JCSAT-4
Names
| JCSAT-4
(Dec 1995 to Feb 1997)
JCSAT-R
(Feb 1997 to 2009)
Intelsat 26
(2009 onward)
|
---|
|
Mission type
| Communications
|
---|
Operator
| JSAT
/
INTELSAT
|
---|
COSPAR ID
| 1997-007A
[1]
|
---|
SATCAT
no.
| 24732
[2]
|
---|
Mission duration
| 12 years (planned)
|
---|
|
|
|
Spacecraft
| JCSAT-4
|
---|
Spacecraft type
| JCSAT
|
---|
Bus
| HS-601
|
---|
Manufacturer
| Hughes
|
---|
Launch mass
| 3,105 kg (6,845 lb)
|
---|
Dry mass
| 1,841 kg (4,059 lb)
|
---|
Dimensions
| 26.2 m × 7.5 m (86 ft × 25 ft) with
solar panels
and antennas deployed
|
---|
Power
| 5
kW
|
---|
|
|
|
Launch date
| 17 February 1997, 01:42:02
UTC
[1]
|
---|
Rocket
| Atlas IIAS
|
---|
Launch site
| Cape Canaveral
,
LC-36B
|
---|
Contractor
| International Launch Services
(ILS)
|
---|
|
|
|
Reference system
| Geocentric orbit
[3]
|
---|
Regime
| Geostationary orbit
|
---|
Longitude
| 124° East
|
---|
|
|
|
Band
| Ku-band
:
12 × 36
Mhz
+ 16 × 27 MHz
C-band
:
12 x 36 MHz
|
---|
Bandwidth
| 1296 MHz
|
---|
Coverage area
| Japan,
East Asia
,
South Asia
, Australia, New Zealand,
Hawaii
|
---|
TWTA power
| Ku-band:
4 × 36 MHz 95 watts
8 × 36 MHz 63 watts
16 × 27 MHz 63 watts
C-band:
12 x 36 MHz 34 watts
|
---|
|
|
JCSAT-4
was known as
JCSAT-R
until it was sold to
INTELSAT
in 2009 (
Intelsat 26
). It is a
geostationary
communications satellite
designed and manufactured by
Hughes
(now
Boeing
) on the
HS-601
satellite bus
. It was originally ordered by
JSAT Corporation
, which later merged into the
SKY Perfect JSAT Group
. It has a mixed
Ku-band
and
C-band
payload and was used as an on orbit spare.
[4]
[2]
Satellite description
[
edit
]
The spacecraft was designed and manufactured by
Hughes
on the
HS-601
satellite bus
. It had a launch mass of 3,105 kg (6,845 lb), a dry mass of 1,841 kg (4,059 lb) and a 12-year design life. When stowed for launch, its dimensions were 2.8 m × 4.9 m × 3.8 m (9 ft 2 in × 16 ft 1 in × 12 ft 6 in). With its solar panels fully extended it spanned 26.2 m (86 ft), and its width when its antennas were fully deployed was 7.5 m (25 ft).
[4]
Its power system generated approximately 5
kW
of power due to two wings with four
solar panels
each.
[5]
[4]
It also had a single
NiH
2
battery
composed of 30
cells
and a 200
Ah
charge.
[4]
It would serve as on orbit backup for the
JSAT fleet
.
[4]
Its propulsion system was composed of an
R-4D-11-300
liquid apogee engine
(LAE) with a thrust of 490 N (110 lb
f
). It also used had 12 22 N (4.9 lb
f
)
bipropellant
thrusters
for
station keeping
and
attitude control
. It included enough propellant for
orbit circularization
and 12 years of operation.
[4]
Its payload is composed of four octagonal antenna fed by twelve 36
MHz
and sixteen 27 MHz Ku-band plus twelve 27 MHz C-band
transponders
for a total bandwidth of 1296 MHz.
[5]
[4]
Eight of the 36 MHz and the sixteen 27 MHz Ku-band transponders have a
TWTA
output power of 63 watts, the other four 36 MHz ones have 95 watts. It can configure four 27 MHz transponders into a single 54 MHz with an effective 125 watts.
[4]
The twelve C-band transponders have 36 MHz bandwidth and 34 watts of power.
[4]
History
[
edit
]
In December 1995,
JSAT
ordered its fourth satellite from
Hughes
, and second of the
HS-601
platform, the
JCSAT-4
. It was an almost copy of the
JCSAT-3
, also based on the HS-601, but with more powerful transponders. It would have a mixed Ku-band and C-band payload, a power generation capability of 5000 watts and a 12 year of design life. It was expected to be delivered by early 1997 and be positioned at the 124° East
longitude
. It would provide telecommunications and television services to Japan, all of
Asia
,
Hawaii
and Australia and New Zealand.
[4]
[6]
On 25 March 1996,
International Launch Services
(ILS) announced a contract with JSAT for the launch of JCSAT-4 aboard an Atlas IIAS. At the time it was expected to launch in January 1997 from Cape Canaveral at LC-36A launch pad. This was the second contract of ILS with JSAT after the successful launch of
JCSAT-3
in August 1995.
[7]
On 18 February 1997 at 01:42:02
UTC
, and
Atlas IIAS
launched from Cape Canaveral
LC-36B
with JCSAT-4 towards a
geosynchronous transfer orbit
(GTO).
[8]
After the successful launch, it was renamed
JCSAT-R
. During its tenure as JCSAT-R it operated on the 124° East
longitude
.
[4]
In August, 2008, JSAT was merged into the
SKY Perfect JSAT Group
.
[9]
Intelsat 26
[
edit
]
In late 2009,
Intelsat
bought JCSAT-R and rechristened it
Intelsat 26
.
[10]
[4]
In March 2010, Intelsat announced an agreement with
Turksat
for loaning Intelsat 26 so the latter could keep its orbital rights until a new satellite could be launched.
[10]
In July 2010, it was positioned at the 50° East longitude with a 3.4°
inclination
.
[11]
In January 2013, the inclination had increased to 4.6°.
[12]
In August 2016, the satellite was positioned at 64.1° East with a 6.97° inclination.
[13]
[3]
References
[
edit
]
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Launch designations
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Operational designations
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Payloads are separated by bullets ( · ), launches by pipes ( | ). Crewed flights are indicated in
underline
. Uncatalogued launch failures are listed in
italics
. Payloads deployed from other spacecraft are denoted in (brackets).
|