Spacecraft electric propulsion encompasses spacecraft propulsion systems that use electric energy to accelerate and expel propellant, generating thrust through electric or magnetic fields. Their principal advantage over chemical rockets is much higher specific impulse, meaning greater propellant efficiency, but the limited electrical power available aboard spacecraft yields much lower thrust, making electric propulsion unsuitable for launch from Earth's surface and better suited to long-duration in-space maneuvers.
The main families of spacecraft electric propulsion include electrostatic devices such as gridded ion engines, Hall-effect thrusters, and colloid thrusters; electromagnetic devices such as pulsed plasma thrusters, magnetoplasmadynamic thrusters, and pulsed inductive thrusters; and electrothermal devices such as resistojets and arcjets. Radio-frequency and electron cyclotron resonance ion engines form a further subclass that avoids physical electrode contact with the propellant plasma.
Electric propulsion concepts date to Konstantin Tsiolkovsky's 1911 writings and Robert H. Goddard's 1917 electrostatic accelerator patent, with the first laboratory thruster built by Valentin Glushko at the Gas Dynamics Laboratory in 1933. The first electric engine operated in space aboard SERT-1 in 1964, and Hall-effect thrusters entered operational service on Soviet Meteor spacecraft in the 1970s. After the Cold War, Western researchers gained direct access to Soviet Hall thruster technology, and by the late 1990s electric propulsion had entered routine commercial geostationary satellite service and deep-space primary propulsion with Deep Space 1. Later milestones include Dawn's ion-propelled orbits of Vesta and Ceres, BepiColombo's high-performance gridded ion thruster system, and Psyche's first use of Hall Effect thrusters in interplanetary space.
Background and history
Traditional rocketry has dominated aerospace propulsion in the 20th and early 21st centuries. Conventional rockets achieve motion by expelling mass, most commonly the combustion output from chemical propellants to generate thrust via Newton's third law, which is the familiar rocket launch with explosive flame and smoke beneath it. Electric propulsion developed as a parallel track for spacecraft propulsion, focusing on electrical and electrostatic methods of accelerating propellant rather than relying solely on chemical combustion.
1900s to the 1950s
Early antecedents of electric propulsion emerged by the early 20th century. Konstantin Tsiolkovsky writing in 1911 included an early published statement of the basic electric-propulsion idea: using electricity to increase the velocity of ejected particles. Tsiolkovsky wrote:
Early work on electrostatic acceleration dates to Robert H. Goddard, whose 1917 patent application (granted 1920) Edgar Choueiri has described in Journal of Propulsion and Power as the first documented electrostatic ion accelerator intended for propulsion. In his 1918-1919 manuscript "To whomsoever will read in order to build", Yuri Kondratyuk discussed electric propulsion in the context of cathode rays and described thrust from electrically discharging and repelling material particles, alongside a schematic that Choueiri noted may be the "first conceptualization of a colloid thruster". Hermann Oberth's 1929 book Wege zur Raumschiffahrt defined, in Edgar Choueiri's assessment, 'for the first time publicly and unambiguously' that related propulsion concepts were 'a serious and worthy pursuit in astronautics'.
During the interwar period, early electric-propulsion work began moving from theory toward experiment. Valentin Glushko joined the Gas Dynamics Laboratory in Leningrad in 1929, and by 1933 with staff developed an early electric thruster prototype, an electrothermal approach intended for spacecraft propulsion. The device was likely the first electric thruster to ever be studied on a thruster stand, and was the first electrothermal thruster ever built.
According to Choueiri, early thinking and experimentation in related propulsion research focused mainly on electrostatic concepts, but the first laboratory electric thruster was electrothermal and the first electric thruster to fly in space was a mostly electromagnetic pulsed plasma device. After the 1930s, related electric-propulsion research reached a lull in public published activity for over a decade through and after World War II.
The postwar period saw growing institutional interest in electric propulsion within both military and civilian research programs. The first clear postwar reappearance of these propulsion concepts in open scientific literature was in December 1945, in the Journal of the American Rocket Society, where the term "ion rocket" was first coined by Herbert Radd. In 1947 at Fort Bliss, Wernher von Braun encouraged Ernst Stuhlinger to investigate his spacecraft propulsion ideas, telling Stuhlinger, "I wouldn't be a bit surprised if one day we flew to Mars electrically!"
1960s-1970s During the 1960s through the 1970s, electric and electromagnetic propulsion matured experimentally, with some systems flying in limited operational roles. Electric propulsion research during this period expanded across multiple countries and institutional settings.
