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Combined display of all available logs of NPrize. You can narrow down the view by selecting a log type, the username (case-sensitive), or the affected page (also case-sensitive).
- 00:45, 6 November 2017 Vincent talk 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 talk contribs uploaded File:Pegasus wings.gif (3 views of Orbital Pegasus' wings)
- 03:33, 12 December 2012 Vincent talk 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 talk 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 talk 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 talk contribs uploaded a new version of File:Isp.png (starting at 280 instead of 270)
- 20:53, 11 December 2012 Vincent talk 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 talk 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 talk 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 talk 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.)
- 20:06, 11 December 2012 Vincent talk contribs uploaded a new version of File:Overall thrust to weight.png (Updated with version 3 of File:Rocket_mass.c. Delta V is 8300 instead of 9000 m/s too.)
- 20:04, 11 December 2012 Vincent talk contribs uploaded a new version of File:Final acceleration.png (Updated with version 3 of File:Rocket_mass.c. Delta V is 8300 instead of 9000 m/s too.)
- 20:02, 11 December 2012 Vincent talk contribs uploaded a new version of File:Payload 0-80kg.png (fixing update)
- 19:58, 11 December 2012 Vincent talk contribs uploaded a new version of File:Payload 0-80kg.png (Updated with version 3 of File:Rocket_mass.c. Delta V is 8300 instead of 9000 m/s too.)
- 19:57, 11 December 2012 Vincent talk contribs uploaded a new version of File:Payload 0-6k.png (Updated with version 3 of File:Rocket_mass.c. Delta V is 8300 instead of 9000 m/s too.)
- 13:26, 11 December 2012 Vincent talk contribs uploaded a new version of File:Rocket mass.c (Refining the model: better structure, more realistic fairing, adding forgotten pipes and valves, tanks alignment on outer shell, composite skirts for non-structural or soft tanks.)
- 00:26, 11 December 2012 Vincent talk contribs uploaded File:Rocket model.png (Rocket model illustration for the computed rocket model: File:Rocket_mass.c)
- 03:10, 27 November 2012 Vincent talk contribs uploaded File:Rocket ignition.png (Graph of the rocket trajectory for first moments after release, assuming ignition at the time of the release, a thrust vector with 45 deg pitch, and an overall thrust-to-weight ratio of 2. No atmosphere considered whatsoever.)
- 02:01, 24 November 2012 Vincent talk contribs uploaded File:Heat transfer to rocket tank.c (Program calculating the heat transferred to a cryogenic tank (typically LOX) for balloon- or air-to-orbit vehicles. Two heat transfer approximations are done. * when the vehicle is waiting on the ground after tank filling and before it lifts-off from the )
- 02:59, 17 November 2012 Vincent talk contribs uploaded File:ISA atmospheric model.c (C Implementation of the international standard atmosphere ([https://en.wikipedia.org/wiki/International_Standard_Atmosphere ISA]) model. This is a port of http://www.digitaldutch.com/atmoscalc/ .)