Minimize THEMIS

THEMIS (Time History of Events and Macroscale Interactions during Substorms) / ARTEMIS

THEMIS is a mission within NASA's MIDEX (Medium Explorer) program, approved in May 2004. The goal of THEMIS is to fly five small spacecraft through explosive geomagnetic disturbances to solve the mystery of what triggers the colorful eruptions of the Northern and Southern lights. These violent ”substorms” reflect major reconfigurations of near-Earth space and have significant implications for space weather, affecting satellites and terrestrial communications.

The overall objective is to study fundamental questions regarding the magnetospheric substorm instability, a dominant mechanism of transport and explosive release of solar wind energy within Geospace. THEMIS will elucidate which magnetotail process is responsible for substorm onset at the region where substorm auroras map (~10 RE): i) a local disruption of the plasma sheet current or ii) that current's interaction with the rapid influx of plasma emanating from lobe flux annihilation at ~25 RE. Correlative observations from long-baseline (2-25 RE) probe conjunctions, will delineate the causal relationship and macroscale interaction between the substorm components.

The five identical probes (P1, P2, P3, P4, P5) of THEMIS measure particles and fields on orbits which optimize tail-aligned conjunctions over North America. Ground observatories time auroral breakup onset. Three inner probes at ~10 RE monitor current disruption onset, while two outer probes, at 20 and 30 RE respectively, remotely monitor plasma acceleration due to lobe flux dissipation. In addition to addressing its primary objective, THEMIS answers critical questions in radiation belt physics and solar wind - magnetosphere energy coupling. THEMIS's probes use flight-proven instruments and subsystems, yet demonstrate spacecraft design strategies ideal for Constellation class missions. THEMIS is complementary to NASA's MMS (Magnetosphere Multistage) program and a science and a technology pathfinder for future STP (Solar Terrestrial Probe) missions. 1) 2) 3)

In July 2009, the THEMIS mission split into two missions:

- The first, THEMIS-Low, consisting of the three inner probes (P3, P4, P5), will continue to study the Earth's space environment.

- The two outer probes, P1 and P2, will explore the space environment of the moon. This new mission was renamed to ARTEMIS (Acceleration Reconnection Turbulence, and Electrodynamics of Moon Interaction with the Sun). The ARTEMIS mission is a collaborative effort between NASA/GSFC, UCB (University of California at Berkeley), and NASA/JPL (Jet Propulsion Laboratory).

Table 1: The ARTEMIS mission is descibed in the last chapter of the file (as well as in the status)

The THEMIS science objectives are:

• Onset and evolution of the macroscale substorm instability, a fundamental mode of mass, and energy transport throughout Geospace

• Production of storm-time MeV electrons

• Control of the solar wind-magnetosphere coupling by the bow shock, magnetosheath, and magnetopause.

THEMIS is essential for understanding Earth's space environment and a prerequisite to understanding space weather.

THEMIS is a NASA PI mission, lead by Vassilis Angelopoulos at SSL (Space Sciences Laboratory) of the University of California, Berkeley (UCB). In turn, UCB awarded Swales Aerospace the prime contract for design, development and integration of the THEMIS satellite constellation and satellite dispensers.

Note: In the spring of 2007, Swales Aerospace of Beltsville, MD was purchased by Alliant Techsystems Inc. (ATK) with corporate headquarters in Edina, Minnesota.

In Greek mythology, Themis is the goddess of justice, wisdom and good counsel, and the guardian of oaths.


Figure 1: Artist's view of the THEMIS constellation in orbit (image credit: ATK Space)


THEMIS consists of a constellation of five spin-stabilized microsatellites (called Probes), each a highly integrated “sciencecraft.” The spacecraft buses, including the separation system and carrier, are designed and built by Swales Aerospace, Beltsville, MD. The science requirements call for a spacecraft that is magnetically clean and externally conductive. 4) 5) 6)

The spacecraft design is based on a single bus architecture with selected redundancy and some graceful degradation. The bus is composed of a graphite structure with an approximately square-shaped body with eight sides, a top deck, a bottom deck and an axial tube (referred to as mast). The primary structure consists of four side panels with face-mounted solar arrays. Each spacecraft has a total mass of 128 kg. The S/C size is: 84 cm x 84 cm x 51 cm (height) excluding the mast holding the RF antenna above the bus and the instruments in the stowed position. 7) 8)

An average power of 39 W (EOL) is provided for the worst case 24 hour orbit with a 3 hour eclipse, and 58 W BOL (Beginning of Life) with no eclipse.


Figure 2: The bus system architecture of THEMIS (image credit: ATK Space)

The spacecraft attitude is measured by a digital spinning sun sensor, referred to as MSSS (Miniature Spinning Sun Sensor), two single axis IRUs (Inertial Reference Unit), and the science instrument FGM (Flux Gate Magnetometer). The GN&C (Guidance Navigation & Control) subsystem includes the ACS (Attitude Control Subsystem) and the RCS (Reaction Control Subsystem). The ACS utilizes a thruster interface driven by ground-processed estimation and command algorithms with on-board limit and time-out protection. Attitude data collected from the MSSS and the FGM are sampled at 10 Hz and telemetered to the ground for standard, 3-axis, post-processing estimation. Ground generated thruster command sequences are tested in a high-fidelity probe simulator prior to any upload. Also, two single-axis gyros, transverse to the spin plane, provide short-term attitude verification (prior to orbit maneuvers). The on-board protection logic monitors real-time sun aspect angle and spin period, comparing them to a ground commanded reference uploaded for each maneuver. If thresholds are exceeded, the maneuver is terminated. Actuation is provided by the RCS consisting of the four thruster complement and the two fuel tanks (Inconel), operated in a blow-down fashion. The tanks feed a four thruster complement (5 N for each thruster, two axial, two radial for spin and pointing control).


Figure 3: Block diagram of the ACS and BAU (image credit: ATK Space)


Figure 4: Illustration of the MSSS device (image credit: ATK Space)

The S/C avionics are stowed into a single box called BAU (Bus Avionics Unit). BAU features 3 modules: a single board computer module (identical to the IDPU processor card), a single board communication module (of SMEX heritage), and a 3-board power control module. BAU has a size of 23 cm x 15 cm x 13 cm and a mass of 2.8 kg. 9)


Figure 5: View of the BAU (Bus Avionics Unit), image credit: ATK Space

The CDHS (Command and Data Handling Subsystem) provides real-time and stored command capability for the bus subsystems and instruments, collects, formats, and transmits to the ground data from the bus subsystems and instruments, provides engineering data storage, distributes time to the IDPU (Instrument Data Processing Unit), and implements autonomous fault protection features to ensure the health and safety of the probe. The CDHS functions are implemented in flight software and hardware that reside in the BAU.

The power subsystem uses a DET (Direct Energy Transfer) topology with the battery and solar array (triple-junction GaAs cells) connected directly to the power bus. The solar array consists of eight panels, four on each side, and two on each deck. The power available is 41.7 W. Eclipse and peak transient loads (i.e., transmitter operation) are balanced with an 11.8 Ahr, 28 V Li-ion battery of ABSL. Thermal management using heaters and thermistors keeps the battery temperature in the range of -5º to +25º C. The power subsystem is contained in AEB (Auxiliary Electronics Box). The solar arrays feature a conductive glass cover and a complex external grounding scheme to minimize surface charging.


Figure 6: Block diagram of the power subsystem (image credit: ATK Space, Ref. 45)

To obtain the required orbits, the five Probes will be deployed in nearly simultaneously separations from the spinning Probe Carrier (Figure 12), which is hard mounted to the Delta II 3rd stage. This unique deployment demands a custom-built separation system. Once deployed each Probe requires approximately 900 m/s of ΔV to reach its required science orbit (including inclination change) and perform its mission. The ΔV requirement creates the need for each Probe to carry 49 kg of hydrazine.

Note: The mass of a Probe bus was not dictated by the launch vehicle lift-off capacity since there was ample mass margin for the Probe Carrier Assembly (five probes and probe carrier) on the Delta II. Rather, the mass requirements were driven by the individual ΔV requirements (> 920 m/s) for the largest apogee orbit (Ref. 45).

The mission reliability scheme relies on the availability of only four out of five spacecraft for one winter season to meet the minimum science requirements. The constellation of five spin-stabilized satellites has a (nominal) baseline life of two years - with a possible one-year extension.

Nr of spacecraft in constellation



- Spacecraft bus dry mass: 51 kg
- Instrument Mass: 26 kg
- Observatory dry mass: 77 kg
- Propellant: 49 kg
- Observatory wet mass: 126 kg
- Allowable mass (max): 134 kg
- Margin: 8 kg (6.3%)


- Spacecraft bus power: 11 W
- Instrument power: 15 W
- Heater power (EOL/24 hr orbit/3 hr eclipse): 11 W
- Observatory power: 37 W
- Available power: 40.5 W
- Margin: 3.5 W (9.5%)
- Battery capacity (BOL): 12 Ah

RF communications

- S band
- EIRP: 2.4 dBW
- Two-way Doppler tracking
- Uplink command rate: 1 kbit/s
- Max downlink telemetry rate: 1.024 Mbit/s


- Spin rate (science): 16 ±2 rpm
- Spin axis orientation: < 1º (knowledge), < 3º (control)
- Spin phase knowledge: < 0.1º
- Ground based attitude determination


- Monopropellant hydrazine system
- Number of thrusters: 4 (4.4N ea.)
- Total ΔV: 940 m/s
- Propellant: 49 kg

Radiation Environment

Total dose: 66 krad (2 years, 5 mm Al shielding, RDM of 2)

Nominal mission design life

2 years

Table 2: Overview of spacecraft parameters


Figure 7: External view of the THEMIS spacecraft in stowed configuration (image credit: Swales Aerospace Inc.)


Figure 8: Internal view of the THEMIS spacecraft (image credit: Swales Aerospace Inc.)


Figure 9: View of the IDPU instrument (image credit: Swales Aerospace)

Propulsion subsystem: The RCS (Reaction Control Subsystem) is a hydrazine blowdown system pressurized with helium. The RCS consists of two spherical propellant tanks, a single use pyro-actuated re-pressurization tank, and four 4.5 N thrusters.

