Instrument
Contents
Mission and Spacecraft
Payload & Instrument
Performance & Simulations
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Mission and Spacecraft
ARRAKIHS will operate in a Low Earth Orbit (LEO) at an altitude of 700 km, following a dawn-dusk Sun-synchronous orbit. This orbit was selected because it provides stable illumination conditions, minimizes thermal variations, and satisfies debris mitigation and radiation requirements.
The mission is scheduled for launch in 2030, with Vega-C as the baseline launcher from Kourou. Alternative compatibility is maintained with future European launchers such as Isar Spectrum and RFA One.
Key mission parameters are summarized in next table:

The operational timeline includes:
- Launch and Early Operations Phase (LEOP)
- Initial Orbit Commissioning (IOC)
- 1-month Science Performance Verification and Demonstration (SPVD)
- 3 years of nominal science operations
- Potential extension of at least 2 additional years
At mission end, the spacecraft will be de-orbited in compliance with ESA debris mitigation regulations.
Payload & Instrument
The payload consists of a single instrument developed by the ARRAKIHS Mission Consortium (AMC), led by Spain and involving more than 18 organizations from ESA member states.
The instrument simultaneously observes targets in four spectral channels:
- VIS1 (Visible): 350 nm (λmean)
- VIS2 (Visible): 622 nm (λmean)
- NIR1 (Near Infrared): 1056 nm (λmean)
- NIR2 (Near Infrared): 1367 nm (λmean)

covering wavelengths from 280 nm to 1600 nm.
A major feature is that the NIR channels also function as a Fine Guidance Sensor (FGS), helping the spacecraft achieve a pointing stability of 1 arcsecond during a 10-minute exposure.
- Visible detectors: The ARRAKIHS VIS detector is the Teledyne-e2v CIS 304-33, a digital CMOS image sensor of
4500px × 4340px format with a pixel size of 10μm. The near UV VIS 1 has a QE greater that 40% from 280nm, and the broadband VIS2 has a peak QE of 80% at 660nm. - NIR detectors: The ARRAKIHS NIR detector system (detectors and front-end electronics) relies on the flight-proven Teledyne HAWAII-2RG (H2RG) Sensor Chip System (SCS). The Sensor is composed of Mercury-Cadmium-Telluride (MCT) alloy hybridised to a CMOS multiplexer with 2048 x 2048 pixels format with a 18μm pixel size.
The payload is built around:
- Two binocular telescope assemblies
- Four telescopes in total
- Maksutov-Cassegrain optical design
- 150 mm aperture
- f/10 focal ratio
- 1.3° field of view per channel
The design is derived from the flight-proven iSIM-170 payload developed by Satlantis.
The optical system uses four Maksutov-Cassegrain telescopes arranged into two binoculars. One binocular is dedicated to visible wavelengths, while the other is dedicated to near-infrared observations. Folding mirrors redirect incoming light and reduce instrument volume while improving thermal management.
Because ARRAKIHS observes extremely faint structures, straylight suppression is critical. For this reason, each optical channel includes a compact but highly effective internal baffling system designed to eliminate direct and indirect light paths originating from outside the nominal FOV, an also an external Straylight Baffle Assembly mounted on the Telescope and Camera Module structure.
Performance & Simulations
The mission’s sensitivity was evaluated using a comprehensive noise budget that incorporates both astronomical and instrumental noise sources. These include zodiacal light, Galactic foreground emission, cosmological infrared background, Earthshine, straylight from stars, detector dark current, readout noise, flat-field uncertainties, and cosmic-ray impacts. The results show that ARRAKIHS can reach surface-brightness limits of approximately 30.3–30.6 mag arcsec⁻² in the visible channels and around 29.4–29.7 mag arcsec⁻² in the near-infrared channels, placing the mission among the most sensitive low-surface-brightness observatories ever designed.
Related to the dectector dark current, simulations demonstrated that dark current becomes the dominant noise source when it exceeds roughly 10⁻³ electrons per second per pixel. However, recent detector characterization results indicate that the visible detectors are likely to operate close to this threshold even at end-of-life conditions. Furthermore, the thermal design of the payload allows operation at temperatures lower than the baseline value of 200 K. Lowering the detector temperature to 180 K could reduce the dark current by approximately a factor of sixteen, providing substantial performance margin and supporting the expectation that the system will remain close to a background-limited regime throughout the mission.
Image-quality performance was assessed through detailed optical simulations that included diffraction effects, wavefront errors, thermo-elastic deformations, pointing jitter, detector pixelization, and modulation transfer function analysis. These simulations generated realistic point-spread functions and evaluated key image-quality metrics such as EE50, EE80, and FWHM. The results demonstrate that all four channels satisfy the mission requirements and provide the image quality necessary to resolve faint extended structures while maintaining accurate photometric measurements.
To validate mission performance under realistic observing conditions, the consortium developed the ATREIDS simulation framework. This end-to-end simulator reproduces the complete observational process, generating synthetic images that closely mimic those expected from the spacecraft in orbit. The simulations include target galaxies, background galaxies, Milky Way stars, Galactic dust extinction, Galactic cirrus, zodiacal light, Earthshine, cosmic rays, satellite trails, detector noise, straylight, and realistic point-spread functions. ATREIDS also reproduces the mission observing strategy of 900 individual 10-minute exposures distributed over multiple offsets and dithers, allowing realistic testing of the scientific data-processing pipeline.
The simulated sky background is constructed using state-of-the-art astronomical datasets and models. Background galaxies are generated from Euclid Flagship simulations, stellar foregrounds are based on Gaia, SDSS, 2MASS, and the Besançon Galaxy Model, while Galactic cirrus structures are represented using both observational data and synthetic interstellar-medium models. Zodiacal light is modeled dynamically according to the position of the spacecraft and the time of year, reflecting the fact that observations of a single galaxy may extend over several months and therefore experience changing background conditions
Overall, the mission-performance analysis demonstrates that ARRAKIHS possesses the sensitivity, image quality, thermal stability, and straylight control necessary to achieve its scientific objectives. The combination of advanced detector technology, optimized optical performance, detailed calibration strategies, and highly realistic simulations provides strong evidence that the mission will be capable of detecting and characterizing extremely faint stellar halos and tidal structures around nearby galaxies at unprecedented levels of surface brightness.
