Wahana peluncur antariksa: Perbedaan antara revisi
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{{tanpa_referensi|date=31 Juli 2013}}
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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 [[satelit]] buatan 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.
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* '''Kendaraan peluncur super-heavy lift''' mampu mengangkut lebih dari 50.000 kg (110.200 £ +) dari muatan ke LEO.
== Perakitan ==
Setiap tahap roket individu umumnya dikumpulkan di lokasi pabrik dan dikirim ke lokasi peluncuran; jangka waktu perakitan kendaraan mengacu pada penggabungan tahap roket dengan muatan pesawat ruang angkasa dalam satu kendaraan perakitan yang dikenal sebagai kendaraan ruang angkasa.
Kendaraan tahap tunggal (seperti sounding roket), dan kendaraan multi tahap mulai yang lebih kecil dari berbagai ukuran, biasanya dapat dirakit secara vertikal, langsung di landasan peluncuran dengan mengangkat setiap tahap pesawat ruang angkasa dan secara berurutan di tempat dengan cara diderek.
== Perbandingan Sistem orbital launch ==
<small>'''Legend for orbit abbreviations in table:'''</small>
{{MultiCol}}
* GEO - [[Geostationary orbit]]
* GSO - [[Geosynchronous orbit]]
* GTO - [[Geostationary transfer orbit]]
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* HCO - [[Heliocentric orbit]]
* HEO - [[High Earth orbit]]
* LEO - [[Low Earth orbit]]
{{ColBreak}}
* MEO - [[Medium Earth orbit]]
* SSO - [[Sun-synchronous orbit]]
* TLI - [[Trans Lunar Injection]]
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|[[Simorgh (rocket)|Simorgh]]
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| [[Alliant Techsystems]] ([[Space Shuttle Solid Rocket Booster|SRBs]])<br>
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| [[Space Launch System
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| [[Alliant Techsystems]] ([[Space Shuttle Solid Rocket Booster|SRBs]])<br>
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|[[Satellite Launch Vehicle|SLV]]
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== Lihat pula ==
* [[Roket]]
* [[Mesin roket]]
* [[Pelabuhan angkasa]]
== Catatan ==
<references group="note">
<ref name="N3">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; [http://history.msfc.nasa.gov/saturn_apollo/documents/Flight_History.pdf NASA, Saturn V News Reference, Appendix: Saturn V Flight History (1968)]. For more information, see the [[Saturn V]] article.
<ref name="N4">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.</ref>
<ref name="N6">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.</ref>
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{{Reflist|colwidth=30em}}
== Pranala luar ==
* http://web.archive.org/web/20100805045010/http://cryptome.org/eyeball/satspy/satspy-eyeball.htm
* S. A. Kamal, A. Mirza: ''[http://www10.brinkster.com/drakamal/pub/confabst.htm#C66: The Multi-Stage-Q System and the Inverse-Q System for Possible application in SLV]'', Proc. IBCAST 2005, Volume 3, Control and Simulation, Edited by Hussain SI, Munir A, Kiyani J, Samar R, Khan MA, National Center for Physics, Bhurban, KP, Pakistan, 2006, pp 27–33 [http://www.ngds-ku.org/Papers/C66.pdf Free Full Text]
* S. A. Kamal: ''[http://www10.brinkster.com/drakamal/pub/confabst.htm#C67: Incorporating Cross-Range Error in the Lambert Scheme]'', Proc. 10th National Aeronautical Conf., Edited by Sheikh SR, Khan AM, Pakistan Air Force Academy, Risalpur, KP, Pakistan, 2006, pp 255–263 [http://www.ngds-ku.org/Papers/C67.pdf Free Full Text]
* S. A. Kamal: ''[http://www10.brinkster.com/drakamal/pub/confabst.htm#C72: The Multi-Stage-Lambert Scheme for Steering a Satellite-Launch Vehicle]'', Proc. 12th IEEE INMIC, Edited by Anis MK, Khan MK, Zaidi SJH, Bahria Univ., Karachi, Pakistan, 2008, pp 294–300 (invited paper) [http://www.ngds-ku.org/Papers/C72.pdf Free Full Text]
* S. A. Kamal: ''[http://www10.brinkster.com/drakamal/pub/confabst.htm#C56: Incompleteness of Cross-Product Steering and a Mathematical Formulation of Extended-Cross-Product Steering]'', Proc. IBCAST 2002, Volume 1, Advanced Materials, Computational Fluid Dynamics and Control Engineering, Edited by Hoorani HR, Munir A, Samar R, Zahir S, National Center for Physics, Bhurban, KP, Pakistan, 2003, pp 167–177 [http://www.ngds-ku.org/Papers/C56.pdf Free Full Text]
* S. A. Kamal: ''[http://www10.brinkster.com/drakamal/pub/confabst.htm#C55: Dot-Product Steering: A New Control Law for Satellites and Spacecrafts]'', Proc. IBCAST 2002, Volume 1, Advanced Materials, Computational Fluid Dynamics and Control Engineering, Edited by Hoorani HR, Munir A, Samar R, Zahir S, National Center for Physics, Bhurban, KP, Pakistan, 2003, pp 178–184 [http://www.ngds-ku.org/Papers/C55.pdf Free Full Text]
* S. A. Kamal: ''[http://www10.brinkster.com/drakamal/pub/confabst.htm#C64: Ellipse-Orientation Steering: A Control Law for Spacecrafts and Satellite-Launch Vehicles]'', Space Science and the Challenges of the twenty-First Century, ISPA-SUPARCO Collaborative Seminar, Univ. of Karachi, 2005 (invited paper)
* [https://archive.is/20130117062846/www.allvoices.com/contributed-news/7713795-christmas-turns-bad-for-isro-gslv-mission-fails Christmas turns bad for ISRO, GSLV mission fails.]
* http://themittani.com/features/satellite-extravaganza-us-vs-russia?page=0%2C1
* http://www.spacelaunchreport.com/dnepr.html
* http://www.astronautix.com/articles/costhing.htm Encyclopedia Astronautica: Cost, Price, and the Whole Darn Thing
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[[Kategori:Kendaraan peluncur luar angkasa]]
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