Two of the thrusters, A1 and A2, point parallel to the spacecraft’s spin-axis. When these two thrusters are fired in a continuous mode they provide a ΔV in the +Z spin-axis direction. These events are referred to as axial maneuvers. Attitude precession maneuvers are performed by firing either A1 or A2 in a sun-synchronous pulsed-mode.

The other two thrusters, T1 and T2, are mounted in a radial direction. When T1 and T2 are fired simultaneously in a sun-synchronous pulsed-mode these thrusters provide a ΔV in a radial direction, perpendicular to the spacecraft’s spin-axis. Firing either T1 or T2 alone, with thrust pulses phased 180º from each other provides control over the spacecraft’s spin rate while minimizing torque on the EFI wire booms.


Figure 10: Illustration of the RCS thruster placements (image credit: NASA)

By combining the axial and radial maneuvers into a series of burns executed in short succession the spacecraft can thrust in any direction in the southern ecliptic hemisphere without performing an attitude precession to point the thrusters in a specific direction. However, there is a small vectorization ΔV penalty for performing maneuvers in this manner, but the ΔV cost incurred by performing an attitude precession is prohibitively higher due to the spacecraft’s large angular momentum.


Figure 11: Photo of the THEMIS spacecraft lined up in the SSL clean room prior to launch in 2007 (image credit: UCB/SSL) 10)


Figure 12: Photo of the THEMIS Probe Carrier Assembly (PCA), image credit: NASA

RF communications: An S-band system is being used based on a stacked patch antenna with a toroidal pattern that has a maximum gain normal to the spin axis of the bus. This configuration provides a continuous view of the Earth at nominal attitudes and insures an Earth view for the greatest part of the orbit at any attitude. - The antenna is fed by a 5 W STDN (Standard Tracking and Data Network) compatible transponder (with flight heritage) that features ranging and TDRSS compatibility including LEO support of a fixed 1 kbit/s uplink (operated in PCM/PSK/PM mode with a 16-kHz subcarrier at a modulation index of 1.0 rad). The downlink has 10 selectable rates from 1.024 to 1048.576 kbit/s. The communication protocol standard CCSDS is being used along with Reed-Salomon encoding. The telemetry channel can also be configured for direct carrier (BPSK) modulation with all 10 data rates.

All THEMIS probes are equipped with model CXS-610 transponders manufactured by L3 Communications Telemetry-West. All transponders operate on the same S-band frequencies. The transponder can be operated in PCM/PSK/PM mode with the lowest six data rates up to 65.536 kbit/s, utilizing a 1024 kHz subcarrier.


Figure 13: THEMIS S-band phase-locked transponder block diagram (image credit: USB/SSL)

Frequency (S-band)

Downlink: 2282.5 MHz; uplink: 2101.8 MHz


LHCP (Left-Hand Circular Polarized)


Downlink: BPSK (4 highest data rates), PCM/PSK/PM (6 lowest data rates)
Uplink: PCM/PSK/PM


Downlink: Reed-Solomon + rate-1/2 convolution

Compression Scheme (VC3 only)

Differencing and truncation or Huffman (TBR)

Data rates

1.024, 4.096, 8.192, 16.384, 32.768, 65.536, 131.072, 262.144, 524.288, 1048.576 kbit/s

Virtual channels

0-3, 6

Data volume per orbit per probe

480 - 640 Mbit

Table 3: Summary of RF communication subsystem

Launch: A common launch of all THEMIS spacecraft took place on Feb. 17, 2007 on a Delta-2-7925-10 vehicle. The launch site was CCAS (Cape Canaveral Air Station), FLA.


Figure 14: Artist's view of of the THEMIS Probes just after deployment (image credit: NASA)

Orbit: HEO (Highly Elliptical Orbit) of constellation

• Probe 1: Orbital period of 4 days, perigee 1.500 RE, apogee 31.645 RE, inclination 7.0º

• Probe 2: Orbital period of 2 days, perigee 1.168 RE, apogee 19.770 RE, inclination 7.0º

• Probe 3: Orbital period of 1 day, perigee 1.118 RE, apogee 12.127 RE, inclination 9.0º

• Probe 4: Orbital period of 1 day, perigee 1.118 RE, apogee 12.127 RE, inclination 9.0º

• Probe 5, Orbital period of 0.8 days, perigee 1.350 RE, apogee 10.044 RE, inclination 4.5º


Figure 15: Constellation setup relative to the geomagnetic tail (image credit: UCB) 11)


Figure 16: Illustration of deployed constellation (image credit: UCB/Swales)

The five satellites use their onboard mono-propellant propulsion systems to maintain the primary science constellation configuration with orbital periods ranging from 1 to 4 days. The constellation alignment is carefully designed to achieve an apogee alignment of the HEOs at local midnight over North America in the winter. The orbits are designed to provide the required spatial and temporal sampling of the local plasma, electric field, and magnetic field. 12) 13)


Figure 17: Artist’s view of the THEMIS mission orbit configuration. The white flash represents energy released during a magnetospheric substorm (image credit: NASA).


Figure 18: Schematic diagram of Earth's magnetosphere (image credit: UCLA)



Status of THEMIS / ARTEMIS (Acceleration Reconnection Turbulence, and Electrodynamics of Moon Interaction with the Sun) mission:

• March 2014: “The THEMIS-Low mission finds evidence of a new process protecting Earth from space weather.”
In the giant system that connects Earth to the sun, one key event happens over and over: solar material streams toward Earth and the giant magnetic bubble around Earth, the magnetosphere helps keep it at bay. The parameters, however, change: The particles streaming in could be from the constant solar wind, or perhaps from a giant cloud erupting off the sun called a coronal mass ejection, or CME. Sometimes the configuration is such that the magnetosphere blocks almost all the material, other times the connection is long and strong, allowing much material in. Understanding just what circumstances lead to what results is a key part of protecting our orbiting spacecraft from the effects of such space weather. 14)

Now, for the first time, a study shows that in certain circumstances a pool of dense particles normally circling Earth, deep inside the magnetosphere, can extend a long arm out to meet – and help block – incoming solar material.

In the words of Brian Walsh at NASA/GSFC: “ It’s like what you might do if a monster tried to break into your house. You’d stack furniture up against the front door, and that’s close to what the Earth is doing here. The material that is usually much nearer Earth stacks up against the outer boundary of the magnetosphere, throttling the interaction there and stopping solar material from entering.”

In the March 7, 2014, issue of Science, Walsh and his colleagues compared observations from the ground and in space during a solar storm on Jan. 17, 2013. 15) This was a fairly moderate solar storm caused by a CME (Coronal Mass Ejection) impacting Earth's magnetosphere for several hours. As the CME encountered the boundary of the magnetosphere, its magnetic fields and those around Earth realigned in a process called magnetic reconnection, which allowed energy and solar material to cross the boundary into the magnetosphere. NASA's three THEMIS (Time History of Events and Macroscale Interactions during Substorms) spacecraft, referred to as THEMIS-Low, were in the right place at the right time, flying through the magnetosphere's boundary approximately 45 minutes apart, and caught this interaction.


Figure 19: NASA's THEMIS mission observed how dense particles normally near Earth in a layer of the uppermost atmosphere, called the plasmasphere, can send a plume up through space to help protect against incoming solar particles during certain space weather events (image credit: NASA/GSFC)

Closer to Earth, scientists could also study the sphere of cold dense gas at the very top of our atmosphere. This region is called the plasmasphere and it's made of what's known as plasma, a gas made of charged particles. GPS signals travel through the plasmasphere and they travel at different speeds depending on how thick or thin the plasmasphere is along the journey. Tracking the GPS radio signals, therefore, can help researchers map out the properties of the plasmasphere.

"A colleague who works with these kind of observations said I had to see some interesting data showing a plume from the ground," said Walsh. "And I typed in the dates and saw that it was a date when THEMIS was in the right position. So, for the first time, we could make a comparison."

THEMIS showed that the tongue of this cold, dense plasmasphere material stretched all the way up to the magnetic reconnection point where the CME had made contact with the magnetopause. The three sets of THEMIS observations demonstrated that the plume had a dramatic impact on the characteristics of the magnetic reconnection region.

A magnetic reconnection process becomes effective if it lasts long enough, then the whole magnetosphere gets involved. This tongue of the plasmasphere surges out, adding another layer of protection, curbing the magnetic reconnection.

As scientists try to better understand the space weather system around Earth, they rely on multipoint observations such as this to connect what's seen on the ground to what's seen in space. In this case THEMIS data connected to ground-based GPS TEC (Total Electron Content) data, but such combinations are increasingly being used to watch how Earth is affected by its closest star. Eventually such observations could lead to improvements in space weather predictions, which would be as useful for spacecraft operators as terrestrial weather forecasts are for us here on Earth.


Figure 20: A thin layer of cold, dense material called the plasmasphere surrounds Earth. Researchers have found that material in the plasmasphere can help prevent particles from the sun crossing into near Earth space (image credit: NASA)

• March 2014: The THEMIS (and ARTEMIS) spacecraft are doing very well. The project has yet to see any permanent radiation effects (only occasional resets due to Single Event Upsets) and the solar array power has barely moved below BOL values, this is attributed to the extra glass cover that was put on). New discoveries are happening every day. 16)

- In 2013, the THEMIS / ARTEMIS project proposed to a Senior Review Panel to perform maneuvers to align THEMIS and the future MMS (Magnetospheric MultiScale) in the sky so they form a greater tetrahedron (3THEMIS+MMS as a point) engulfing a larger tetrahedron (the MMS one). However, after the recent MMS launch delay to Feb/Mar of 2015, the project is revising the maneuver scenario so that it will still meet the launch restrictions/mission requirements for MMS.

