Path: Orbit/OrbitManeuver
% Demonstrate a Hohmann Transfer in simulation The spacecraft has 3 reaction wheels and a single thruster that needs to be aligned with the velocity vector for the burns. The delta-V is computed with OrbMnvrHohmann, and the propellant mass is then computed using RocketMass. The fuel mass is then used to compute the duration of the finite burn. A numerical simulation implements the necessary attitude and orbit ------------------------------------------------------------------------- See also: Mag, RV2El, Period, OrbMnvrHohmann, RocketMass, InertiaCubeSat, RHSRWAOrbit, PID3Axis, RK4, TimeHistory, Figui ------------------------------------------------------------------------- % ------------------------------------------------------------------------------- Copyright (c) 2022 Princeton Satellite Systems, Inc. All rights reserved. Since version 2022.1 -------------------------------------------------------------------------------
CubeSat: AttitudeControl/InertiaCubeSat Orbit: OrbitManeuver/OrbMnvrHohmann Propulsion: Rocket/RocketMass SC: BasicOrbit/Period SC: BasicOrbit/RV2El SCPro: DynamicalModels/RHSRWAOrbit SCPro: ProControl/PID3Axis Common: Database/Constant Common: GUIs/Figui Common: Graphics/TimeHistory Common: Quaternion/QTForm Math: Integration/RK4 Math: Linear/Mag
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