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[[Berkas:Apollo 11 Saturn V lifting off on July 16, 1969.jpg|jmpl|250px]]
{{tanpa_referensi|date=31 Juli 2013}}
'''Kendaraan peluncur''' biasanya adalah [[kendaraan]] bertenaga [[roket]] yang dirancang untuk membawa muatan (pesawat antariksa berawak maupun kargo tidak beraak atau [[satelit]]) dari permukaan Bumi atau atmosfer bawah ke luar angkasa. Bentuk yang paling umum adalah [[roket multitahap]] berbentuk rudal balistik, tetapi istilahnya lebih umum dan juga mencakup kendaraan seperti [[Pesawat Ulang Alik]]. Sebagian besar kendaraan peluncur beroperasi dari [[landasan peluncuran]], didukung oleh [[Pusat kendali misi|pusat kendali]] peluncuran dan sistem seperti perakitan dan pengisian bahan bakar kendaraan. Kendaraan peluncur direkayasa dengan aerodinamika dan teknologi canggih, yang berkontribusi pada biaya operasi yang tinggi.
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.
 
Kendaraan peluncur orbital harus mengangkat muatannya setidaknya ke batas ruang angkasa, sekitar 150 km (93 mil) dan mempercepatnya ke kecepatan horizontal setidaknya 7.814 m/s (17.480 mph). Kendaraan suborbital meluncurkan muatannya ke kecepatan yang lebih rendah atau diluncurkan pada sudut elevasi yang lebih besar dari horizontal.
Peluncuran kendaraan, kendaraan peluncur khususnya orbital, memiliki minimal dua tahap, tapi kadang-kadang sampai 4.
 
Kendaraan peluncur orbital praktis menggunakan [[propelan]] [[kimia]] seperti [[bahan bakar padat]], [[Kriogenik (bahan bakar)|kriogenik]] temperatur rendah [[hidrogen cair]], [[minyak tanah]], [[metana cair]], [[oksigen cair]], atau propelan [[Hipergolik (propelan)|hipergolik]] yang mudah terbakar karena reaksi.
==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.
 
=== Kendaraan peluncur methalox ===
==Perbandingan Sistem orbital launch==
Penggunaan metana cair dan oksigen cair sebagai propelan terkadang disebut propulsi methalox. Metana cair memiliki impuls spesifik yang lebih rendah daripada hidrogen cair, tetapi lebih mudah disimpan karena titik didih dan kepadatannya yang lebih tinggi, serta tidak mudah rapuh. Metana cair juga meninggalkan lebih sedikit residu di mesin dibandingkan dengan minyak tanah, yang bermanfaat untuk penggunaan ulang.
<small>'''Legend for orbit abbreviations in table:'''</small>
 
Metana cair yang dimurnikan dan juga [[LNG]] digunakan sebagai bahan bakar [[propelan]] [[Kriogenik (bahan bakar)|kriogenik]] [[temperatur]] rendah [[roket]], bila dikombinasikan dengan [[oksigen cair]], seperti pada mesin [[TQ-12]], [[BE-4]], [[SpaceX Raptor|Raptor]], dan [[YF-215]]. Karena kesamaan antara metana dan LNG, mesin-mesin tersebut umumnya dikelompokkan bersama di bawah istilah [[methalox]].
 
Sebagai bahan bakar roket cair, kombinasi metana/oksigen cair menawarkan keuntungan dibandingkan kombinasi [[minyak tanah]]/oksigen cair, atau [[kerolox]], dalam menghasilkan molekul-molekul gas buang kecil, mengurangi [[kokas]] atau pengendapan [[jelaga]] pada komponen-komponen mesin. Metana lebih mudah disimpan daripada [[hidrogen]] karena [[titik didih]] dan kepadatannya yang lebih tinggi, serta tidak adanya kerapuhan hidrogen. [[Berat molekul]] gas buang yang lebih rendah juga meningkatkan [[Fraksi mol|fraksi]] [[energi panas]] yang berupa [[energi kinetik]] yang tersedia untuk [[Propulsi wahana antariksa|propulsi]], sehingga meningkatkan [[impuls spesifik]] roket. Dibandingkan dengan hidrogen cair, energi spesifik metana lebih rendah tetapi kekurangan ini diimbangi oleh kepadatan dan kisaran suhu metana yang lebih besar, yang memungkinkan tangki yang lebih kecil dan lebih ringan untuk [[massa]] bahan bakar tertentu. Metana cair memiliki kisaran suhu (91–112 K) yang hampir sesuai dengan oksigen cair (54–90 K). Bahan bakar ini saat ini digunakan dalam kendaraan peluncur operasional seperti [[Zhuque-2]] dan [[Vulcan (roket)|Vulcan]] serta peluncur yang sedang dikembangkan seperti Starship, Neutron, dan [[Terran R]].
 
Karena keuntungan yang ditawarkan bahan bakar metana, beberapa penyedia peluncuran ruang angkasa swasta bertujuan untuk mengembangkan sistem peluncuran berbasis metana selama tahun 2010-an dan 2020-an. Persaingan antarnegara ini dijuluki sebagai Perlombaan Methalox menuju Orbit, dengan roket methalox [[Zhuque-2]] milik LandSpace menjadi yang pertama mencapai orbit.
 
Pada Januari 2024, dua roket berbahan bakar metana telah mencapai orbit. Beberapa roket lainnya sedang dalam tahap pengembangan dan dua upaya peluncuran orbital gagal:
 
* Zhuque-2 berhasil mencapai orbit pada penerbangan keduanya pada 12 Juli 2023, menjadi roket berbahan bakar metana pertama yang berhasil melakukannya. Roket ini gagal mencapai orbit pada penerbangan perdananya pada 14 Desember 2022. Roket yang dikembangkan oleh LandSpace ini menggunakan mesin TQ-12.
* Vulcan Centaur berhasil mencapai orbit pada percobaan pertamanya, yang disebut Cert-1, pada 8 Januari 2024. Roket yang dikembangkan oleh [[United Launch Alliance]] ini menggunakan mesin [[BE-4]] milik [[Blue Origin]], meskipun tahap kedua menggunakan hydrolox RL10.
* Terran 1 mengalami kegagalan dalam upaya peluncuran orbital pada penerbangan perdananya pada 22 Maret 2023. Roket yang dikembangkan oleh Relativity Space ini menggunakan mesin Aeon 1.
* Starship mencapai orbit transatmosfer pada penerbangan ketiganya pada 14 Maret 2024, setelah dua kali gagal. Roket yang dikembangkan oleh SpaceX ini menggunakan mesin Raptor.
 
[[SpaceX]] mengembangkan mesin Raptor untuk wahana peluncur superberat Starship. Mesin ini telah digunakan dalam uji terbang sejak 2019. SpaceX sebelumnya hanya menggunakan RP-1/LOX pada mesin mereka. Blue Origin mengembangkan mesin BE-4 LOX/LNG untuk New Glenn dan United Launch Alliance [[Vulcan Centaur]]. BE-4 akan menghasilkan daya dorong sebesar 2.400 kN (550.000 lbf). Dua mesin penerbangan telah dikirim ke ULA pada pertengahan tahun 2023.
 
Pada bulan Juli 2014, Firefly Space Systems mengumumkan rencana untuk menggunakan bahan bakar metana untuk kendaraan peluncur satelit kecil mereka, Firefly Alpha dengan desain mesin aerospike.
 
[[ESA]] sedang mengembangkan mesin roket methalox Prometheus 980kN yang diuji coba pada tahun 2023.
 
=== Tahap atas ===
[[Berkas:Centaur upper stage being lifted.jpg|jmpl|Single Engine Centaur (SEC) stage ]]
[[Berkas:Centaur-propellant-system.jpg|jmpl|Centaur-propellant-system.]]
[[Berkas:Titan 3E Centaur launches Voyager 2.jpg|jmpl|Voyager 2 yang menaiki wahana peluncur Titan III-Centaur lepas landas pada tanggal 20 Agustus 1977. Voyager 2 adalah satelit ilmiah yang mempelajari planet luar Jupiter, Saturnus, Uranus, dan Neptunus.]]
[[Berkas:SHUTTLE-CENTAUR.JPG|jmpl|Wahana antariksa Centaur dan Ulysses dari Space Shuttle Cargo Bay]]
[[Berkas:LCROSS Centaur 2.jpg|jmpl|LCROSS Centaur 2.]]
[[Berkas:Payload fairing jettison.jpg|jmpl|Selama penerbangan Centaur Stage dengan satelit Intelsat IV di atasnya, fairing muatan dibuang.]]
[[Roket tahap atas]] atau Tahap atas saja adalah [[roket]] tahap sekunder dalam [[roket multi tahap]] yang mendorong [[Muatan (transportasi)|muatan]] ke [[orbit]] atau pada lintasan antarplanet. Tahap ini diaktifkan setelah tahap primer terpisah. Tahap atas mendorong muatan ke orbit yang lebih tinggi atau pada lintasan antarplanet daripada yang dapat dilakukan oleh pendorong roket sendiri. Tahap atas sering kali dapat retart menghidupkan kembali mesinnya beberapa kali dan dapat diatur thortle daya dorongnya saat berada di luar angkasa untuk penempatan pesawat ruang angkasa yang presisi ke orbit. Beberapa tahap atas tetap melekat pada muatannya dan menyediakan layanan seperti daya, komunikasi, dan kendali arah.
 
