Electrically powered spacecraft propulsion is any of a number of forms of electric motors which spacecraft can employ to gain mechanical energy in outer space.
Most of these kinds of propulsion work by electrically powering propellant to high speed. Electric thrusters typically offer much higher specific impulse, however, due to practical power source constraints thrust is weaker compared to chemical thrusters by several orders of magnitude.[1] Russian satellites have used electric propulsion for decades, and newer Western geo-orbiting spacecraft are starting to use them for north-south stationkeeping.
Contents |
The idea of electric propulsion dates back to 1906, when Robert Goddard considered the possibility in his personal notebook.[2] Konstantin Tsiolkovsky published the idea in 1911.
This type of rocket-like reaction engine uses electric energy to obtain thrust from propellant carried with the vehicle. Unlike rocket engines these kinds of engines do not necessarily have rocket nozzles, and thus many types are not considered true rockets.
Electric Propulsion thrusters for spacecraft are usually grouped in three families based on the type of force used to accelerate the ions of the plasma.
Electric propulsion systems can also be characterized as either steady (continuous firing for a prescribed duration) or unsteady (pulsed firings accumulating to a desired impulse).
If the acceleration is caused mainly by the Coulomb Force (i.e application of a static electric field in the direction of the acceleration) the device is considered electrostatic.
The electrothermal category groups the devices where electromagnetic fields are used to generate a plasma to increase the heat of the bulk propellant. The thermal energy imparted to the propellant gas is then converted into kinetic energy by a nozzle of either solid material or magnetic fields. Low molecular weight gases (e.g. hydrogen, helium, ammonia) are preferred propellants for this kind of system.
Performance of electrothermal systems in terms of specific impulse (Isp) is somewhat modest (500 to ~1000 seconds), but exceeds that of cold gas thrusters, Monopropellant rockets, and even most bipropellant rockets. In the USSR, electrothermal engines were used since 1971; the Soviet "Meteor-3", "Meteor-Priroda", "Resurs-O" satellite series and the Russian "Elektro" satellite are equipped with them.[3] Electrothermal systems by Aerojet (MR-510) are currently used on Lockheed-Martin A2100 satellites using hydrazine as a propellant.
If ions are accelerated either by the Lorentz Force or by the effect of an electromagnetic fields where the electric field is not in the direction of the acceleration, the device is considered electromagnetic.
|
||||||||||||||||||||||||||||||||||||||
|
|
Wikis
Quiz
Search
