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timelines:kolyma_vehicles

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.

Rockets compared


USSR

R-6

The R-6 "Shesterka" ICBM

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

The R-200 "Kosmos" and Orel Raketoplan

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 Proton

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, -B and -BM

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-22 rocket and Dynasoar Mk.I

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

”Orville” from “Wilbur” during the joint Mercury-6/7 mission.

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

”Diana” lands at White Sands.

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 circumlunar spaceship (WIP)

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

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

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.txt · Last modified: 2015/12/11 05:42 by Petike