==== Muatan ====
Untuk roket, muatan dapat berupa [[satelit]], [[Kuar antariksa|probe antariksa]], atau [[wahana antariksa]] yang membawa manusia, hewan, atau kargo. Salah satu manfaat utama muatan adalah memungkinkan kita untuk mengumpulkan data dan melakukan eksperimen di lingkungan yang tidak dapat diakses oleh manusia. Dengan mengirimkan muatan ke luar angkasa, kita dapat mempelajari tentang benda-benda langit lainnya dan kondisi yang ada di ruang hampa.
 
=== Centaur (tahapan roket) ===
[[Centaur (tahapan roket)|Centaur]] adalah keluarga roket [[tahap atas]] yang telah digunakan sejak 1962. Saat ini diproduksi oleh penyedia layanan peluncuran AS [[United Launch Alliance]], dengan satu versi utama aktif dan satu versi dalam pengembangan. Common Centaur/Centaur III berdiameter 3,05 m (10,0 kaki) terbang sebagai tingkat atas kendaraan peluncur [[Atlas V]], dan Centaur V berdiameter 5,4 m (18 kaki) telah dikembangkan sebagai tingkat atas roket [[Vulcan (roket)|Vulcan]] baru ULA. Centaur adalah tingkat roket pertama yang menggunakan propelan hidrogen cair (LH 2) dan oksigen cair (LOX), kombinasi propelan berenergi tinggi yang ideal untuk tingkat atas tetapi memiliki kesulitan penanganan yang signifikan. Centaur adalah tahap atas energi tinggi pertama di dunia, pembakaran hidrogen cair (LH2) dan [[oksigen cair]] (LOX), dan telah memungkinkan peluncuran beberapa misi ilmiah paling penting [[Badan Penerbangan dan Antariksa Amerika Serikat|NASA]].
 
Common Centaur dibangun di sekitar tangki propelan balon bertekanan baja tahan karat yang distabilkan dengan dinding setebal 0,51 mm (0,020 in). Ia dapat mengangkat muatan hingga 19.000 kg (42.000 lb). Dinding tipis meminimalkan massa tangki, memaksimalkan kinerja keseluruhan panggung tahapan.
 
Sekat umum memisahkan tangki LOX dan LH 2, yang selanjutnya mengurangi massa tangki. Sekat ini terbuat dari dua kulit baja tahan karat yang dipisahkan oleh sarang lebah fiberglass. Sarang lebah fiberglass meminimalkan perpindahan panas antara LH 2 yang sangat dingin dan LOX yang kurang dingin.
 
Sistem propulsi utamanya terdiri dari satu atau dua mesin Aerojet Rocketdyne [[RL10]]. Tahap ini mampu melakukan hingga dua belas kali [[restart]], dibatasi oleh propelan, masa pakai orbital, dan persyaratan misi. Dikombinasikan dengan isolasi tangki propelan, hal ini memungkinkan Centaur untuk melakukan peluncuran selama beberapa jam dan beberapa pembakaran mesin yang diperlukan pada [[penyisipan orbital]] yang kompleks.
 
[[Sistem kendali reaksi]] ([[RCS]]) juga menyediakan ullage dan terdiri dari dua puluh pendorong monopropelan hidrazin yang terletak di sekitar panggung dalam dua pod pendorong 2 dan empat pod pendorong 4. Untuk propelan, 150 kg (340 lb) [[Hidrazina|Hidrazin]] disimpan dalam sepasang tangki kandung kemih dan diumpankan ke pendorong RCS dengan gas [[helium]] bertekanan, yang juga digunakan untuk menyelesaikan beberapa fungsi mesin utama.
 
Pada tahun 2024, dua varian Centaur digunakan: Centaur III pada Atlas V, dan Centaur V pada Vulcan Centaur. Semua varian Centaur lainnya telah dihentikan.
 
Mesin Centaur telah berevolusi dari waktu ke waktu, dan tiga versi (RL10A-4-2, RL10C-1 dan RL10C-1-1) digunakan pada tahun 2024 (lihat tabel di bawah). Semua versi menggunakan hidrogen cair dan oksigen cair.
 
== Jenis kendaraan peluncuran ==
Peluncuran kendaraan, kendaraan peluncur khususnya orbital, memiliki minimal dua tahap, tetapi kadang-kadang sampai 4.
=== 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:
* '''Roket sonda''' tidak dapat mencapai orbit dan hanya mampu spaceflight sub-orbital.
* '''Kendaraan peluncur angkut ringan''' mampu mengangkut hingga 2.000&nbsp;kg (£ 4400) dari muatan ke orbit bumi rendah (LEO).
* '''Kendaraan peluncur angkut medium''' mampu mengangkut antara 2.000 sampai 20.000&nbsp;kg (4.400 sampai £ 44.000) dari muatan ke LEO.
* '''Kendaraan peluncur angkut berat''' mampu mengangkut antara 20.000 sampai 50.000&nbsp;kg (44.000 sampai £ 110.200) dari muatan ke LEO.
* '''Kendaraan peluncur angkut superberat''' mampu mengangkut lebih dari 50.000&nbsp;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 peluncur orbital ==
<small>'''Keterangan singkatan orbit dalam tabel:'''</small>
{{MultiCol}}
* GEO - [[GeostationaryOrbit orbitgeostasioner]]
* GSO - [[GeosynchronousOrbit orbitgeosinkron]]
* GTO - [[GeostationaryOrbit transfer orbitgeostasioner]]
{{ColBreak}}
* HCO - [[HeliocentricOrbit orbitheliosentris]]
* HEO - [[HighOrbit EarthBumi orbittinggi]]
* LEO - [[LowOrbit EarthBumi orbitrendah]]
{{ColBreak}}
* MEO - [[MediumOrbit EarthBumi orbitmenengah]]
* SSO - [[Sun-synchronousOrbit sinkron orbitMatahari]]
* TLI - [[Trans LunarInjeksi Injectiontranslunar]]
{{Multicol-end}}
 
