Figure 2 - uploaded by James Garnett
Content may be subject to copyright.
SIDECAR ASIC packaged in a PGA package (top left) and an LGA package (bottom left) with 337 pins each, and the development board with the SIDECAR ASIC socket (right).
Source publication
The SIDECAR ASIC is a fully integrated FPA controller system-on-a-chip. Compared to conventional control electronics, it requires significantly less power, less space and less weight. The SIDECAR ASIC, which can operate at ambient and cryogenic temperatures, is currently being space-qualified for integration in the science instruments of the James...
Contexts in source publication
Context 1
... package size is about 36mm x 36mm. Figure 2 shows a photograph of the SIDECAR ASIC packaged in the micro-PGA and the LGA package. The LGA package is currently used and recommended for all ground-based astronomy applications and is included as part of the SIDECAR development kit. ...
Context 2
... LGA package is currently used and recommended for all ground-based astronomy applications and is included as part of the SIDECAR development kit. The development board comprising one SIDECAR ASIC (socket in the center of the board) and a number of test points and LEDs can be seen in the right half of Figure 2. ...
Similar publications
Citations
... The NIRISS detector is controlled by an Application-Specific Integrated Circuit (ASIC) called SIDECAR (Loose et al. 2006) which provides biases, clocking and output digitization. The SIDECAR bias voltages affect the read noise, dark current and dynamic range of the detector, thus best performance is obtained when the detector and SIDECAR are optimized together. ...
The Near-Infrared Imager and Slitless Spectrograph (NIRISS) is the science module of the Canadian-built Fine Guidance Sensor onboard the James Webb Space Telescope (JWST). NIRISS has four observing modes: (1) broadband imaging featuring seven of the eight NIRCam broadband filters, (2) wide-field slitless spectroscopy at a resolving power of ∼150 between 0.8 and 2.2 μ m, (3) single-object cross-dispersed slitless spectroscopy (SOSS) enabling simultaneous wavelength coverage between 0.6 and 2.8 μ m at R ∼ 700, a mode optimized for exoplanet spectroscopy of relatively bright ( J < 6.3) stars and (4) aperture masking interferometry (AMI) between 2.8 and 4.8 μ m enabling high-contrast (∼10 ⁻³ − 10 ⁻⁴ ) imaging at angular separations between 70 and 400 mas for relatively bright ( M < 8) sources. This paper presents an overview of the NIRISS instrument, its design, its scientific capabilities, and a summary of in-flight performance. NIRISS shows significantly better response shortward of ∼2.5 μ m resulting in 10%–40% sensitivity improvement for broadband and low-resolution spectroscopy compared to pre-flight predictions. Two time-series observations performed during instrument commissioning in the SOSS mode yield very stable spectro-photometry performance within ∼10% of the expected noise. The first space-based companion detection of the tight binary star AB Dor AC through AMI was demonstrated.
... The NIRISS detector is controlled by an Application-Specific Integrated Circuit (ASIC) called SIDECAR (Loose et al. 2006) which provides biases, clocking and output digitization. The SIDECAR bias voltages affect the read noise, dark current and dynamic range of the detector, thus best performance is obtained when the detector and SIDECAR are optimized together. ...
The Near-Infrared Imager and Slitless Spectrograph (NIRISS) is the science module of the Canadian-built Fine Guidance Sensor (FGS) onboard the James Webb Space Telescope (JWST). NIRISS has four observing modes: 1) broadband imaging featuring seven of the eight NIRCam broadband filters, 2) wide-field slitless spectroscopy (WFSS) at a resolving power of $\sim$150 between 0.8 and 2.2 $\mu$m, 3) single-object cross-dispersed slitless spectroscopy (SOSS) enabling simultaneous wavelength coverage between 0.6 and 2.8 $\mu$m at R$\sim$700, a mode optimized for exoplanet spectroscopy of relatively bright ($J<6.3$) stars and 4) aperture masking interferometry (AMI) between 2.8 and 4.8 $\mu$m enabling high-contrast ($\sim10^{-3}-10^{-4}$) imaging at angular separations between 70 and 400 milliarcsec for relatively bright ($M<8$) sources. This paper presents an overview of the NIRISS instrument, its design, its scientific capabilities, and a summary of in-flight performance. NIRISS shows significantly better response shortward of $\sim2.5\,\mu$m resulting in 10-40% sensitivity improvement for broadband and low-resolution spectroscopy compared to pre-flight predictions. Two time-series observations performed during instrument commissioning in the SOSS mode yield very stable spectro-photometry performance within $\sim$10% of the expected noise. The first space-based companion detection of the tight binary star AB Dor AC through AMI was demonstrated.
