Jump to content

HS-393: Difference between revisions

Add links
From Wikipedia, the free encyclopedia
Browse history interactively
← Previous edit
Content deleted Content added
VisualWikitext
Grammar and punctuation
m v2.04b - Bot T20 CW#61 - WP:WCW project (Reference before punctuation)
 
(3 intermediate revisions by 2 users not shown)
Line 24: Line 24:
| volume =
| volume =
| power = 2 to 2.2 k[[Watt]]s
| power = 2 to 2.2 k[[Watt]]s
| batteries = 2 × 38[[Ampere-hour|Ah]] [[Nickel–hydrogen battery|NiH<sub>2</sub> batteries]]
| batteries = 2 × 38[[ampere hour|Ah]] [[Nickel–hydrogen battery|NiH<sub>2</sub> batteries]]
| equipment =
| equipment =
| orbits =[[Geostationary orbit]]
| orbits =[[Geostationary orbit]]
Line 69: Line 69:
The satellite bus was designed and manufactured by [[Hughes Space and Communications Company|Hughes]]. It had a launch mass of {{convert|2.2|to|2.5|tonne|abbr=on}}, a mass of {{convert|1.35|to|1.5|tonne|abbr=on}} after reaching [[geostationary orbit]], and an 8-year design life. When stowed for launch, its dimensions were {{convert|3.4|m|abbr=on}} in height and {{convert|3.7|m|abbr=on}} in diameter.<ref name=boeingdefenseandspace-jcsat1and2/><ref name=boeingdefenseandspace-sbs6 /> With its solar panels fully extended its height was {{convert|10|m|abbr=on}}.<ref name=gsp-jcsat1 /><ref name=gsp-sbs6 />
The satellite bus was designed and manufactured by [[Hughes Space and Communications Company|Hughes]]. It had a launch mass of {{convert|2.2|to|2.5|tonne|abbr=on}}, a mass of {{convert|1.35|to|1.5|tonne|abbr=on}} after reaching [[geostationary orbit]], and an 8-year design life. When stowed for launch, its dimensions were {{convert|3.4|m|abbr=on}} in height and {{convert|3.7|m|abbr=on}} in diameter.<ref name=boeingdefenseandspace-jcsat1and2/><ref name=boeingdefenseandspace-sbs6 /> With its solar panels fully extended its height was {{convert|10|m|abbr=on}}.<ref name=gsp-jcsat1 /><ref name=gsp-sbs6 />


Its power system generated approximately 2,350&nbsp;[[Watt|watts]] of power at [[BOL (engineering)|beginning of life]] and 2,200 at end of life, thanks to two cylindrical solar panels. These panels used K7 and K4-3/4 solar cells, with more than twice the number of cells on the [[HS-376]]<ref name=boeingdefenseandspace-jcsat1and2/>. The bottom panel was retracted around the body and top panel for launch, and extended downwards for operation.<ref name=boeingdefenseandspace-jcsat1and2/> It also had two 38[[Ampere-hour|Ah]] [[Nickel–hydrogen battery|NiH<sub>2</sub> batteries]].<ref name=gsp-jcsat1 />
Its power system generated approximately 2,350&nbsp;[[Watt|watts]] of power at [[BOL (engineering)|beginning of life]] and 2,200 at end of life, thanks to two cylindrical solar panels. These panels used K7 and K4-3/4 solar cells, with more than twice the number of cells than on the [[HS-376]].<ref name=boeingdefenseandspace-jcsat1and2/> The bottom panel was retracted around the body and top panel for launch, and extended downwards for operation.<ref name=boeingdefenseandspace-jcsat1and2/> It also had two 38 [[ampere hour|Ah]] [[Nickel–hydrogen battery|NiH<sub>2</sub> batteries]].<ref name=gsp-jcsat1 />


Its propulsion system was composed of two [[R-4D]] [[Liquid Apogee Engine|liquid apogee engines]] with a thrust of {{convert|490|N|abbr=on}}. It also had two axial and four radial {{convert|22|N|abbr=on}} [[Bipropellant rocket|bipropellant]] [[Thrusters (spacecraft)|thrusters]] for [[Orbital station-keeping|station-keeping]] and [[attitude dynamics and control|attitude control]].<ref name=boeingdefenseandspace-jcsat1and2/> It included enough propellant for [[Geostationary transfer orbit|orbit circularization]] and 8 years of operation.<ref name=gsp-jcsat1 />
Its propulsion system was composed of two [[R-4D]] [[Liquid Apogee Engine|liquid apogee engines]] with a thrust of {{convert|490|N|abbr=on}}. It also had two axial and four radial {{convert|22|N|abbr=on}} [[Bipropellant rocket|bipropellant]] [[Thrusters (spacecraft)|thrusters]] for [[Orbital station-keeping|station-keeping]] and [[attitude dynamics and control|attitude control]].<ref name=boeingdefenseandspace-jcsat1and2/> It included enough propellant for [[Geostationary transfer orbit|orbit circularization]] and 8 years of operation.<ref name=gsp-jcsat1 />
Line 95: Line 95:
! [[JCSAT-2]] || || [[JSAT Corporation]] || HS-393 || 1985 || 1990-01-01 || [[Commercial Titan III]] || {{success}} || {{convert|2280|kg|abbr=on}} || {{convert|1346|kg|abbr=on}} || <ref name=gsp-jcsat1 /><ref name=boeingdefenseandspace-jcsat1and2 />
! [[JCSAT-2]] || || [[JSAT Corporation]] || HS-393 || 1985 || 1990-01-01 || [[Commercial Titan III]] || {{success}} || {{convert|2280|kg|abbr=on}} || {{convert|1346|kg|abbr=on}} || <ref name=gsp-jcsat1 /><ref name=boeingdefenseandspace-jcsat1and2 />
|-
|-
! [[SBS 6 (satellite)|SBS 6]] || || [[Satellite Business Systems]] || HS-393 || 1985 || 1990-10-12 || [[Ariane 4|Ariane 44L]] || {{success}} || {{convert|2478|kg|abbr=on}} || {{convert|1500|kg|abbr=on}} || Launched along [[Galaxy 6]].<ref name=gsp-sbs6 /><ref name=boeingdefenseandspace-sbs6 />
! [[SBS 6 (satellite)|SBS 6]] || || [[Satellite Business Systems]] || HS-393 || 1985 || 1990-10-12 || [[Ariane 4|Ariane 44L]] || {{success}} || {{convert|2478|kg|abbr=on}} || {{convert|1500|kg|abbr=on}} || Launched alongside [[Galaxy 6]].<ref name=gsp-sbs6 /><ref name=boeingdefenseandspace-sbs6 />
|-
|-
|}
|}

