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• 00:45, 6 November 2017 Vincent Sọ̀rọ̀ contribs uploaded File:Solar system exploration with cubesats.pdf (This presentation was made at SpaceUp Cote d'Azur (Nice, France) in October 2017. The goal was to explain the challenges of solar system exploration using small satellites, emphasizing that it will cost a lot of money on either launches or reliable spa...)
• 00:14, 12 March 2013 Vincent Sọ̀rọ̀ contribs uploaded File:Pegasus wings.gif (3 views of Orbital Pegasus' wings)
• 03:33, 12 December 2012 Vincent Sọ̀rọ̀ contribs uploaded a new version of File:Gravity drag and thrust to weight.png (Updated with the gravity drag curve and make the image larger.)
• 03:05, 12 December 2012 Vincent Sọ̀rọ̀ contribs uploaded File:Gravity drag and thrust to weight.png (Made with File:Rocket_mass.c v3 plus a gravity drag evaluation added in the iteration.)
• 01:42, 12 December 2012 Vincent Sọ̀rọ̀ contribs uploaded a new version of File:Rocket mass.c (clarification about the propellant mass. vehicle_wet_mass is the dry mass + the burnt propellant mass, but it doesn't include the propellant taken aboard and evaporated during the ascent. The output indicates the ground value now. This is still version 3.)
• 20:59, 11 December 2012 Vincent Sọ̀rọ̀ contribs uploaded a new version of File:Isp.png (starting at 280 instead of 270)
• 20:53, 11 December 2012 Vincent Sọ̀rọ̀ contribs uploaded File:DeltaV.png (Graph representing rocket dry and wet mass as function of the Delta V. Done with version 3 of File:Rocket_mass.c, overall thrust-to-weight ratio is 2.5 and Isp is 340s.)
• 20:52, 11 December 2012 Vincent Sọ̀rọ̀ contribs uploaded File:Isp.png (Graph representing rocket dry and wet mass as function of the Isp. This is clearly exponential on the left because a too low Isp means that orbit cannot be reached, the mass ratio gets too high. Done with version 3 of File:Rocket_mass.c. Delta V is 8300 m)
• 20:09, 11 December 2012 Vincent Sọ̀rọ̀ contribs uploaded a new version of File:Mass ratio.png (Updated with version 3 of File:Rocket_mass.c. Delta V is 8300 instead of 9000 m/s too, and overall thrust-to-weight ratio is 2.5 instead of 1.25.)
• 20:08, 11 December 2012 Vincent Sọ̀rọ̀ contribs uploaded a new version of File:Engine thrust to weight.png (Updated with version 3 of File:Rocket_mass.c. Delta V is 8300 instead of 9000 m/s too, and overall thrust-to-weight ratio is 2.5 instead of 1.25.)