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|{{RUS}}
|[[Khrunichev]]
|{{nts|3800}}<ref name="khru_angara">{{cite web|url=http://www.khrunichev.ru/main.php?id=44|title=Angaga Launch Vehicle Family|publisher=Khrunichev|access-date=2013-11-15|archive-date=2017-01-18|archive-url=https://web.archive.org/web/20170118135419/http://www.khrunichev.ru/main.php?id=44|dead-url=yes}}</ref>
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| [[Khrunichev]]
| {{nts|14600}}<ref name="khru_angara"/>
| {{nts|2400}}–3,600 to GTO<ref name="khru_angara">{{cite web|url=http://www.khrunichev.ru/main.php?id=44|title=Angara Launch Vehicle Family|publisher=Khrunichev}}</ref>
| {{ntsh|70}} €50 (US$70)<ref name="esd2006">European Space Directory 2006. Referenced in: Brian Harvey, The Rebirth of the Russian Space Program. p.296.</ref>
|
Baris 96 ⟶ 153:
| {{RUS}}
| [[Khrunichev State Research and Production Space Center|Khrunichev]]
| {{nts|24500}} (63°) <ref name="rus">[http://www.khrunichev.ru/main.php?id=44 Семейство ракет-носителей «Ангара»] {{Webarchive|url=https://web.archive.org/web/20170118135419/http://www.khrunichev.ru/main.php?id=44 |date=2017-01-18 }}, date unknown, Retrieved 2010-08-09.</ref><ref name="eng">{{cite web|url=http://www.russianspaceweb.com/angara7.html |title=The Angara-7 rocket |publisher=Russianspaceweb.com |date= |accessdate=2012-07-25}}</ref>
| {{nts|24500}} (63°) <ref name="rus">
[http://www.khrunichev.ru/main.php?id=44 Семейство ракет-носителей «Ангара»], date unknown, Retrieved 2010-08-09.</ref><ref name="eng">{{cite web|url=http://www.russianspaceweb.com/angara7.html |title=The Angara-7 rocket |publisher=Russianspaceweb.com |date= |accessdate=2012-07-25}}</ref>
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| {{flag|Europe}}
| [[EADS Astrium Space Transportation|EADS Astrium]]
| {{nts|21000}}<ref name="Ariane5_U_M">{{cite web | url= http://www.arianespace.com/site/documents/Ariane5_users_manual_Issue4.pdf | format=PDF | title=Ariane 5 Users Manual, Issue 4, P. 39 (ISS orbit) | publisher=[[Arianespace]] | accessdate=2007-11-13 | archiveurl = httphttps://web.archive.org/web/20070927021638/http://www.arianespace.com/site/documents/Ariane5_users_manual_Issue4.pdf <!-- Bot retrieved archive| archivedate=2007-09->27 |archivedate dead-url=yes 2007-09-27}}</ref>
| {{nts|10050}} to GTO<ref name="Ariane5RecordGTOMassApr2011">{{cite web| url=http://www.arianespace.com/news-mission-update/2011/789.asp | title=Ariane 5 delivers a record performance with two payloads for new Arianespace customers | publisher=[[Arianespace]] | accessdate=2011-04-11}}</ref>
|{{nts|220}} <ref name="faa ocst 2009">{{cite web | url=http://www.faa.gov/about/office_org/headquarters_offices/ast/media/10998.pdf | title=FAA Semi-Annual Launch Report: Second Half of 2009 | publisher=Federal Aviation Administration - Office of Commercial Space Transportation | accessdate=August 18, 2011 | pages=end of document}}</ref>
| {{nts|10476}} <ref name="faa ocst 2009" />
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| {{nts|31}}<br> <ref group="note">A full listing of the [[Ariane 5]] launch history is in its main article.</ref>
| Operational
| 2002
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| {{flag|Europe}}
| [[EADS Astrium Space Transportation|EADS Astrium]]
| {{nts|21000}}<ref name="Ariane5_U_M"/>
| {{nts|21000}}<ref name="Ariane5_U_M">{{cite web| url=http://www.arianespace.com/site/documents/Ariane5_users_manual_Issue4.pdf |format=PDF| title=Ariane 5 Users Manual, Issue 4, P. 39 (ISS orbit) | publisher=[[Arianespace]] | accessdate=2007-11-13 |archiveurl = http://web.archive.org/web/20070927021638/http://www.arianespace.com/site/documents/Ariane5_users_manual_Issue4.pdf <!-- Bot retrieved archive --> |archivedate = 2007-09-27}}</ref>
| {{nts|8000}} to GTO<ref name="gsp-ariane5">{{cite web|url=http://space.skyrocket.de/doc_lau/ariane5.htm |title=Ariane-5 |publisher=Space.skyrocket.de |date= |accessdate=2012-07-25}}</ref>
| {{nts|220}} <ref name="faa ocst 2009" />
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|[[Augmented Satellite Launch Vehicle|ASLV]]
|{{IND}}
|[[Indian Space Research Organisation|ISRO]]<ref>{{cite web |url=http://www.isro.org/Launchvehicles/launchvehicles.aspx#ASLV |title=Welcome To ISRO :: Launch Vehicles |publisher=Isro.org |date= |accessdate=2013-11-04 |archive-date=2014-10-29 |archive-url=https://web.archive.org/web/20141029221429/http://www.isro.org/launchvehicles/launchvehicles.aspx#ASLV |dead-url=yes }}</ref>
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|[[Athena I]]
|- style="background:khaki;font-style:italic"
|[[Athena I]]c <ref name="Athena c">[{{Cite web |url=http://www.lockheedmartin.com/news/press_releases/2010/0325_ss_athena.html ]{{dead|title=Salinan arsip link|access-date=November 2013-11-15 |archive-date=2010-03-28 |archive-url=https://web.archive.org/web/20100328161229/http://www.lockheedmartin.com/news/press_releases/2010/0325_ss_athena.html |dead-url=yes }}</ref>
|{{USA}}
|[[Alliant Techsystems|ATK]]<br>[[Lockheed Martin]]
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|{{nts|3}}<ref name="GSP-Delta">{{cite web |url= http://space.skyrocket.de/doc_lau/delta.htm |title=Delta |archiveurl= httphttps://www.webcitation.org/60dqY3Xtj?url=http://space.skyrocket.de/doc_lau/delta.htm |archivedate=2 August 2011-08-02 |first=Krebs |last=Gunter |work=Gunter's Space Page |accessdate=2 August 2011 |dead-url=no }}</ref>
|Retired<ref name="EA-D0300">{{cite web |url= http://www.astronautix.com/lvs/dela0300.htm |title=Delta 0300 |first=Mark |last=Wade |archiveurl= httphttps://www.webcitation.org/60dqp35oP?url=http://www.astronautix.com/lvs/dela0300.htm |archivedate=2 August 2011-08-02 |work=Encyclopedia Astronautica |accessdate=2 August 2011 |dead-url=no }}</ref>
|1972
|1973
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|{{USA}}
|[[McDonnell Douglas]]
|{{nts|1300}}<ref name="EA-D0900">{{cite web |url= http://www.astronautix.com/lvs/dela0900.htm |title=Delta 0900 |first=Mark |last=Wade |archiveurl= httphttps://www.webcitation.org/60dqt327u?url=http://www.astronautix.com/lvs/dela0900.htm |archivedate=2 August 2011-08-02 |work=Encyclopedia Astronautica |accessdate=2 August 2011 |dead-url=no }}</ref>
| {{nts|818}} to SSO<ref name="GSP-Delta"/>
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|{{USA}}
|[[McDonnell Douglas]]
|{{nts|2000}}<ref name="EA-D2913">{{cite web |url= http://www.astronautix.com/lvs/dela2913.htm |title=Delta 2913 |first=Mark |last=Wade |archiveurl= httphttps://www.webcitation.org/60dt0Zu2u?url=http://www.astronautix.com/lvs/dela2913.htm |archivedate=2 August 2011-08-02 |work=Encyclopedia Astronautica |accessdate=2 August 2011 |dead-url=no }}</ref>
| {{nts|700}} to GTO<ref name="EA-D2913"/>
|
