User:Fotoguzzi: Difference between revisions

DIRECT - Original DIRECT v2.0 Jupiter Launch Vehicle specs.
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
	[edit on Wikidata]

DIRECT v3.0 - Jupiter Launch Vehicle family (J-130 / J-246)^[1]
	DIRECT v2.0 illustration demonstrating commonality of components
Function	Alternative launch vehicle system to Ares I and Ares V 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 core stage with optional Jupiter Upper Stage (similar to Earth Departure Stage (EDS))
Capacity
Payload to LEO
Mass	60282 kg (J-130 Crew, 100 x 100 nmi, 51.6°)
Payload to LEO
Mass	91670 kg (J-246 EDS, 130 x 130 nmi, 29°)
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; LSAM; 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 (Jupiter 130) – Common core stage
Diameter	8.41
Powered by	3 SSME-Block-II -->
Maximum thrust	5,234–6,550 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 (Jupiter 246) – Common core stage
Diameter	8.41
Powered by	4 SSME-Block-II -->
Maximum thrust	6,980.6–8,733.6 kN (1,569,300–1,963,400 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 (Jupiter 246) – Jupiter Upper Stage
Diameter	8.41
Powered by	6 RL10B-2 -->
Maximum thrust	660.6 kN (148,500 lbf) (vacuum; six engines combined)
Specific impulse	361.4 - 452.2 sec (sea level - vacuum)
Burn time	384.1 sec
Propellant	LOX/LH2
	[edit on Wikidata]

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Revision as of 03:01, 20 July 2009

 |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

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

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

[direct_v3_specs-1] [example.com "foobar"]. {{cite web}}: Check |url= value (help)

[j_130-2] Cite error: The named reference j_130 was invoked but never defined (see the help page).

[j_246-3] Cite error: The named reference j_246 was invoked but never defined (see the help page).

[1]

[2]

[3]

@@ Line 64: / Line 64: @@
     |diff       =  Jupiter 130 <!--variant of rocket this is used on, optional-->
     |stageno    =  First <!--position of stage in rocket, spelled out (eg. First, Second, etc), required-->
-    |name       =  Common core stage - Liquid <!--name of the stage/booster, optional-->
+    |name       =  Common core stage <!--name of the stage/booster, optional-->
     |number     =  <!--number of boosters, required if type = booster-->
     |length     =  <!--length of a single booster/stage in metres, optional, use {{convert}}-->
@@ Line 70: / Line 70: @@
     |empty      =  <!--empty mass of a single booster/stage in kilograms, optional, use {{convert}}-->
     |gross      =  <!--gross (fuelled) mass of a single booster/stage, optional-->
-    |engines    =  3 [[SSME]]s <!--number and type of engines used on each individual booster/stage, required-->
+    |engines    =  3 [[SSME]]-Block-II <!--number and type of engines used on each individual booster/stage, required-->
 <!--
     |thrust     =  {{convert|1745|-|2183|kN|abbr=on|lbf}} (sea level - vacuum) <!--thrust provided by a single booster/stage in kN, required, use {{convert}}-->
 -->
-    |thrust     =  {{convert|5234|-|6550|kN|abbr=on|lbf}} (sea level - vacuum; total for three engines) <!--total thrust for all boosters in kN, optional, use {{convert}}-->
+    |thrust     =  {{convert|5234|-|6550|kN|abbr=on|lbf}} (sea level - vacuum; three engines combined) <!--total thrust for all boosters in kN, optional, use {{convert}}-->
     |SI         =  361.4 - 452.2 sec (sea level - vacuum) <!--specific impulse of an individual booster/stage, in secs, optional-->
     |burntime   =  524.5 sec <!--burn time, required-->
@@ Line 83: / Line 83: @@
     |diff       =  Jupiter 246 <!--variant of rocket this is used on, optional-->
     |stageno    =  First <!--position of stage in rocket, spelled out (eg. First, Second, etc), required-->
-    |name       =  Common core stage - Liquid <!--name of the stage/booster, optional-->
+    |name       =  Common core stage <!--name of the stage/booster, optional-->
     |number     =  <!--number of boosters, required if type = booster-->
     |length     =  <!--length of a single booster/stage in metres, optional, use {{convert}}-->
@@ Line 89: / Line 89: @@
     |empty      =  <!--empty mass of a single booster/stage in kilograms, optional, use {{convert}}-->
     |gross      =  <!--gross (fuelled) mass of a single booster/stage, optional-->
-    |engines    =  4 [[SSME]]s <!--number and type of engines used on each individual booster/stage, required-->
+    |engines    =  4 SSME-Block-II <!--number and type of engines used on each individual booster/stage, required-->
 <!--
     |thrust     =  {{convert|1745|-|2183|kN|abbr=on|lbf}} (sea level - vacuum) <!--thrust provided by a single booster/stage in kN, required, use {{convert}}-->
 -->
     |thrust      =  {{convert|6980.6|-|8733.6|kN|abbr=on|lbf}} (sea level - vacuum; four engines combined) <!--total thrust for all boosters in kN, optional, use {{convert}}-->
+    |SI         =  361.4 - 452.2 sec (sea level - vacuum) <!--specific impulse of an individual booster/stage, in secs, optional-->
+    |burntime   =  384.1 sec <!--burn time, required-->
+    |fuel       =  [[LOX]]/[[LH2]] <!--fuel used in stage/boosters, required-->
+  }}
+  {{Infobox Rocket/Stage
+    |type       =  stage <!--booster or stage-->
+    |diff       =  Jupiter 246 <!--variant of rocket this is used on, optional-->
+    |stageno    =  Second <!--position of stage in rocket, spelled out (eg. First, Second, etc), required-->
+    |name       =  Jupiter Upper Stage <!--name of the stage/booster, optional-->
+    |number     =  <!--number of boosters, required if type = booster-->
+    |length     =  <!--length of a single booster/stage in metres, optional, use {{convert}}-->
+    |diameter   =  8.41 <!--diameter of a single booster/stage, optional in metres, use {{convert}}-->
+    |empty      =  <!--empty mass of a single booster/stage in kilograms, optional, use {{convert}}-->
+    |gross      =  <!--gross (fuelled) mass of a single booster/stage, optional-->
+    |engines    =  6 [[RL10#Current_designRL10|RL10B-2]] <!--number and type of engines used on each individual booster/stage, required-->
+<!--
+    |thrust     =  {{convert|110.1|kN|abbr=on|lbf}} (vacuum) <!--thrust provided by a single booster/stage in kN, required, use {{convert}}-->
+-->
+    |thrust     =  {{convert|660.6|kN|abbr=on|lbf}} (vacuum; six engines combined) <!--total thrust for all boosters in kN, optional, use {{convert}}-->
     |SI         =  361.4 - 452.2 sec (sea level - vacuum) <!--specific impulse of an individual booster/stage, in secs, optional-->
     |burntime   =  384.1 sec <!--burn time, required-->