- Between Sept. 25 and Oct. 22, 2013, the THEMIS project performed an orbit maneuver campaign for the three THEMIS probes (a total of 19 maneuvers). There were 4 orbit change maneuvers, one attitude, and one spin rate adjustment per probe. By lowering the perigee and apogee altitudes, the project further increased the orbital drift. These maneuvers were needed for the upcoming conjunctions with MMS in 2016 and 2017. 17)


Figure 21: Schematic view of the future THEMIS-MMS conjunctions (image credit: UCLA, UCB)

• September 2013: Analysis of a reconnection event on July 3, 2012.
Taking advantage of an unprecedented alignment of eight satellites through the vast magnetic environment that surrounds Earth in space, including NASA’s ARTEMIS and THEMIS, scientists now have comprehensive details of the energy’s journey through a process that forms the aurora, called a substorm. Their results, published in the journal Science on Sept. 27, 2013, showed that small events unfolding over the course of a millisecond can result in energy flows that last up to half an hour and cover an area 10 times larger than Earth. 18) 19) 20)


Figure 22: On July 3, 2012, 8 spacecraft were lined up on the night side of Earth, enabling scientists to track how magnetic energy from the sun moved around Earth, reconnected at a point about half way to the moon, and then spread through the back end of Earth’s magnetic environment, the magnetotail (image credit: NASA)

Trying to understand how gigantic explosions on the sun can create space weather effects involves tracking energy from the original event all the way to Earth. It’s not unlike keeping tabs on a character in a play with many costume changes, because the energy changes form frequently along its journey: magnetic energy causes eruptions that lead to kinetic energy as particles hurtle away, or thermal energy as the particles heat up. Near Earth, the energy can change through all these various forms once again.

Most of the large and small features of substorms take place largely in the portion of Earth’s magnetic environment called the magnetotail. Earth sits inside a large magnetic bubble called the magnetosphere. As Earth orbits around the sun, the solar wind from the sun streams past the bubble, stretching it outward into a teardrop. The magnetotail is the long point of the teardrop trailing out to more than 1.6 million km on the night side of Earth. The moon orbits Earth much closer, some 365,000 km away, crossing in and out of the magnetotail.

Tracking how such small events can have large-scale space weather effects requires observatories located throughout the whole system. To help with this endeavor, in July 2011, two of the five THEMIS spacecraft moved into place around the moon for a different vantage point on the magnetotail, through which the moon travels once a month. NASA renamed these two spacecraft the ARTEMIS mission. Once per year, all the orbits of the THEMIS and ARTEMIS spacecraft line up in the magnetotail together. On the most recent conjunction, in July 2012, a substorm occurred. During the same period, the joint GEOTAIL mission of JAXA/NASA and the GOES-13 and GOES-15 missions of NOAA were also in the magnetotail.

With eight spacecraft making observations at once, the scientists had a comprehensive view of how the energy in any given region moved around and transformed into other kinds of energy.

Scientists have observed much of the energy’s journey through a substorm before. When the solar wind streams off the sun it can connect with the front of Earth’s magnetosphere. As the two sets of magnetic fields come together, a process called magnetic reconnection turns the energy of the forward-moving solar wind into an explosion that sends particles and magnetic fields moving around the planet to the far side of Earth. Here, the fields reconnect again creating a burst that turns magnetic energy into acceleration of particles and heating. Just where and how this energy converted to particle movement, however, has been unclear.

The details of what happened next required observations from many spacecraft simultaneously. While the magnetic reconnection event itself happened in a specific place somewhere halfway between Earth and moon’s orbit in a region just a couple hundreds of miles across, this is not the main place where the energy was converted. Regions, labeled as “reconnection fronts” in the paper, surged away from the original reconnection point — one propagated toward Earth and one moved away, past the moon and down the magnetotail. These fronts are like sheets of current, a wall hurtling in each direction, continuing to convert energy for up to 30 minutes afterward. The energy moving in toward Earth helps to create the aurora and it also funnels into the giant donuts of radiation around Earth called the radiation belts.

The amount of energy released is equivalent to a 7.1 Richter scale earthquake. The fact that this energy can move around so dramatically is not in and of itself surprising. Scientists have certainly previously suggested such things based on computer models. But it is only with a fleet of spacecraft that scientists can confirm the location and exact nature of the process, not to mention learning something new such as how continuous and long term the energy conversion process is after the initial magnetic reconnection event.

• On Feb. 17, 2013, the THEMIS / ARTEMIS mission was 6 years on-orbit, all spacecraft are still operating. 21)

After 6 years, THEMIS has now traveled through more than 50 solar storms that caused particles in the outer radiation belts to either increase or decrease in number. Historically, it has been difficult for scientists to find commonalities between such occurrences and discover what, if anything consistently caused an enhancement or a depletion. With so many events to study, however, and a more global view of the system from several spacecraft working together – including, in this case, ground based observations and NOAA's GOES (Geostationary Operational Environment Satellites) and POES (Polar Operational Environmental Satellites) data, in addition to THEMIS data – a team of scientists led by Drew Turner at UCLA could better characterize what processes caused which results. 22)

- Turner's group recently presented evidence linking specific kinds of electromagnetic waves in space – waves that are differentiated based on such things as their frequencies, whether they interact with ions or electrons, and whether they move along or across the background magnetic fields – to different effects. Chorus waves, so called because when played through an amplifier they sound like a chorus of singing birds, consistently sped up particles, leading to an increase in particle density. On the other hand, two types of waves known as hiss and EMIC (Electromagnetic Ion Cyclotron) waves occurred in those storms that showed particle depletion. Turner also observed that when incoming activity from the sun severely pushed in the boundaries of the magnetosphere this, too, led to particle drop outs, or sudden losses throughout the system. Such information is helpful to those attempting to forecast changes in the radiation belts, which if they swell too much can encompass many of our spacecraft. 23)

- Another group has a paper in print in 2013 based on 2008 data from the five THEMIS spacecraft in conjunction with three of NOAA's GOES (Geostationary Operational Environmental Satellites) spacecraft, and the ESA/NASA Cluster mission. Led by Michael Hartinger at the University of Michigan in Ann Arbor, this group compared observations at the bow shock where the supersonic solar wind brakes to flow around the magnetosphere to what happens inside the magnetosphere. They found that instabilities drive perturbations in the solar wind particles streaming towards the bow shock and that these perturbations can be correlated with another type of magnetized wave – ULF (Ultra Low Frequency) waves — inside the magnetosphere. ULF waves, in turn, are thought to be important for changes in the radiation belts. 24)

- A third interesting science paper from THEMIS's sixth year focused on features originating even further upstream in the solar wind. Led by Galina Korotova at IZMIRAN in Troitsk, Russia, this work made use of THEMIS and GOES data to observe the magnetosphere boundary, the magnetopause. The researchers addressed how seemingly small perturbations in the solar wind can have large effects near Earth. Wave-particle interactions in the solar wind in the turbulent region upstream from the bow shock act as a gate valve, dramatically changing the bow shock orientation and strength directly in front of Earth, an area that depends critically on the magnetic field orientation. The extreme bow shock variations cause undulations throughout the magnetopause, which, launch pressure perturbations that may in turn energize particles in the Van Allen radiation belts. 25)


Figure 23: Artist's view of Earth's magnetosphere reconstructed from THEMIS observations (image credit: NASA, Ref. 22)

Note: ARTEMIS (Acceleration Reconnection Turbulence, and Electrodynamics of Moon Interaction with the Sun) is an extension to the successful THEMIS (Time History of Events and Macroscale Interactions during Substorms) mission that has relocated two of the THEMIS spacecraft from Earth orbit to the Moon.

• In the spring of 2012, the two ARTEMIS spacecraft continue to collect solar wind, lunar wake, magnetospheric, and crustal magnetic anomaly data. Over the next few years the operations team will be executing approximately two maneuvers per year, per spacecraft, to control their periselene altitudes and enhance the low altitude transits while maintaining a safe distance from the surface. The team also plans to bring at least one of the ARTEMIS spacecraft into the near-terminator exospheric region in conjunction with NASA’s upcoming LADEE (Lunar Atmosphere and Dust Environment Explorer) mission. 26)

- ARTEMIS completed a two-year lunar transfer by way of multiple lunar gravity assists and a low-energy trans-lunar trajectory that culminated into EM L1 and EM L2 (Earth-Moon Libration point 2) and finally stable prograde and retrograde elliptical lunar orbits in July 2011. Between the two spacecraft, 170 maneuvers events were executed from the start of the mission extension to the final lunar placement with a 100% successful execution rate.

- In early May 2012, P2 will execute a short series of maneuvers to slow its spin rate down to P1’s rotational rate, with a goal of matching their spin synchronized data collection volumes and enhancing science operations. This maneuver sequence is being designed using a new spin control maneuver scheme that will not only spin the spacecraft down, but provide a beneficial attitude change to further mitigate the post-LOI (Lunar Orbit Insertion) thermal conditions and to take the place of an altitude control maneuver.

Many of the challenges encountered by the ARTEMIS mission were a result of taking two spacecraft created for Earth orbit into regions of space not encompassed in their original design. It is hoped that the experiences of the ARTEMIS team will help further the goals of future missions to the Moon and that the navigation data collected by the first spacecraft ever to continuously orbit Earth-Moon libration points will be of benefit to continued exploration of that interesting region of space (Ref. 26).

• In Feb. 2012, the THEMIS project celebrated 5 years of watching aurora and space weather. 27)

- On Feb. 13, 2012, one of the two probes, ARTEMIS P1 (formerly THEMIS-B), made the first lunar wake flyby of the mission. 28)

• As of late July 2011, the ARTEMIS mission is transferring two spacecraft from Lissajous orbits around Earth-Moon Lagrange Point No 1 (EML1) into highly-eccentric lunar science orbits with periods of roughly 28 hr. The ARTEMIS project plans to conduct a variety of scientific studies at the Moon using the on-board particle and fields instrument package.29) 30) 31)

Many aspects of the transfer from Lissajous to the science orbits contribute to the novelty of the design. Firstly, the ARTEMIS probes have been the first spacecraft to fly Lissajous orbit near the Earth-Moon Lagrange points and thus, they are the first to approach a traditional lunar orbit from this location. Second, the ARTEMIS probes plan to routinely operate in the most eccentric lunar science orbits of any mission to date. These orbits are strongly perturbed by the Earth’s gravity, which makes for interesting three-body dynamics that are more typically considered in the context of outer planet moon orbiters. - Furthermore, ARTEMIS plans a number of different science investigations while in lunar orbit, many of which have particular trajectory implications that must be satisfied. Finally, P1 and P2 were built as low-cost Earth orbiters; the spacecraft capabilities, particularly in the area of available thrust and ΔV , are less robust than they may have been if the lunar mission had been planned before launch (Ref. 29).

