Minimize IBEX

IBEX (Interstellar Boundary Explorer)

IBEX is a Small Explorer (SMEX-class) microsatellite and technology demonstration mission of NASA in the category of a low-cost focused science mission - selected in November 2003. The mission was proposed by Southwest Research Institute (SwRI) in San Antonio, Texas, to study the interstellar boundary – the region between our solar system and interstellar space. In May 2006, SwRI received official confirmation from NASA/HQ to proceed into the mission implementation phase for IBEX.

IBEX is designed to investigate “the global interaction between the solar wind and the interstellar medium.” This is achieved by imaging ENAs (Energetic Neutral Atoms) originating at the boundary between the solar wind and the interstellar medium. Energetic neutral atoms are also generated by the interaction of the Sun with the Earth’s magnetic field. Therefore, the spacecraft must operate outside this regime. Science operations only occur when the spacecraft altitude is greater than 10 RE. It is this limitation that drives the need for such a high-energy orbit. 1)

IBEX is a PI mission of NASA with SwRI (David McComas) leading the mission. For IBEX, SwRI is partnering with other flight hardware developers OSC (Orbital Science Corporation), LANL (Los Alamos National Laboratory), LMATC (Lockheed Martin Advanced Technology Center), NASA/GSFC (Goddard Space Flight Center), the University of New Hampshire, and the JHU/APL (Johns Hopkins University / Applied Physics Laboratory). In addition, the team includes a number of US and international scientists from universities and other institutions, as well as the Adler Planetarium, which is leading education and public outreach for the mission. 2)


Figure 1: Artist's view of the IBEX spacecraft in HEO (image credit: NASA)


The microsatellite is based on the MicroStar octagonal platform of OSC (Orbital Sciences Corporation), Dulles, VA (contract award in January 2005). The bus is spin-stabilized at nominally 4 rpm with the major axis pointing toward the sun. 3) 4) 5)

The spacecraft bus consists of a central “thrust-tube” core structure, the components are mounted on 6 side panels. The solar array is surface-mounted on the top deck.

The IBEX mission illustrates multiple key points about the potential for Micro-GEO spacecraft:

• First, it demonstrates that a microsatellite can perform groundbreaking science investigations. It is making key measurements of a region only now being visited by the Voyager spacecraft.

• Second, IBEX demonstrates that large propulsive maneuvers can be performed on small satellites. The IBEX HEO orbit raising maneuver requires approximately a ΔV of 3,000 m/s, about double the value needed to raise a spacecraft from GTO to GEO.

• Finally, IBEX shows that Micro-GEO spacecraft may come in many different configurations.

For IBEX, the MicroStar avionics were put into a new thrust-tube structure, but the avionics architecture remained largely unchanged. The SCB (Spacecraft Bus) features a distributed Motorola 68302 microprocessor-based architecture, with the C&DH (Command and Data Handling) subsystem, ACS (Attitude Control Subsystem), and EPS (Electrical Power Subsystem) each featuring a dedicated processor. An expanded view of the spacecraft showing component location is given in Figure 2.


Figure 2: Schematic view of the spacecraft bus configuration (image credit: IBEX consortium)

Structure: The IBEX spacecraft structure is an irregular octagon approximately 0.93 m across and 50 cm tall composed of a core module, two payload equipment panels, four bus equipment panels, two close out panels, and the solar array panel. The six equipment panels were constructed from 3 mm thick aluminum 6061-T6 skins, 5056 aluminum honeycomb core and FM73U film adhesive. The remainder of the structure was constructed from 3-ply graphite-reinforced cyanate ester prepreg M55J/RS-3C skins, 5056 aluminum honeycomb core, and FM73U film adhesive, except the solar array deck, which used RS-4A film adhesive for the higher service temperature. The inner facesheets and honeycomb core of all panels were perforated for venting. The core module consists of the thrust tube, base panel and four core panels bonded together with pre-cured graphite clips. The other structural panels and solar array deck were assembled to each other and to the core module with bonded aluminum clips and threaded fasteners. The clips were match bonded with EA9309NA epoxy for a shear interface. Inserts to attach components were potted into the panels using EA9396.6MD syntactic foam. Thermal isolators between the solar array and core structure (5 mm thick G-10 washers) isolate the core structure from the Sun-pointing solar array panel. The primary structure was fabricated by Alliance Space Systems LLC in Signal Hill, CA.

The FC (Flight Computer) is the spacecraft controller; the ACE (Attitude Control Electronics) interfaces to the ACS components and hosts the ACS software. The BCR (Battery Charge Regulator) provides power for all spacecraft loads and performs ancillary functions including heater control, SRM (Solid Rocket Motor) fire, and separation system actuation. The MIU (Mission Interface Unit) is the interface between the SCB (Spacecraft Bus) and the CEU (Combined Electronics Unit) in the payload. The CEU provides power and data connections to the IBEX-Hi and IBEX-Lo sensors and stores all mission data, including SCB housekeeping telemetry. The MIU also provides the interface to the S-band transceiver to receive uplinked commands and downlink telemetry and science data. On-board propulsion for perigee and apogee raising, spin down, and orbital maneuvers is provided by the HPS. The following sections describe the subsystems of the SCB.

ACS (Attitude Control Subsystem) : The ACS maintains stability and control throughout all mission phases, beginning with separation from Pegasus. The ACS uses one processor contained in the ACE, which drives core ACS algorithms and interfaces to the ACS sensors and actuators.

Attitude determination is provided by the sensors listed in Table 1. The two Honeywell QA2000-030 accelerometers are mounted on different axes such that one measures spin rate and the other measures nutation. The spin rate accelerometer saturates at around 27.5 rpm. Coarse Sun sensor data can be used to approximate a value, but at high spin rates only the accelerometer reading is available for onboard spin rate determination. The rate gyro, a BEI Systron Donner QRS100, offers a backup nutation measurement, which is needed for the ΔV maneuvers (SRM burn and hydrazine orbit raising), during which the nutation accelerometer is saturated.

The star tracker, the ASC (Advanced Stellar Compass) of DTU Space (Technical University of Denmark), is only used at a low (<4.5 rpm) spin rate and is the high accuracy sensor used during the nominal science mission. When on, the star tracker also measures spin rate and nutation (more accurately than the accelerometer or rate gyro). The coarse sun sensors are used as a backup to the star tracker, providing a reference to perform maneuvers to point the solar array at the sun.



