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Aviation History
1991
1991 - 1008.PDF
MANUFACTURER/Booster Burn Payload Total Payload Launch record/schedule Notes Stage Engine Propellants Thrust time fairing length capability PaylDad/Date/Site ISRAEL Shavit LTV (USA) ScoutG-1 Scout 2 1st 2nd 1st 2nd 3rd 4th 1st 2nd 3rd 4th 1 x UTC Algol 3A 1 x Thiokol Caster 1 x Thiokol Antares 1 x Thiokol Altair 3 1 x UTC Algol 3A (d) 2 x SNIA-BPD (e) 1 x Thiokol Casler I 1 x Thiokol Antares 1 x SEP Mage 2 solid solid solid solid solid solid solid solid MARTIN MARIETTA (USA) Titan II 23G (a) 1st 2 x A50jet LR87-AJ5 2nd 1 x A50jet LR87 Titan II S Titan IV-IUS Titan IV-Centaur 2nd 1st 2nd 3rd 1st 2nd 3rd Titan IV-Centaur 1st 2nd 3rd Commercial Titan 1st 2nd 2 x A50jet LR87-AJ5 2 x Thiokol Caster I 1 x A50jet LR87 2 x A50jet LR87 (uprated) 2 x UTC seven-segment 1 x A50jet LR91 (uprated) 1 x Boeing IUS -1st stage 2nd stage 2 x A50jet LR87 (uprated) 2 x UTC seven-segment 1 xA50jetLR91 (uprated) 2xP&WRL-10(m) 2 x A50jet LR87 (uprated) 2 x Hercules three-segment 1 x A50jet LR91 (uprated) 2xP&WRL-10(m) 2 x A50jet LR87 (p) 2 x UTC 51/2-segment 1 x A50jet LR91 MCDONNELL DOUGLAS(USA) Interim 1st 1 x Rocketdyne RS-27 Delta 6920 9 x Thiokol Castor I 2nd 1 xA50jetAJ-10(c Interim Delta II 6925 Delta II7920 Delta II 7925 1st 2nd 3rd 1st 1st 2nd 3rd 1 x Rocketdync RS-27 9 x Thiokol Castor I 1 x ASOjet AJ-10 (c 1 x Thiokol Star 48B 1 x Rocketdyne RS-27 9 x Hercules GEM (h) 1 xA50jet AJ-10 (c 1 x Rocketdyne RS-27 9 x Hercules GEM (h) 1 xA50jet AJ-10 (c 1 x Thiokol Star 48B NA + A50 + A50 NA + A50 N204 + A50 NA + A50 solid solid solid solid A50 LOX < LH N20, + A50 solid LOX + LH N20, + UDMH solid N204 + UDMH LOX i RP-1 solid NA + A50 LOX + RP-1 solid N20, t A50 solid LOX + RP-1 NA + A50 LOX + RP-1 N20, t A50 solid 465kN 268kN 81 kN 26kN 465kN 1,300kN 268kN 81 kN 45kN 1,913kN 445kN 1.913kN 962kN (f) 445kN 2,437kN 14.234kN 467kN 203kN 82kN 2,437kN 14.234kN 467kN 147kN 2l437kN 467kN 147kN 2;429kN 12.400kN 463kN 920kN 3,879kN 43kN 920kN 3,879kN 43kN 67kN 1,054kN 3,951 kN 1.054kN 3,951kN 43kN 67kN 11m 82s 0.9m or 1.1m dia 22.9m 39s 46s 34s 82s 1.4m dia 23m 42s 39s 46s 43s 170s 3.1m dia, 6.1m long 37.5m 183s 170s As Titan II 183s 33.5m 220s 5.1m dia, 17.1m long 54m 120s 245s 152s 289s 220s 5.1m dia, 26.2m long 63.1m 120s 245s 220s As above 245s 160s 4m dia, 10.1m long 44m 118s 225s 264s 2 8m dia, 8.5m long 38.4m 56s 3.1m dia, 7.9m long 440s 264s As above 56s 440s 264s As above each 64s 417s 264s As above 64s 417s 38.4m 38.4m 38.4m 150kg to 250km x 1,150km 205kg to 555km 37" LEO (a) 165kg to 555km 99" LEO (b) 220kg to 555km 2' LEO (c 520kg lo 278km LEO (c) 450kg to 555km LEO (c) 330kg to 1.000km (c) 2 launches (both successful) Ofleg 3/-/Palmachin 14 launches (all successlul) Prolile/1991/- SAMPEX/Jun 92/Vandenberg TOMS/Jun 93/uandenberg FAST/Dec 93/- First flight C1993 2,180kg to 185km polar (b) 2 launches (both successful) 3,082kg to 560km Sun-sync (c) Landsat 6/1991/Vandenberg NOAA K/1993/Vandenberg NOAAL/1995/Vandenberg NOAA M/1996/Vandenberg Military launches include: DMSP, N-ROSS, Slarscan 3,400kg to polar (g,i 4,445kg to polar (h,l 2,313kg to GEO (k) 17,690kg to LEO (k) 4,540kg to GT0 (k) 14,525kg to Sun-sync (i) 63,1m 5,5670kg to GEO (k) (a) From Palmachin (a) From Wallops Island (b) From \tadenberg (c) From San Marco (d) Core (e Boosters, Ariane 4-class 14,742kg to LEO (k) 4,990kg lo GTO (k,q) 2,600 to Mars (k,q) No launches to date MSX-SDIO/1992/\andenberg 4 launches (successlul) No launches to date First launch due 1991 No launches to date CRAF launch for NASA in 1995? Cassini launch for ESA in 1996 31990 launches (successful) ( Mars 0bserver/1992/Cape Canaveral (a) Refurbished ICBM (b) From Vindenberg (c) With satellite upper stage (d) Core (e) Boosters, up to 10 (I) 4,310kN with 10 boosters (g) With 8 boosters (h) With 10 boosters (i) From \andenberg (j) Ignite a T+108s (k) From Cape Canaveral (I) With UTC strap-ons (m) GD Centaur G Prime stage (n) With Hercules strap-ons (o) Filament-wound (p) Ignite at T+118s (q) Using Transfer Orbit Stage (r) Intelsat VI-F3 failed to seperate 3,983kg to 185km 28" LEO (d) 2 launches (both successlul) 2,567kg to 833km Sun-sync (e) EUVE/Aug 91/Cape Canaveral 1,447kg to GTO (g) 839kg to GPS (d) 962kg to Molniya-type (e) 3,175kg to 98" Sun-sync (e) 5,039kg to 28" LEO (d) 3,819kg to 90" (e) 1,819kg to GTO (d) 1,134kg to GPS (d) 1,275kg to Molniya-class 13 launches (successful) Geotail/1992/Cape Canaveral (a) Uprated Delta 3925 core stage, extended tanks (b)Boosters, 6 ignite at lift-off, 3 at T+62s (c) Restartable. (d) From Cape Canaveral. (e) From Vandenberg. (f) Pani D1 stage (g) Expansion ratio up from 8:1 to 12:1 (h) Each 439kN thrust - as (b) No launches to date Radarsat/1994/Vandenberg Lifesats 1-4/1994-6/Cape Canaveral 2 launches (both successlul) Contel ASC/1991/Cape Canaveral Aurora/May 91/Cape Canaveral GPS 11/1991/Cape Canaveral
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