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Vapor has been around since 2012. Since then, we've had many key players come and go, as well as a significant reboot in 2018, which has left many articles contained in this wiki out-of-date or entirely non-canon. Rather than simply remove parts of our history that no longer apply, we have decided to preserve them in our "Legends Canon," so that they may exist outside of Vapor's proper and current canon history. This is one of those articles.
Launch Vehicle
Karshi I
Titan 1 ICBM
Launch of a Karshi I-CLV from Amano Space Center
Detailed Information
Function CLV
Manufacturer Chandra Aerospace
Country of Origin Sri Tschow
Height 31m
Diameter 3.05m
Mass 105,140kg
Stages 2
Payload to LEO 1,800kg
Status Indefinite Hold
Launch Sites Amano Space Center
Total Launches 14
Launch Failures 2
First Flight TBA
Last Flight TBA
The Chandra Aerospace CLV-106A Karshi I is Sri Tschow's first multistage crew launch vehicle. After [TBA] sent the first human into space in [TBA], the government Sri Tschow set out to design the first rocket dedicated to taking humans into space. The Royal Space Advisory Commision, or RSAC, launched a design competition among the major aerospace and rocketry contractors of the time. The proposal for a multistage, liquid fueled expendable launch system entered by a small aircraft design firm, Chandra Aerospace, won the bid. By the November [TBA], the first rocket, dubbed the Karshi I, was launched, carrying the first Tschowan into space, Hitachi Narin. Thirteen launches were scheduled, and on the fifth, a problem with the staging system caused the second stage engine to ignite too early, causing a massive explosion. Fortunately, the Crew Escape System pulled the capsule away from the burning rocket moments before it exploded, allowing the crew to float safely back to the ground. On the fourteenth launch, a fuel leak ignited by the engines caused the entire rocket to explode, killing the pilot, Bratya Sendal. The program was placed on indefinite hold while an investigation into what caused the leak was launched.



Research and DevelopmentEdit


Launch HistoryEdit



First Stage:

  • Empty Mass: 4,000kg
  • Thrust (Vacuum): 1,467kn
  • Specific Impulse (Vacuum): 2.84kn/s
  • Burn Time: 138s
  • Diameter: 3.1m
  • Span: 3.1m
  • Length: 16.0m
  • Propellants: LOX/Hydrogen
  • Engines: 2 Armstrong R-8

Second Stage:

  • Empty Mass: 1,725kg
  • Thrust (Vacuum): 356kn
  • Specific Impulse (Vacuum): 3.02kn/s
  • Burn Time: 225s
  • Diameter: 2.3m
  • Span: 2.3m
  • Length: 9.8m
  • Propellants: LOX/Hydrogen
  • Engines: 1 Armstrong R-12