Since ARTEMIS is both a heliophysics and a planetary science mission, a wide range of science observations are planned for during the lunar orbit phase, including:

- 3-D mapping of the lunar wake induced by the solar wind at a range of downstream distances

- Measurements of selected lunar crustal magnetic anomalies

- Measurements of the lunar exosphere and surface charging

- Coordinated measurements with NASA’s forthcoming LADEE (Lunar Atmosphere and Dust Environment Explorer) mission to characterize the near-terminator exosphere.

The above science measurement objectives directly drive the design of the lunar science orbit and approach from Lissajous. To achieve the desired lunar wake measurements, the two spacecraft should be in highly eccentric orbits that precess at rates different from each other and from the Sun direction. The mission duration should be long enough so that a full range of measurement altitudes and relative orientations can be achieved. To measure the crustal magnetic anomalies, periapsis altitudes must be less than 50 km and in the vicinity of the anomaly. Each anomaly dictates a minimum orbit inclination required to achieve this. Measurements of the lunar exosphere require a range of altitudes and orientations with respect to the Sun. To coordinate near-terminator exosphere investigations with LADEE, an ARTEMIS spacecraft must be below 200 km within 30º of the dawn terminator at least once during the 3-month LADEE science mission scheduled for 100 days between July 2013 and March 2014 (depending on launch date). Finally, to maximize the quantity of all measurements, the orbits should have long-term stability (Ref. 29).

• In July 2011, the two ARTEMIS Probes are in lunar orbit. The first spacecraft entered lunar orbit on June 27, and the second on July 17, 2011. With two spacecraft orbiting in opposite directions, the project can acquire a full 3-D view of the structure of the magnetic fields near the moon and on the lunar surface. 32) 33)

• In late June 2011, the two Probes have almost arrived at the moon. It took one and a half years, over 90 orbit maneuvers, and – wonderfully – many gravitational boosts and only the barest bit of fuel to move two spacecraft from their orbit around Earth to their new home around the moon. 34)

- On January 9, 2011, ARTEMIS P1 jumped over the moon and joined ARTEMIS P2 on the side of the moon closest to Earth. Now the last steps are about to begin.

- On June 27, 2011, P1 will spiral in toward the moon and enter lunar orbit. On July 17, P2 will follow. P2 will travel in the same direction with the moon, or in prograde; P1 will travel in the opposite direction, in retrograde.

Along their travels, the spacecraft have been through orbits never before attempted and made lovely curlicue leaps from one orbit to the next. In the summer of 2011, the two ARTEMIS spacecraft — which began their lives as part of the five-craft THEMIS mission studying Earth's aurora – will begin to orbit the moon instead.

Even with NASA's decades of orbital mechanics experience, this journey was no easy feat. The trip required several maneuvers never before attempted, including several months when each craft moved in a kidney-shaped path on each side of the moon around, well, nothing but a gravitational point in space marked by no physical planet or object.

• On October 22, 2010, the ARTEMIS-P2 probe settled into a temporary "Lagrange-point" orbit. 35)

Over the next several years, ARTEMIS will help space scientists understand how the earth’s magnetosphere is shaped by the strong solar wind at the distance of the moon and also how the moon’s own tiny magnetic field interacts with the solar wind. Using simultaneous measurements of particles and electric and magnetic fields from two locations, ARTEMIS will provide the first three-dimensional perspective of how energetic particle acceleration occurs near the moon’s orbit, in the distant magnetosphere, and in the solar wind.

In August 2010, ARTEMIS-P1 became the first spacecraft to navigate to and perform stationkeeping operations around the Earth-Moon L1 and L2 Lagrangian point (Ref. 58).

The ARTEMIS mission is an absolute success and this success can be attributed to the use of several tools to validate and confirm the planning and execution of maneuvers necessary to transit a dynamically challenging environment. The combined method of optimization with manifold verification, thought not new, is a substantial leap in the operational design of such missions. With the completion of the ARTEMIS trajectory, a viable multi-tiered process and trajectory feasibility is demonstrated. The opportunities of the ARTEMIS mission provide the space community with the first ever completed design from Earth to the Earth-Moon L2 and L1 Lissajous orbits. The ARTEMIS P1 spacecraft has completed its transfer and is in now in the Earth-Moon L2 Lissajous trajectory; the P2 spacecraft is on-track for Earth-Moon libration orbit insertion (Ref. 59).


Figure 24: The view from above of the ARTEMIS orbits as they make the transition from the kidney-shaped Lissajous orbits on either side of the moon to orbiting around the moon (image credit: NASA/GSFC)


Figure 25: An artist's concept of one of the twin ARTEMIS probes in orbit around the moon (image credit: UCB, Ref 35)

• The THEMIS/ARTEMIS constellation is operating nominally in 2010. All probes are very healthy and collecting science data. The fuel reserves allow for an ambitious mission extension. The THEMIS mission has answered the longstanding fundamental questions concerning the nature of the substorm instabilities that abruptly and explosively release solar wind energy stored within the Earth’s magnetotail.

• The extended science mission will keep the three innermost THEMIS spacecraft in elliptical Earth orbits and maneuver the two outermost spacecraft to the lunar regime. In July 2009, the THEMIS mission split into two missions: 36)

- The first, THEMIS-Low, consisting of the three inner probes (P3, P4, P5), will continue to study the Earth's space environment.

- The two outer probes, P1 and P2, will explore the space environment of the moon. This new mission was renamed to ARTEMIS(Acceleration Reconnection Turbulence, and Electrodynamics of Moon Interaction with the Sun). The ARTEMIS mission is a collaborative effort between NASA/GSFC, UCB (University of California at Berkeley), and NASA/JPL (Jet Propulsion Laboratory). Note: see ARTEMIS chapter at end of file. 37) 38) 39)

At the request of the Principal Investigator (PI), analysts at the JPL designed transfer trajectories for both P1 and P2 to insert them into Earth-Moon libration point orbits. The maneuver plan includes a series a propulsive ORMs (Orbit-Raising Maneuvers) to position each spacecraft for a series of lunar and Earth gravity assist maneuvers. The translunar orbit injections for P1 and P2 will occur in January and March 2010, respectively, with lunar libration point orbit captures in August and October 2010. After collecting science data in the Lissajous orbits for several months, the two spacecraft will be maneuvered into selenocentric orbits (Ref. 37).

The ARTEMIS science mission begins once each spacecraft is inserted into its Lissajous orbit. Since L1 and L2 are unstable Lagrangian points, the operations team must perform frequent stationkeeping maneuvers to maintain each spacecraft in the Lissajous orbits for several months.

Lunar phase: At the completion of the Lissajous orbit phase, the ARTEMIS satellites will perform large orbit maneuvers to depart the lunar libration point orbits and be captured into selenocentric orbits.

ARTEMIS is considered a pathfinder for future missions operating in the lunar libration point regions and will provide unprecedented science observations of the magnetosphere in selected lunar regimes.


Figure 26: Illustration of the trajectory design to the Earth-Moon Lagrangian points (image credit: UCB/NASA)

• With a design life of 2 years, THEMIS completed also its primary mission goal in April 2009 - having achieved its primary objectives of establishing when and where the substorms begin. Officially, the THEMIS prime mission was completed in July, 2009 after two successful observing seasons in the Earth’s magnetospheric tail.

NASA has extended the THEMIS mission to the year 2012. - Also, a new mission was designed of the two outer probes of the constellation, P1 and P2, referred to as ARTEMIS (Acceleration Reconnection Turbulence, and Electrodynamics of Moon Interaction with the Sun). The goal is to maneuver the two spacecraft into the Earth-Moon Lagrangian points and eventually into lunar orbit - to observe the same phenomena as before but from a different perspective. 40)
The planning for the ARTEMIS mission started in 2008. The vast experience, ingenuity and dedication of the THEMIS project team made this extended mission to the moon possible. This represents an extra science bonus that could not be foreseen in the early project phases of THEMIS (see ARTEMIS at end of file).

Spacequakes: A spacequake is a temblor in Earth's magnetic field. It is felt most strongly in Earth orbit, but is not exclusive to space. The effects can reach all the way down to the surface of Earth itself. 41)

In 2007, THEMIS discovered the precursors of spacequakes. The action begins in Earth's magnetic tail, which is stretched out like a windsock by the solar wind. Sometimes the tail can become so stretched and tension-filled, it snaps back like an over-torqued rubber band. Solar wind plasma trapped in the tail hurtles toward Earth. On more than one occasion, the five THEMIS spacecraft were in the line of fire when these "plasma jets" swept by. Clearly, the jets were going to hit Earth. But what would happen then? The fleet moved closer to the planet to find out.

According to THEMIS, the jets crash into the geomagnetic field some 30,000 km above Earth's equator. The impact sets off a rebounding process, in which the incoming plasma actually bounces up and down on the reverberating magnetic field. Researchers call it "repetitive flow rebuffing." It's akin to a tennis ball bouncing up and down on a carpeted floor. The first bounce is a big one, followed by bounces of decreasing amplitude as energy is dissipated in the carpet.

The THEMIS team has studied the phenomenon of spacequakes for several years and continues to do so in 2010. The surprise is plasma vortices, huge whirls of magnetized gas as wide as Earth itself, spinning on the verge of the quaking magnetic field (Ref. 41).


Figure 27: During a spacequake, Earth's magnetic field shakes in a way that is analogous to the shaking of the ground during an earthquake (image credit: Space Research Institute of Austria)

• A network of ASIs (All-Sky Cameras) deployed around the Alaskan/Canadian Arctic region in support of NASA's THEMIS mission has made a startling discovery about the Northern Lights. Sometimes, vast curtains of aurora borealis collide, producing spectacular outbursts of light. The 20 ASIs photographed auroras from below while the spacecraft sampled charged particles and electromagnetic fields from above. Together, the on-ground cameras and spacecraft could see the action from both sides and were able to piece together cause and effect. In 2009, Toshi Nishimura of UCLA assembled continent-wide movies from the observations of the individual ASI cameras. 42) 43) 44)


Figure 28: A fast-moving knot of auroras is poised to collide with a slower moving curtain hanging over the Arctic. The ASIs photographed the collision on Feb. 29, 2008 (image credit: Toshi Nishimura/UCLA)

National Science Foundation-funded radars located in Poker Flat, Alaska, and Sondrestrom, Greenland, confirm this basic picture. They have detected echoes material rushing through Earth's upper atmosphere just before the auroras collide and erupt. The five THEMIS spacecraft also agree. They have been able to fly through the plasma tail and confirm the existence of lightweight flows rushing toward Earth.

