 km Eccentricity 024180 Inclination 28672 deg Right Ascension of the Ascending Node 208435 deg Argument of Perigee 256658 deg Mean Anomaly 178836 deg Epoch 780127 14h 54m 10s0 GMT
Right Ascension 2225 deg Declination 338 deg Spin Rate 6292 rpm
9-2
Events following the apogee boost motor firings included a maneuver to reorient the spacecraft spin axis to a sun angle of 120 degrees and to reduce the spacecraft spin rate from 628 to 44 rpm
93 STATION ACqUISITION MANEUVERS
Due to the violation of a tracking constraint at NTTF the first station acquisition maneuver was performed at 01 h 54m 32s 0 on February 14 1978 with the objective of changing the eastward drift rate of 015 degrees per day to a westward drift rate of 005 degrees per day The predicted post-maneuver elements and the achieved post-maneuver elements are presented as evaluated at the Epoch of the maneuver
Predicted Achi eved Post-Maneuver Post-Maneuver
Semi-major Axis (km) 42169053 42166995 middot Eccentricity 02396278 02395886 Inclination (deg) 286330 286333 Node (deg) 2017397 2077482 Argument of Perigee (deg) 2573918 2573944 Mean Anomaly (deg) 37637 37765 Drift Rate (degday) 004909 W 002274 W
The second station acquisition maneuver was executed at 16 h 34m 13 s0 on July 24 1978 to avoid a violation of the tracking constraint at the VILSPA tracking site The predicted Post-Maneuver parameters and the achieved Post-Maneuver parameters are presented as evaluated at the epoch of the maneuver
Predicted Achieved Post-Maneuver Post-Maneuver
Semi -major Axi s (km) 4215444 4215217 Eccentri city 023966 023962 Inclination 28485 28482 Node 204319 204303 Argument of Perigee (deg) 260812 260808 Mean Anomaly 4756 4760 Drift Rate (degday) 013269E 016205E
9-3
Periodically subsequent maneuvers will be necessary to maintain the spaceshycraft in a position such that the tracking constraints will not be violated
9-4
u-Ishy~
u
r shy0
o ~
lLJ =gt
-I I
en QJ ~ J 0)
r-lJ
9-5
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
sEpoch 780126 18h 19m 500 GMT
Right Ascension 19647 deg
Declination -574 deg Spin Rate 6313 rpm
In the transfer orbit a maneuver was executed to reori ent the spin axis of the spacecraft from the injection attitude to the attitude necessary for firing the apogee boost motor (ABM) The subsequent orbital parameters were
Semi -major Ax s 29458648 km Eccentri city 077769 Inclination 28668 deg Right Ascension of the Ascending Node 208556 deg Argument of Perigee 257586 deg Mean Anomaly 236826 deg Epoch 780127 03h 30m 30 s0 GMT Right Ascension 2243 deg Declination 330 deg Spin Rate 6283 rpm
Prior to the firing of the apogee boost motor two attitude tOllcbup maneuvers were executed The firing of the ABM occurred on January 27~ 1978 at 14h 53m 54s GMT which placed the spacecraft in a drift orbit with an eastshyward drift rate of 0123 degrees per day The resuJting orbital parameters as evaluated were
Semi-major Axis 42085412 km Eccentricity 024180 Inclination 28672 deg Right Ascension of the Ascending Node 208435 deg Argument of Perigee 256658 deg Mean Anomaly 178836 deg Epoch 780127 14h 54m 10s0 GMT
Right Ascension 2225 deg Declination 338 deg Spin Rate 6292 rpm
9-2
Events following the apogee boost motor firings included a maneuver to reorient the spacecraft spin axis to a sun angle of 120 degrees and to reduce the spacecraft spin rate from 628 to 44 rpm
93 STATION ACqUISITION MANEUVERS
Due to the violation of a tracking constraint at NTTF the first station acquisition maneuver was performed at 01 h 54m 32s 0 on February 14 1978 with the objective of changing the eastward drift rate of 015 degrees per day to a westward drift rate of 005 degrees per day The predicted post-maneuver elements and the achieved post-maneuver elements are presented as evaluated at the Epoch of the maneuver
Predicted Achi eved Post-Maneuver Post-Maneuver