Operational range

Coarse sun sensor

Measure the sun vector

±70º half cone

Star tracker

Measure spacecraft attitude by referencing local stars in the star tracker field of view

Any attitude, spin rate up to 4.5 rpm

Spin rate accelerometer

Measure acceleration in the spin axis to determine spacecraft spin rate

0 to 27.5 rpm (2.88 rad/s)

Nutation accelerometer

Measure acceleration in the transverse axes to determine vehicle nutation

±0.08 rad/s

Rate gyro

Measure angular rate to determine nutation

±50º/s in X–Y

Pressure sensors

Measure propulsion tank pressure

0 to 2909 x 103 Pa (or 422 psi)

Table 1: Attitude control subsystem sensors


Figure 3: Block diagram of the IBEX spacecraft (image credit: IBEX consortium)

Spacecraft bus

MicroStar platform built on an octagonal base, roughly 58 cm high and 95 cm across

Spacecraft mass (IBEX)

Launch mass = 107 kg; dry mass of 80 kg of which the instrument payload comprises 26 kg

Spacecraft mass

Entire flight system launch mass, including the ATK Star 27 solid rocket motor = 462 kg


- 116 W (max), the nominal power is 66 W (16 W for payload)
- The Li-ion battery has a cells of 10.5 Ah arranged in a 2 parallel/4 series configuration to supply 14.4 VDC nominal with 21 Ah of capacity

ACS (Attitude Control Subsystem)

- Attitude sensing is provided by the star tracker ASC (Advanced Stellar Compass), coarse sun sensors, and a rate gyro
- Attitude actuation is provided by thrusters
- Spin stabilization at 4 rpm

Mission life

2 years (baseline mission)

Table 2: Overview of some spacecraft parameters

C&DH (Command & Data Handling) subsystem: The C&DH subsystem provides command decoding and distribution, performs data collection and storage, performs health and maintenance functions, and provides the electrical interface to the payload through the CEU. The C&DH subsystem consists of the FC, the ACE, and the MIU. A block diagram of the C&DH Subsystem is shown in Figure 4.


Figure 4: Block diagram of the C&DH subsystem (image credit: IBEX consortium, Ref. 5)

The FC and ACE serve as the core of the subsystems, with internal architectures based on the radiation-tolerant version of the Motorola 68302 multi-protocol communications processor. The FC communicates with the BCR and ACE via a multi-drop RS-485 bus and with the MIU via a dedicated RS-422 interface; the MIU communicates with the payload CEU via another dedicated RS-422 interface. The FC also includes eight discrete I/O ports for resetting systems, power switching, and other functions. A 256 kB boot ROM stores code for processor startup and boot load functions, and a 256 kB EEPROM holds the application code at startup.

The FC executes real-time commands, as well as time-based stored commands. Its 3 MB EDAC-protected RAM stores spacecraft state-of-health telemetry received from the BCR, ACE, MIU, and CEU. All stored telemetry is also sent to the CEU to be stored in its much larger SSR (Solid-State Recorder ) until the downlink ground pass. Several orbits of telemetry can thus be stored in the CEU, while the FC maintains telemetry from only the most recent day or so.

The MIU is the interface between the FC, payload CEU, and RF communications subsystem. The MIU receives payload commands and spacecraft telemetry from the FC and forwards those to the CEU, which de-commutates the message to determine if it is a command to be executed or telemetry to be stored in the SSR. The MIU also collects discrete telemetry from, and controls the interfaces to, the CEU and S-band transceiver. During a data downlink, the MIU performs CCSDS data encoding prior to sending the data to the transmitter and controls the downlink data rate based on commands from the FC.

The MIU provides the spacecraft-to-ground interface for commanding, telemetry, and science data. The MIU interfaces with the RF communications subsystem, the FC, the CEU, and the ACE. For the RF communications interface, the MIU receives and decodes data from the S-band receiver and forwards that data to the FC. It also performs CCSDS encoding on telemetry data from both the FC and CEU and sends that data to the transmitter for downlink.

The MIU is the sole electrical interface between the SCB and the payload. All payload commands are forwarded by the MIU from the FC to the CEU. The MIU also sends pulse-per-second and spin pulse signals to the CEU as commanded by the FC and ACE. In addition, the MIU provides switched +28 V power and six switched heater interfaces to the CEU. - The MIU also provides the interface to several other components, including the SRM safe and arm, separation breakwires for safety inhibits, two coarse Sun sensors, the accelerometers, eight temperature sensors, and both ΔV thrusters.

EPS (Electrical Power Subsystem): The EPS provides and controls the electrical power that operates the IBEX spacecraft. Its functions include power generation and storage, load management, voltage conversion and regulation, heater control, safety inhibits, and launch/deployment sequence control. A block diagram of the EPS is shown in Figure 5.

The EPS is comprised of the BCR (Battery Charge Regulator), PCM (Power Converter Module), lithium-ion battery, and solar array panel. These components operate collectively to supply optimal power to the spacecraft.

The BCR is the hardware core of the EPS, converting solar array power into unregulated (+14 V) and regulated (+5 V) power and distributing that power to the SCB; the power outputs are switchable. The EPS software architecture integrates the functionality of the major BCR components: microcontroller, telemetry card, accessory card, central regulator, and charge regulator. Through these components, the BCR controls the MPPT (Maximum Power Point Tracking), battery charging, battery protection, load switching, load management, the +5 V regulated bus, and the 14 V unregulated bus. The BCR also collects voltage, current, and temperature data from several spacecraft sensors and controls battery charging/discharging based on battery cell voltage monitoring.

Additional BCR functions include controlling load shedding and heaters and managing separation and deployment sequence. The EPS communicates with the FC and the ACE via the avionics bus, and the BCR is the token master. The central regulator provides regulated +5 Vdc power to the spacecraft components, excluding the BCR internal electronics. Power provided by the central regulator is mainly used by the digital electronics components in other subsystems. The solar array feeds into the charge regulator, which converts the 20–40 V solar array voltage to the unregulated 14 V bus. The charge regulator is responsible for managing power between the solar array and battery.


Figure 5: Block diagram of the EPS (image credit: IBEX consortium)

The PCM receives power from the BCR unregulated bus and uses it to generate secondary voltages, including +28 V, ±5 V, ±15 V, and ±12 V. In addition to secondary power conversion, the PCM is also responsible for the following: sequencing the startup of the ACE, accelerometers, gyro, and SCU; providing triple breakwire based inhibits for the S-band transmitter and all hydrazine thrusters; providing spare switching capability; and controlling the aft antenna RF switch.

