The Ultraviolet Micromirror Imaging Spectrograph (UMIS) will be the first UV integral field spectrograph (IFS) to use micro-electro-mechanical systems (MEMS) micromirrors, specifically in the form of two-axis analog micromirror arrays (AMAs). This novel application of AMAs will increase both the flexibility and spectral multiplexing efficiency of UMIS relative to currently available instruments. AMAs are already a widely used technology in telecommunications; this study investigated and proved their suitability for high performance scientific instrumentation. Suitability was determined through evaluation of the individual micromirror component on a custom optical bench set up. The following metrics were evaluated: temporal stability, thermal drift and stability, large-scale linear response and pointing precision. The tests demonstrated that under conditions of 20C - 40C the micromirror's temporal stability, thermal stability, large-scale linear response and pointing precision were stable within the required range. The micromirror's performance, as measured in this experiment, meets the requirements specified in UMIS design and indicates feasibility for future flight instruments. We present the experiment test setup and results in the context of the development of the UMIS testbed instrument.
Improving the spectral multiplexing efficiency of ultraviolet (UV) instruments is one of the essential technology developments for future large missions. This is particularly hard in the far UV (FUV), where high reflectivity coatings and high material transmission are difficult to achieve. We present here the concept and design of the Ultraviolet Micromirror Imaging Spectrograph (UMIS), which utilizes Analog Micromirror Arrays (AMAs) as the spectral multiplexing element. These Micro-Opto-Electro-Mechanical-Systems (MOEMS)-based mirrors can be dynamically programmed to probe multiple points of interest across a wide field of view without spectral confusion limitations. We have assembled a benchtop version of UMIS, to characterize the individual arrays and to evaluate the performance of the overall system in optical and FUV wavelengths. The instrument consists of a 75 cm off-axis telescope, with two AMAs placed on either side of the focal plane, and an optical spectrograph with a resolution of about R=1000. The individual mirror orientations can be adjusted by varying their bias voltages, which are controlled using custom electronic boards designed and fabricated by Ball Aerospace and LASP. The same testbed will be reconfigured with an FUV grating and detector, to calibrate the instrument in a vacuum environment and qualify the AMAs for future flight missions.
The Colorado Ultraviolet Transit Experiment (CUTE) is a 6U CubeSat designed to explore the upper atmospheres of short-period exoplanets via near-ultraviolet (2500 – 3300 Å) transmission spectroscopy, with an anticipated launch date of September 2021. The 4U science instrument comprises a Cassegrain telescope with a 20 × 8 cm primary mirror, a spectrograph, and a thermal-electrically cooled CCD detector. The spacecraft structure and a 1.5U XB1 avionics module are provided by Blue Canyon Technologies. CUTE’s novel and compact instrument design presents unique challenges to conducting component-level testing, alignment, instrument and spacecraft integration, calibration, and end-to-end performance testing. We provide a description of several custom test setups and procedures designed to characterize the spectrograph performance and its expected science return. We also outline the remainder of our integration and testing plan.
SING is a near ultraviolet (NUV) spectrograph with a size close to 6U CubeSat form-factor. The spectrograph operates in the wavelength range from 1800 Å to 3000 Å, with a spectral resolution of 2 Å at the central wavelength. The spectrograph is intended to operate in low Earth orbit (LEO), with the primary goal to generate spectral maps of the regions of the sky covered within the field of view (FOV) of the instrument, constrained by the orbital inclination of the spacecraft. The payload consists of the telescope in Cassegrain configuration focusing the light on the slit, the corrector lens, the concave grating, the detector, and other required electronics components. As the event rate in the UV is low, the spectrograph employs a photon-counting detector because of its low noise performance. The payload uses FPGA as the main system controller to handle the detector readout, data compression and storage, health monitoring, and telemetry. In this work, we present the optical design and its analysis, along with a brief description of the architecture of electronic subsystems of the payload.
Spatial Heterodyne Spectroscopy (SHS) is a relatively novel interferometric technique similar to Fourier transform spectroscopy and shares design similarities with a Michelson Interferometer. An Imaging detector is used at the output of a SHS to record the spatially heterodyned interference pattern. The spectrum of the source is obtained by Fourier transforming the recorded interferogram. The merits of the SHS -its design, including the lack of moving parts, compactness, high throughput, high SNR and instantaneous spectral measurements - makes it suitable for space as well as ground observatories. The small bandwidth limitation of the SHS can be overcome by building it in tunable configuration (Tunable Spatial Heterodyne Spectrometer(TSHS)). In this paper, we describe the wavelength calibration of the tunable SHS using a Halogen lamp and Andor monochromator setup. We found a relation between the fringe frequency and the wavelength.
The Pesit/IIA Observatory for the Night Sky(PIONS) is a near UV imaging telescope to be flown on a small satellite. The instrument is a 150mm RC telescope that covers a wavelength range of 180-280 nm. We are using an intensified CMOS detector with a solar blind photocathode, to be operated in photon counting mode. The telescope has a wide field of view of 3 degrees and an angular resolution of 13”. We plan to point the telescope to scan the sky continuously along the sun pointing axis to look for variable UV sources such as flare stars, AGNs, and other transient events. We can detect objects as faint as 21 magnitude and perform their photometric analysis. Since the aperture and the effective area of the telescope are comparatively small, it can be pointed to relatively brighter parts of the UV sky which were not accessible to larger mission due to detector limitations.