The explosions of light, researchers believe, are a sign of something dramatic happening in the space around Earth—specifically, in Earth's "plasma tail." The same magnetic field that holds the tail together also connects it to Earth's polar regions. Because of this connection, watching the dance of Northern Lights can reveal much about what's happening in the plasma tail.

• On Feb. 16, 2009 the constellation was in orbit for 2 years. THEMIS has now fully accomplished its baseline objectives by completing the full second year's worth of magnetotail observations. Despite the extended Solar Minimum, solar wind energy coupling was strong and frequent enough to enable observations of at least two dozen substorms. THEMIS P1 and P2's tail orbits were changed in order to increase current sheet encounters, with excellent results in the data. In addition, there have been 3 second resolution full angular distributions of electrons 12 hrs per orbit on P1 and P2 in the tail season for ~3 weeks, while P3, 4, 5 stayed in that mode since mid-February. The resulting data recovery from all probes is about twice what was initially promised. The scientific potential of the dataset is astounding.

The flight data and feedback from various organizations have confirmed robust spacecraft validation that can survive multiple attitudes in highly elliptical orbits as designed. The flight telemetry has shown consistency in the data between the probes in various orbits demonstrating the high quality and workmanship of the probes. In addition, probe bus design limits have been consistently nominal throughout launch, early orbit, and the mission phases. 45)

• Using data from NASA's THEMIS mission, a team of University of Alberta researchers has pinpointed the impact epicenter of an earthbound space storm as it crashes into the atmosphere, and given an advance warning of its arrival. The team uses ground-based observatories spread across northern Canada and the five satellites of the THEMIS mission to detect magnetic disturbances as storms crash into the atmosphere. Using a technique the researchers call "space seismology," they look for the eye of the storm hundreds of thousands of miles above Earth. 46)

• Regarding science returns, NASA reports researchers have discovered that an explosion of magnetic energy a third of the way to the moon powers substorms, sudden brightenings and rapid movements of the aurora borealis, called the Northern Lights. The culprit turns out to be magnetic reconnection, a common process that occurs throughout the universe when stressed magnetic field lines suddenly ”snap” to a new shape, like a rubber band that's been stretched too far.47)

• At a Press Conference of the EGU (European Geosciences Union) General Assembly Meeting in Vienna, Austria (April 23, 2009), the researchers Andreas Keiling, Karl-Heinz Glaßmeier, and Olaf Amm reported: “NASA's THEMIS spacecraft discovered that these flow vortices, or “space tornados”, generate currents of more than one hundred thousand A (ampere) in space and channel them into the ionosphere. The flow vortices are composed of rotating clouds of charged particles, called plasma, with embedded twisted magnetic field lines. Located about forty thousand miles away from Earth, they span a volume of approximately the size of the Earth or larger.”


Figure 29: Space tornados span a volume of approximately the size of the Earth or larger (image credit: UBC, NASA, IGEP, FMI)

• On March 5, 2008, a little more than one year following launch, the three hour eclipse probe bus performance was demonstrated without issue during the P1 orbit. It was found that the probes were consistent in performance in various orbits and sun attitudes.

• At the end of Feb. 2008, the THEMIS constellation had observed 154 hours of four-probe conjunctions (the requirement was 94 hours), during which it observed 57 substorms. Of these 57 substorms, about 6-10 were observed from an excellent vantage point during the period Feb 02-26, 2008. During the first tail season, THEMIS accomplished about 200 hours of four-probe conjunctions and caught in excess of five dozen substorms, a dozen of which were pristine vantage points within the meridian.

• EFI deployment operations for the entire constellation were completed on 14 January 2008 with the deployment of THEMIS-A axial booms. This followed the deployment of THEMIS-A spin planes booms the previous week. In total, the EFI had nominal deploys of 20 wire boom and 10 stacer boom systems. Hence, by mid January 2008, less than one year after launch, the constellation was fully configured for science data acquisition in the primary observing season.

• Between early September and early November 2007, four of the five probes were maneuvered into their synchronized mission orbits with 1, 2 and 4-day periods, and with their lines of apsides aligned along the Earth’s magnetospheric tail in preparation for the primary observing season in the winter of 2007/2008. Orbital conjunctions allowing multiprobe measurements to be made at various distances within the magnetotail occurred every 4 days during this observing season. The fifth probe, acting as an on-orbit spare, was maneuvered into its 4/5-day period orbit in December 2007, once the four primary probes were completely deployed in their mission orbits.

• During the summer of 2007, the spacecraft were in a “coast phase” (July 1 to Aug. 31, 2007) collecting information about the interaction of the solar wind and the Earth's magnetic field.

• March 2007: The first science observations from the spacecraft were obtained on March 23, during a disturbance in the Earth's magnetic field known as a substorm. The multipoint spacecraft and dedicated ground observatories allowed researchers to track the development of the substorm via a proof-of-concept study demonstrating novel techniques that will be used throughout the course of the mission. All 25 instruments on each spacecraft have been operating well ever since.

• After launch the five THEMIS spacecraft were deployed into a “string-of-pearls” configuration on near-identical highly elliptical orbits with periods of 31 hours.




Sensor complement: (FGM, ESA, SST, SCM, EFI)

The five spin-stabilized (Tspin = 3 s) Probes carry identical suites of electric field, magnetic field, and particle instruments. The THEMIS instruments measure particles and fields on orbits which optimize tail-aligned conjunctions over North America. Ground observatories time auroral breakup onset. Three inner Probes at ~10 RE monitor the current disruption onset, while two outer Probes, at ~ 20 and 30 RE respectively, remotely monitor plasma acceleration due to lobe flux dissipation.


Figure 30: THEMIS instrument configuration and Probe with all booms deployed (image credit: UCB, NASA)

FGM (Fluxgate Magnetometer):

FGM is a triaxial fluxgate instrument provided by Germany [DLR, TUBS (Technical University of Braunschweig)], and Austria [ASA, IWF (Institut für Weltraumforschung)]. FGM has a flight heritage on AMPTE/IRM (1985), Phobos (1988), Interball (1992), Equator-S (1997), MIR (1998), Rosetta (2004), and Venus Express (2007). FGM measures the 3D ambient magnetic field. The objectives are to: 1) Measure DC and low frequency perturbations of the magnetic field, 2) Time wave and structure propagation between Probes, 3) Provide information on plasma currents based on instantaneous magnetic field differences on two or more Probes, separated by > 0.2 RE.

FGM is mounted on a 2 m deployable boom. The FGM unit consists of two orthogonal ring-core elements of different diameter, made of an ultra-stable 6-81-Mo permalloy band (2 mm x 20 µm), fixed within a bobbin. The unit is mounted on a 2 m double-hinge carbon epoxy boom with FAST and Lunar Prospector heritage. The electronics consist of the driver and control circuits, on a 10 x 12 cm2 board within the IDPU (Instrument Data Processing Unit). The controller controls digital excitation, data acquisition, feedback and compensation making the device low power. Its low noise permits easy intercalibration with the search-coil magnetometer at frequencies of~10 Hz. 48) 49)


Figure 31: View of the FGM vector compensated fluxgate ringcore sensor (image credit: TUBS)

FGM calibration: Although a 1 nT absolute accuracy requirement is achievable with independent sensor calibration, it is important to ascertain that two separate Probes provide identical values when properties of the medium are steady. Once per orbit calibration data are acquired at 32Hz to determine (on individual Probes) zero levels, gains, and sensor orientation.

ESA (Electrostatic Analyzer):

ESA was designed and built at UCB/SSL. The ESA instrument has a flight heritage on the following missions: AMPTE/IRM, Giotto, FAST, WIND, and Cluster. The objective is to measure electrons and ions with high time resolution. The science requirements are to measure:

• Plasma moments to within 10%, at high time resolution (10 s or better) for inter-Probe timing studies

• Instantaneous differences in velocity and ion pressure between Probes, to estimate the scale size of transport, the size and strength of flow vortices and the pressure gradient

• Distribution functions of ions and electrons, to ascertain the presence of free energy sources.

ESA consists of an ion spectrometer and an electron spectrometer to make detailed distribution function measurements; in addition, there are electron-stepped ESAs to make very high time resolution electron measurements with lower energy and angle resolution.

Both the ion and the electron ESA units have a look direction of 180º in elevation, split in eight, 22.5º bins (one per anode). Measurements over a 4 π steradian, are made once per spin as the Probe rotates. The particles are selected in E/q (where q is the charge) by a sweeping potential applied in 32 steps, 32 times/spin (32 azimuths) between the outer (0 kV) and inner (~0-3 kV) concentric spheres and are focussed onto an MCP pair arranged in a Chevron configuration. On-board moment, pitch angle, and averaging computations are implemented at the IDPU. These operations routinely utilize FGM and SST data (to ensure correct values when the peak flux extends beyond the plasma instrument energy range). 50)


Figure 32: Block diagram of the ESA instrument (image credit: UCB)


Figure 33: ESA instrument (image credit: UCB)


Figure 34: ESA instrument mounted to the IDPU (image credit: UCB)

SST (Solid State Telescope):

SST was built by UCB. SST has a flight heritage on ISEE-1, -2, -3 and WIND. The objective is to measure the super-thermal part of the ion and electron distributions. The detector operation is very similar to the SST telescope pairs flown on WIND. Each Probe carries two such pairs. The SST geometric factors are optimized for THEMIS: They are WIND-like for THEMIS's high altitude apogees but a mechanical pin-hole attenuator reduces the geometric factor by a factor of 100 when fluxes get high close to Earth. The electronics are comprised of highly integrated version of WIND electronics chain afforded by FPGAs and Amptecs. The primary science needs for the SST are: 51)

1) To perform remote sensing of the tailward-moving current disruption boundary (at P3, P4, P5)

2) To measure the time-of-arrival of superthermal ions and electrons (30-300 keV, at 10 s resolution or better) during injections, and ascertain the Rx onset time (P1, P2).


Figure 35: Illustration of the SST units (image credit: UCB)

Instrument: Each double-ended telescope unit is equipped with three stacked, fully depleted, passivated, ion-implanted, 1.5 cm2 silicon detectors. The center (T) detector is 500 µm thick, while the outside (O & F) detectors are 300 m thick. The two detector pairs are mounted such that two telescope units point on the spin-plane (~ecliptic), one points above and the other below the spin-plane. One of the two spin-plane telescopes has detectors of area 0.075 cm2 and provides a geometric factor 20 times smaller that all the others to ensure no saturation at times of very high flux levels near the radiation belts.