In West Germany, electric-propulsion development also proceeded from 1960 at German Aerospace Center (DLR) institutes in Stuttgart and Braunschweig and at the University of Giessen. At Gießen, Horst Löb's group began development of radio-frequency ion thrusters of the RIT type, which use radio frequency fields rather than physical electrodes to ionize propellant, starting with the conception, laboratory model, and first tests of the RIT-10; the prototype was further improved through the 1960s and transferred to industry for qualification in 1970. A June 1960 decree of the Central Committee and Council of Ministers (No. 715-296), declassified after the Soviet period, directed the development of "space electric rocket engines". This included ion and electroplasma thrusters with target specific impulse of 5,000-10,000 seconds, a measure of propellant efficiency, assigning work to OKB-1, the Kurchatov Institute, and other named bureaus as part of a broader 1960-1967 Soviet Union space development plan. In 1964, Ernst Stuhlinger published Ion Propulsion for Space Flight, characterized by Choueiri as the first comprehensive book on electric rocket technology, marking the field's transition into a serious engineering discipline.
On 20 July 1964, two electrostatic ion engines were tested in space in the Space Electric Rocket Test (SERT I), and the mercury electron-bombardment engine produced thrust in flight. SERT I was the first spacecraft to incorporate electric propulsion; its mercury electron bombardment ion engine, which ionizes mercury vapor by bombarding it with electrons and then accelerates the resulting ions electrically, ran for 31 minutes, becoming the first electric engine to operate in space. A 1966 NASA Lewis Research Center overview stated that electric-propulsion spacecraft then under study could not be expected to take off from Earth and therefore would need to be launched to Earth orbit by chemical rockets before beginning low-thrust operation. The 30 November 1964 Zond 2 mission to Mars from the Soviet Union marked the first planetary use of electric propulsion. Following the Zond 2 demonstration, pulsed plasma thruster development was transferred from the Kurchatov Institute to OKB Fakel, whose "Globus" pulsed propulsion unit flew in 1968. The follow-on Space Electric Rocket Test II (SERT II), launched on 3 February 1970, was the first long-duration operation of ion thrusters in space; its two mercury electron-bombardment engines accumulated over 5 months and 3.5 months of continuous operation respectively, and after intermittent restarts, one thruster logged over 11 years of total operation through 1981.
Alongside ion engine development, a distinct line of electromagnetic thruster research was advancing in the Soviet Union. In the 1960s, A. I. Morozov proposed the stationary plasma thruster (SPT), a Hall-effect device that accelerates ionized propellant using perpendicular electric and magnetic fields. Within decades, hundreds would fly in space.
The first SPT was tested in orbit aboard a Meteor spacecraft in 1972, with corrective propulsion units operating on further Meteor missions through 1980.
1980s Commercial electrothermal propulsion entered operational satellite service during this period. Hydrazine resistojets, electric thrusters that heat propellant before expelling it, began commercial geostationary north-south orbital station-keeping, used to maintain orbital position, with Intelsat V in 1980.
1990s
The end of the Cold War opened access to previously restricted Soviet electric propulsion technology. U.S. electric propulsion specialists traveled to Russia in 1991 to evaluate the Russian SPT-100 at the Scientific-Research Institute of Thermal Processes in Moscow and at Fakel in Kaliningrad using U.S. instrumentation. Brophy's subsequent JPL report said the measured performance appeared close to the advertised values, and noted claims that more than fifty lower-power SPT units had already flown on Russian spacecraft. The report laid out a second program phase in which thrusters would be brought to the United States for testing toward possible Western use. That work fed into the later Ballistic Missile Defense Organization Russian Hall Electric Thruster Technology (RHETT) effort to move Hall thruster technology toward Western operational use.
Electric-propulsion work matured across the decade. Hydrazine-based arcjet rockets were deployed in 1993 on Telstar 401, extending electrothermal electric propulsion into higher-performance commercial geostationary use.
Alongside these experimental programs, electric propulsion was also entering routine commercial service. Commercial electric propulsion also entered Western geostationary satellite operations in the 1990s, as Hughes Boeing 601HP communications satellites began using gridded xenon ion thrusters (XIPS) for station-keeping in 1997. After initial Russian usage from the 1970s, beginning in the 1990s qualified SPT units entered service on American and European spacecraft as well. European electric propulsion programs reached similar milestones in the years that followed. The Gießen RIT line later reached flight application on the European Space Agency's Artemis satellite, launched in 2001, which carried two German RIT-10 thrusters for station-keeping. By the late 1990s, ESA was already positioning solar electric primary propulsion as a key technology for future deep-space missions through SMART-1, whose PPS-1350-G Hall thruster was later developed in the CNES Stentor satellite program and adapted from a geostationary station-keeping design.
By the late 1990s, electric propulsion had moved from experimental and military programs into routine commercial satellite operations, particularly for geostationary station-keeping, orbit raising, and related orbit-control maneuvers. Deep Space 1 became the first U.S. space mission to use an ion thruster as its primary means of propulsion through 1998, validating NASA's NSTAR solar electric propulsion system in long-duration flight.
21st century
SMART-1, launched in 2003, demonstrated solar electric primary propulsion in flight for ESA and carried the Hall thruster system that had been developed from late-1990s European work on commercial electric-propulsion applications and deep-space mission preparation.