Battery: IBEX uses a 300 Whr lithium-ion battery manufactured by Yardney (NCP8-2 cells) for energy storage. The battery features eight cells (4s2p) and balancing electronics. Battery management electronics are incorporated within the battery pack, with the MEQ (Monitor Equalizer Board) ensuring that charge is equalized between cells and counteracting the effects of cell internal leakage currents on internal cell balance. The battery operates over a range of 12 V to 16.4 V, with each cell going from 3 to 4.1 V. For ideal battery maintenance, the battery cells are generally kept at 3.9 V in full sunlight, except in cases of a long eclipse when the full 4.1 V charge is used. As a lithium-ion battery, battery state of charge is determined by battery voltage; temperature is not used.

Solar array: Power generation for the spacecraft comes from a single body-mounted solar array on the +Z deck of the spacecraft. The spacecraft is nominally a sun-pointed (within 8º) spinner, keeping the solar array illuminated. Between launch and the end of orbit raising, however, the spacecraft can remain power positive with the sun as much as 55 º off of the +Z-axis.

The solar array generates 114 W EOL at 110°C and 8° angle of incidence with 168 standard Emcore ATJ cells laid out in 12 strings of 14 cells each. The solar array is thermally isolated from the rest of the spacecraft and operates within a range of -160ºC to 145ºC, depending on the solar angle of incidence or if the vehicle is in sunlight or eclipse. ITO (Indium Tin Oxide) coating on the front surface of the solar cell coverglasses was used to minimize the solar array static charge build-up. The cells are laid out to reduce the number of strings affected at one time by shadowing from the +Z thruster or antenna mast when the sun is off at an angle from the +Z direction.

HPS (Hydrazine Propulsion Subsystem): The HPS is a simple monopropellant (hydrazine) blowdown system. Propellant is contained within two outboard spherical tanks; the location and shape of the tanks were selected to minimize nutation effects due to propellant sloshing. Four radial thrusters (5 N nominal) are oriented to provide impulse in the ±X direction for active nutation control during the SRM burn. During normal spacecraft operation these thrusters perform spin-rate adjustment, spin-axis repointing, and general attitude control. Two axial thrusters (22 N nominal) are oriented to provide impulse in the ±Z direction for orbit-raising maneuvers. The HPS design includes service and service valves, filters, and pressure transducers.

A functional schematic of the HPS is shown in Figure 6. The thruster orientation on the spacecraft, with thruster plumes identifying the firing direction is shown in Figure 7. The thruster locations were deliberately chosen to prevent the sensor apertures from observing the plumes.


Figure 6: Schematic view of the HPS (image credit: IBEX consortium)


Figure 7: Illustration of the HPS thruster plumes (image credit: IBEX consortium)

RF communications subsystem: All data links are in S-band (use of CCSDS protocols) featuring a TAS (Thales Alenia Space) S-band transponder that provides not only ground communications but also orbit-determination capability in the form of coherent Doppler measurements. Table 3 gives the parameters for the uplink and downlink. Two hemispherical antennas are used with a nominal downlink data rate of 320 kbit/s (max) and an uplink rate of 2 kbit/s. Onboard data storage is provided in the CEU (Combined Electronics Unit).




Data rate (total symbols/s post-encoding)

320, 160, 64, 40, or 2 ksample/s

2 ksample/s

Data rate accuracy


≤ 1%

Data transmission density

≥1 per 50 bit

≥1 per 50 bit

Error control coding

CCSDS Reed-Solomon (255,223) code, 1/2 rate Viterbi (k = 7)


Modulation format



Modulation type



Table 3: Summary of communication parameters


Figure 8: Block diagram of the RF communications subsystem (image credit: IBEX consortium)

IBEX features an omni-directional antenna system that consists of two antennas, a quadrifilar in the +Z direction and a monofilar in the -Z direction, which are joined by a 10 dB coupler. The quadrifilar has a cardiod pattern to get full +Z and X–Y plane coverage, while the monofilar helix has a narrow spectral pattern to augment coverage in the -Z direction with minimal interference on the +Z quadrifilar helix. - The quadrifilar antenna is mounted on a boom to maximize the field of view, allowing coverage of the X–Y plane of the spacecraft, which is required for communications during orbit-raising burns performed at apogee. The combined antenna pattern is designed to provide >85% spherical coverage for 2 ksample/s uplink and downlink at 50 RE altitude (USN Hawaii ground station) as well as opportunities every orbit to downlink to any of the USN stations at 320 ksample/s for at least 30 minutes.

An RF switch in the path between the 10 dB coupler and monofilar antenna allowed the spacecraft to turn on its transmitter (with RF switch open, preventing transmission through the -Z monofilar antenna) while still attached to Pegasus. This made it possible to initiate the TDRSS link prior to spin-up and SRM burn without radiating into the Pegasus fairing, which is not allowed. The RF switch was closed (essentially turning on the monofilar antenna) by the BCR as a final step in the SRM burn and separation sequence.


Figure 9: Photo of the IBEX spacecraft with the exposed IBEX-Lo sensor on the left (image credit: OSC)

The spacecraft is coupled with an ATK Star 27 solid rocket motor (SRM), which boosts it from the injection orbit to its high altitude apogee. The spacecraft, SRM and the launch vehicle are connected by an adapter cone and 3 motorized light bands. The IBEX hydrazine propulsion system features a fully flight-qualified architecture with significant excess capacity.


Figure 10: Illustration of the IBEX flight system (image credit: IBEX consortium)






Flight system dry mass

163.61 kg

160.07 kg


Based on 461.60 kg LV capability, 271.38 kg SRM Propellant, and 26.3 kg hydrazine


60 W

140 W


Requirement is with transmitter off and no battery charging needed

Energy margin, nominal mission

13945.0 Whr

15873.6 Whr


Based on S/A energy generation

Pointing knowledge




By analysis

Downlink margin

See note

See note

> 3 dB

Dependent on symbol rate & downlink altitude

Uplink margin

See note

See note

> 3 dB

Dependent on uplink altitude

Propellant delta-V

See note

See note


On top of delta-V margin

Delta-V (mean)

175.5 m/s

514.0 m/s


Amount of delta-V available

Delta-V (3σ)

200.1 m/s

514.0 m/s


Amount of delta-V available

Data storage on SEU

515.68 Mbit

1073.74 Mbit


Based on 2 orbits of data

Commands, nominal mission




Based on 2 orbits of commands

Table 4: Summary of IBEX technical resources (Ref. 5)


Launch: The IBEX spacecraft was launched on a Pegasus-XL rocket of OSC on October 19, 2008. The Pegasus was released from a Lockheed L-1011 aircraft that took off from Kwajalein Atoll in the South Pacific. 6) 7)

Orbit: HEO (Highly Elliptical Orbit) with a perigee of 7,000 km and an apogee of 50 RE (amounting to 319,000 km, or more than 80% the distance to the moon). The inclination is 11º, the orbital period around Earth is 7.5 days.