Figure 36: The SST telescope operation concept (image credit: UCB)

SST calibration: Absolute calibration points are determined by monitoring the highest energy of protons stopped and by placing the pairs (or triplets) of detectors in coincidence and monitoring the minimum ionizing energy for penetrating particles.

SCM (Search Coil Magnetometer):

SCM was built by CNRS/CETP (Centre d'etude des Environnements Terrestre et Planetaire) of Velizy/ Saint-Maur, France. SCM is mounted on a 1 m deployable boom. The instrument has a flight heritage on GEOS 1&2, Galileo, Ulysses, Cassini, Freja and Cluster. SCM is identical to the one flown on the CLUSTER/STAFF instrument, while its electronics are a simplification of the ones flown on the FAST IDPU (Instrument Data Processing Unit).

SCM measures the variation of the magnetic flux threading three orthogonal high permeability m-metal rods. The unit sensitivity is 0.5 pT (Hz)1/2 @ 10 Hz. A flux feedback loop is employed to ensure phase stability. The triaxial sensor is mounted on a single-hinge, 1m graphite epoxy boom. The signals from the three sensors are pre-amplified and then processed together with EFI data at the IDPU. The IDPU consists of one analog and one digital board. The analog board serves primarily the B- and E-fields processing and includes the SCM pre-amplifiers. The analog signal is pre-amplified and then filtered (together with the E-fields signals) and processed for routine waveform (DC 32 samples/s) and for burst waveform (128Hz-8kHz) production. The DSP (Digital Signal Processor) takes 2n continuous segments (n=0...7, commandable) of 1024 data points and performs FFTs of the data and subsequent averaging in frequency. Consecutive spectral averaging reduces noise further. 52)

SCM calibration: Absolute amplitude and phase calibration takes place with calibration coils that create a known AC pseudo-random noise consisting of a series of discrete frequencies covering most of the bandwidth (10 Hz-8 kHz).


Figure 37: View of the SCM device (image credit: CETP)

EFI (Electric Field Instrument):

The experiment is built by UCB to the heritage of S3-3, ISEE-1, CRRES, POLAR and CLUSTER. The 3D EFI experiment consists of 4 spin-plane spherical sensors each on a 20 m deployable cable and 2 axial tubular sensors, each 1m-long and mounted on a 4 m long stacer element. The sensors (8 cm in diameter) are identical to the ones delivered for flight on the CLUSTER-II satellites. The axial, two-stage stacer elements are identical to ones used on POLAR, FAST and rockets. The 1 m long, 2 mm diameter, stowable tubular sensor is of the standard STEM line built by commercial outfits (Orbital/TRW/AEC-ABLE). The sensor electronics are simplified versions of the CLUSTER design. 53)


Figure 38: Illustration of the EFI sensors (image credit: UCB)

The primary science requirements are derived from the need to determine at the times of onset at 8-10 RE: 1) The plasma pure convective motion, i.e., without the effects of diamagnetic drifts that ESA measurements are subject to. 2) The low frequency (T~1min) wave mode and pointing flux.

EFI specifications: The preamplifier electronics for the wire sensors are housed inside a hockeypuck arrangement, which also acts as a stub for the wires. The deployment mechanism is identical to CLUSTER's but packaging is analogous to FAST due to the reduced volume requirements of the THEMIS EFI experiment. The boom electronics, located at the EFI housing, perform stub and guard voltage control and sphere-biasing. Signal processing takes place in the IDPU, together with the SCM. Routine waveforms (at 32 samples/s) or burst waveforms (at 128 - 8192 samples/s) are captured and processed just as for the SCM data. Spectral processing of the low frequency (< 8 kHz) data occurs in the DSP in a fashion identical to the SCM.

EFI calibration: The individual Probe calibration results in absolute DC measurement accuracy of 0.1 mV/m, i.e., <10% of the field value anticipated during fast flows. Increased confidence in the measurements is being obtained from inter-spacecraft calibration at quiet times.


Mass (kg)

Power (W)

Recent Flight


FGM @ sensor





FGM boom


Fast, Lunar Prospector







ESA @ sensor










SST @ sensor










SCM @ sensor





SCM boom



Lunar Prospector


SCM pre-amps





EFI (4) spin plane





EFI (2) axials










DPU process, compress & store



FAST. Lunar Prospector







Maximum expected





Average reserve





Table 4: Summary of each Probe's instrument characteristics



Ground segment:

THEMIS uses multiple ground stations to communicate with the five probes and to recover telemetry data. In addition, special real-time operations such as the post-launch probe separation event and near-perigee orbit maneuvers are supported by NASA's TDRSS (Tracking and Data Relay Satellite System). Orbit determination is based on Doppler tracking, and attitude determination on sun sensor and three-axis magnetometer data. 54) 55)

The THEMIS constellation is operated in store-and-forward mode. Science and engineering data are recorded in onboard solid-state memory and are recovered primarily near perigee at the highest data rate compatible with the predicted link margin for any given pass. The required, uncompressed science data volume is 750 Mbit per orbit for each probe. Prior to transmission to the ground, science data are compressed, typically along the inbound leg of the orbits. Instrument configuration for science data acquisition is based on predicted crossing times of magnetospheric regions of interest in combination with various on-board trigger algorithms.

Use of the UCB ground station and USN stations. All aspects of THEMIS constellation operations are performed at the MOC (Mission Operations Center) at UCB/SSL and include mission and science operations, flight dynamics and ground station operations. Virtually all state-of-health monitoring and tracking passes are conducted in lights-out mode, while passes involving commanding or special operations are supported by flight controllers at the console.

NASA's GN (Ground Network) and Space Network (SN) support special real-time operations such as launch and near-perigee orbit maneuvers. All THEMIS command and control, as well as mission planning functions are performed at the MOC. Data are transferred between individual ground systems elements via secure network segments, such as NASA's Internet Protocol Operational Network (IONet). The Open Internet is used for post-pass transfer of telemetry files, and also for transfer of acquisition and tracking data with some of the ground stations.

Probe bus identifiers

Mission orbital slot identifiers

Orbital period



4-day orbit



2-day orbit



1-day orbit



1-day orbit



4/5 day orbit

Table 5: Assignment of probe bus and mission orbit identifiers

The probe placement decision concerned the assignment of probe bus identifiers THEMIS A-E to mission orbit slots P1-P5. While the latter designators were assigned primarily for mission design and science data analysis, all MOC functions continued to use the probe bus identifiers assigned prior to launch for all aspects of operations. This approach had the advantage that no reconfiguration of the MOC was required as a result of the orbit slot assignment.

The THEMIS ground and flight systems were designed and implemented to support both autonomous and automated functions with the goal to increase reliability and to reduce risk and operations costs.


Figure 39: Overview of the THEMIS mission control network (image credit: UCB/SSL)

Obtaining sufficient measurements from the instrument subsystems requires that each THEMIS probe collect and store approximately 100-140 MB of data per orbit, which translates to an average rate of between 270-1500 byte/s, depending on the orbit period. The S-band communications system allows downlink of these data at the highest two (524.288 and 1048.576 kbit/s) of ten available telemetry data rates near perigee, using a worldwide network of 11 m class ground stations, including the BGS (Berkeley Ground Station) located at UCB/SSL. To ensure the probes are never completely out of contact, the telemetry link can still be closed at 4 kbit/s through these same 11 m class ground stations at the maximum apogee distance of 200,000 km.

Range rate measurements from multiple ground stations allow maintaining accurate orbit models for all five probes. Two-way Doppler tracking is achieved at all ranges and is conducted concurrently with both scheduled data playback and state of health monitoring pass supports.

Ground system extension for ARTEMIS:

During the Earth-Moon transfer phase, the probes will travel as far as 1.6 million km away from Earth – over seven times farther than the highest apogees of the prime mission phase. Once in the lunar orbit, the probes will be approximately 400,000 km from Earth. Recovering stored scientific measurements collected at a frequency commensurate with the prime mission from lunar distances can only be accomplished by utilizing much larger, more efficient ground antennas. Therefore, the project undertook the development effort to add seven DSN Deep Space Network) 34 m antennas (stations 15, 24, 27, 34, 45, 54 and 65) to the existing spectrum of ground stations already supporting the THEMIS mission. his effort required integrating new telemetry and telecommand interfaces, supporting new tracking and ranging data formats, and adopting new scheduling interfaces into the existing mission operations framework.. 56)

The SGS (SatTrack Gateway Server) orchestrates the processes of pass and event scheduling, flight dynamics product generation, ground station automation, telemetry and command flow management, and command and control system operation. A crucial component of the SatTrack Suite is FrameRouter, which acts as the network equivalent of a matrix switch, providing TCP/IP (Transmission Control Protocol/Internet Protocol) socket-based telemetry and telecommand data flows between remote ground stations and the active command and control software. This scheme, shown in Figure 40 for a pass support with the BGS 11 m antenna, greatly simplifies operations in a multi-ground station, multi-satellite environment, as all ground stations see a consistent virtual interface to the Berkeley MOC.


Figure 40: Network routing scheme for unidirectional telemetry and command socket connections (image credit: USB/SSL)

Legend of Figure 40: The example shown for THEMIS A real-time telemetry and telecommand data flows between the BGS (Berkeley Ground Station) and the primary ITOS (Integrated Test and Operations System) command and control workstation. Telemetry data are also routed to additional ITOS workstations to allow remote monitoring of spacecraft state-of-health for special operations.

The interface between the MOC and the DSN ground stations is facilitated by the SLE (Space Link Extension), a CCSDS recommended standard which extends existing CCSDS telemetry and telecommand space link protocols with a cross-support service model that governs data transport and management.

In contrast to the unidirectional data flows that are commonly used for THEMIS with GN and SN, SLE telemetry and telecommand service providers and users communicate as peers connected by bidirectional TCP/IP sockets, constantly exchanging data, management, and heartbeat messages. The SLE recommendation presently provides service models for transporting all telemetry transfer frames on the master channel RAF (Return All Frames), or frames from a single virtual channel RCF (Return Channel Frame) from a ground station to the MOC, and for transporting forward CLTUs (FCLTU - Forward Command Link Transmission Units) from the MOC to the ground station.

