{{:timelines:p4_p00.png?650|}}

=====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.

{{:timelines:rockets_4.png?650|Rockets compared}}

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===== USSR =====

====R-6 ====

{{:timelines:r6.png?500|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====

{{:timelines: orel2.png?500|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.

{{:timelines:proton_5.png?150|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====

{{:timelines:zaryas.png?500|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 | 

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=====USA=====

==== Minerva ====

{{:timelines:minerva-2.png?500|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 ====
{{:timelines:mercury6.png|”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 ====
{{:timelines:ds-land6b.png?500|”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 ====
{{:timelines:columbia1.png?400|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 |

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=====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.

{{:timelines:europa-side1.png?500|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.

{{:timelines:theseus-side1.png?500|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 |   

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==== Navigation ====

**[[kolyma_s_shadow_an_alternate_space_race|Kolyma's Shadow]]**