timelines:kolyma_vehicles
This is an old revision of the document!
Table of Contents
Vehicle Technical Data
This page provides a reference to the launchers and spacecraft of the Kolyma’s Shadow timeline.
NB: All Isp values are given as vacuum-equivalent.
USSR
R-6
R-6 Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| Blok-A | R-6 1st stage | Nitric acid/UDMH | 27 300 kg | 246 000 kg | 4x RD-215 | 3 456 kN | 291 s |
| Blok-B | R-6 2nd stage | Nitric acid/UDMH | 6 715 kg | 60 430 kg | 1x RD-221 | 1 118 kN | 318 s |
| Blok-V | R-6A 3rd stage | kerolox | 1 440 kg | 6 335 kg | 1x RD-0105 | 49.4 kN | 316 s |
R-6 Family Performance
| R-6 “Shesterka” | R-6A “Luna” | |
|---|---|---|
| 3rd Stage | None | Blok-V |
| 250 km, 55 deg (Tyuratam) | 3 117 kg | 4 683 kg |
| 250 km, 90 deg (Plesetsk) | 2 192 kg | 4 029 kg |
| C3=0 (Tyuratam) | N/A | 486 kg |
R-200
R-200 Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| Blok-A | R-200 1st stage | Nitric acid/UDMH | 34 928 kg | 388 095 kg | 4x RD-xxx | 6 400 kN | 297 s |
| Blok-B | R-200 2nd stage | Nitric acid/UDMH | 5 467 kg | 72 628 kg | 1x RD-yyyy | 900 kN | 320 s |
R-200 Family Performance
| R-200 “Kosmos” | |
|---|---|
| 250 km, 55 deg (Tyuratam) | 9 499 kg |
| 250 km, 90 deg (Plesetsk) | 8 105 kg |
| C3=0 (Tyuratam) | N/A |
M-1
M-1 Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| Blok-A/B/V | M-1 1st stage core (3x) | kerolox | 36 127 kg | 344 155 kg | 6x VM-12 | 6 600 kN | 322 s |
| Blok-G | M-1 2nd stage | kerolox | 5 544 kg | 73 658 kg | 1x VM-202 | 1100 kN | 322 s |
| Blok-D | M-1 bis 3rd stage | kerolox | 1 440 kg | 6 335 kg | 1x RD-0105 | 49.4 kN | 316 s |
M-1 Family Performance
| M-1 “Zarya” | M-1 bis “Signal” | |
|---|---|---|
| 250 km, 55 deg (Tyuratam) | 9 370 kg | 10 663 kg |
| 250 km, 90 deg (Plesetsk) | 7 927 kg | 9 345 kg |
| C3=0 (Tyuratam) | N/A | 2 010 kg |
UR-500
Note: This vehicle is substantially the same as the 3-stage Proton of OTL.
UR-500 Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| 1st stage | 1st stage core | N2O4/UDMH | 31 500 kg | 419 410 kg | 6x RD-nnn | 9 500 kN | 316 s |
| 2nd stage | 2nd stage | N2O4/UDMH | 12 215 kg | 156 113 kg | 4x RD-ooo | 2 300 kN | 326 s |
| 3rd stage | 3rd stage | N2O4/UDMH | 4 685 kg | 46 562 kg | 1x RD-xxxx | 613 kN | 325 s |
UR-500 Family Performance
| UR-500 “Proton” | |
|---|---|
| 250 km, 55 deg (Tyuratam) | 20 313 kg |
| 250 km, 90 deg (Plesetsk) | 18 066 kg |
| C3=0 (Tyuratam) | 4 144 kg |
Zarya
Zarya-A, Zarya-B (Zarya-4 configuration, airlock extended) and Zarya-BM.