Semi-major Axis (km) 42169053 42166995 middot Eccentricity 02396278 02395886 Inclination (deg) 286330 286333 Node (deg) 2017397 2077482 Argument of Perigee (deg) 2573918 2573944 Mean Anomaly (deg) 37637 37765 Drift Rate (degday) 004909 W 002274 W
The second station acquisition maneuver was executed at 16 h 34m 13 s0 on July 24 1978 to avoid a violation of the tracking constraint at the VILSPA tracking site The predicted Post-Maneuver parameters and the achieved Post-Maneuver parameters are presented as evaluated at the epoch of the maneuver
Predicted Achieved Post-Maneuver Post-Maneuver
Semi -major Axi s (km) 4215444 4215217 Eccentri city 023966 023962 Inclination 28485 28482 Node 204319 204303 Argument of Perigee (deg) 260812 260808 Mean Anomaly 4756 4760 Drift Rate (degday) 013269E 016205E
9-3
Periodically subsequent maneuvers will be necessary to maintain the spaceshycraft in a position such that the tracking constraints will not be violated
9-4
u-Ishy~
u
r shy0
o ~
lLJ =gt
-I I
en QJ ~ J 0)
r-lJ
9-5
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
Events following the apogee boost motor firings included a maneuver to reorient the spacecraft spin axis to a sun angle of 120 degrees and to reduce the spacecraft spin rate from 628 to 44 rpm
93 STATION ACqUISITION MANEUVERS
Due to the violation of a tracking constraint at NTTF the first station acquisition maneuver was performed at 01 h 54m 32s 0 on February 14 1978 with the objective of changing the eastward drift rate of 015 degrees per day to a westward drift rate of 005 degrees per day The predicted post-maneuver elements and the achieved post-maneuver elements are presented as evaluated at the Epoch of the maneuver
Predicted Achi eved Post-Maneuver Post-Maneuver
Semi-major Axis (km) 42169053 42166995 middot Eccentricity 02396278 02395886 Inclination (deg) 286330 286333 Node (deg) 2017397 2077482 Argument of Perigee (deg) 2573918 2573944 Mean Anomaly (deg) 37637 37765 Drift Rate (degday) 004909 W 002274 W
The second station acquisition maneuver was executed at 16 h 34m 13 s0 on July 24 1978 to avoid a violation of the tracking constraint at the VILSPA tracking site The predicted Post-Maneuver parameters and the achieved Post-Maneuver parameters are presented as evaluated at the epoch of the maneuver
Predicted Achieved Post-Maneuver Post-Maneuver
Semi -major Axi s (km) 4215444 4215217 Eccentri city 023966 023962 Inclination 28485 28482 Node 204319 204303 Argument of Perigee (deg) 260812 260808 Mean Anomaly 4756 4760 Drift Rate (degday) 013269E 016205E
9-3
Periodically subsequent maneuvers will be necessary to maintain the spaceshycraft in a position such that the tracking constraints will not be violated
9-4
u-Ishy~
u
r shy0
o ~
lLJ =gt
-I I
en QJ ~ J 0)
r-lJ
9-5
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
Periodically subsequent maneuvers will be necessary to maintain the spaceshycraft in a position such that the tracking constraints will not be violated
9-4
u-Ishy~
u
r shy0
o ~
lLJ =gt
-I I
en QJ ~ J 0)
r-lJ
9-5
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
u-Ishy~
u
r shy0
o ~
lLJ =gt
-I I
en QJ ~ J 0)
r-lJ
9-5
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
I ~
01
7 6
PERIGEE 12
or-
o o Ramiddot 52264 KIn Right Rp bull 32045 KIn APOGEE ascension of
major axis 23 258 0 (plot RA
of sun countershyc I ockw1 se from major axis)
HOURS ArtER APOGEE
IUE ORBIT PLANE (V I EWED FROImiddot NORTH)
SCALE 02 1n z 2500 KIn
17 18
Figure 9-2 IUE Orbit Plane (Viewed From North)
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
80
ii50 w w II t)
e w
10 I
70
60
z 40 o i= laquo gt w Jw30
20
APOGEE
PERIGEE
~OUR BETWEENo ~CK MARKS
AZIMUTH (DEGREESI
Figure 9-3 GSFC Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
I ~
OJ
50
1 40
() w w a () 30 w Cl
Z o ~ laquo 20gt W I W
10
1 HOUR BETWEEN TICK MARKS
_+----4~
VILFRA MASK + 10 DEGREES
0~1----~----~----~----~----~----~----~--~~------------- 200 210 220 230 240 250 260 270 280 290 300 310
AZIMUTH (DEGREES)
Figure 9-4 VILSPA Tracking Mask and Nominal Tracking Pattern
