Path: Propulsion/Rocket
% Computes the thrust and exhaust velocity given one pair [uE0,t0]. This assumes that the available energy from combustion and the engine efficiency does not change. The relationship is parabolic. You can also input T instead of uE and the output will be uE. This relationship does not extend beyond stochiometric conditions. Type RocketVariableUEAndT for a demo for the RL10B-2. Since version 2014.1 -------------------------------------------------------------------------- Form: t = RocketVariableUEAndT( uE0, t0, uE ) -------------------------------------------------------------------------- ------ Inputs ------ uE0 (1,1) Reference exhaust velocity (m/s) t0 (1,1) Reference thrust in vacuum (N) uE (1,:) Exhaust velocity (m/s) ------- Outputs ------- t (1,:) Thrust (N) --------------------------------------------------------------------------
Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
Back to the Propulsion Module page