The Lunar Ultraviolet Cosmic Imager (LUCI) is an innovative all-spherical mirrors telescope, proposed to fly as a scientific UV imaging payload on a lunar mission in collaboration with Indian Aerospace Company-TeamIndus, Axiom Research Labs Pvt. Ltd. Observations from the Moon provide a unique opportunity to observe the sky from a stable platform far above the Earths atmosphere. LUCI will observe at a fixed elevation angle and will detect stars in the near ultraviolet (200-320 nm) to a limiting magnitude of 12 AB, with a field of view of around 0.5 degrees. The primary science goal is to search for transient sources and flag them for further study. The instrument has been assembled in the class 1000 clean room at the M.G.K Menon Laboratory for Space Sciences. Here we will describe the optomechanical assembly procedures we have carried out during the optical alignment and integration of the payload. Opto-mechanical alignment of the instrument was carried out by using alignment telescope cum autocollimator (for coarse alignment) and ZYGO interferometer (fine alignment). We will also discuss the ground calibration tests performed on the assembled telescope. The results from the ground calibration activities will help in establishing the full calibration matrix of the instrument once operational.
Spatial heterodyne spectroscopy (SHS) is an interferometric technique similar to the Fourier transform spectroscopy with heritage from the Michelson interferometer. An imaging detector is used at the output of an SHS to record the spatially heterodyned interference pattern. The spectrum of the source is obtained by Fourier transforming the recorded interferogram. The merits of the SHS—its design, including the absence of moving parts, compactness, high throughput, high SNR, and instantaneous spectral measurements—make it suitable for space as well as for ground observatories. The small bandwidth limitation of the SHS can be overcome by building it in tunable configuration [tunable spatial heterodyne spectrometer (TSHS)]. We describe the design, development, and simulation of a TSHS in refractive configuration suitable for optical wavelength regime. Here we use a beam splitter to split the incoming light compared with all-reflective SHS where a reflective grating does the beam splitting. Hence, the alignment of this instrument is simple compared with all-reflective SHS where a fold mirror and a roof mirror are used to combine the beam. This instrument is intended to study faint diffuse extended celestial objects with a resolving power above 20,000 and can cover a wavelength range from 350 to 700 nm by tuning. It is compact and rugged compared with other instruments having similar configurations.
We describe the development and implementation of a light-weight, fully autonomous 2-axis pointing and stabilization system designed for balloon-borne astronomical payloads. The system is developed using off-the-shelf components such as Arduino Uno controller, HMC 5883L magnetometer, MPU-9150 inertial measurement unit, and iWave GPS receiver unit. It is a compact and rugged system which can also be used to take images/video in a moving vehicle or in real photography. The system performance is evaluated from the ground, as well as in conditions simulated to imitate the actual flight by using a tethered launch.
The ultraviolet (UV) window has been largely unexplored through balloons for astronomy. We discuss here the development of a compact near-UV spectrograph with fiber optics input for balloon flights. It is a modified Czerny-Turner system built using off-the-shelf components. The system is portable and scalable to different telescopes. The use of reflecting optics reduces the transmission loss in the UV. It employs an image-intensified CMOS sensor, operating in photon counting mode, as the detector of choice. A lightweight pointing system developed for stable pointing to observe astronomical sources is also discussed, together with the methods to improve its accuracy, e.g. using the in-house build star sensor and others. Our primary scientific objectives include the observation of bright Solar System objects such as visible to eye comets, Moon and planets. Studies of planets can give us valuable information about the planetary aurorae, helping to model and compare atmospheres of other planets and the Earth. The other major objective is to look at the diffuse UV atmospheric emission features (airglow lines), and at column densities of trace gases. This UV window includes several lines important to atmospheric chemistry, e.g. SO2, O3, HCHO, BrO. The spectrograph enables simultaneous measurement of various trace gases, as well as provides better accuracy at higher altitudes compared to electromechanical trace gas measurement sondes. These lines contaminate most astronomical observations but are poorly characterized. Other objectives may include sprites in the atmosphere and meteor ashes from high altitude burn-outs. Our recent experiments and observations with high-altitude balloons are discussed.
We describe the characterization and removal of noises present in the Inertial Measurement Unit (IMU) MPU- 6050, which was initially used in an attitude sensor, and later used in the development of a pointing system for small balloon-borne astronomical payloads. We found that the performance of the IMU degraded with time because of the accumulation of different errors. Using Allan variance analysis method, we identified the different components of noise present in the IMU, and verified the results by the power spectral density analysis (PSD). We tried to remove the high-frequency noise using smooth filters such as moving average filter and then Savitzky Golay (SG) filter. Even though we managed to filter some high-frequency noise, these filters performance wasn't satisfactory for our application. We found the distribution of the random noise present in IMU using probability density analysis and identified that the noise in our IMU was white Gaussian in nature. Hence, we used a Kalman filter to remove the noise and which gave us good performance real time.
We are developing a compact UV Imager using light weight components, that can be own on a small CubeSat or a balloon platform. The system has a lens-based optics that can provide an aberration-free image over a wide field of view. The backend instrument is a photon counting detector with off-the-shelf MCP, CMOS sensor and electronics. We are using a Z-stack MCP with a compact high voltage power supply and a phosphor screen anode, which is read out by a CMOS sensor and the associated electronics. The instrument can be used to observe solar system objects and detect bright transients from the upper atmosphere with the help of CubeSats or high altitude balloons. We have designed the imager to be capable of working in direct frame transfer mode as well in the photon-counting mode for single photon event detection. The identification and centroiding of each photon event are done using an FPGA-based data acquisition and real-time processing system.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.