After launch into a 200 km circular injection orbit, a STAR 27 solid rocket motor (SRM) was fired to raise the orbit. After several days of on-orbit checkout, an on-board hydrazine propulsion system is used to fine tune the orbit apogee to the desired 50 RE altitude and to raise perigee. The perigee raising maneuver lowers the radiation dose accumulated by the spacecraft over its two year design life.


Figure 11: Summary of IBEX launch sequence, orbit raising, and normal operations (image credit: SwRI)


Figure 12: Illustration of the sun-pointing spacecraft in its orbit around Earth and the Sun (image credit: SwRI, OSC)


New orbit selection for IBEX:

In June 2011, IBEX was shifted to a new more efficient orbit. It does not come as close to the Moon in the new orbit, and expends less fuel to maintain its position. 8)

Although the mission design was so far highly successful, there were several important shortcomings of the orbit. First, the orbit at perigee took the spacecraft through the outer radiation belt in each orbit, leading to the accumulation of dose that posed a risk to spacecraft electronic systems (e.g., raising the likelihood of SEUs (Single Event Upsets). In addition, the orbit was not synchronized with the Moon. With an apogee of nearly reaching the Moon’s orbit, there were periods where the spacecraft would pass relatively close to the Moon, and the lunar gravitational force would perturb the orbit. This orbit was very difficult to predict over several year periods. 9)

After extensive studies, the science team chose a 3:1 resonant orbit with a perigee above 7.3 RE. This also ensured that the perigee altitude would not evolve to be below the crowded geostationary belt, alleviating collision concerns. After studying the engine performance and developing procedures and a timeline to calibrate the engine, an initial orbit was chosen with a period of 9.03 days. This orbit is shown for ten years in Figure 13 in the Earth-Moon rotating coordinate frame. The figure shows how the apogees never get close to the Moon, which reduces the perturbations on the orbit.


Figure 13: Nominal mission orbit (in green) and extended mission orbit (in blue) shown in Earth-Moon rotating coordinates (image credit: IBEX team)

Legend to Figure 13: In the rotating Earth-Moon coordinate system, the Earth is in the middle, the Moon’s orbit is the big outer circle, and the Moon is fixed at the top of the circle. The green plot in the background shows the old orbit pattern of IBEX where in some of the orbits the spacecraft passed relatively close to the Moon (straight up) – whenever this happened, the Moon’s gravity changed IBEX’s orbit, requiring the project to make additional maneuvers to keep the spacecraft from burning up in the Earth’s atmosphere or leaving Earth orbit entirely. - In the new orbit (in blue), the spacecraft makes three "petals" that are synchronized to always stay away from the Moon.

Orbit change maneuvers: The orbit change consisted of 5 maneuvers executed over the course of ~3 weeks as shown in Figure 14. Time progresses toward the right, and the locations of the maneuvers, as well as the increase in perigee altitude, are depicted (not to scale). Orbit 128 perigee kicked off the maintenance maneuver procedure. First, the spacecraft spin axis was re-pointed along the velocity vector of the o0129 (orbit 129) apogee (where the bulk of the delta-V was expended). Then the spacecraft was spun-up to a higher spin rate to remain spin-stabilized during the delta-V maneuvers.

- ADV1 was executed at the apogee of o0128. Orbit determination data was collected through perigee to calculate delta-V, calibrate the pressure based models, and plan the duration of the third delta-V burn.

- ADV2 was executed on the ascending side of o0129 apogee. Analysis of long term trajectory based on pressure models lead the team to increase the duration of ADV3 to 600 s.

- ADV3 was executed ~17 h after ADV2.

All three delta-V maneuvers performed nominally. Pressure data allowed us to quickly determine a TCM would not be needed. This quick diagnosis allowed the remaining steps of the maneuver procedure to be pushed up in the timeline. The spin-down to nominal spin rate and re-point to nominal pointing maneuvers occurred just after o0129 perigee. Science data collection resumed early in arc a of o0130 (i.e. o0130a) rather than the planned apogee of o0130 (collecting another full swath of the sky).


Figure 14: Maneuver timeline (Image credit: IBEX team)

The orbit change maneuver and the associated changes to science operations that were necessary to support the change were, in the end, a great success. It was a process that required meticulous planning and patient follow-through, along with careful attention to detail.



Mission status:

• Feb. 2014: The spacecraft data in the past five years from near Earth and cosmic ray observations have painted a better picture of the magnetic system that surrounds us, while at the same time raising new questions. Scientists are challenging our current understanding in a new study that combines observations of massively energetic cosmic ray particles streaming in from elsewhere in the Milky Way along with observations from NASA's IBEX (Interstellar Boundary Explorer). 10) 11) 12) 13)

The data sets show a magnetic field that is nearly perpendicular to the motion of our solar system through the galaxy. In addition to shedding light on our cosmic neighborhood, the results offer an explanation for a decades-old mystery on why we measure more incoming high-energy cosmic rays on one side of the sun than on the other. The IBEX team is discovering how the interstellar magnetic field shapes, deforms, and transforms our entire heliosphere.


Figure 15: The magnetic fields in interstellar space proposed by IBEX predict that cosmic rays would come in as shown on the right – blue represents fewer rays (image credit: Nathan Schwadron, UNH-EOS, NASA, IBEX Team)

Legend to Figure 15: Cosmic ray intensities (left) compared with predictions (right) from IBEX. The similarity between these observations and predictions-as evidenced by the similar color regions-supports the local galactic magnetic field direction determined from IBEX observations made from particles at vastly lower energies than the cosmic ray observations shown here. The blue area represents regions of lower fluxes of cosmic rays. The gray and white lines separate regions of different energies-lower energies above the lines, high energies below.

• October 30, 2013: Launched on Oct. 19, 2008, the IBEX spacecraft is unique to NASA's heliophysics fleet: it images the outer boundary of the heliosphere, a boundary at the furthest edges of the solar system, far past the planets, some 12-13 million km away. There, the constant stream of solar particles flowing off the sun, the solar wind, pushes up against the interstellar material flowing in from the local galactic neighborhood. 14)

IBEX is also different because it creates images from particles instead of light. IBEX, scientists create maps from the observed neutral atoms. Some are of non-solar origin, others were created by collisions of solar wind particles with other neutral atoms far from the sun. Observing where these ENAs (Energetic Neutral Atoms) come from describes what's going on in these distant regions. Over the course of six months and many orbits around Earth, IBEX can paint a picture of the entire sky in ENAs.