Baris 1.134 ⟶ 1.190:
|{{USA}}
|[[McDonnell Douglas]]
|{{nts|3400}}<ref name="EA-D4000">{{cite web |url= http://www.astronautix.com/lvs/dela4000.htm |title=Delta 4000 |first=Mark |last=Wade |archiveurl= httphttps://www.webcitation.org/60e2WpW6v?url=http://www.astronautix.com/lvs/dela4000.htm |archivedate=2 August 2011-08-02 |work=Encyclopedia Astronautica |accessdate=2 August 2011 |dead-url=no }}</ref>
| {{nts|1312}} to GTO<ref name="GSP-Delta"/>
|
Baris 1.148 ⟶ 1.204:
|{{USA}}
|[[McDonnell Douglas]]
|{{nts|3848}}<ref name="EA-D5000">{{cite web |url= http://www.astronautix.com/lvs/dela5000.htm |title=Delta 5000 |first=Mark |last=Wade |archiveurl= httphttps://www.webcitation.org/60e2dul4v?url=http://www.astronautix.com/lvs/dela5000.htm |archivedate=2 August 2011-08-02 |work=Encyclopedia Astronautica |accessdate=2 August 2011 |dead-url=no }}</ref>
|
|
Baris 1.330 ⟶ 1.386:
| {{USA}}
| [[United Launch Alliance]]
| {{nts|22950}}<ref name="DeltaIV">{{cite web | url= http://www.ulalaunch.com/images/product_sheet/Delta_Product_Sheet_FINAL.pdf | format=PDF | title=Delta Product Sheet, FINAL | publisher=[[United Launch Alliance]] | accessdate=2007-11-14 | archiveurl = httphttps://web.archive.org/web/20070928093124/http://www.ulalaunch.com/images/product_sheet/Delta_Product_Sheet_FINAL.pdf <!-- Bot retrieved archive| archivedate=2007-09->28 |archivedate dead-url=yes 2007-09-28}}</ref>
| {{nts|12980}} to GTO <ref name="DeltaIV" />
| {{nts|300}}(€220)<ref>{{cite web|url=http://www.spaceflightnow.com/news/n1111/10orioneft1/ |title=Breaking News &#124; Lockheed Martin to select Delta 4 rocket for Orion test |publisher=Spaceflight Now |date= |accessdate=2012-07-25}}</ref>
Baris 1.344 ⟶ 1.400:
|{{USA}}
|[[Boeing IDS]]
|{{nts|8120}}<ref name="GSP-Delta4">{{cite web |url= http://space.skyrocket.de/doc_lau/delta-4.htm |title=Delta-4 |archiveurl= httphttps://www.webcitation.org/60e9nhnjT?url=http://space.skyrocket.de/doc_lau/delta-4.htm |archivedate=2 August 2011-08-02 |first=Krebs |last=Gunter |work=Gunter's Space Page |accessdate=2 August 2011 |dead-url=no }}</ref>
| {{nts|4210}} to GTO<br/>2,722 to HCO<ref name="GSP-Delta4"/>
|
Baris 1.414 ⟶ 1.470:
|{{UKR}}
|[[Yuzhmash]]
|{{nts|3700}}<ref name="GSP-Dnepr">{{cite web |url= http://space.skyrocket.de/doc_lau_det/dnepr-1.htm |title=Dnepr-1 |archiveurl= httphttps://www.webcitation.org/60eARVyOE?url=http://space.skyrocket.de/doc_lau_det/dnepr-1.htm |archivedate=2 August 2011-08-02 |first=Krebs |last=Gunter |work=Gunter's Space Page |accessdate=2 August 2011 |dead-url=no }}</ref>
|
| {{nts|14}}(€10)<ref name="esd2006"/>
Baris 1.442 ⟶ 1.498:
| {{USSR}}
| [[NPO Energia]] ([[Energia|Launcher]])<br>[[NPO Molniya]] ([[Buran (spacecraft)|Orbiter]])
| {{nts|30000}}<ref name="Energia">{{cite web | url = http://www.energia.ru/english/energia/launchers/vehicle_energia.html | title = S.P.Korolev RSC Energia - LAUNCHERS | publisher = Energia | access-date = 2013-11-15 | archive-date = 2016-03-03 | archive-url = https://web.archive.org/web/20160303172607/http://www.energia.ru/english/energia/launchers/vehicle_energia.html | dead-url = yes }}</ref><br><ref group="note" name="spaceplane">The US [[Space Shuttle|Space Shuttle Transportation System]] and the Soviet [[Energia]]-[[Buran (spacecraft)|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 [[spaceplane]]s, excluding the mass of the spaceplanes themselves.</ref>
|
|
Baris 1.453 ⟶ 1.509:
| [[Energia]]-[[Buran (spacecraft)|Buran]]
|- style=style="background:lightgrey;"
|[[Epsilon (rocketroket)|Epsilon]]
|{{JPN}}
|[[IHI Aerospace]]<ref name=IHIAERO>{{cite web | url=http://www.ihi.co.jp/ia/en/product/rocket.html | title=Projects&Products | publisher=IHI Aerospace | accessdate=2011-03-08 | archive-date=2011-04-06 | archive-url=https://web.archive.org/web/20110406035626/http://www.ihi.co.jp/ia/en/product/rocket.html | dead-url=yes }}</ref>　　　　　
|{{nts|1200}}<ref name=ISAS/>
|
Baris 1.465 ⟶ 1.521:
|2013
|
|[[Epsilon (rocketroket)|Epsilon]]
|- style="background:lightgrey;"
|[[Falcon 1]]
Baris 1.490 ⟶ 1.546:
|
|{{nts|0}}
|Retired<ref name=Falcon1>{{cite web | url=http://www.spacex.com/falcon1.php | title=Space Exploration Technologies Corporation - Falcon 1 | accessdate=2010-10-29 | archive-date=2013-04-05 | archive-url=https://web.archive.org/web/20130405065921/https://spacex.com/falcon1.php | dead-url=yes }}</ref>
|
|
Baris 1.498 ⟶ 1.554:
| {{USA}}
| [[SpaceX]]
| {{nts|10450}}<ref name="SpaceX_f9">{{cite web | url= http://www.spacex.com/falcon9.php | title= FALCON 9 OVERVIEW | publisher= [[SpaceX]] | accessdate= 2013-11-04 | archive-date= 2013-05-01 | archive-url= https://web.archive.org/web/20130501002858/http://www.spacex.com/falcon9.php | dead-url= yes }}</ref><ref name=spacex>{{cite web |url= http://spacex.com/falcon9.php |title=Falcon 9 Overview |publisher=Space Exploration Technologies |accessdate=29 Oct 2010 |archive-date=2007-10-13 |archive-url=https://web.archive.org/web/20071013152341/http://spacex.com/falcon9.php |dead-url=yes }}</ref><ref name=sxf9_20111201archive>{{cite web
| url = http://www.spacex.com/falcon9.php
| title = Falcon 9 Overview
|year = 2011
| publisher = SpaceX
| accessdate = 2011-12-01
| archiveurl =http https://www.webcitation.org/63btGA0Bq?url=http://www.spacex.com/falcon9.php
| archivedate = 2011-12-01}}</ref>
|dead-url = no
}}</ref>
| {{nts|4680}} to GTO<ref name="SpaceX_f9" />
| {{nts|56}}<ref name="SpaceX_f9" />
| {{nts|5359}}{{citation needed|date=December 2012}}
|
| {{nts|5}}<ref name=sn20130906>{{cite news|last=Klotz|first=Irene|title=Musk Says SpaceX Being "Extremely Paranoid" as It Readies for Falcon 9’s California Debut|url=http://www.spacenews.com/article/launch-report/37094musk-says-spacex-being-%E2%80%9Cextremely-paranoid%E2%80%9D-as-it-readies-for-falcon-9%E2%80%99s|accessdate=2013-11-04|newspaper=Space News|date=2013-09-06|quote=''...the company’s five previous Falcon 9 boosters, all launched from Cape Canaveral Air Force Station here. Three of those rockets carried Dragon cargo capsules to the international space station for NASA. Two others were test flights.''|archive-date=2013-09-22|archive-url=https://wayback.archive-it.org/all/20130922163105/http://www.spacenews.com/article/launch-report/37094musk-says-spacex-being-%E2%80%9Cextremely-paranoid%E2%80%9D-as-it-readies-for-falcon-9%E2%80%99s|dead-url=yes}}</ref>
| {{nts|5}}<ref name=sn20130906>
{{cite news |last=Klotz|first=Irene |title=Musk Says SpaceX Being "Extremely Paranoid" as It Readies for Falcon 9’s California Debut |url=http://www.spacenews.com/article/launch-report/37094musk-says-spacex-being-%E2%80%9Cextremely-paranoid%E2%80%9D-as-it-readies-for-falcon-9%E2%80%99s |accessdate=2013-11-04 |newspaper=Space News |date=2013-09-06 |quote=''...the company’s five previous Falcon 9 boosters, all launched from Cape Canaveral Air Force Station here. Three of those rockets carried Dragon cargo capsules to the international space station for NASA. Two others were test flights.''}}</ref>