Ranging: The original THEMIS concept of operations required only two-way Doppler tracking data from all supporting ground stations to be used for orbit determination. However, the project became interested in exploring the existing, but so far untested ranging capabilities in light of the upcoming DSN integration for ARTEMIS.

Ground observations:

Ground observations are being carried out by 20 Ground Based Observatories (GBO), spread across Alaska and Canada. Each GBO uses an ASI (All-Sky Imager) camera and a GMAG (Ground Magnetometer) to monitor the auroral light and ionospheric currents in order to localize the time, location, and evolution of the auroral manifestation of the substorm. A second ground network will include 10 Education and Public Outreach (E/PO) GMAGs located in schools at sub-auroral latitudes in the US.


Figure 41: The Northern Lights as observed by THEMIS and a system of ground cameras (image credit: NASA)



ARTEMIS (Acceleration Reconnection Turbulence, and Electrodynamics of Moon Interaction with the Sun)

ARTEMIS represents an ambitious THEMIS mission extension involving the transfer of the outer two spacecraft (P1 and P2) from Earth orbits to lunar orbits where they will conduct measurements of the Moon’s interaction with the solar wind and its crustal magnetic fields. Earth departure of these two spacecraft is accomplished by successively raising the apogees of their orbits until lunar perturbations become the dominant forces significantly altering their trajectories. This orbit raise sequence requires over forty maneuvering events, with multiple lunar approaches and fly-bys, before setting the two spacecraft on low-energy transfer trajectories to lunar orbit in February and March 2010. 57)

The goal is to maneuver the two spacecraft into the Earth-Moon Lagrangian points and eventually into lunar orbit - to observe the same phenomena as before but from a different perspective.

ARTEMIS orbit raise maneuver sequence:

At the beginning of the ARTEMIS Earth-Orbit Phase, P1 occupied the largest of the THEMIS orbits with a period of 4-days, a perigee of 1,936 km, and an apogee of 195,703 km. P2 held the second largest orbit with a period of 2-days, a perigee of 3,201 km, and an apogee of 117,438 km. Figure 3 illustrates the general configuration of these orbits. The spacecraft spin-axis orientations at this time were approximately 8º from an ecliptic south attitude and with a spin period of approximately 3 seconds.


Figure 42: THEMIS end of mission orbit configuration (image credit: NASA)

Legend to Figure 42: ARTEMIS-P1 is colored magenta and P2 is blue. The red, green and black are the other three THEMIS spacecraft.

The Earth-Orbit Phase of the ARTEMIS trajectory had two goals to accomplish; raise the apogee of both spacecraft through a series of ORMs (Orbit Raise Maneuvers) to near lunar altitudes and to target the lunar gravity assists needed to transition into the Trans-Lunar trajectories through a series of FTMs (Flyby Targeting Maneuvers). Both ORM and FTM events are designated serially from 1 (ORM1, ORM2, etc).

The goal of the ORMs is to increase the altitude of apogee and the orbital period. The ORM sequence for both spacecraft can be highly sensitive to phasing with the mission baseline. As ORM maneuvers are executed navigation and performance errors could accumulate in the spacecraft’s phase and prevent proper targeting of the flyby events. Subsequent maneuvers in the sequence would have to be adjusted to remove these errors. This issue is analogous to challenges faced during the operation of the THEMIS mission where five spacecraft were required to maintain proper phasing with ground based observatories located in central Canada.

ARTEMIS-P1’s orbit raise maneuver sequence:

P1’s orbit raise maneuver sequence consisted of five radial thrust ORMs starting on August 1st, 2009. Due to the time of year, P1’s orbital alignment was phased relative to the sun such that the majority of its near perigee trajectory was shadowed by the Earth. The requirement that sun-synchronous maneuvers be performed in full sunlight necessitated that all of P1’s ORM maneuvers be split into two burn events that bracketed these shadows. The split ORMs are designated such that the pre-shadow maneuvers are labeled A and the post shadow maneuvers are labeled B (e.g. ORM1A and ORM1B).

The total P1 ORM sequence used 99.168 m/s of ΔV, which was 2.6% more than predicted in the baseline trajectory due to performance errors.

ARTEMIS-P2 orbit raise maneuver sequence:

The P2 ORM sequence is more extensive, consisting of 27 ORM events, due to the significantly smaller orbital size at the start of the ARTEMIS Earth-Orbit Phase. The spacecraft was also experiencing Earth shadows near perigee, which necessitated the segmenting of ORM3 through ORM14 into pre- and post-shadow maneuvers, increasing the total number of burn events to 39. - The trajectory of P2 from July 21, 2009 through March 1, 2010 is shown in Figure 43.


Figure 43: ARTEMIS P2 ORM sequence in Earth Inertial coordinates ( the grid represents the equatorial plane), image credit: NASA

ARTEMIS FTM (Flyby Targeting Maneuver) sequence:

With the completion of the ORM sequence, the two ARTEMIS spacecraft were on course to navigating the lunar flybys that will result in their transfer to the Trans-Lunar phase of the mission. To complete the targeting of these flyby events both spacecraft required a series of FTMs to properly connect the final ORM orbital states to the trans-lunar injections.

- P1 FTM sequence: On December 8, 2009, P1 experienced it first lunar flyby event, passing within 18,576 km of the Moon and receiving a significant inclination change as a result.

- P2 FTM and shadow deflection sequence: P2’s path to the Trans-Lunar transfer trajectory only requires one lunar flyby event. This flyby occurred on March 28, 2010, after the long Earth shadow event on March 22, 2010.


ARTEMIS Trans-Lunar Phase:

The Trans-Lunar Phase started for both ARTEMIS spacecraft upon the conclusion of their lunar flyby events. P1 and P2 will reach maximum ranges of 1.5 million km and 1.2 million km respectively. P1 will execute one deterministic maneuver in deep space and an insertion burn resulting in a LL2 (Lunar Lagrangian point 2) Lissajous orbit on August 23rd, 2010.

P2 will be executing two maneuvers in deep space, along with its insertion burn, which will result in a LL1 (Lunar Lagrangian point 1) Lissajous orbit on October 22, 2010.

The ARTEMIS extension to the THEMIS mission is a very ambitious endeavor that is expected to return a high scientific yield from the study of the Moon and it nearby environment. The planned layovers in LL1 and LL2 Lissajous orbits will be of further interest to the space exploration communities and the challenges faced in the implementation of their station-keeping19 will be the subject of future publications.

The implementation of the ARTEMIS trajectory has been on schedule. The P1 and P2 spacecraft are now well into their Trans-Lunar trajectories. Both spacecraft will be arriving in their respective Lissajous orbits in August and October, 2010 respectively.


ARTEMIS-P1 First Earth-Moon Libration Orbiter:

In August 2010, ARTEMIS-P1 became the first spacecraft to navigate to and perform stationkeeping operations around the Earth-Moon L1 and L2 Lagrangian points (also referred to as LL1 and LL2, respectively). There are five Lagrangian points associated with the Earth-Moon system. The two points nearest the moon are of great interest for lunar exploration. These points are called L1 (located between the Earth and Moon) and L2 (located on the far side of the Moon from Earth), each about 61,300 km above the lunar surface. It takes about 14 to 15 days to complete one revolution about either the L1 or L2 point. These distinctive kidney-shaped orbits are dynamically unstable and require weekly monitoring from ground personnel. Orbit corrections to maintain stability are regularly performed using onboard thrusters (Ref. 38). 58) 59)


Figure 44: Lagrangian points of the Sun-Earth and Earth-Moon systems

After the ARTEMIS-P1 spacecraft has completed its first four revolutions in the L2 orbit, the ARTEMIS-P2 spacecraft will enter the L1 orbit. The two sister spacecraft will take magnetospheric observations from opposite sides of the moon for three months, then ARTEMIS-P1 will move to the L1 side where they will both remain in orbit for an additional three months. Flying the two spacecraft on opposite sides, then the same side, of the moon provides for collection of new science data in the Sun-Earth-Moon environment.

ARTEMIS will use simultaneous measurements of particles and electric and magnetic fields from two locations to provide the first three-dimensional perspective of how energetic particle acceleration occurs near the Moon's orbit, in the distant magnetosphere, and in the solar wind. ARTEMIS will also collect unprecedented observations of the space environment behind the dark side of the Moon – the greatest known vacuum in the solar system – by the solar wind.

In late March 2011, both spacecraft will be maneuvered into elliptical lunar orbits where they will continue to observe magnetospheric dynamics, solar wind and the space environment over the course of several years.


Figure 45: Illustration of the Artemis-P1 librations orbits, (image credit NASA/GSFC)


Figure 46: Illustration of ARTEMIS-P1 libration orbits, side or ecliptic view (image credit: NASA/GSFC)

Other benefits of this first ever libration orbit mission include the investigation of lunar regions to provide a staging location for both assembly of telescopes or human exploration of planets and asteroids or even to serve as a communication relay location for a future lunar outpost. The navigation and control of the spacecraft will also provide NASA engineers with important information on propellant usage, requirements on ground station resources, and the sensitivity of controlling these unique orbits (Ref. 58).