| Zarya-A | Zarya-B | Zarya-BM | |
|---|---|---|---|
| Crew | 1 | 2 | 2 |
| First flight | Zarya-1 (1962) | Zarya-3 (1964) | Zarya-9 (1970) |
| Total mass | 4 050 kg | 5 520 kg | 6 030 kg |
| Re-entry module (SA) mass | 2 280 kg | 2 400 kg | 2 450 kg |
| Service module (PA) mass (wet) | 1 930 kg | 2 600 kg | 2 650 kg |
| Orbital module (BO) mass | N/A | Varies. Typical 520 kg (Zarya-4) | 930 kg |
| Delta-v | 140 m/s | 265 m/s | 242 m/s |
USA
Minerva
Minerva Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| LRB | Minerva-1 1st stage, Minerva-2 boosters | kerolox | 6 230 kg | 82 700 kg | 1x E-1 | 1 884 kN | 290 s |
| Core Stage | Minerva-2 1st stage | kerolox | 16 600 kg | 220 400 kg | 2x E-1 | 3 768 kN | 290 s |
| Upper Stage | Minerva-2 2nd Stage | hydrolox | 6 000 kg | 51 000 kg | 1x J-2 | 1 033 kN | 421 s |
| Centaur-M | Minerva-1 2nd Stage, Minerva-2 3rd stage (TBC) | hydrolox | 2 240 kg | 19 085 kg | 2x RL-10 | 134 kN | 442 s |
Minerva Family Performance
| Minerva-1 | Minerva-20 | Minerva-20c | Minerva-22 | Minerva-22c | Minerva-24 | Minerva-24c | |
|---|---|---|---|---|---|---|---|
| Boosters | None | None | None | 2xLRBs | 2xLRBs | 4xLRBs | 4xLRBs |
| 3rd Stage | None | None | Centaur-M | None | Centaur-M | None | Centaur-M |
| 250 km, 28.5 deg (Cape Canaveral) | 3 719 kg | 9 794 kg | 12 854 kg | 16 146 kg | 18 727 kg | 21 395 kg | 23 643 kg |
| 250 km, 90 deg (Vandenberg AFB) | 3 319 kg | 8 740 kg | 11 542 kg | 14 618 kg | 16 834 kg | 19 459 kg | 21 223 kg |
| 35,786 x 250 km, 28.5 deg (Cape) | 1 036 kg | N/A | 6 500 kg | N/A | 10 876 kg | N/A | 14 550 kg |
| C3=0 (Cape Canaveral) | 456 kg | 898 kg | 4 585 kg | 3 595 kg | 7 234 kg | 5 739 kg | 9 493 kg |
Minerva B
Uprated Minerva variant developed beginning in 1970 for Columbia lunar orbit program. Featured improved E-1A and J-2S engines for increased performance as well as changes aimed at assembly simplification and cost reduction.
Minerva B Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| LRB | Minerva-B1 1st stage, Minerva-B2 boosters | kerolox | 6 230 kg | 82 700 kg | 1x E-1A | 2 250 kN | 310 s |
| Core Stage | Minerva-B2 1st stage | kerolox | 16 600 kg | 220 400 kg | 2x E-1A | 4 500 kN | 310 s |
| Upper Stage | Minerva-B2 2nd Stage | hydrolox | 6 000 kg | 51 000 kg | 1x J-2S | 1 036 kN | 436 s |
| Centaur-M | Minerva-B1 2nd Stage, Minerva-B2 3rd stage (TBC) | hydrolox | 2 240 kg | 19 085 kg | 2x RL-10 | 134 kN | 444 s |
Minerva B Family Performance
| Minerva-B1 | Minerva-B20 | Minerva-B20c | Minerva-B22 | Minerva-B22c | Minerva-B24 | Minerva-B24c | |
|---|---|---|---|---|---|---|---|
| Boosters | None | None | None | 2xLRBs | 2xLRBs | 4xLRBs | 4xLRBs |
| 3rd Stage | None | None | Centaur-M | None | Centaur-M | None | Centaur-M |
| 250 km, 28.5 deg (Cape Canaveral) | 4 623 kg | 13 297 kg | 15 213 kg | 21 414 kg | 22 404 kg | 28 274 kg | 28 532 kg |
| 250 km, 90 deg (Vandenberg AFB) | 3 884 kg | 11 180 kg | 13 302 kg | 18 316 kg | 19 628 kg | 24 291 kg | 24 991 kg |
| 35,786 x 250 km, 28.5 deg (Cape) | 1 365 kg | N/A | 7 112 kg | N/A | 11024 kg | N/A | 14 465 kg |
| C3=0 (Cape Canaveral) | 743 kg | 2216 kg | 5 524 kg | 5 540 kg | 8 787 kg | 8 238 kg | 11 697 kg |
Mercury
Cosmetic differences only from OTL.