| Retired<ref name=sfn>{{cite web |last=Clark|first=Stephen |url=http://spaceflightnow.com/falcon9/003/120518musk/ |title=Q&A with SpaceX founder and chief designer Elon Musk |date=2012-05-18 |accessdate=2013-11-04 |quote=''The next version of Falcon 9 will be used for everything. The last flight of version 1.0 will be Flight 5. All future missions after Flight 5 will be v1.1. We've got this mission, which is Flight 3. And we've two CRS [Commercial Resupply Services] missions, Flight 4 and Flight 5, which will fly Version 1.0. Then all future missions, CRS or otherwise, will fly Version 1.1.'' }}</ref>
| 2010
Baris 1.519 ⟶ 1.577:
| {{USA}}
| [[SpaceX]]
| {{nts|16625}}<ref name="SpaceX_f91.1">{{cite web | url= http://elvperf.ksc.nasa.gov/elvMap/elvMap.ui.PerfQuery0?ReqType=Query&ContSource=-5&OrbitType=LEO&Incl=28&Contract=2&Vehicles=4&Drop1=Apogee&Entry1=200 | title= FALCON 9 Launch Vehicle Performance | publisher= [[NASA]] | accessdate= 2013-11-04 }}{{Pranala mati|date=Mei 2021 |bot=InternetArchiveBot |fix-attempted=yes }}</ref>
| {{nts|5760}} to GTO<ref name="SpaceX_f91.1GTO">{{cite web | url= http://elvperf.ksc.nasa.gov/elvMap/elvMap.ui.PerfQuery0?ReqType=Query&ContSource=-5&OrbitType=GTO&Contract=2&Vehicles=4&Drop1=Apogee&Entry1=35700&Drop2=Incl&Entry2=28.5&Plot=Ap_Mass | title= FALCON 9 Launch Vehicle Performance | publisher= [[NASA]] | accessdate= 2013-11-04 }}{{Pranala mati|date=Mei 2021 |bot=InternetArchiveBot |fix-attempted=yes }}</ref>
| {{nts|56}}<ref name="SpaceX_f9" />
| {{nts|4109}}<ref name=nbf20130323/>
Baris 1.533 ⟶ 1.591:
| {{USA}}
| [[SpaceX]]
| {{nts|53000}}<ref name=sxFH20130322>{{cite web |title=Falcon Heavy Overview |url=https://spacex.com/falcon_heavy.php |date=2013<!-- SpaceX copyright on the web page --> |publisher=SpaceX |accessdate=2013-03-22 |archive-date=2013-04-05 |archive-url=https://web.archive.org/web/20130405070749/https://spacex.com/falcon_heavy.php |dead-url=yes }}</ref><ref name="SpaceX">{{cite web |title=SpaceX Brochure |url= http://www.spacex.com/downloads/spacex-brochure.pdf|publisher=Spacex.com |accessdate=14 June 2011|archiveurl=https://web.archive.org/web/20100107075247/http://www.spacex.com/downloads/spacex-brochure.pdf|archivedate=2010-01-07|dead-url=no}}</ref>
| {{nts|12000}} to GTO<ref name=sxFH20130322/><br/>{{nts|16000}} to TLI<ref name="SpaceX"/>
| {{nts|83}}–128<ref name=sxFH20130322/><!-- "Pricing: Payloads up to 6.4 ton to GTO: $83M*; greater than 6.4 ton to GTO $128M* ... *Paid in full standard launch prices for 2012" --><!-- these published prices are explicitly listed on the 2013 version of the FH web page at SpaceX, but are listed as "launch prices for 2012"; the older/somewhat lower numbers that had been claimed have no source provided at all. -->
Baris 1.546 ⟶ 1.604:
|[[Geosynchronous Satellite Launch Vehicle|GSLV Mk.I(a)]]
|{{IND}}
|[[Indian Space Research Organisation|ISRO]]<ref>{{cite web |url=http://www.isro.org/gslv-d1/gslv-d1.aspx |title=Welcome To ISRO :: GSLV :: GSLV-D1 |publisher=Isro.org |date= |accessdate=2013-11-04 |archive-date=2013-11-11 |archive-url=https://web.archive.org/web/20131111011907/http://www.isro.org/gslv-d1/gslv-d1.aspx |dead-url=yes }}</ref><ref>{{cite web |url=http://www.isro.org/gslv-d2/gslv-d2.aspx |title=Welcome To ISRO :: Launch Vehicles :: GSLV :: GSLV-D2 |publisher=Isro.org |date=2001-04-18 |accessdate=2013-11-04 |archive-date=2013-11-11 |archive-url=https://web.archive.org/web/20131111011708/http://www.isro.org/gslv-d2/gslv-d2.aspx |dead-url=yes }}</ref>
|
|
Baris 1.558 ⟶ 1.616:
|[[Geosynchronous Satellite Launch Vehicle|GSLV Mk.I(a)]]
|- style="background:lightgrey;"
|[[Geosynchronous Satellite Launch Vehicle|GSLV Mk.I(b)]] <ref>{{cite web |url=http://www.isro.org/gslv-f01/gslv-f01.aspx |title=Welcome To ISRO |publisher=Isro.org |date= |accessdate=2013-11-04 |archive-date=2013-11-11 |archive-url=https://web.archive.org/web/20131111011712/http://www.isro.org/gslv-f01/gslv-f01.aspx |dead-url=yes }}</ref><ref>{{cite web |url=http://www.isro.org/gslv-f04/gslv-f04.aspx |title=Welcome To ISRO :: Launch Vehicles :: GSLV :: GSLV-F04 |publisher=Isro.org |date= |accessdate=2013-11-04 |archive-date=2013-08-22 |archive-url=https://web.archive.org/web/20130822075148/http://www.isro.org/gslv-f04/gslv-f04.aspx |dead-url=yes }}</ref>
|{{IND}}
|[[Indian Space Research Organisation|ISRO]]
Baris 1.586 ⟶ 1.644:
|[[Geosynchronous Satellite Launch Vehicle|GSLV Mk.I(c)]]
|- style="font-style:italic;"
|[[Geosynchronous Satellite Launch Vehicle|GSLV Mk.II]] <ref>{{cite web |url=http://www.isro.org/gslv-d3/gslv-d3.aspx |title=Welcome To ISRO :: Launch Vehicles :: GSLV :: GSLV-D3 |publisher=Isro.org |date=2010-04-15 |accessdate=2013-11-04 |archive-date=2010-04-16 |archive-url=https://web.archive.org/web/20100416141241/http://isro.org/gslv-d3/gslv-d3.aspx |dead-url=yes }}</ref>
|{{IND}}
|[[Indian Space Research Organisation|ISRO]]
Baris 1.602 ⟶ 1.660:
| [[Geosynchronous Satellite Launch Vehicle Mk III|GSLV Mk.III]]
| {{IND}}
| [[ISRO]]<ref>{{cite web |url=http://www.isro.gov.in/Launchvehicles/GSLVMARKIII/mark3.aspx |title=Welcome To ISRO :: Launch Vehicles :: GSLV Mark III |publisher=Isro.gov.in |date= |accessdate=2013-11-04 |archive-date=2013-08-11 |archive-url=https://web.archive.org/web/20130811185233/http://isro.gov.in/Launchvehicles/GSLVMARKIII/mark3.aspx |dead-url=yes }}</ref>
| {{nts|10000}}{{citation needed|date=August 2012}}<!-- note: no sourced claim for LEO payload appears to be in the GSLV article as of 2012-08-12 -->
| {{nts|5,000}}<ref name=isro20120812>{{cite web |url=http://isro.org/Launchvehicles/GSLVMARKIII/mark3.aspx |title=GSLV Mark III |year=2011 |publisher=Indian Space Research Organisation |accessdate=2012-08-12 |archive-date=2012-11-25 |archive-url=https://web.archive.org/web/20121125032756/http://isro.org/Launchvehicles/GSLVMARKIII/mark3.aspx |dead-url=yes }}</ref>
|
|
Baris 1.702 ⟶ 1.760:
| [[Mitsubishi Heavy Industries]]
| {{nts|16500}}<ref name=sxFH20130322/>
| {{nts|8000}}<ref name="H-IIB_2">{{cite web | url= http://www.jaxa.jp/pr/brochure/pdf/01/rocket05.pdf | title=H-IIB Launch Vehicle, P. 2 | publisher=[[Jaxa]] | accessdate=3 September 2008}}< | archiveurl=https:/ref>{{deadlink/web.archive.org/web/20090730201604/http://www.jaxa.jp/pr/brochure/pdf/01/rocket05.pdf |date archivedate=March2009-07-30 | dead-url=yes 2013}}</ref>
|
|
Baris 1.954 ⟶ 2.012:
| [[China Academy of Launch Vehicle Technology|CALT]]
|
|{{nts|5,500}} to GTO <ref name="长征三号甲运载火箭简述">{{cite web|title=长征三号甲运载火箭简述|url=http://news.sina.com.cn/c/2007-09-13/103113882288.shtml|accessdate=31 October 2011}}</ref>
 
