User:Fotoguzzi
 DIRECT v2.0 illustration demonstrating commonality of components | |
| Function | Launch vehicle system proposal supporting the Vision for Space Exploration |
|---|---|
| Manufacturer | None |
| Country of origin | United States |
| Size | |
| Height | 70.9–92.3 m (233–303 ft) |
| Diameter | 8.41 m (27.6 ft) |
| Mass | 2,061,689–2,177,650 kg (4,545,246–4,800,896 lb) |
| Stages | One common core stage with optional Jupiter Upper Stage (similar role to Earth Departure Stage (EDS)) |
| Capacity | |
| Payload to LEO | |
| Mass | 60,282 kg (132,899 lb) (J-130, 100 x 100 nmi, 51.6° inclination) |
| Payload to LEO | |
| Mass | 91,670 kg (202,100 lb) (J-246, 130 x 130 nmi, 29° inclination) |
| Associated rockets | |
| Family | Shuttle Derived Launch Vehicle |
| Comparable | National Launch System |
| Launch history | |
| Status | Proposal |
| Launch sites | LC-39, Kennedy Space Center |
| Total launches | 0 |
| Type of passengers/cargo | Orion Crew Exploration Vehicle Altair Lunar Surface Access Module Jupiter Upper Stage (similar to EDS) |
| Boosters (Jupiter) – Shuttle RSRM | |
| No. boosters | 2 |
| Powered by | 1 RSRM |
| Maximum thrust | 12,868–13,977 kN (2,893,000–3,142,000 lbf) (sea level - vacuum) |
| Total thrust | 25,737–27,955 kN (5,786,000–6,285,000 lbf) (sea level - vacuum) |
| Specific impulse | 237.0 - 269.1 sec (sea level - vacuum) |
| Burn time | 123.8 sec |
| Propellant | APCP, PBAN |
| First stage (J-130) – Common core stage | |
| Diameter | 8.41 m (27.6 ft) |
| Powered by | 3 SSME-Block-II |
| Maximum thrust | 5,235–6,550 kN (1,177,000–1,472,000 lbf) (sea level - vacuum; three engines combined) |
| Specific impulse | 361.4 - 452.2 sec (sea level - vacuum) |
| Burn time | 524.5 sec |
| Propellant | LOX/LH2 |
| First stage (J-246) – Common core stage | |
| Diameter | 8.41 m (27.6 ft) |
| Powered by | 4 SSME-Block-II |
| Maximum thrust | 6,981–87,334 kN (1,569,000–19,633,000 lbf) (sea level - vacuum; four engines combined) |
| Specific impulse | 361.4 - 452.2 sec (sea level - vacuum) |
| Burn time | 384.1 sec |
| Propellant | LOX/LH2 |
| Second stage (J-246) – Jupiter Upper Stage | |
| Diameter | 8.41 m (27.6 ft) |
| Powered by | 6 RL10B-2 |
| Maximum thrust | 661 kN (149,000 lbf) (vacuum; six engines combined) |
| Specific impulse | 459 sec (vacuum) |
| Burn time | 609.9 sec |
| Propellant | LOX/LH2 |
|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
| |
| Function | Partially re-usable launch vehicle |
|---|---|
| Manufacturer | None |
| Country of origin | United States |
| Size | |
| Height | 80.4 to 108.1m |
| Diameter | 8.41 m (identical to Shuttle External Tank) (27ft 7in) |
| Mass | 2,033,472 to 2,390,708 kg |
| Stages | One core stage with optional upper stage |
| Capacity | |
| Payload to LEO | 41,121 to 111,254 kg (90,655 to 220,746 lb) |
| Launch history | |
| Status | Proposal |
| Launch sites | LC-39, Kennedy Space Center |
| Type of passengers/cargo | Orion EDS LSAM |
| Boosters - Shuttle SRB | |
| No. boosters | 2 |
| Engines | 1 solid |
| Thrust | 13,982 kN (3,142,302 lbf) |
| Specific impulse | 269.1 sec |
| Burn time | 123.8 seconds |
| Propellant | solid |
| First stage (Jupiter-120 Variant) - Core Stage based on Shuttle External Tank | |
| Engines | (2 RS-68 "Ablative") |
| Thrust | 6,686 kN (1,502,000 lbf) |
| Specific impulse | 409.0 sec |
| Burn time | 494.8 sec |
| Propellant | LOX/LH2 |
| First stage (Jupiter-232 Variant) - Core Stage based on Shuttle External Tank | |
| Engines | (3 RS-68B "Ablative") |
| Thrust | 10,639 kN (2,391,000 lbf) |
| Specific impulse | 414.2 sec |
| Burn time | 279.8 sec |
| Propellant | LOX/LH2 |
| Second stage (Jupiter-232 Variant) J-232 EDS | |
| Engines | 2 J-2X |
| Thrust | 2,616 kN (588,000 lbf) |
| Specific impulse | 448.0 sec |
| Burn time | 423.9 sec |
| Propellant | LOX/LH2 |
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Test of references.[1] Maypraps they don't work between an infobox[2] and the main text[3]. Seems a pity.