KEYWORDS: Mirrors, Image segmentation, Telescopes, Space telescopes, Silicon carbide, James Webb Space Telescope, Polishing, Signal to noise ratio, Observatories, Manufacturing
High resolution imaging from space requires very large apertures, such as NASA’s current mission the James Webb Space Telescope (JWST) which uses a deployable 6.5m segmented primary. Future missions requiring even larger apertures (>>10m) will present a great challenge relative to the size, weight and power constraints of launch vehicles as well as the cost and schedule required to fabricate the full aperture. Alternatively, a highly obscured annular primary can be considered. For example, a 93.3% obscured 30m aperture having the same total mirror area (91m2) as a 10.7m unobscured telescope, can achieve ~3X higher limiting resolution performance. Substantial cost and schedule savings can be realized with this approach compared to fully filled apertures of equivalent resolution. A conceptual design for a ring-shaped 30m telescope is presented and the engineering challenges of its various subsystems analyzed. The optical design consists of a 20X annular Mersenne form beam compactor feeding a classical 1.5m TMA telescope. Ray trace analysis indicates the design can achieve near diffraction limited images over a 200μrad FOV. The primary mirror consists of 70 identical rectangular 1.34x1.0m segments with a prescription well within the demonstrated capabilities of the replicated nanolaminate on SiC substrate technology developed by AOA Xinetics. A concept is presented for the deployable structure that supports the primary mirror segments. A wavefront control architecture consisting of an optical metrology subsystem for coarse alignment and an image based fine alignment and phasing subsystem is presented. The metrology subsystem is image based, using the background starfields for distortion and pointing calibration and fiducials on the segments for measurement. The fine wavefront control employs a hill climbing algorithm operating on images from the science camera. The final key technology required is the image restoration algorithm that will compensate for the highly obscured aperture. The results of numerical simulations of this algorithm will be presented and the signal-tonoise requirements for its successful application discussed. It is shown that the fabrication of the 30m telescope and all its supporting subsystems are within the scope of currently demonstrated technologies. It is also shown that the observatory can be brought to geosynchronous orbit, in its entirety, with a standard launch vehicle.
Gimbals have been the main mechanism to perform pointing and beam steering for most Electro-optic sensors. A new
class of pointing and beam steering devices based on a pair of counter-rotating Grisms is presented here. The device is
capable of wide spectral band. The paper first describes the design principles of counter-rotating Grisms for beam
pointing and beam steering. Comparison between gimbals and counter-rotating prisms is given next. Finally potential
applications of a pair of counter-rotating grisms are illustrated.
KEYWORDS: Fabry–Perot interferometers, Spectral resolution, Reflectivity, Absorption, Spectroscopy, Optical design, Systems modeling, Staring arrays, Infrared spectroscopy, Signal to noise ratio
The high spectral resolution capability of a Fabry-Perot spectrometer (FPS)1,2 has many unique applications. Although
the basic theory is well established, a physically accurate end-to-end system model is much desired for understanding
the capability of FPS-based systems. This paper describes the optical design of an infrared FPS along with a coherent
beam propagation model of the FPS. Parameters that affect FPS signal-to-noise ratio such as FPS reflectivity,
absorption, scattering and surface flatness are analyzed. Results from the coherent beam model are compared with endto-
end system performance model findings. System performance impact of background noise due to self-emission of the
FPS is also discussed. A trade-off study between a single etalon and a double etalon FPS is discussed.
The Low Cost Microsensors (LCMS) Program recently demonstrated state-of-the-art imagery in a long-range infrared (IR) sensor built upon an uncooled vanadium oxide (VOx) 640 x 480 format focal plane array (FPA) engine. The 640 x 480 sensor is applicable to long-range surveillance and targeting missions. The intent of this DUS&T effort was to further reduce the cost, weight, and power of uncooled IR sensors, and to increase the capability of these sensors, thereby expanding their applicability to military and commercial markets never before addressed by thermal imaging. In addition, the Advanced Uncooled Thermal Imaging Sensors (AUTIS) Program extended this development to light-weight, compact unmanned aerial vehicle (UAV) applications.
The Low Cost Microsensors (LCMS) Program recently demonstrated state-of-the-art imagery in a long-range infrared (IR) sensor built upon an uncooled vanadium oxide (VOx) 640 X 480 format focal plane array (FPA) engine. The 640 X 480 sensor is applicable to long-range surveillance and targeting missions. The intent of this DUS&T effort is to further reduce the cost, weight, and power of uncooled IR sensors, and to increase the capability of these sensors, thereby expanding their applicability to military and commercial markets never before addressed by thermal imaging.
The objectives of the Low Cost Microsensors (LCMS) Program are twofold. The first is to develop and deliver a long-range infrared (IR) sensor built upon an uncooled vanadium oxide (VOx) 640 X 512 format focal plane array (FPA) engine. The second is to develop an expendable microsensor built upon a VOx 160 X 128 format FPA engine. The 640 X 480 sensor is applicable to long-range surveillance and targeting missions and is a reusable asset. The 160 X 120 sensor is designed for applications where miniaturization is required as well as low cost and low power. The 160 X 120 is also intended for expendable military applications. The intent of this DUS&T effort is to further reduce the cost, weight, and power of uncooled IR sensors, and to increase the capability of these sensors, thereby expanding their applicability to military and commercial markets never before addressed by thermal imaging.
The diffractive optical element (DOE) provides unique and improved chromatic aberration reduction for both visible and IR optical systems. The DOE simplifies the optical design form and improves the image quality of refractive optical systems. This paper formulates and analyzes the theory of chromatic aberration correction and compares DOE performance with that of a conventional optical element (COE). It presents several design examples with spectral bandwidth ranging from visible to long wavelength infrared to illustrate the advantages of optical systems using a DOE. DOE improves optical system performance while lowering the cost and weight by reducing the number of lens elements and desensitizing misalignment tolerances.
The use of diffractive optical elements ( DOE ) in most refractive reimaging infrared optical systems significantly simplifies the optical design form and improves the image quality. The basic theory of chromatic aberration correction using DOE is analyzed. A 3 to 5 um design is shown comparing the optical design form and image quality of the conventional design and the DOE improved design. The DOE improves performance while lowering cost and weight by reducing the number of lens elements and desensitizing the design to misalignments. MTF, MRT, and NEDT tests of the hardware empirically demonstrate the superior performance of the DOE design.
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