During its first five years on orbit, IBEX has made some astounding discoveries.

1) Mapping the Boundaries: In its first year, IBEX scientists created the first-ever all-sky map of the heliosphere's boundary, where the influence of the solar wind diminishes and interacts with the interstellar medium. The most startling finding is that the map was not uniform or symmetrical, but shows a bright ribbon of energetic neutral atoms snaking through it.

During its second and third years, IBEX showed that the heliosphere's boundaries changed more rapidly than expected, with variations as short as six months. Additional sets of all-sky maps showed the evolution of the interstellar boundary region: the mysterious ribbon feature at the nose, of the heliosphere – in the front as it moves through space – evolved. Also, a knot-like feature spread and diminished. This variation over time is challenging scientists to try to understand how the heliosphere can change so rapidly.

2) ENAs Near Earth: Because IBEX is orbiting Earth, it also can look back toward Earth's neutral-atom environment and so has provided the first ENA images of the magnetosphere from the outside.

Nearby, IBEX has scanned the moon, as well. The moon has no atmosphere or magnetosphere, so the solar wind slams unimpeded into its surface. IBEX observations showed that the moon creates a backscattered, neutral solar wind: about 10 percent of the impinging solar-wind protons bounce off the lunar surface, becoming ENAs as they do.

3) The Heliosphere: Looking Ahead and Looking Behind: Measurements by IBEX announced in 2012 show the influence of the heliosphere on the local interstellar medium is different than expected. Previous models showed a boundary ahead of the heliosphere, outside the influence of the sun: a shock formed by the entire heliosphere pushing through the interstellar material around it. IBEX data suggests that there is no bow shock preceding the heliosphere's movement through space.

IBEX also offered up the first observations of the heliotail. If our eyes could see particles and we looked straight down the tail we would see an unexpected shape a little like a four-leaf clover. The two side leaves are filled with slow moving particles and the upper and lower leaves with fast ones.

4) Into the Galaxy: Much further away, IBEX also provided information about the local galactic environment. It made the first direct measurements of neutral hydrogen, oxygen, and neon coming into the heliosphere from the interstellar medium. The measurements show that the composition of the current galactic neighborhood is different than that of the sun and the solar system. This puzzle may mean that the sun has moved out of the region where it formed, or that some of the oxygen has been captured by dust in interstellar space.

IBEX also found that the speed of the galactic wind registered around 52,000 miles/hr. By comparing this wind to previous results from other missions over the last 40 years, scientists believe that the direction of the wind has changed by about 7 degrees in the last four decades. While the cause of this shift is unknown, it may be telling us something about changing conditions as we move through our region of the Milky Way (Ref. 14).

• Sept. 5, 2013: Data from NASA's IBEX spacecraft reveal that neutral interstellar atoms are flowing into the solar system from a different direction than previously observed. 15)

Interstellar atoms flow past the Earth as the solar system passes through the surrounding interstellar cloud at 23 km/s (82,800 km/hr). The latest IBEX measurements of the interstellar wind direction were discovered to differ from those made by the Ulysses spacecraft in the 1990s. That difference led the IBEX team to compare the IBEX measurements to data gathered by 11 spacecraft between 1972 and 2011. Statistical testing of the Earth-orbiting and interplanetary spacecraft data showed that, over the past 40 years, the longitude of the interstellar helium wind has changed by 6.8±2.4 degrees.

The earliest historical data on the interstellar wind comes from the 1970s from the U.S. Department of Defense's Space Test Program 72-1 and SOLRAD 11B, NASA's Mariner, and the Soviet Prognoz 6. While instruments have improved since the 1970s, comparing information from several sets of observations helped the researchers gain confidence in results from that early data. The team went on to look at another seven data sets including the Ulysses information from 1990 to 2001, and more recent data from IBEX, as well as four other NASA missions: STEREO (Solar Terrestrial Relations Observatory), ACE (Advanced Composition Explorer), EUVE (Extreme Ultraviolet Explorer), and the MESSENGER (MErcury Surface, Space ENvironment, GEochemistry, and Ranging) mission, currently in orbit around Mercury. The eleventh set of observations came from JAXA's (Japanese Aerospace Exploration Agency) Nuzomi mission. 16)

The team concluded it's highly likely that the direction of the interstellar wind has changed over the past 40 years. It's also highly unlikely that the direction of the interstellar helium wind has remained constant. The team estimates that the change in wind direction could be explained by turbulence in the interstellar cloud around the Sun.The results, based on data spanning four decades from 11 different spacecraft, were published in Science on Sept. 6, 2013. 17)


Figure 16: The solar system moves through a local galactic cloud at a speed of 23 km/s, creating an interstellar wind of particles, some of which can travel all the way toward Earth to provide information about our neighborhood (image credit: NASA/Adler, U. Chicago/Wesleyan)

• July 2013: Our solar system has a tail, called the heliotail, just like a comet. IBEX has for the first time mapped out the structure of this tail, which is shaped like a four-leaf clover. 18) 19) 20) 21) 22)

IBEX measures the neutral particles created by collisions at the solar system's boundaries. This technique, called energetic neutral atom imaging, relies on the fact that the paths of neutral particles are not affected by the solar magnetic field. Instead, the particles travel in a straight line from collision to IBEX. Consequently, observing where the neutral particles came from describes what is going on in these distant regions.

By combining observations from the first three years of IBEX imagery, the IBEX team showed a tail with a combination of fast and slow moving particles. There are two lobes of slower particles on the sides and faster particles above and below. This four-leaf clover shape can be attributed to the fact that the sun has been sending out fast solar wind near its poles and slower wind near its equator for the last few years. This is a common pattern in the most recent phase of the sun's 11-year activity cycle.

The clover shape does not align perfectly with the solar system, however. The entire shape is rotated slightly, indicating that as it moves further away from the sun and its magnetic influence, the charged particles begin to be nudged into a new orientation, aligning with the magnetic fields from the local galaxy.


