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|diameter = {{convert|8.41|m|abbr=on|ft|}}
|diameter = {{convert|8.41|m|abbr=on|ft|}}
|mass = {{convert|2061689|-|2177650|kg|abbr=on|lb}} <!-- J-130 GLOW to J-246 GLOW -->
|mass = {{convert|2061689|-|2177650|kg|abbr=on|lb}} <!-- J-130 GLOW to J-246 GLOW -->
|stages = One common core stage with optional Jupiter Upper Stage (similar to [[Earth Departure Stage]] (EDS))
|stages = One common core stage with optional Jupiter Upper Stage (similar role to [[Earth Departure Stage]] (EDS))
<!----Payloads (optional)---->
<!----Payloads (optional)---->
|capacities = <!--insert one of the following templates for each payload:-->
|capacities = <!--insert one of the following templates for each payload:-->

Revision as of 05:30, 20 July 2009

DIRECT v3.0 - Jupiter Launch Vehicle family (J-130 / J-246)[1]
DIRECT v2.0 illustration demonstrating commonality of components
FunctionLaunch vehicle system proposal supporting the Vision for Space Exploration
ManufacturerNone
Country of originUnited States
Size
Height70.9–92.3 m (233–303 ft)
Diameter8.41 m (27.6 ft)
Mass2,061,689–2,177,650 kg (4,545,246–4,800,896 lb)
StagesOne common core stage with optional Jupiter Upper Stage (similar role to Earth Departure Stage (EDS))
Capacity
Payload to LEO
Mass60,282 kg ([convert: unit mismatch]) (J-130 CLV, 100 x 100 nmi, 51.6° inclination)
Payload to LEO
Mass91,670 kg ([convert: unit mismatch]) (J-246 EDS, 130 x 130 nmi, 29° inclination)
Associated rockets
FamilyShuttle Derived Launch Vehicle
ComparableNational Launch System
Launch history
StatusProposal
Launch sitesLC-39, Kennedy Space Center
Total launches0
Type of passengers/cargoOrion Crew Exploration Vehicle
Lunar Surface Access Module
Jupiter Upper Stage (similar to EDS)
Boosters (Jupiter) – Shuttle RSRM
No. boosters2
Powered by1 RSRM
Maximum thrust12,868–13,977 kN (2,893,000–3,142,000 lbf) (sea level - vacuum)
Total thrust25,737–27,955 kN (5,786,000–6,285,000 lbf) (sea level - vacuum)
Specific impulse237.0 - 269.1 sec (sea level - vacuum)
Burn time123.8 sec
PropellantAPCP, PBAN
First stage (J-130) – Common core stage
Diameter8.41 m (27.6 ft)
Powered by3 SSME-Block-II
Maximum thrust5,235–6,550 kN (1,177,000–1,472,000 lbf) (sea level - vacuum; three engines combined)
Specific impulse361.4 - 452.2 sec (sea level - vacuum)
Burn time524.5 sec
PropellantLOX/LH2
First stage (J-246) – Common core stage
Diameter8.41 m (27.6 ft)
Powered by4 SSME-Block-II
Maximum thrust6,981–87,334 kN (1,569,000–19,633,000 lbf) (sea level - vacuum; four engines combined)
Specific impulse361.4 - 452.2 sec (sea level - vacuum)
Burn time384.1 sec
PropellantLOX/LH2
Second stage (J-246) – Jupiter Upper Stage
Diameter8.41 m (27.6 ft)
Powered by6 RL10B-2
Maximum thrust661 kN (149,000 lbf) (vacuum; six engines combined)
Specific impulse459 sec (vacuum)
Burn time609.9 sec
PropellantLOX/LH2
[edit on Wikidata]



 |boosters = 2
 |boostername=Shuttle SRB
 |boosterengines = 1 solid rocket per booster
 |boosterSI = 237.0 - 269.1 sec (sea level - vacuum)
 |boostertime = 123.8 sec
 |boosterfuel = solid
 |stage1name = Core Stage
based on Shuttle External Tank
 |stage1engines =(3 SSME-Block-2 regeneratively-cooled)
 |stage1SI = 361.4 - 452.2 sec (sea level - vacuum)
 |stage1time = 524.5 sec
 |stage1fuel =LOX/LH2
 |stage1diff = Jupiter-130 Variant
 |stage1aname = Core Stage
based on Shuttle External Tank
 |stage1aengines =(4 SSME-Block-2 regeneratively-cooled)
 |stage1aSI = 361.4 - 452.2 sec (sea level - vacuum)
 |stage1atime = 384.1 sec
 |stage1afuel =LOX/LH2
 |stage1adiff = Jupiter-246 Variant
 |stage2name = J-246 Jupiter Upper Stage
 |stage2engines =6 RL-10B-2
 |stage2thrust = 661 kN (149,000 lbf) (vacuum; six engines combined)
 |stage2SI = 459.0 sec (vacuum)
 |stage2time = 609.9 sec
 |stage2fuel = LOX/LH2
 |stage2diff = Jupiter-246 Variant


DIRECT - Original DIRECT v2.0 Jupiter Launch Vehicle specs.
FunctionPartially re-usable launch vehicle
ManufacturerNone
Country of originUnited States
Size
Height80.4 to 108.1m
Diameter8.41 m (identical to Shuttle External Tank) (27ft 7in)
Mass2,033,472 to 2,390,708 kg
StagesOne core stage with optional upper stage
Capacity
Payload to LEO41,121 to 111,254 kg (90,655 to 220,746 lb)
Launch history
StatusProposal
Launch sitesLC-39, Kennedy Space Center
Type of passengers/cargoOrion
EDS
LSAM
Boosters - Shuttle SRB
No. boosters2
Engines1 solid
Thrust13,982 kN (3,142,302 lbf)
Specific impulse269.1 sec
Burn time123.8 seconds
Propellantsolid
First stage (Jupiter-120 Variant) - Core Stage
based on Shuttle External Tank
Engines(2 RS-68 "Ablative")
Thrust6,686 kN (1,502,000 lbf)
Specific impulse409.0 sec
Burn time494.8 sec
PropellantLOX/LH2
First stage (Jupiter-232 Variant) - Core Stage
based on Shuttle External Tank
Engines(3 RS-68B "Ablative")
Thrust10,639 kN (2,391,000 lbf)
Specific impulse414.2 sec
Burn time279.8 sec
PropellantLOX/LH2
Second stage (Jupiter-232 Variant) J-232 EDS
Engines2 J-2X
Thrust2,616 kN (588,000 lbf)
Specific impulse448.0 sec
Burn time423.9 sec
PropellantLOX/LH2
[edit on Wikidata]

Here is some text

Test of references.[1] Maypraps they don't work between an infobox[2] and the main text[3]. Seems a pity.

References

  1. ^ a b [example.com "foobar"]. {{cite web}}: Check |url= value (help)
  2. ^ Cite error: The named reference j_130 was invoked but never defined (see the help page).
  3. ^ Cite error: The named reference j_246 was invoked but never defined (see the help page).
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