|
Baris 2.038 ⟶ 2.096:
| {{CHN}}
| [[China Academy of Launch Vehicle Technology|CALT]]
| {{nts|25000}} <ref name="longmarch">{{Cite news| url= http://www.sinodefence.com/space/launcher/changzheng5.asp | title= ChangZheng 5 (Long March 5) Launch Vehicle | publisher=SinoDefence.com | date=2009-02-20 | accessdate=2009-03-06}}</ref>
| {{nts|14000}} to GTO <ref name="longmarch" />
|
Baris 2.108 ⟶ 2.166:
|{{USA}}
|[[Orbital Sciences Corporation|Orbital]]
|{{nts|580}}<ref name=osc20120228>{{cite web |url=http://www.orbital.com/NewsInfo/Publications/Minotaur_I_Fact.pdf |title=Minotaur I Space Launch Vehicle—Fact Sheet |year=2012 |work= |publisher=Orbital Sciences Corporation |accessdate=2012-02-28 |quote=''Spacecraft mass-to-orbit of up to 580 kg to LEO (28.5 deg, 185 km)'' |archiveurl=https://web.archive.org/web/20061018165506/http://www.orbital.com/NewsInfo/Publications/Minotaur_I_Fact.pdf |archivedate=2006-10-18 |dead-url=no }}</ref>
|{{nts|580}}<ref name=osc20120228>
{{cite web |url=http://www.orbital.com/NewsInfo/Publications/Minotaur_I_Fact.pdf |title=Minotaur I Space Launch Vehicle—Fact Sheet |year=2012 |work= |publisher=Orbital Sciences Corporation |accessdate=2012-02-28 |quote=''Spacecraft mass-to-orbit of up to 580 kg to LEO (28.5 deg, 185 km)'' }}</ref>
|
|
Baris 2.128 ⟶ 2.185:
|
|
|{{nts|3}}(+2)<ref name="minotaur">[{{Cite web |url=http://www.orbital.com/SpaceLaunch/Minotaur/History/minotaur_history.shtml] {{dead|title=Salinan arsip link|access-date=November2013-11-15 |archive-date=2013-09-19 |archive-url=https://web.archive.org/web/20130919032016/http://www.orbital.com/SpaceLaunch/Minotaur/History/minotaur_history.shtml |dead-url=yes }}</ref>
|Operational
|2010<ref name="minotaur"/>
Baris 2.235 ⟶ 2.292:
|{{JPN}}
|[[Nissan Motors]]<ref name=Nissan/>
|{{nts|180}}<ref name=ISAS>{{cite web|title=Satellite Launch Vehicles|url=http://www.isas.jaxa.jp/e/enterp/rockets/vehicles/index.shtml|publisher=[[Institute of Space and Astronautical Science{{!}}|Institute of Space and Astronautical Science (ISAS)]]|accessdate=4 March 2011}}</ref>
|
|
Baris 2.323 ⟶ 2.380:
|
|
|{{nts|41}}<ref name="Pegasus">[{{Cite web |url=http://www.orbital.com/SpaceLaunch/Pegasus/pegasus_history.shtml] {{dead|title=Salinan arsip link|access-date=November2013-11-15 |archive-date=2013-07-22 |archive-url=https://www.webcitation.org/6IIm5SI3B?url=http://www.orbital.com/SpaceLaunch/Pegasus/pegasus_history.shtml |dead-url=yes }}</ref>
|Operational
|1990
Baris 2.333 ⟶ 2.390:
|[[Orbital Sciences Corporation|Orbital]]
|{{nts|6120}}<ref name=nsf20130524>
{{cite news |last=Bergin|first=Chris |title=Stratolaunch and Orbital – The Height of Air Launch |url=http://www.nasaspaceflight.com/2013/05/stratolaunch-orbital-air-launch/ |accessdate=2013-05-24 |newspaper=NASA SpaceFlight |date=2013-05-25 }}</ref>
|{{nts|2000}} to GTO<ref name=nsf20130524/>
|
Baris 2.375 ⟶ 2.432:
| {{USSR}}<br>{{RUS}}
| [[Khrunichev State Research and Production Space Center|Khrunichev]]
| {{nts|21600}}<ref name="ProtonM">{{cite web | archiveurl= httphttps://web.archive.org/web/20071027045349/http://www.ilslaunch.com/products/proton/protonmpg/protonr6/pmpg_2e.pdf |archivedate=2007-10-27 | url= http://www.ilslaunch.com/launch-services/proton-mission-planners-guide| |title=Proton Launch System Mission Planner’s Guide, LKEB-9812-1990 | publisher=[[International Launch Services]] |pages=2–2 |quote=LEO i = 51.6°, H = 200&nbsp;km circular ... GTO (1800 m/s from GSO) i = 31.0°, Hp = 2100&nbsp;km, Ha = 35,786&nbsp;km | accessdate=2007-11-12 |dead-url=no }}</ref>
| {{nts|6150}} to GTO<ref name="ProtonM"/>
| {{nts|85}} <ref name="Futron_Launch_Costs">{{cite web | url= http://www.futron.com/upload/wysiwyg/Resources/Whitepapers/Space_Transportation_Costs_Trends_0902.pdf | format=PDF | title=Space Transportation Costs: Trends in Price Per Pound to Orbit 1990-2000 | publisher=[[Futron]] | accessdate=2010-05-02 | archive-date=2011-07-11 | archive-url=https://web.archive.org/web/20110711061933/http://www.futron.com/upload/wysiwyg/Resources/Whitepapers/Space_Transportation_Costs_Trends_0902.pdf | dead-url=yes }}</ref>
| {{nts|4302}}<ref name="Futron_Launch_Costs" />
|
Baris 2.390 ⟶ 2.447:
| [[Indian Space Research Organisation|ISRO]]
| {{nts|3200}}<ref name=PSLV>{{cite web |url= http://1.bp.blogspot.com/_JRgHKYCaeH4/S-mJE29KQwI/AAAAAAAAAJk/ctRSrE7P72c/s1600/PSLV+variants1.jpg |title=PSLV variants capability |publisher=ISRO |accessdate=15 May 2010}}</ref>
| {{nts|1600}} to SSO<br/>1,050 to GTO<ref name="GSP-PSLV">{{cite web |url= http://space.skyrocket.de/doc_lau/pslv.htm |title=PSLV |archiveurl= httphttps://www.webcitation.org/60eAq5vzm?url=http://space.skyrocket.de/doc_lau/pslv.htm |archivedate=2 August 2011-08-02 |first=Krebs |last=Gunter |work=Gunter's Space Page |accessdate=2 August 2011 |dead-url=no }}</ref>
|
|
Baris 2.556 ⟶ 2.613:
|{{IRI}}
|[[Iranian Space Agency]]
|{{nts|60}}-100<ref name="fars">{{cite web|url=http://english.farsnews.comir/newstext.php?nn=8811141592|title=Iranian DM: Simorgh to Carry Tolou, Mesbah Satellites into Space|publisher=Fars News Agency|date=2010-02-03|accessdate=2010-02-03|archiveurl=https://web.archive.org/web/20111113072413/http://english.farsnews.ir/newstext.php?nn=8811141592|archivedate=2011-11-13|dead-url=no}}</ref><ref>{{cite web |url=http://www.payvand.com/news/10/feb/1025.html |title=Iran unveils three new home-made satellites |publisher=Payvand.com |date= |accessdate=2012-07-25 |archive-date=2010-02-06 |archive-url=https://web.archive.org/web/20100206215559/http://www.payvand.com/news/10/feb/1025.html |dead-url=yes }}</ref>
|
|
Baris 2.567 ⟶ 2.624:
|[[Simorgh (rocket)|Simorgh]]
|- style="background:khaki;font-style:italic;"
| [[Space Launch System |SLS Block 1]]
| {{USA}}
| [[Alliant Techsystems]]&nbsp;([[Space Shuttle Solid Rocket Booster|SRBs]])<br>
Baris 2.580 ⟶ 2.637:
|
|
| [[Space Launch System |SLS Block 1]]
|- style="background:khaki;font-style:italic;"
| [[Space Launch System |SLS Block 2]]
| {{USA}}
| [[Alliant Techsystems]]&nbsp;([[Space Shuttle Solid Rocket Booster|SRBs]])<br>
Baris 2.595 ⟶ 2.652:
|
|
| [[Space Launch System |SLS Block 2]]
|-
|[[Satellite Launch Vehicle|SLV]]
Baris 2.656 ⟶ 2.713:
|{{USSR}}<br>{{RUS}}
|[[TsSKB-Progress]]
|{{nts|6200}}–6,700&nbsp;kg from [[Plesetsk Cosmodrome|Plesetsk]])<br/>6590-6950 from [[Baikonur Cosmodrome|Baikonour]]<ref name="soyuz-u">[{{Cite web |url=http://www.samspace.ru/ENG/RN/souz_u.htm ]{{dead|title=Salinan arsip link|access-date=November 2013-11-15 |archive-date=2012-10-29 |archive-url=https://web.archive.org/web/20121029153716/http://www.samspace.ru/ENG/RN/souz_u.htm |dead-url=yes }}</ref>
|
|
Baris 2.684 ⟶ 2.741:
|{{RUS}}
|[[TsSKB-Progress]]
|{{nts|6790}}–7130&nbsp;kg<ref name="soyuz-fg">[{{Cite web |url=http://www.samspace.ru/ENG/RN/souz_fg.htm ]{{dead|title=Salinan arsip link|access-date=November 2013-11-15 |archive-date=2012-10-29 |archive-url=https://web.archive.org/web/20121029153725/http://www.samspace.ru/ENG/RN/souz_fg.htm |dead-url=yes }}</ref>
|
|
Baris 2.796 ⟶ 2.853:
|{{USA}}
|[[Stratolaunch Systems]]
|{{nts|6100}}<ref name=aw2011213>{{cite web |url=http://www.aviationweek.com/aw/generic/story_channel.jsp?channel=space&id=news/awx/2011/12/13/awx_12_13_2011_p0-405946.xml&headline=Stratolaunch%20Aims%20to%20Break%20Affordability%20Barrier |title=Stratolaunch Aims to Break Affordability Barrier |date=2011-12-13 |publisher=Aviation Week |accessdate=2011-12-15 |archive-date=2012-12-05 |archive-url=https://archive.today/20121205201822/http://www.aviationweek.com/Article.aspx?id=/article-xml/awx_12_13_2011_p0-405946.xml |dead-url=yes }}</ref>
|{{nts|6100}}<ref name=aw2011213>
{{cite web |url=http://www.aviationweek.com/aw/generic/story_channel.jsp?channel=space&id=news/awx/2011/12/13/awx_12_13_2011_p0-405946.xml&headline=Stratolaunch%20Aims%20to%20Break%20Affordability%20Barrier |title=Stratolaunch Aims to Break Affordability Barrier |date=2011-12-13 |publisher=Aviation Week |accessdate=2011-12-15}}</ref>
|
|
Baris 2.804 ⟶ 2.860:
|
|Development<ref name=aw2011213/>
|2016<ref name=aw20111220>{{cite news|last=Mecham|first=Michael|author2=Frank Morring, Jr.|title=Allen Places Big Bet On Air Launches|url=http://www.aviationweek.com/aw/generic/story.jsp?channel=space&id=news/awst/2011/12/19/AW_12_19_2011_p26-406657.xml&headline=Allen%20Places%20Big%20Bet%20On%20Air%20Launches&prev=10|accessdate=2011-12-23|newspaper=Aviation Week|date=2011-12-20|quote=''the overall team is still working through details of how to progress toward its 2016 first launch.''}}{{Pranala mati|date=Februari 2022 |bot=InternetArchiveBot |fix-attempted=yes }}</ref>
|2016<ref name=aw20111220>
{{cite news |last=Mecham|first=Michael | author2=Frank Morring, Jr. |title=Allen Places Big Bet On Air Launches |url=http://www.aviationweek.com/aw/generic/story.jsp?channel=space&id=news/awst/2011/12/19/AW_12_19_2011_p26-406657.xml&headline=Allen%20Places%20Big%20Bet%20On%20Air%20Launches&prev=10 |accessdate=2011-12-23 |newspaper=Aviation Week |date=2011-12-20 |quote=''the overall team is still working through details of how to progress toward its 2016 first launch.''}}</ref>
|
|[[Stratolaunch launch vehicle|StratoLaunch]]
Baris 2.846 ⟶ 2.901:
|
|{{nts|9}}{{citation needed|date=July 2012}}
|Operational<ref>[{{Cite web |url=http://www.orbital.com/spacelaunch/taurus/] {{dead|title=Salinan arsip link|access-date=November 2013-11-15 |archive-date=2014-02-09 |archive-url=https://web.archive.org/web/20140209053850/http://www.orbital.com/SpaceLaunch/Taurus/ |dead-url=yes }}</ref>
|1994
|2011{{citation needed|date=July 2012}}
Baris 2.854 ⟶ 2.909:
| {{USA}}
| [[Orbital Sciences Corporation|Orbital]]
| {{nts|6000}}<ref name="ostug13_201104">{{cite web |url=http://www.orbital.com/NewsInfo/Publications/Taurus_II_Guide.pdf |format=PDF |title=Taurus II User’s Manual, Rev. 1.3 |publisher=Orbital |date = April 2010 |accessdate = 2010-11-11 |archiveurl=https://web.archive.org/web/20100509062344/http://www.orbital.com/NewsInfo/Publications/Taurus_II_Guide.pdf |archivedate=2010-05-09 |dead-url=no }}</ref>
| {{nts|1900}} to GTO<ref name="ostug13_201104"/>
|
Baris 2.994 ⟶ 3.049:
| {{USA}}
| [[Lockheed Martin]]
| {{nts|21682}}<ref name="titan4">{{cite web | url= https://www.maxwell.af.mil/au/awc/space/factsheets/titan_ivb.htm | title=Fact Sheet - TITAN IVB | publisher=[[United States Air Force]] | accessdate=2007-11-12 }}{{Pranala mati|date=Februari 2021 |bot=InternetArchiveBot |fix-attempted=yes }}</ref>
| {{nts|5761}} to GTO <ref name="titan4" /><br>(9,000 with upper stage)
| {{nts|432}}
Baris 3.064 ⟶ 3.119:
|{{UKR}}
|[[Yuzhmash]]
|{{nts|5500}} <ref name="tsyklon">{{Cite news| url= http://www.nkau.gov.ua/nsau/catalogNEW.nsf/systemE/2C16C6A39AAF93DBC3256BF8004C1235?OpenDocument&Lang=E | title= Tsyklon-4 launcher main features | publisher=nkau.gov.ua | accessdate=2013-02-25}}</ref>
|{{nts|1700}} to GTO <ref name="tsyklon" />
|
Baris 3.275 ⟶ 3.330:
| [[Yuzhmash]]<br>[[RKK Energia]] <ref group=note>Operated by [[Sea Launch]]</ref>
|
| {{nts|6000}} to GTO <ref name="sea-launch launch_vehicle">{{cite web | url= http://www.sea-launch.com/sllaunch_vehicle.htm | title=Launch Vehicle | publisher=[[Sea Launch]] | accessdate=2012-12-10 | archive-date=2009-04-04 | archive-url=https://web.archive.org/web/20090404002737/http://www.sea-launch.com/sllaunch_vehicle.htm | dead-url=yes }}</ref>
| {{nts|100}}<ref name="faa ocst 2011">{{cite web | url=http://www.faa.gov/about/office_org/headquarters_offices/ast/media/HQ-121473.pdf | title=FAA Semi-Annual Launch Report: Second Half of Fiscal Year 2011 | publisher=Federal Aviation Administration - Office of Commercial Space Transportation | accessdate=December 10, 2012 | pages=end of document}}</ref>
|
Baris 3.300 ⟶ 3.355:
|}
 