Figure 17: NASA's IBEX payload has observed and described the solar system's tail for the first time (image credit: NASA, SwRI, Ref.20)

Legend to Figure 17: The data from NASA’s Interstellar Boundary Explorer shows what it observed looking down the solar system’s tail. The image illustrates the IBEX observation of spectral slope where red and yellow indicate lower energy particles and green and blue higher energy ones. The central portion (circle) is looking down the heliotail and shows two lower energy “lobes” on the port and starboard sides and high energy regions at higher northern and southern latitudes.

• Feb. 2013: In a new "retention model," researchers from the University of New Hampshire and SwRI (Southwest Research Institute) suggest that charged particles trapped in this region create the ribbon as they escape as neutral atoms. 23) 24) 25) 26)

The ribbon can be used to tell us how we're moving through the magnetic fields of the interstellar medium and how those magnetic fields then influence our space environment. - In particular, these strong magnetic fields appear to play a critical role in shaping our heliosphere — the huge bubble that surrounds our solar system and shields us from much of harmful galactic cosmic radiation that fills the galaxy. This may have important ramifications for the history and future of radiation in space, and its impact here on Earth, as the heliosphere changes in response to changing conditions in the interstellar medium or the "space between the stars."

According to the retention theory, the ribbon exists in a special location where neutral hydrogen atoms from the solar wind move across the local galactic magnetic field. Neutral atoms are not affected by magnetic fields, but when their electrons get stripped away, they become charged ions and begin to gyrate rapidly around magnetic field lines. That rapid rotation creates waves or vibrations in the magnetic field, and the charged ions then become trapped by the waves. This is the process that creates the ribbon.


Figure 18: A 3D diagram of the retention region shown as a "life preserver" around our heliosphere bubble along with the original IBEX ribbon image (image credit: IBEX Team)

Legend to Figure 18: The interstellar magnetic field lines are shown running from upper left to lower right around the heliosphere, and the area where the field lines "squeeze" the heliosphere corresponds to the ribbon location. The red arrow at the front shows the direction of travel of our solar system (Ref. 25).

• In May 2012, new results from IBEX reveal that the bow shock, widely accepted by researchers to precede the heliosphere as it plows through tenuous gas and dust from the galaxy, does not exist. 27) 28)

For a quarter century, researchers believed that the heliosphere moved through the interstellar medium at a speed fast enough to form a bow shock. IBEX data have shown that the heliosphere actually moves through the local interstellar cloud at about 52,000 miles per hour, roughly 7,000 miles per hour slower than previously thought — slow enough to create more of a bow "wave" than a shock.

The IBEX team combined its data with analytical calculations and modeling and simulations to determine the conditions necessary for creating a bow shock. Two independent global models — one from a group in Huntsville, Ala., and another from Moscow — correlated with the analytical findings.


Figure 19: Schematic view of the of the heliosphere model (image credit: SwRI)

• The IBEX spacecraft and its payload are operating nominally in 2012.

- NASA's IBEX has captured the best and most complete glimpse yet of what lies beyond the solar system. The new measurements give clues about how and where our solar system formed, the forces that physically shape our solar system, and the history of other stars in the Milky Way. 29)

The Earth-orbiting spacecraft observed four separate types of atoms including hydrogen, oxygen, neon and helium. These interstellar atoms are the byproducts of older stars, which spread across the galaxy and fill the vast space between stars. IBEX determined the distribution of these elements outside the solar system (i.e. outside the heliosphere), which are flowing charged and neutral particles that blow through the galaxy, or the so-called interstellar wind.

Using data from IBEX, the researchers team compared the neon-to-oxygen ratio inside vs. outside the heliosphere. In a series of six science papers in the Astrophysical Journal, they reported that for every 20 neon atoms in the galactic wind, there are 74 oxygen atoms. In our own solar system, however, for every 20 neon atoms there are 111 oxygen atoms. - That translates to more oxygen in any given slice of the solar system than in local interstellar space. 30)

• The IBEX Ribbon of energy is a major discovery of the mission requiring scientific interpretation. This was done by the IBEX science team in a publication of the Astrophysical Journal in April 2011. 31)

The finding, which overturns 40 years of theory, provides insight into the fundamental structure of the heliosphere, which in turn helps scientists understand similar structures or “astrospheres” that surround other star systems throughout the cosmos. Isolating and separating the ribbon from the IBEX maps was like pulling the drapes from our window to discover the landscape at the edge of the solar system. The IBEX maps are very rich scientifically and are critical in helping scientists understand how our space environment is controlled by the galactic medium. They provide the first images of our solar system’s boundaries, which control the access to potentially harmful galactic cosmic rays as well as all other matter from deep space. - The most energetic galactic cosmic rays penetrate even the powerful magnetic fields closest to Earth and eventually collide and interact with Earth’s atmosphere. The direct or indirect effects of these cosmic rays on the Earth system, including our biosphere, remain poorly understood and are often highly controversial.

Prior to IBEX, most scientists believed that the global boundaries of our solar system were controlled mainly by the motion of our solar system through the galaxy and the solar wind, an extremely fast flow of electrically charged matter that flows out from the Sun. The IBEX maps reveal the galactic magnetic field is also a critical part of the Sun’s interaction with the galaxy. 32)

• The IBEX spacecraft and its payload are operating nominally in 2011. IBEX passed a couple of major mission milestones in Feb./March 2011. IBEX began collecting science data on February 1, 2009, so the End of Prime Mission was set at February 1, 2011 .On March 2, 2011, the IBEX mission was reviewed by NASA and given a 2 year mission extension (until the next review in the spring of 2013). 33)

Some special events/discoveries during he prime mission were:

- Discovered the "IBEX Ribbon" and made the first observations of energetic neutral hydrogen atoms originating from our heliosphere’s interaction with the local part of the galaxy

- Made the first direct observations of interstellar neutral hydrogen and oxygen drifting into the heliosphere from interstellar space

- Detected the first energetic neutral atoms coming from the surface of our Moon

- Imaged our Earth’s magnetospheric "plasma tail"

- Imaged the interactions between the Earth’s dayside magnetosphere and the solar wind

- Detected changes in the IBEX Ribbon.

• Sept. 30, 2010: The unusual "knot" in the bright, narrow ribbon of neutral atoms emanating in from the boundary between our solar system and interstellar space appears to have "untied.". 34) 35) 36) 37) 38)

After the second complete sweep of the sky had been completed in the summer of 2010, IBEX has again delivered an unexpected result: the map has changed significantly. Overall, the intensity of ENAs has dropped 10% to 15%, and the hotspot has diminished and spread out along the ribbon.

