peluncuran kendaraan, kendaraan peluncur khususnya orbital, memiliki minimal dua tahap, tetapi 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
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.
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
legend for orbit abbreviations in table:
legend for launch system status in below table: [under development]  [retired]  [operational]
mass toother orbits(kg)
ariane 4 40
1,900 to gto
ariane 4 40
ariane 4 40 h10+
ariane 4 40 h10+
ariane 4 40 h10-3
ariane 4 40 h10-3
ariane 4 42l
3,200 to gto
ariane 4 42l
ariane 4 42l h10+
ariane 4 42l h10+
ariane 4 42l h10-3
ariane 4 42l h10-3
ariane 4 42p
2,600 to gto
ariane 4 42p
ariane 4 42p h10+
ariane 4 42p h10+
ariane 4 42p h10-3
ariane 4 42p h10-3
ariane 4 44l
4,200 to gto
ariane 4 44l
ariane 4 44l h10+
ariane 4 44l h10+
ariane 4 44l h10-3
ariane 4 44l h10-3
ariane 4 44lp
3,700 to gto
ariane 4 44lp
ariane 4 44lp h10+
ariane 4 44lp h10+
ariane 4 44lp h10-3
ariane 4 44lp h10-3
ariane 4 44p
3,000 to gto
ariane 4 44p
ariane 4 44p h10-3
ariane 4 44p h10-3
a full listing of the ariane 5 launch history is in its main article.
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.
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 9095 mt, if a liquid-hydrogen upper stage engine could be developed.
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.
s. a. kamal, a. mirza: 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 2733 free full text
s. a. kamal: 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 255263 free full text
s. a. kamal: 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 294300 (invited paper) free full text
s. a. kamal: 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 167177 free full text
s. a. kamal: 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 178184 free full text
s. a. kamal: 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)
christmas turns bad for isro, gslv mission fails.
encyclopedia astronautica: cost, price, and the whole darn thing
kategori:kendaraan peluncur luar angkasa