== Persaingan pasar peluncuran antariksa ==
Persaingan pasar peluncuran antariksa merupakan manifestasi kekuatan pasar dalam bisnis penyedia layanan peluncuran. Secara khusus, tren dinamika persaingan di antara kemampuan transportasi muatan dengan harga yang beragam memiliki pengaruh yang lebih besar pada pembelian peluncuran daripada pertimbangan politik tradisional negara pembuat atau entitas nasional yang menggunakan, mengatur, atau memberi lisensi layanan peluncuran.
 
Setelah munculnya teknologi penerbangan antariksa pada akhir tahun 1950-an, layanan peluncuran antariksa muncul, secara eksklusif oleh program nasional. Kemudian pada abad ke-20, operator komersial menjadi pelanggan penting penyedia peluncuran. Persaingan internasional untuk subset muatan satelit komunikasi dari pasar peluncuran semakin dipengaruhi oleh pertimbangan komersial. Namun, bahkan selama periode ini, untuk satelit komunikasi yang diluncurkan oleh komersial dan entitas pemerintah, penyedia layanan peluncuran untuk muatan ini menggunakan kendaraan peluncur yang dibuat sesuai spesifikasi pemerintah, dan dengan pendanaan pengembangan yang disediakan negara secara eksklusif.
==Catatan==
 