Latest revision as of 22:58, 16 November 2020

Boeing 393
ManufacturerBoeing Satellite Development Center
Country of originUnited States
ApplicationsCommunications satellite
Specifications
Spacecraft typeSpin-stabilized
Launch mass2.2 to 2.5 t (2.4 to 2.8 tons)
DimensionsDiameter: 3.7 m (12 ft)
Height (stowed): 3.4 m (11 ft)
Height (deployed): 10 m (33 ft)
Power2 to 2.2 kWatts
Batteries2 × 38Ah NiH2 batteries
RegimeGeostationary orbit
Design life8 years
Production
StatusRetired
On order3
Built3
Launched3
Retired3
Maiden launchJCSAT-1 March 6, 1989
Last launchSBS 6, October 12, 1990
Related spacecraft
Derived fromHS-376
← HS-376 Boeing 601 →

The Hughes 393 (sometimes referred to as the HS-393) is a communications satellite bus introduced in 1985 by Hughes Space and Communications Company. It was a spin-stabilized bus that had twice as much power as the HS-376 platform.[1][2]

Design

[edit]

The satellite bus was designed and manufactured by Hughes. It had a launch mass of 2.2 to 2.5 t (2.4 to 2.8 tons), a mass of 1.35 to 1.5 t (1.49 to 1.65 tons) after reaching geostationary orbit, and an 8-year design life. When stowed for launch, its dimensions were 3.4 m (11 ft) in height and 3.7 m (12 ft) in diameter.[1][3] With its solar panels fully extended its height was 10 m (33 ft).[4][5]

Its power system generated approximately 2,350 watts of power at beginning of life and 2,200 at end of life, thanks to two cylindrical solar panels. These panels used K7 and K4-3/4 solar cells, with more than twice the number of cells than on the HS-376.[1] The bottom panel was retracted around the body and top panel for launch, and extended downwards for operation.[1] It also had two 38 Ah NiH2 batteries.[4]

Its propulsion system was composed of two R-4D liquid apogee engines with a thrust of 490 N (110 lbf). It also had two axial and four radial 22 N (4.9 lbf) bipropellant thrusters for station-keeping and attitude control.[1] It included enough propellant for orbit circularization and 8 years of operation.[4]

Its payload was composed of a 2.4 m (7 ft 10 in) antenna that fed Ku band transponders.[1][3]

Satellites

[edit]

The HS-393 was a more powerful platform than the HS-376, being able to supply 2,200 kW of power versus the 1,400 kW of the HS-376HP. Only three were ever built.[2]

Satellite Other Names Operator Model Ordered Launch Launch Vehicle Launch Result Mass at launch (kg) Mass at BOL (kg) Remarks
JCSAT-1 JSAT Corporation HS-393 1985 1989-03-06 Ariane 44LP Success 2,280 kg (5,030 lb) 1,346 kg (2,967 lb) First Japanese commercial satellite.[4][1]
JCSAT-2 JSAT Corporation HS-393 1985 1990-01-01 Commercial Titan III Success 2,280 kg (5,030 lb) 1,346 kg (2,967 lb) [4][1]
SBS 6 Satellite Business Systems HS-393 1985 1990-10-12 Ariane 44L Success 2,478 kg (5,463 lb) 1,500 kg (3,300 lb) Launched alongside Galaxy 6.[5][3]

See also

[edit]

References

[edit]
  1. ^ a b c d e f g h "JCSAT 1,2". Boeing Satellite Development Center. Archived from the original on 2010-02-07. Retrieved 2016-08-17.
  2. ^ a b Krebs, Gunter Dirk (2016-04-21). "Hughes: HS-393". Gunter's Space Page. Retrieved 2016-08-17.
  3. ^ a b c "SBS 6". Boeing Satellite Development Center. Archived from the original on 2010-02-07. Retrieved 2016-08-17.{{cite web}}: CS1 maint: bot: original URL status unknown (link)
  4. ^ a b c d e Krebs, Gunter Dirk (2016-08-17). "JCSat 1, 2". Gunter's Space Page. Retrieved 2016-07-20.
  5. ^ a b Krebs, Gunter Dirk (2016-08-17). "SBS 6". Gunter's Space Page. Retrieved 2016-07-20.
Retrieved from "https://en.wikipedia.org/enwiki/w/index.php?title=HS-393&oldid=989079643"