Researchers theorize the ribbon, first revealed in maps produced by NASA's IBEX spacecraft, forms in response to interactions between interstellar space and the heliosphere, the protective bubble in which the Earth and other planets reside. Sensitive neutral atom detectors aboard IBEX produce global maps of this region every six months.

Analyses of the first map, released in the fall of 2009 (Figure 22), suggest the ribbon is somehow ordered by the direction of the local interstellar magnetic field outside the heliosphere, influencing the structure of the heliosphere more than researchers had previously believed. The knot feature seen in the northern portion of the ribbon in the first map stood apart from the rest of the ribbon as the brightest feature at higher energies.

In Sept. 2010, after a year of observations, scientists have seen vast changes, including an unusual knot in the ribbon which appears to have ‘untied.’ Changes in the ribbon — a ‘disturbance in the force,’ so to speak, along with a shrunken heliosphere, may be allowing galactic cosmic rays to leak into our solar system. - The scientists are hopeful IBEX will continue to operate through an entire solar cycle so that they can track the changes in the ribbon as solar activity is expected to increase in the next few years. This implies also that mission extensions will be granted by NASA beyond the planned two year mission. 39)

• IBEX has also made some very important new observations of the space environment much closer to home. As the solar wind streams outward from the Sun at ~1.6 million km/hr, the solar wind protons and electrons pile up along the outer boundary of Earth’s magnetosphere, called the “magnetopause”. These charged particles are shocked, heated, and slowed almost to a stop before getting diverted sideways. A few of those charged particles interact with neutral atoms in the very outer reaches of our atmosphere about 56,000 km from the surface of the Earth (Figure 20). 40) 41)

This extremely low-density region of our atmosphere, called the “exosphere”, extends beyond Earth’s protective magnetic field. The solar wind charged particles exchange electrons with our exosphere’s neutral particles, and the solar wind particles become neutral in the process. Now, they are no longer affected by Earth’s magnetic field and fly off in whatever direction they were going when they became neutral. Because some of these particles happen to be traveling in the direction of the IBEX spacecraft and its sensors, IBEX can detect them. Just like our heliosphere boundary, our magnetosphere boundary does not give off light that we can detect, so we must use particle sensors like those of IBEX to study regions like this. IBEX detected ENAs from this process in March and April 2009.



Figure 20: Model of the solar wind crashing into the magnetopause of Earth (image credit: SwRI)

• In January 2010, the IBEX researchers presented an explanation of the giant ribbon. The ribbon is a reflection -- it is where solar wind particles heading out into interstellar space are reflected back into the solar system by a galactic magnetic field. 42) 43)


Figure 21: A comparison of the IBEX ENA observations (left) with a 3D magnetic reflection model (image credit: NASA)

• In Oct. 2009, the IBEX spacecraft had made the first all-sky maps of the heliosphere and the results have taken researchers by surprise. The maps are bisected by a bright, winding ribbon of unknown origin (Figure 22). The sky map was produced with data that two detectors on the spacecraft collected during six months of observations. The detectors measured and counted particles scientists refer to as ENAs (Energetic Neutral Atoms). 44) 45) 46)

Although the ribbon looks bright in the IBEX map, it does not glow in any conventional sense. The ribbon is not a source of light, but rather a source of particles--energetic neutral atoms or ENAs. IBEX's sensors can detect these particles, which are produced in the outer heliosphere where the solar wind begins to slow down and mix with interstellar matter from outside the solar system.

The IBEX sky maps also put observations from NASA's Voyager spacecraft into context. The twin Voyager spacecraft, launched in 1977, traveled to the outer solar system to explore Jupiter, Saturn, Uranus and Neptune. In 2007, Voyager 2 (V2) followed Voyager 1 (V1) into the interstellar boundary. Both spacecraft are now in the midst of this region where the energetic neutral atoms originate. However, the IBEX results show a ribbon of bright emissions undetected by the two Voyagers.


Figure 22: IBEX's all-sky map of energetic neutral atom emission reveals a bright filament of unknown origin (image credit: NASA, SwRI)

• In June 2009, the IBEX team reported that the IBEX-Hi instrument has made the first observations of very fast hydrogen atoms coming from the moon, following decades of speculation and searching for their existence. The IBEX team estimates that only about 10% of the solar wind ions reflect off the sunward side of the moon as neutral atoms, while the remaining 90% are embedded in the lunar surface. The characteristics of the lunar surface, such as dust, craters and rocks, play a role in determining the percentage of particles that become embedded and the percentage of neutral particles, as well as their direction of travel, that scatter. 47)

• Following two months of commissioning, during which the spacecraft and sensors were tuned for optimum mission performance, the IBEX spacecraft began gathering data in early January 2009 to build the first maps of the edge of the heliosphere, the region of space influenced by the sun. 48)

• On Nov. 12, 2008, the IBEX spacecraft concluded its orbit-raising phase and is beginning instrument commissioning in preparation to start science observations. 49)



Sensor complement: (IBEX-Lo, IBEX-Hi)

The IBEX payload consists of two ENA sensors and a CEU (Combined Electronics Unit). The CEU serves as the single electrical interface between the payload and the SCB. This system architecture was chosen early in the project primarily to minimize overall system mass as well as to simplify the interface between the payload and spacecraft. The CEU is comprised of 2 circuit boards,the digital board and the HVPS (High-Voltage Power Supply) board) and the mechanical chassis (Ref. 5).

The digital board accepts, parses and routes commands from the spacecraft to the two sensors and serves as the SSR (Solid State Recorder) where spacecraft and science data is stored and played back for downlink. The digital board creates and distributes custom low voltage for the sensors and gathers housekeeping telemetry from the sensors and the high-voltage board in the CEU. The digital board is responsible for sweeping high-voltage supplies and gathering, binning, processing and storing all raw science data. The multilayer digital board is based on an 8051 core in an Actel FPGA. It includes 2 Gbit of SSR memory for science and SCB back-orbit telemetry. Solid state relays are included for low-voltage distribution. Figure 22 shows a block diagram of the CEU digital board.


Figure 23: Top side photo of the CEU digital board (image credit: IBEX consortium)

The CEU HVPS board provides 16 high-voltage outputs ranging in voltage from 300 V to 11 kV. The board includes standalone independent power supplies for each of the two sensor positive collimators and two independent bulk supplies for the remainder of the high voltages. The supplies use a resonant flyback topology running at approximately 100 kHz. High-voltage pigtail cables are connected directly to and strain-relieved to the HVPS. No HV connectors are used anywhere on the payload. Custom lug connections are used at the sensor end of the high-voltage cables. The CEU includes a “V/16” mode that limits the output of the high-voltage supplies, when the payload safing plug is installed, to a level safe for turn on at ambient conditions. Figure 24 shows a block diagram of the HVPS board.