Pada awal tahun 2010-an, lima dekade setelah manusia pertama kali mengembangkan teknologi penerbangan antariksa, sistem kendaraan peluncur yang dikembangkan secara pribadi dan penawaran layanan peluncuran antariksa muncul. Perusahaan kini menghadapi insentif ekonomi, bukan insentif politik seperti pada dekade-dekade sebelumnya. Bisnis peluncuran antariksa mengalami penurunan harga per unit yang drastis, bersamaan dengan penambahan kemampuan yang sama sekali baru, yang membawa babak baru persaingan di pasar peluncuran antariksa.
 
Pada tahun 2024 dilaporkan bahwa, dengan menghitung semua aktivitas peluncuran dan penerbangan antariksa global, [[SpaceX]], yang memanfaatkan keluarga roket [[Falcon (keluarga roket)|Falcon]] miliknya, telah meluncurkan hampir 87% dari semua upmass di Bumi pada tahun 2023.
 
{{Anchor|table of costs}}<center>
{| class="wikitable"
|+ Perkiraan biaya muatan kendaraan peluncur per kg
|-
! Kendaraan peluncur !! Biaya muatan per kg
|-
| [[Vanguard (rocket)|Vanguard]] || $1,000,000 <ref name ="Trends" />
|-
| [[Space Shuttle]] || $54,500 <ref name ="Trends" />
|-
| [[Electron (rocket)|Electron]] || $19,039 <ref>{{cite news |title=Rocket Lab points out that not all rideshare rocket launches are created equal |url=https://techcrunch.com/2020/01/30/rocket-lab-points-out-that-not-all-rideshare-rocket-launches-are-created-equal/ |website=TechCrunch|date=30 January 2020 |last1=Etherington |first1=Darrell }}</ref><ref>{{cite web |title=Payload User Guide|url=https://www.rocketlabusa.com/assets/Uploads/Payload-User-Guide-LAUNCH-V6.6.pdf |website=rocklabusa.com |publisher=Rocket Lab|access-date=November 22, 2022}}</ref>
|-
| [[Ariane 5|Ariane 5G]] || $9,167 <ref name ="Trends" />
|-
| [[Long March 3B]] || $4,412 <ref name ="Trends" />
|-
| [[Proton (rocket family)|Proton]] || $4,320 <ref name ="Trends" />
|-
| [[Falcon 9]] || $2,720 <ref name ="NASAtrends">{{cite journal |title=NASA Technical Reports Server (NTRS) |url=https://ntrs.nasa.gov/citations/20200001093 |archive-url=https://web.archive.org/web/20210801024432/https://ntrs.nasa.gov/citations/20200001093 |url-status=dead |archive-date=2021-08-01 |website=ntrs.nasa.gov |date=8 July 2018 |publisher=NASA |access-date=4 January 2021}}</ref>
|-
| [[Falcon Heavy]] || $1,500 <ref name ="Aerospace">{{cite journal |title=Space Launch to Low Earth Orbit: How Much Does It Cost? |url=https://aerospace.csis.org/data/space-launch-to-low-earth-orbit-how-much-does-it-cost/|website=aerospace.csis.org |date=1 September 2022 |publisher=CSIS|access-date=8 September 2023}}</ref>
|}
</center>
 
== 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)] {{Webarchive|url=https://web.archive.org/web/20110517075159/http://history.msfc.nasa.gov/saturn_apollo/documents/Flight_History.pdf |date=2011-05-17 }}. 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; [http://www.apogeespacebooks.com/Books/Saturn.html 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]].</ref>
<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>
Baris 3.312 ⟶ 3.404:
<ref name="Rocket and Space Technology">{{cite web| url = http://www.braeunig.us/space/specs/saturn.htm | title = Rocket and Space Technology | publisher = Braeunig.us|accessdate=2013-11-04}}</ref>
<ref name="Saturn">Alan Lawrie and Robert Godwin, '' [http://www.apogeespacebooks.com/Books/Saturn.html Saturn],'' 2005 (paperback, Apogee Books Space Series, 2010), ISBN 1-894959-19-1</ref>
<ref name="Saturn V Flight History">John Duncan, [http://www.apollosaturn.com/satvhist.htm Saturn V Flight History] {{Webarchive|url=https://web.archive.org/web/20110805154018/http://www.apollosaturn.com/satvhist.htm |date=2011-08-05 }} (1999), web page (accessed 20 August 2010)</ref>
<ref name="refN1-1">{{cite web | url = http://www.energia.ru/en/history/systems/vehicles/vehicle_n1-l3.html | title = Complex N1-L3 | publisher = Energia.ru | accessdate = 2013-11-04 | archive-date = 2016-10-30 | archive-url = https://web.archive.org/web/20161030204839/http://www.energia.ru/en/history/systems/vehicles/vehicle_n1-l3.html | dead-url = yes }}</ref>
<ref name="refN1-2">{{cite web|url=http://www.astronautix.com/craft/l3.htm |title=L3 |publisher=Astronautix.com |date= |accessdate=2013-11-04}}</ref>
<ref name="refN1-3">{{cite web |url=http://www.energia.ru/en/history/systems/vehicles/vehicle_n1-l3_c.html |title=RSC "Energia" - History |publisher=Energia.ru |date=2011-04-12 |accessdate=2013-11-04 |archive-date=2016-10-30 |archive-url=https://web.archive.org/web/20161030202622/http://www.energia.ru/en/history/systems/vehicles/vehicle_n1-l3_c.html |dead-url=yes }}</ref>
<ref name="refN1-4">{{cite web|url=http://www.astronautix.com/lvs/n1.htm|title=N1|last=Wade|first=Mark|publisher=Encyclopedia Astronautica|accessdate=9 August 2010}}</ref>
<ref name="Energia"/>
<ref name="Energia">{{cite web| url = http://www.energia.ru/english/energia/launchers/vehicle_energia.html | title = S.P.Korolev RSC Energia - LAUNCHERS | publisher = Energia}}</ref>
<ref name="Energia3">{{cite web|url=http://www.astronautix.com/fam/energia.htm|title=Energia|last=Wade|first=Mark|publisher=Encyclopedia Astronautica|accessdate=9 August 2010}}</ref>
<ref name="Space Launch System">{{cite web|url=http://www.nasa.gov/pdf/664158main_sls_fs_master.pdf|title=Space Launch System|publisher=Nasa.gov|accessdate=27 August 2013|archive-date=2012-08-13|archive-url=https://web.archive.org/web/20120813043824/http://www.nasa.gov/pdf/664158main_sls_fs_master.pdf|dead-url=yes}}</ref>
{{Reflist|colwidth=30em}}
 
== Pranala luar ==
* httphttps://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] {{Webarchive|url=https://web.archive.org/web/20100414071325/http://www10.brinkster.com/drakamal/pub/confabst.htm#C66: |date=2010-04-14 }}'', 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] {{Webarchive|url=https://web.archive.org/web/20100414071325/http://www10.brinkster.com/drakamal/pub/confabst.htm#C67: |date=2010-04-14 }}'', 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#C67C72: IncorporatingThe CrossMulti-RangeStage-Lambert ErrorScheme infor theSteering Lamberta SchemeSatellite-Launch Vehicle] {{Webarchive|url=https://web.archive.org/web/20100414071325/http://www10.brinkster.com/drakamal/pub/confabst.htm#C72: |date=2010-04-14 }}'', Proc. 10th National12th AeronauticalIEEE Conf.INMIC, Edited by SheikhAnis SRMK, Khan AMMK, PakistanZaidi AirSJH, ForceBahria AcademyUniv., Risalpur, KPKarachi, Pakistan, 20062008, pp 255–263294–300 (invited paper) [http://www.ngds-ku.org/Papers/C67C72.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] {{Webarchive|url=https://web.archive.org/web/20100414071325/http://www10.brinkster.com/drakamal/pub/confabst.htm#C56: |date=2010-04-14 }}'', 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#C72C55: The MultiDot-Stage-LambertProduct SchemeSteering: A New Control Law for SteeringSatellites aand SatelliteSpacecrafts] {{Webarchive|url=https://web.archive.org/web/20100414071325/http://www10.brinkster.com/drakamal/pub/confabst.htm#C55: |date=2010-Launch04-14 Vehicle]}}'', Proc. 12thIBCAST IEEE2002, Volume 1, Advanced Materials, Computational Fluid Dynamics and Control INMICEngineering, Edited by AnisHoorani MKHR, KhanMunir MKA, ZaidiSamar SJHR, BahriaZahir Univ.S, KarachiNational Center for Physics, PakistanBhurban, 2008KP, ppPakistan, 294–3002003, (invitedpp paper)178–184 [http://www.ngds-ku.org/Papers/C72C55.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] {{Webarchive|url=https://web.archive.org/web/20100414071325/http://www10.brinkster.com/drakamal/pub/confabst.htm#C64: |date=2010-04-14 }}'', Space Science and the Challenges of the twenty-First Century, ISPA-SUPARCO Collaborative Seminar, Univ. of Karachi, 2005 (invited paper)
 
* [https://archive.today/20130117062846/www.allvoices.com/contributed-news/7713795-christmas-turns-bad-for-isro-gslv-mission-fails Christmas turns bad for ISRO, GSLV mission fails.]
*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]
* http://themittani.com/features/satellite-extravaganza-us-vs-russia?page=0%2C1 {{Webarchive|url=https://web.archive.org/web/20131207100440/http://themittani.com/features/satellite-extravaganza-us-vs-russia?page=0%2C1 |date=2013-12-07 }}
 
* http://www.spacelaunchreport.com/dnepr.html
*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]
* http://www.astronautix.com/articles/costhing.htm Encyclopedia Astronautica: Cost, Price, and the Whole Darn Thing
 
*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)
* [http://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
 
[[Kategori:Kendaraan peluncur antariksa| ]]
{{astronomi-stub}}
[[Kategori:Kendaraan peluncur luar angkasa]]
Diperoleh dari "https://wiki-indonesia.club/wiki/Wahana_peluncur_antariksa"