... The detectors are cooled with margin to their 35-K requirement to minimize dark current, particularly in the long wavelength channel. An array of Teledyne SIDECAR ASIC-based detector controllers (Loose et al., 2006) is located near the H2RG detectors to minimize cable length; it has its own small radiator outside the telescope housing cooled to 140 K; there is substantial cooling margin as the radiator can be enlarged. Instrument control electronics are mounted in a compact PCI chassis below the radiators and operated close to room temperature. ...
The Cosmic Dawn Intensity Mapper (CDIM) will transform our understanding of the era of reionization when the Universe formed the first stars and galaxies, and UV photons ionized the neutral medium. CDIM goes beyond the capabilities of upcoming facilities by carrying out wide area spectro-imaging surveys, providing redshifts of galaxies and quasars during reionization as well as spectral lines that carry crucial information on their physical properties. CDIM will make use of unprecedented sensitivity to surface brightness to measure the intensity fluctuations of reionization on large-scales to provide a valuable and complementary dataset to 21-cm experiments. The baseline mission concept is an 83-cm infrared telescope equipped with a focal plane of 24 \times 20482 detectors capable of R = 300 spectro-imaging observations over the wavelength range of 0.75 to 7.5 {\mu}m using Linear Variable Filters (LVFs). CDIM provides a large field of view of 7.8 deg2 allowing efficient wide area surveys, and instead of moving instrumental components, spectroscopic mapping is obtained through a shift-and-stare strategy through spacecraft operations. CDIM design and capabilities focus on the needs of detecting faint galaxies and quasars during reionization and intensity fluctuation measurements of key spectral lines, including Lyman-{\alpha} and H{\alpha} radiation from the first stars and galaxies. The design is low risk, carries significant science and engineering margins, and makes use of technologies with high technical readiness level for space observations.
... The detectors are cooled with margin to their 35-K requirement to minimize dark current, particularly in the long wavelength channel. An array of Teledyne SIDECAR ASIC-based detector controllers (Loose et al., 2006) is located near the H2RG detectors to minimize cable length; it has its own small radiator outside the telescope housing cooled to 140 K; there is substantial cooling margin as the radiator can be enlarged. Instrument control electronics are mounted in a compact PCI chassis below the radiators and operated close to room temperature. ...
The Cosmic Dawn Intensity Mapper (CDIM) will transform our understanding of the era of reionization when the Universe formed the first stars and galaxies, and UV photons ionized the neutral medium. CDIM goes beyond the capabilities of upcoming facilities by carrying out wide area spectro-imaging surveys, providing redshifts of galaxies and quasars during reionization as well as spectral lines that carry crucial information on their physical properties. CDIM will make use of unprecedented sensitivity to surface brightness to measure the intensity fluctuations of reionization on large-scales to provide a valuable and complementary dataset to 21-cm experiments. The baseline mission concept is an 83-cm infrared telescope equipped with a focal plane of 24 x 2048^2 detectors capable of R = 300 spectro-imaging observations over the wavelength range of 0.75 to 7.5 µm using Linear Variable Filters (LVFs). CDIM provides a large field of view of 7.8 deg^2 allowing efficient wide area surveys, and instead of moving instrumental components, spectroscopic mapping is obtained through a shift-and-stare strategy through spacecraft operations. CDIM design and capabilities focus on the needs of detecting faint galaxies and quasars during reionization and intensity fluctuation measurements of key spectral lines, including Lyman-α and Hα radiation from the first stars and galaxies. The design is low risk, carries significant science and engineering margins, and makes use of technologies with high technical readiness level for space observations.
... The TIGER Focal Plane Array (FPA) is from Teledyne Imaging Sensors and utilizes the same HgCdTe detector and H2RG qualified for James Webb Space Telescope (JWST) Near Infrared Camera (NIRCam) (Rieke et al., 2005), Near Infrared Spectrometer (NIRSpec) (Rauscher et al., 2004), and Fine Guidance Sensor (FGS) (Doyon et al., 2012) instruments. TIGER also implements FPA readout electronics that have been qualified extensively for the JWST instruments (Loose et al., 2006) and are used by the Euclid Near Infrared Spectrometer and Photometer (NISP) (Maciaszek et al., 2014). ...
Titan, with its organically rich and dynamic atmosphere and geology, and Enceladus, with its active plume, both harbouring global subsurface oceans, are prime environments in which to investigate the habitability of ocean worlds and the conditions for the emergence of life. We present a space mission concept, the Explorer of Enceladus and Titan (E²T), which is dedicated to investigating the evolution and habitability of these Saturnian satellites. E²T is proposed as a medium-class mission led by ESA in collaboration with NASA in response to ESA's M5 Cosmic Vision Call. E²T proposes a focused payload that would provide in-situ composition investigations and high-resolution imaging during multiple flybys of Enceladus and Titan using a solar-electric powered spacecraft in orbit around Saturn. The E²T mission would provide high-resolution mass spectrometry of the plume currently emanating from Enceladus' south polar terrain and of Titan's changing upper atmosphere. In addition, high-resolution infrared (IR) imaging would detail Titan's geomorphology at 50–100 m resolution and the temperature of the fractures on Enceladus' south polar terrain at meter resolution. These combined measurements of both Titan and Enceladus would enable the E²T mission scenario to achieve two major scientific goals: 1) Study the origin and evolution of volatile-rich ocean worlds; and 2) Explore the habitability and potential for life in ocean worlds. E²T's two high-resolution time-of-flight mass spectrometers would enable resolution of the ambiguities in chemical analysis left by the NASA/ESA/ASI Cassini-Huygens mission regarding the identification of low-mass organic species, detect high-mass organic species for the first time, further constrain trace species such as the noble gases, and clarify the evolution of solid and volatile species. The high-resolution IR camera would reveal the geology of Titan's surface and the energy dissipated by Enceladus' fractured south polar terrain and plume in detail unattainable by the Cassini mission.
... The overall power consumption of a system composed by a H2RG detector readout by a SIDECAR ASIC by means of four 16 bit ADCs (4 channels) at a frequency of 100 kHz is measured to be less than 10 mW [17], [18]. The detectors FPAs + CFEEs overall power dissipation allocation is a function of wavelength in order to limit the total thermal load from cold module to < 75÷80 mW for the VNIR, < 25÷30 mW for the SWIR and < 15÷20 mW for the MWIR one. ...
EChO is a three-modules (VNIR, SWIR, MWIR), highly integrated spectrometer, covering the wavelength range from 0.55 μ
m to 11.0 μ
m. The baseline design includes the goal wavelength extension to 0.4 μ
m while an optional LWIR module extends the range to the goal wavelength of 16.0 μ
m. An Instrument Control Unit (ICU) is foreseen as the main electronic subsystem interfacing the spacecraft and collecting data from all the payload spectrometers modules. ICU is in charge of two main tasks: the overall payload control (Instrument Control Function) and the housekeepings and scientific data digital processing (Data Processing Function), including the lossless compression prior to store the science data to the Solid State Mass Memory of the Spacecraft. These two main tasks are accomplished thanks to the Payload On Board Software (P-OBSW) running on the ICU CPUs.
... The results show a good agreement with Teledyne's test report validating the low noise quality of the chain, power supply, JADE2 card and SIDECAR ASIC. These results are compatible with the noise study realized by Markus Loose [5] at T=37K who reported (for a same gain of 15) a median noise of 25 µV rms . ...
In the frame work of the European Space Agency's Cosmic Vision program,
the Euclid mission has the objective to map the geometry of the Dark
Universe. Galaxies and clusters of galaxies will be observed in the
visible and near-infrared wavelengths by an imaging and spectroscopic
channel. For the Near Infrared Spectrometer instrument (NISP), the
state-of-the-art HAWAII-2RG detectors will be used, associated with the
SIDECAR ASIC readout electronic which will perform the image frame
acquisitions. To characterize and validate the performance of these
detectors, a test bench has been designed, tested and validated. This
publication will present preliminary measurements on dark current, read
noise, conversion gain and power consumption, In summary, the following
results have been obtained in our system: dark current of 0.014
e-/s/pixel at 82K; readout noise of 23 e- for a
single CDS pair and 5.4e- for a Fowler(32); a total electric
power consumption of 203 mW in LVDS (excluding I/O power) mode. The
SIDECAR ASIC has also been characterized separately at room temperature.
Two references voltages, VPreAmpRef1 and VrefMain, used to adjust the
offset of the pre-amp DAC has been studied. The reset voltage,
Vreset, was measured to have a root mean square stability of
22μV over 15 minutes and a root mean square stability value of
24μV over a 15 hours measurement period. An offset between set value
and measured value of around 60mV for low set voltages has been noticed.
The behavior of VPreAmpRef1 and VrefMain with a adjustable external
input voltage has been conducted in order to tune these two biases to
cover the desired input range with the best linearity.
... Over the course of the last few years, the SIDECAR ASIC has been thoroughly tested under different conditions. Overall cryogenic and room temperature performance has been reported in Loose et al. [4] and Wong et al. [5]), while measurement results specific to JWST can be found in Loose et al. [12]. The essential noise, linearity and power numbers obtained from these measurements are listed in table 4. The SIDECAR ASIC has achieved NASA Technology Readiness Level 6 (TRL6) status by January of 2007. ...
... Performance results of infrared HgCdTe FPAs can be found in Finger et al. [6] and Waterson et al. [7], visible HyViSI detector results are reported in Bai et al. [8]. Other interesting data on guide operation and space based applications are discussed in Baril et al. [9], Riopel et al. [10], Rauscher et al. [11], and Loose et al. [12]. Most of the presented results have been measured using conventional control electronics. ...
The HAWAII-2RG based focal plane arrays represent one the most advanced imaging sensor technologies for near-infrared and visible astronomy. Since its introduction a few years ago, the HAWAII-2RG has been selected for a large number of space and ground-based instruments, including the James Webb Space Telescope. In addition, the SIDECAR ASIC, a fully integrated FPA controller system-on-a-chip, has been matured and is now being implemented in many of the next generation instruments. As a result of the SIDECAR ASIC, the detector system becomes a fully digital unit that is superior to the conventional discrete focal plane electronics with respect to power consumption, mass, volume and noise immunity. This paper includes an introductory description of the HAWAII-2RG and the SIDECAR ASIC, and presents the latest test results. It also discusses the latest generation of astronomy FPAs: the HAWAII-4RG. This new multiplexer contains all of the HAWAII-2RG features, but provides 4 times as many pixels at a pixel pitch of 10µm. Preliminary HAWAII-4RG test data is presented.
Hyperspectral Satellites and System Design is the first book on this subject. It provides a systematic analysis and detailed design of the entire development process of hyperspectral satellites. Derived from the author’s 25-year firsthand experience as a technical lead of space missions at the Canadian Space Agency, the book offers engineers, scientists and decision-makers detailed knowledge, know-how and guidelines on hyperspectral satellite system design, trade-offs, performance modeling and simulation, optimization from component to system level, subsystem design and implementation strategies. This information will help reduce the risk, shorten the development period and lower the cost of hyperspectral satellite missions.
Hyperspectral Satellites and System Design is a must-have reference for professionals in developing hyperspectral satellites and in data applications. It is also an excellent introductory book for early practitioners and students who want to learn more about hyperspectral satellites and their applications.