Figure 24: Block diagram of the HVPS (image credit: IBEX consortium, Ref. 5)


ENA sensors:

Two narrow angle image sensors (IBEX-Hi and IBEX-Lo) are positioned perpendicular to the spin axis (Figure 12). The objective of these special imagers is to detect energetic neutral atoms (instead of photons of light) to create maps from the solar system’s outer edge, enabling scientists to map the boundary between our Solar System and interstellar space.

The IBEX payload is very simple and comprises only three components: two very large, high sensitivity sensors and a Combined Electronics Unit (CEU). The sensors measure ENAs from ~10 eV to 2 keV (IBEX-Lo) and from ~300 eV to 6 keV (IBEX-Hi). 50) 51) 52)

• The CEU, developed at SwRI, contains all but one of the high voltage power supplies (the last is integral to IBEX-Lo), support electronics for both sensors, and the digital data processing unit for the entire payload. The CEU also includes data storage for the entire IBEX spacecraft.

• IBEX-Lo has an energy range of 0.01-2 keV. The science team consists of the following institutions: LMATC (Lockheed Martin Advanced Technology Center, Lead), UNH (University of New Hampshire), NASA/GSFC, JHU/APL, UBern (University of Bern, Switzerland).

• IBEX-Hi has an energy range of 0.3-6 keV. The science team consists of: LANL (Los Alamos National Laboratory, Lead), UNH, and SwRI.


Figure 25: Illustration of the IBEX payload with IBEX-Lo (left) and IBEX-Hi (right), image credit: SwRI

Figure 26 shows the block diagram of the science payload. The CEU provides power and data handling for the sensors and is the payload interface to the SCB (Spacecraft Bus). The CEU provides LV to both sensors, 8 HV lines to IBEX-Hi and 6 to IBEX-Lo. The sensors take science measurements and provide that data to the CEU. The CEU stores that data along with S/C telemetry until the once per orbit downlink time.

CEU (Combined Electronics Unit) has a size of 32 cm x 16.5 cm x 9.5 cm. The primary functions of CEU are:

• Accept +5V, ±14V, and ±15 V from SCB

• Distribute LV (Low Voltage) power to both sensors

• Provide 8 HV (High Voltage) outputs to IBEX-Hi

• Provide 7 HV outputs to IBEX-Lo

• Store all telemetry (science, housekeeping, and S/C).


Figure 26: Block diagram of the IBEX payload (image credit: SwRI)



Figure 27: EMI (Electromagnetic Interference) fixating of the IBEX payload (image credit: SwRI)


Figure 28: Photo of the IBEX payload on its test fixture (image credit: SwRI, NASA)


Figure 29: Photo of the IBEX-Lo sensor (image credit: SwRI, NASA)


Figure 30: Photo of the IBEX-Hi sensor (image credit: SwRI, NASA)

The principle of operation of the two sensors is the same. ENAs (Energetic Neutral Atoms) enter the sensors through collimators that suppress the external electrons below ~600 eV and the external ions below 10 keV. The collimators also set the ENA FOVs and are optimized for measurements of heliospheric ENAs from the inner heliosheath with 7° x 7° FWHM resolution. In addition, a fourth of the aperture area for IBEX-Lo has four times the angular resolution (3.5º x 3.5º FWHM), which is included to precisely measure the cold interstellar neutral oxygen drifting into the heliosphere (Ref. 50).

Just as charge exchange produces ENAs in the inner heliosheath, the two IBEX sensors use charge exchange to convert these ENAs back into ions so that they can be analyzed and detected. In the case of IBEX-Lo, this conversion produces negative ions during reflection from an ultra-smooth diamond-like carbon (DLC) surface. For IBEX-Hi charge exchange to produce positive ions occurs during transmission of the ENAs through ultra-thin (~10 nm) carbon foils. Following their respective conversion subsystems, both sensors have electrostatic analyzers to select energy per charge passbands and triple coincidence detector sections; IBEX-Lo also includes time-of-flight analysis of the detected particles.


Figure 31: Cross section through the IBEX-Lo entrance subsystem (image credit: SwRI)

Legend to Figure 31: Electrons below ~600 eV and ions below 10 keV/q are reflected and cannot enter the IBEX sensors. The integral sun shade ensures no solar illumination while the collimators set the angular FOVs for the observations.

Since IBEX is a sun-pointed spinner, it naturally views all directions perpendicular to the sun-spacecraft line each and every spin. Such observations fill in the two crescents drawn in the all sky image (upper left inset of Figure 32). In addition, IBEX is being repointed once each spacecraft orbit so that it maintains its sun-pointed orientation, as the Earth orbits the sun. This repointing rotates the plane of ENA observations, effectively filling in contiguous crescents in the sky. Each six months the rotation of the spin axis goes through 180º, producing a nearly full-sky map. These revolutionary, energy-resolved ENA images and per pixel energy spectra will disclose the global heliospheric interaction for the first time (Ref. 50).


Figure 32: Simulated image of the heliosphere (background image) including from the inside out, solar wind (inner blue and green), termination shock (TS), inner heliosheath and heliotail (orange to yellow and outer green), heliopause (HP), interstellar medium (outer blue) and bow shock (BS), image credit: SwRI

Legend to Figure 32: The lower right inset shows a schematic diagram of charge exchange while the upper left inset shows an all sky map and how individual pixels from the main image map onto the sky map.



Ground segment:

IBEX ground systems consist of the MOC (Mission Operations Center) at Orbital's Dulles, VA facility, Universal space Network (USN) ground stations and the ISOC (IBEX Science Operations Center) located at SwRI in San Antonio, TX. In addition, the TDRSS network is used during early launch operations to monitor the SRM burn in real time. The ISOC is responsible for evaluating mission data, monitoring payload performance, and delivering IBEX data products. It plans the operations and generates the detailed science and engineering schedule. ISOC processes all mission science and calibration data, distributes science data to the IBEX team, makes data continuously available to the public through a web interface to an Oracle database and prepares and releases the IBEX science archive to the NSSDC (National Space Science Data Center).


Figure 33: Overview of the ground and space network (image credit: SwRI)


Figure 34: Overview of the ISOC elements within the IBEX ground segment (image credit: SwRI)


Figure 35: Overview of the MOC elements within the IBEX ground segment (image credit: OSC)

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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.