| Mission | Capsule | Pilot |
|---|---|---|
| Mercury-1 | Spirit of Freedom | James Wood |
| Mercury-2 | Columbia | Joe Walker |
| Mercury-3 | Liberty | Al Perini |
| Mercury-4 | Bob White | |
| Mercury-5 | Albert Crews | |
| Mercury-6 | Orville | Neil Armstrong |
| Mercury-7 | Wilbur | Al Perini |
Dynasoar
| Glider | Type |
|---|---|
| Diana | Atmospheric Test Vehicle |
| Aura | Mk.I Glider |
| Rhene | Mk.I Glider. Destroyed 1972 |
| Athena | Mk.II Glider |
| Thebe | Mk.II Glider |
| Tara | Mk.I Glider. Replacement for Rhene |
| Mk.I Glider | Mk.II Glider | Standard Mission Module | Dynasoar Experimental Laboratory | |
|---|---|---|---|---|
| Crew | 1 | 3 | N/A | N/A |
| Payload | 600 kg | 250 kg | N/A | N/A |
| Dry mass | 5 800 kg | 6 300 kg | 3 100 kg | 7 250 kg |
| Propellant mass | N/A | N/A | 750 kg | 1 500 kg |
| Thrust | N/A | N/A | 720 N | 720 N |
| Isp | N/A | N/A | 280 s | 280 s |
Columbia
| Columbia CSM | |
|---|---|
| Crew | 2 |
| Command Module mass | 3 400 kg |
| Service Module dry mass | 2 230 kg |
| Propellant mass | 5 500 kg |
| Thrust | 720 N |
| Isp | 310 s |
| Delta-v | 2 046 m/s |
Europe
Europa
First European attempt to build a space launcher under the European Launcher Development Organisation (ELDO) using pre-existing national rockets for each stage. Failed to ever reach orbit.
Europa Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| Blue Streak | Europa 1st stage | kerolox | 6 997 kg | 82 409 kg | 2x RZ-2 | 1 672 kN | 248 s |
| Coralie | Europa 2nd stage | N2O4/UDMH | 2 099 kg | 9 795 kg | 1x Vexin A | 274 kN | 277 s |
| Astris | Europa 3rd stage | N2O4/Aerozine-50 | 610 kg | 2 760 kg | 1x Astris | 23.3 kN | 310 s |
Theseus
First European launcher to reach orbit. Developed by the European Space Launch Agency (ESLA) as a “clean sheet” design.
Theseus Family Elements
| Stage Name | Description/Role | Prop Type | Dry Mass | Prop Mass | Engine | Thrust | ISp |
|---|---|---|---|---|---|---|---|
| Stage-1 | Theseus 1st stage | kerolox | 17 567 kg | 189 103 kg | 4x RZ-3 | 3 600 kN | 288 s |
| Stage-2 | Theseus 2nd stage | kerolox | 4 364 kg | 41 564 kg | 1x RZ-3a | 900 kN | 300 s |
| ECT | “Etape cryogénique pour Thésée.” Theseus 3rd stage | hydrolox | 2 247 kg | 12 733 kg | 1x HM7 | 64.8 kN | 443 s |
| Sorcier | Upper stage | Solid | 34 kg | 335 kg | 1x Sorcier SRM | 19.4 kN | 295 s |
Theseus Performance
| Theseus | |
|---|---|
| LEO (Kourou) | 7 000 kg |
| GTO (Kourou) | 2 500 kg |
timelines/kolyma_vehicles.1446367511.txt.gz · Last modified: 2019/03/29 15:18 (external edit)