2) Information provided by Vassilis Angelopoulos of UCB/SSL and by Thomas Ajluni of Swales Aerospace

3) V. Angelopoulos, “THEMIS in Relation to CLUSTER and Double Star,” Proceedings Cluster and Double Star Symposium - 5th Anniversary of Cluster in Space, Noordwijk, The Netherlands, 19 - 23 Sept. 19-23, 2005 (ESA SP-598, January 2006),

4) W. R. Eppler, “An Optimized Small Satellite Bus and Structure for the THEMIS mission,” Proceedings of the 20th Annual AIAA/USU Conference on Small Satellites, Logan, UT, Aug. 14-17, 2006, paper: SSC06-IV-5

5) T. Ajluni, “SmallSat Lessons Learned on THEMIS: Approaches to Standard Interfaces That Succeeded or Failed,” Proceedings of the 19th AIAA/USU Conference on Small Satellites, Logan, UT, USA, Aug. 8-11, 2005, SSC05-V-8


7) THEMIS Project Data Management Plan, July 15, 2004, URL:

8) M. J. Cully, W. Chen, K. Brenneman, G. T. Delory, “Application of the THEMIS Bus to New Missions,” Proceedings of the 21st Annual AIAA/USU Conference on Small Satellites, Logan, UT, USA, Aug. 13-16, 2007, SSC07-II-5

9) B. Kraeuter, G. Shiblie, “Probe Bus Avionics Unit Development and Validation,” Proceedings of the 21st Annual AIAA/USU Conference on Small Satellites, Logan, UT, USA, Aug. 13-16, 2007, SSC07-XIII-5

10) Debra Werner, “A 50-Year History of Training the Next Generation of Space Scientists,” Space News, Sept. 21, 2009, p. 16

11) “THEMIS Overview and Goals,” UCB, URL:

12) S. Frey, V. Angelopoulos, M. Bester, H. Frey, “THEMIS Orbit Updates Prior to Second Tail Season 2008/2009,” 1st Joint CLUSTER-THEMIS Workshop, UNH (University of New Hampshire), Sept. 23-26, 2008, URL:


14) Karen C. Fox, “NASA's THEMIS Discovers New Process that Protects Earth from Space Weather ,” NASA, March 6, 2014, URL:

15) B. M. Walsh, J. C. Foster, P. J. Erickson, D. G. Sibeck, “Simultaneous Ground- and Space-Based Observations of the Plasmaspheric Plume and Reconnection,” Science, March 7, 2014, Vol. 343, No 6175, pp: 1122-1125, DOI: 10.1126/science.1247212, URL of abstract:

16) Information provided by Vassilis Angelopoulos (Mission PI) of UCLA and UCB.

17) “UCLA Experimental Space Physics — THEMIS-MMS Conjunctions: A Step Closer to Reality,” Nov. 8, 2013, URL:

18) Vassilis Angelopoulos, A. Runov, X.-Z. Zhou, D. L. Turner, S. A. Kiehas, S.-S. Li, I. Shinohara, “Electromagnetic Energy Conversion at Reconnection Fronts,” Science, Vol. 341, No 6153, Sept. 27, 2013, pp. 1478-1482, DOI: 10.1126/science.1236992

19) Karen C. Fox, “Several NASA Spacecraft Track Energy Through Space,” NASA, Sept. 26, 2013, URL:

20) “ARTEMIS News,” Sept. 27, 2013, URL:

21) Information provided by Karen C. Fox of NASA/GSFC, Greenbelt, MD, USA.

22) Karen C. Fox, “Six Years in Space for THEMIS: Understanding the Magnetosphere Better Than Ever,” NASA, Feb. 19, 2013, URL:

23) Drew L. Turner, Vassilis Angelopoulos, Yuri Shprits, Pat Cruce, “Storm-time evolution of relativistic electron equatorial phase space density throughout the outer radiation belt,” The paper has been accepted by JGR and will be published in 2013.

24) M. D. Hartinger, D. L. Turner, F. Plaschke, V. Angelopoulos, H. Singer, “The role of transient ion foreshock phenomena in driving Pc5 ULF wave activity,” JGR (Journal of Geophysical Research), Space Physics, Article first published online: 31 JAN 2013, DOI: 10.1029/2012JA018349, URL:

25) G. I. Korotova, D. G. Sibeck, N. Omidi, V. Angelopoulos, “THEMIS observations of unusual bow shock motion attending a transient magnetospheric event,” JGR (Journal of Geophysical Research), Space Physics, Article first published online: 8 DEC 2012 , DOI: 10.1029/2012JA017510, URL:

26) Daniel Cosgrove, Sabine Frey, Jeffrey Marchese, Brandon Owens, Manfred Bester, “ARTEMIS Operations from Earth-Moon Libration Orbits to Stable Lunar Orbits,” Proceedings of SpaceOps 2012, The 12th International Conference on Space Operations, Stockholm, Sweden, June 11-15, 2012

27) Karen C. Fox, “THEMIS Celebrates Five Years of Watching Aurora and Space Weather,” Space Daily, Feb. 24, 2012, URL:

28) J. B. Tao, R. E. Ergun, D. L. Newman, J. S. Halekas, L. Andersson, V. Angelopoulos, J. W. Bonnell, J. P. McFadden, C. M. Cully, H.-U. Auster, K.H.Glassmeier, D. E. Larson, W. Baumjohann, M. V. Goldman, “Kinetic instabilities in the lunar wake: ARTEMIS observations,” Journal of Geophysical Research, Vol. 117, 2012, A03106, 10 pp, doi:10.1029/2011JA017364

29) Stephen B. Broschart, Theodore H. Sweetser, Vassilis Angelopoulos, David C. Folta, Mark A. Woodard, “ARTEMIS lunar orbit insertion and science orbit design through 2013,” Proceedings of the AAS/AIAA Astrodynamics Specialist Conference, Girdwood, Alaska, USA, July 31- Aug. 4, 2011, paper: AAS 11-509

30) David Folta, Theodore Sweetser, “ARTEMIS Mission Overview,” Proceedings of the AAS/AIAA Astrodynamics Specialist Conference, Girdwood, Alaska, USA, July 31- Aug. 4, 2011, paper: AAS 11-510

31) David Folta, Mark Woodard, Theodore Sweetser, Stephen B. Broschart, Daniel Cosgrove, “Design and Implementation of the ARTEMIS Lunar Transfer using multi-body dynamics,” Proceedings of the AAS/AIAA Astrodynamics Specialist Conference, Girdwood, Alaska, USA, July 31- Aug. 4, 2011, paper: AAS 11-511

32) Robert Sanders, “Twin ARTEMIS Probes to Study Moon in 3-D,” UC Berkeley News Center, July 13, 2011, URL:

33) “Two NASA Probes Tackle New Mission: Studying the Moon,” NASA, July 19, 2011, URL:

34) Karen C. Fox, “ARTEMIS Spacecraft Prepare for Lunar Orbit,” NASA, June 23, 2011, URL:

35) Robert Sanders, “Out of THEMIS, ARTEMIS: Earth’s loss is moon’s gain,” UCB, October 27, 2010, URL:

36) “THEMIS/Artemis,” June 18, 2009, 365 Days of Astronomy, URL:

37) Mark Woodard, David Folta, Dennis Woodfork, “ARTEMIS: The First Mission to the Lunar Libration Orbits,” URL:

38) V. Angelopoulos, “The ARTEMIS Mission,” 2010, URL:

39) D. C. Folta, T. A. Pavlak, K. C. Howell , M. A. Woodard, D. W. Woodfork, “Stationkeeping of Lissajous Trajectories in the Earth-Moon System with Applications to ARTEMIS,” Proceedings of the AAS/AIAA Space Flight Mechanics Meeting, February 14-17, 2010, San Diego, CC, USA, paper: AAS 10¿113, URL:

40) “Road Cleared for ARTEMIS Mission Implementation,” UCB/SSL, Feb. 27, 2009, URL:

41) Tony Phillips, “Spacequakes Rumble Near Earth,” NASA, July 27, 2010, URL:

42) Michael Carlowicz, “Colliding auroras produce an explosion of light,” NASA, Dec. 17, 2009, URL:

43) “Colliding Auroras Create Explosions,” Universe Today, Dec. 17, 2009, URL:

44) “Colliding Auroras Produce Explosions Of Light,” Space Daily, Dec. 18, 2009, URL:

45) Warren Chen, Michael J. Cully, “THEMIS Post Launch Spacecraft Bus Systems Performance Validation: Comparison to Systems Design and Analysis Attributes,” Proceedings of the 22nd Annual AIAA/USU Conference on Small Satellites, Logan, UT, USA, Aug. 11-14, 2008, SSC08-II-1

46) Rani Gran, Laura Layton, “Magnetic Tremors Pinpoint Impact Epicenter Of Earthbound Space Storms,” Space Daily, May 2009, URL:

47) “THEMIS Satellites Discover What Triggers Eruptions of the Northern Lights,” NASA, July 24, 2008, URL:







54) M. Bester, M. Lewis, B. Roberts, L. Croton, R. Dumlao, M. Eckert, J. McDonald, D. Pease, C. Smith, J. Thorsness, J. Wheelwright, S. Frey, D. Cosgrove, D. Rummel, M. Ludlam, H. Richard, T. Quinn, J. Loran, R. Boyd, C. Quan, T. Clemons, “Ground Systems and Flight Operations of the THEMIS Constellation Mission,” Proceedings of the 2008 IEEE Aerospace Conference, Big Sky, MT, USA, March 1-8, 2008

55) Manfred Bester, Mark Lewis, Bryce Roberts, Daniel Cosgrove, “Operations Planning and Mission Readiness Testing for the THEMIS Spacecraft Constellation,” Proceedings of the 2010 IEEE Aerospace Conference, Big Sky, MT, USA, March 6-13, 2010

56) Bryce Roberts, Mark Lewis, Jeremy Thorsness, Gregory Picard, Gregory Lemieux, Jeffrey Marchese, Daniel Cosgrove, Gregory Greer, Manfred Bester, “THEMIS Mission Networks Expansion – Adding the Deep Space Network for the ARTEMIS Lunar Mission Phase,” Proceedings of the SpaceOps 2010 Conference, Huntsville, ALA, USA, April 25-30, 2010, paper: AIAA 2010-1934

57) Daniel Cosgrove, Sabine Frey, Jeffrey Marchese, Brandon Owens, Swapan Gandhi, Manfred Bester, David Folta, Mark Woodard, Dennis Woodfork, “Navigating THEMIS to the ARTEMIS Low-Energy Lunar Transfer Trajectory,” Proceedings of the SpaceOps 2010 Conference, Huntsville, ALA, USA, April 25-30, 2010, paper: AIAA 2010-2352

58) David Folta, Mark Woodard, “ARTEMIS - The First Earth-Moon Libration Orbiter,” NASA, Sept. 13, 2010, URL:

59) David C. Folta, Mark Woodard, Kathleen Howell, Chris Patterson, Wayne Schlei, “Applications of Multi-Body Dynamical Environments: The ARTEMIS Transfer Trajectory Design,” Proceedings of the 61st IAC (International Astronautical Congress), Prague, Czech Republic, Sept. 27-Oct. 1, 2010, IAC-10,C1,9,9,x7461

The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: ”Observation of the Earth and Its Environment: Survey of Missions and Sensors” (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates.