Satellite propulsion changes velocity through momentum transfer: the spacecraft accelerates expelled propellant in one direction, producing a change in its own motion. Chemical thrusters create hot combustion gases and accelerate them through a nozzle. Electric systems first ionize propellant, then use electric or magnetic fields to accelerate charged particles. The physical mechanism differs, but both alter spacecraft velocity after launch.
Specific impulse helps compare how effectively a propulsion system uses propellant. In this context, exhaust velocity is central: electric propulsion produces lower thrust but high exhaust velocity, whereas chemical propulsion uses hot gas acceleration to generate thrust. Considering specific impulse alongside thrust and propellant efficiency allows physicists to judge whether a system suits a required maneuver or long-duration mission.
Electric propulsion uses electrical energy to ionize propellant and accelerate charged particles with electric or magnetic fields. This process produces high exhaust velocity but lower thrust than the rapid gas acceleration associated with chemical thrusters. The tradeoff affects mission suitability: high exhaust velocity supports propellant-efficient operation, while lower thrust influences how the system performs required spacecraft maneuvers.
It supports orbit raising, station keeping, collision avoidance, attitude control, and end-of-life disposal. These operations represent different post-launch needs: changing the orbit, maintaining a desired position, avoiding a hazard, controlling orientation, or deliberately managing the spacecraft’s final phase. Consequently, propulsion is important across communications, Earth observation, navigation, and deep-space exploration missions.
Chemical systems use combustion gases and a nozzle, while electric systems require electrical energy, propellant ionization, and electric or magnetic fields to accelerate charged particles. These components connect an energy source to momentum transfer: chemical processes drive gas acceleration, whereas electrical energy drives charged-particle acceleration. Examining that chain helps relate system design to propulsion performance.
Mission evaluation combines several physical measures rather than relying on thrust alone. Physicists examine momentum transfer, specific impulse, thrust, and propellant efficiency to assess performance and design. Those measures help determine whether a system can provide the required orbit changes, orientation control, station keeping, collision avoidance, or disposal capability for a particular spacecraft mission.