Comparison of medium lift launch systems: Difference between revisions
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For this article, medium-capacity launch systems are determined as being those capable of lifting at least 2,000 kg, but less than 10,000 kg to [[low Earth orbit]].{{Citation needed|date=January 2010}}<!-- Where is this defined? We should not be making this assertion in Wikipedia without a [[WP:RS|reliable secondary source]] [[WP:CS|citation]] for this claim --> |
For this article, medium-capacity launch systems are determined as being those capable of lifting at least 2,000 kg, but less than 10,000 kg to [[low Earth orbit]].{{Citation needed|date=January 2010}}<!-- Where is this defined? We should not be making this assertion in Wikipedia without a [[WP:RS|reliable secondary source]] [[WP:CS|citation]] for this claim --> |
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Revision as of 10:07, 9 December 2010
 | This article includes a list of general references, but it lacks sufficient corresponding inline citations. (July 2010) |
For this article, medium-capacity launch systems are determined as being those capable of lifting at least 2,000 kg, but less than 10,000 kg to low Earth orbit.[citation needed]
Retired, Operational and Under development
In the table below, systems that have not yet conducted a successful launch are listed in italics.
Legend for below table: [under development] — [retired or canceled] — [operational or available]
Proposed and design concepts
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Previously proposed or in development medium heavy lift launch system were:
- SpaceX Falcon 5 with 4,100 kg mass to LEO, previously proposed and later abandoned.[citation needed]
- Galaxy Express using US first stage and Japanese upper stage, 3,600 kg mass to LEO, in development up to 2010.[citation needed]
See also
- Comparison of small lift launch systems
- Comparison of mid-heavy lift launch systems
- Comparison of heavy lift launch systems
- Comparison of super heavy lift launch systems
Notes
- ^ The column launch record is defined here as the number of times the launch vehicle achieved a desired orbit (e.g. payload separation orbit, final mission orbit, etc.) with the payload intact, divided by the total number of attempted launches.
Launches into a useless orbit (i.e., an orbit from which the payload is unable to operate) are excluded from success, as is the case of a launch in which the payload was destroyed before the launch vehicle achieved a desired orbit. Success of the launches is determined by the performance of the launch vehicle itself and classification is not affected by subsequent failures of other elements like payload separation failure, payload propulsion failure (not reaching a desired payload final orbit from the desired transfer orbit), other payload failures (including re-entry failures). Other definitions of launch success may result in different values for the launch success record (see notes where applicable).
The total number of launch attempts includes development and test launches, if the launcher is in its complete expected configuration (and sub-orbital launches if so noted), but pre-launch failures are not included. - ^ The column active period is defined here as the years between first and final scheduled launch flights/attempts or years of development for launch vehicles that have made no launch attempts.
- ^ No flights planned, but 5 unsold heavies could be used.
- ^ a b Launch record numbers include sub-orbital flights.
- ^ Zenit utilized by Sea Launch.
- ^ a b Zenit utilized by Land Launch.
References
- ^ "Angaga Launch Vehicle Family". Khrunichev.
- ^ ULA Atlas V product page
- ^ a b European Space Directory 2006. Referenced in: Brian Harvey, The Rebirth of the Russian Space Program. p.296.
- ^ a b c d "PSLV variants capability". ISRO. Retrieved 15 May 2010.
- ^ "Soyuz-U" launch vehicle State Research and Production Space-Rocket Center "TsSKB-Progress"
- ^ "Soyuz-FG" launch vehicle State Research and Production Space-Rocket Center "TsSKB-Progress"
- ^ a b "Taurus II User's Manual, Rev. 1.3" (PDF). Orbital. April 2010.
{{cite web}}: Text "accessed 2010-11-11" ignored (help)
