Space Propulsion - IAP/TU Wien

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Space Propulsion Kinetics for rotational motion of S/C ω α = rotational motion T = torque [N.m] Θ = angle of rotation of the spacecraft [rad] = angular velocity of the spacecraft [rad/s] angular acceleration of the spacecraft during a firing, [rad/s 2 ] Lin. analogon F = force [N] s = path [m] v = velocity [m/s] a = acceleration [m/s 2 ] rotational motion 1 αt b 2 a s = 2 t 2 Θ = 2 α = T I v ω = αt b Lin. analogon a = v = F m at I v = mass moment of inertia of the vehicle, [kg.m 2 ] m = mass [kg] H = I v ω p = mv t b = duration of the burn [s] H = change of spacecraft angular momentum during the firing, [kg.m 2 /s] t = time [s] p = momentum [m/s] H = Tt b p ∫ Fdt ≅ = Ft
Space Propulsion Kinetics for rotational motion of S/C Linear analogon torque, produced by n thrusters, mounted at torque arm L, firing with equal thrust F T = nFL F during the burn, the angular acceleration of the spacecraft is α = nFL I v a = F m at shut down, the vehicle will have turned by 2 nFLtb 2 at shutdown, the spacecraft is left rotating at angular velocity Θ = ω = 2I v v nFL I t b a s = 2 t v = a. t angular momentum produced by a single firing is p = H = Tt b ∫ Fdt propellant consumed during the burn is nFt b m p = = I sp H LI sp • = F m I sp /
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Space Propulsion - IAP/TU Wien

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