Wahana peluncur antariksa
Dalam penerbangan angkasa, kendaraan peluncur atau roket pembawa adalah roket yang digunakan untuk membawa muatan dari permukaan bumi ke luar angkasa. Sebuah sistem peluncuran termasuk kendaraan peluncur, panggung stage peluncuran dan infrastruktur lainnya. Biasanya muatan payload adalah buatan satelit yang ditempatkan ke orbit, tetapi beberapa spaceflights yang sub-orbital sementara yang lain memungkinkan pesawat ruang angkasa untuk keluar dari orbit Bumi seluruhnya. Sebuah kendaraan peluncuran yang membawa muatan pada lintasan suborbital sering disebut sounding roket.
Peluncuran kendaraan, kendaraan peluncur khususnya orbital, memiliki minimal dua tahap, tapi kadang-kadang sampai 4.
Jenis kendaraan peluncuran
Dengan platform peluncuran
- Darat : Spaceport dan silo rudal tetap (Strela) untuk dikonversi ICBM
- Laut : Platform tetap (San Marco), platform mobile (Sea Launch), kapal selam (Shtil', Volna ) untuk dikonversi SLBM
- Udara : Pesawat (Pegasus, Virgin Galactic LauncherOne, Stratolaunch Sistem), balon (ARCASPACE), JP Aerospace Orbital Ascender, proposal permanen pelabuhan ruang angkasa Buoyant
Dengan ukuran
Ada banyak cara untuk mengklasifikasikan ukuran kendaraan peluncuran. The Komisi Agustinus yang diciptakan untuk meninjau rencana untuk mengganti Space Shuttle , menggunakan skema klasifikasi berikut:
- Sounding rocket tidak dapat mencapai orbit dan hanya mampu spaceflight sub-orbital.
- Kendaraan peluncur small lift mampu mengangkut hingga 2.000 kg (£ 4400) dari muatan ke orbit bumi rendah (LEO).
- Kendaraan peluncur medium lift mampu mengangkut antara 2.000 sampai 20.000 kg (4.400 sampai £ 44.000) dari muatan ke LEO.
- Kendaraan peluncur heavy lift mampu mengangkut antara 20.000 sampai 50.000 kg (44.000 sampai £ 110.200) dari muatan ke LEO.
- Kendaraan peluncur super-heavy lift mampu mengangkut lebih dari 50.000 kg (110.200 £ +) dari muatan ke LEO.
Perbandingan Sistem orbital launch
Legend for orbit abbreviations in table:
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Legend for launch system status in below table: [under development] — [retired] — [operational]
Catatan
- ^ A full listing of the Ariane 5 launch history is in its main article.
- ^ Suborbital test in 1969, first orbital launch attempt in 1970
- ^ a b c d e f g h i j k l With 9.5 foot (2.9 metre) fairing
- ^ No flights planned, but 5 unsold heavies could be used.
- ^ Without Buran, and assuming payload providing orbital insertion
- ^ Encyclopedia Astronautica quotes Energia's "flyaway unit cost" at "$764 million in 1985 dollars". However the realistic exchange rate of Soviet currency was drastically different from the official conversion rate which had been set by decree at 0.8 Soviet rubles per US$1. Unofficially one US dollar in 1980s was in terms of purchasing power roughly equivalent to four Soviet rubles.
- ^ a b The US Space Shuttle Transportation System and the Soviet Energia-Buran system, consist of launch vehicle rockets and returnable spaceplane orbiter. Payload values listed here are for the mass of the payload in cargo bay of the spaceplanes, excluding the mass of the spaceplanes themselves.
- ^ Not including two launches made using the H-II/SSB and H-IIS configurations
- ^ Only launch failed to achieve orbit
- ^ Suborbital test flights in 1995, 1997 and 2002, no orbital launches attempted
- ^ The N1 rocket was initially designed for 75mt LEO capacity and launch attempts were made with this version, but there were studies to increase the payload capacity to 90—95 mt, if a liquid-hydrogen upper stage engine could be developed.
- ^ The Saturn V made 13 launches, 12 of which reached the correct orbits, and the other (Apollo 6) reached a different orbit than the one which had been planned; however, some mission objectives could still be completed; NASA, Saturn V News Reference, Appendix: Saturn V Flight History (1968). For more information, see the Saturn V article. The Saturn V launch record is usually quoted as having never failed, e.g. "The rocket was masterminded by Wernher Von Braun and did not fail in any of its flights", Alan Lawrie and Robert Godwin; Saturn, but the Apollo 6 launch should be considered a partial mission failure. The 13th launch of Saturn V was in special configuration (SA-513) with the Skylab.
- ^ Suborbital test flight in 2004, first orbital launch in 2006
- ^ A third rocket exploded before launch
- ^ First orbital launch attempt in 2005
- ^ a b Operated by Land Launch
- ^ Operated by Sea Launch
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LEO i = 51.6°, H = 200 km circular ... GTO (1800 m/s from GSO) i = 31.0°, Hp = 2100 km, Ha = 35,786 km
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