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The purpose of this NASA SBIR Phase I proposal is to develop a novel type of high resolving power diffraction gratings based on volume Bragg gratings technology. The key innovation to be used for creation of these gratings is the patented technology on production of high efficiency volume diffractive elements in photo-thermo-refractive (PTR) glass on which OptiGrate has an exclusive license from the University of Central Florida. Gratings with diffraction efficiency more than 90% and resolving power up to 20,000 will be demonstrated for the spectral analysis applications in the visible and near-IR spectra (from 400 to 2700 nm). These gratings will have 25- to 50-mm aperture with the spectral resolution down to 50 pm and less. This, to the best of our knowledge, will exceed parameters of all comparable gratings available nowadays. Moreover, PTR volume diffractive gratings are stable over time for decades, thermally-stable up to 400??C, their resistance to CW laser radiation exceeds 10 kW/cm^2, and laser-induced damage threshold is 10 and 40 J/cm^2 for 1- and 8-nm pulse width, respectively. Absorption of these gratings is only 0.1 cm^-1 at 1 um wavelength after exposure to 10 Mrad of gamma radiation.

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The present proposal describes the development of an adaptive Computed Tomography Imaging Spectrometer (CTIS), or "Snapshot" spectrometer which can "instantaneously" capture a full 3D data cube. The technology is applicable to hyperspectral imaging for remote sensing of extra-terrestrial planetary bodies and deep space objects. The snapshot capability of the technology makes it possible to capture transient events otherwise inaccessible with conventional pushbroom or whiskbroom imagers. The adaptive component of the innovation is a liquid crystal spatial light modulator which replaces the standard computer generated hologram in this technology. As such it can be rapidly tuned at KHz rates for optimal performance in real time improving the signal to noise ratio and data cube image reconstruction.

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ATA has demonstrated the primary innovation of combining a precision MEMS gyro (BAE SiRRS01) with a high bandwidth angular rate sensor, ATA's ARS-14 resulting in a low-noise, high bandwidth hybrid sensor, or HYSENS in a Phase I SBIR. The primary emphasis in Phase I development was the implementation and real-time demonstration of the sensor fusion algorithms that combined the output from a MEMS gyro and the ARS-14 resulting in a HYSENS that exhibits a bandwidth of DC to 2000 Hz and NEA of less than 0.1 rad rms (0.5-2000 Hz integration bandwidth), thus meeting the requirement specified in the SBIR SOW. The HYSENS has first applicability in optical Inertial Reference units for used in Free Space Laser Communication. The HYSENS-based IRU, or HIRU, that is proposed for the Phase II effort will result in the state of the art in compact optical IRUs. The significance of the HIRU innovation is that the HIRU will escalate the state-of-the-art in small, precision optical IRUs by virtue of minimal mechanical envelope, low mass, high performance, both in jitter mitigation and Inertial Attitude Knowledge (IAK), and power dissipation. In addition, the HYSENS was designed from the onset to be highly modular and flexible by virtue of the sensor fusion algorithms and computational architecture to allow rapid integration of higher performance MEMS gyros into future versions of the HYSENS.

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This innovation is the design of a monochromatic x-ray source to be used in a mission compatible XPS spectrometer. Existing x-ray sources for XPS are large, require high power and a will have difficulty meeting the vibration specifications for a mission type instrument. The small x-ray sources developed for medical applications are exciting but are designed for high energy x-rays and require refractory anodes. This program will develop a new design suitable for mission applications. It will focus on small sources similar to the medical devices that will use low power. The monochromator will be designed for low mass and use a feedback based stabilization to keep it aligned independent of temperature and vibrations associated with missions launch. The feedback system will use x-ray detectors in a plane near the sample to since the x-ray beam direction and an interment angular vibration to make sure the monochromator is on the optimum angle for diffraction. After a suitable design is implemented with thermal electron sources, a nanotube excitation sources will be considered.

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This proposal introduces an innovative concept aimed to develop, for the first time, a 1k pixel far infrared focal-plane array with the following key design features: 1- A top-illuminated, 2D germanium array (32x32 single or 64x64 mosaic) with the possibility of extension to very large formats. The quantum efficiency is enhanced by metalizing the bottom surface for a second pass. 2- A 2-side buttable 32x32 (64x64 mosaic) CTIA readout multiplexer using advanced cryo-CMOS process. The unit-cell design is optimized for far IR detectors, eliminates detector debiasing, and improves pixel uniformity. The readout is operational down to at least 2.0K. 3- A novel, direct hybrid design using indium-bump technology. This integrated design offers superior noise performance and effectively addresses the readout glow, detector heating, and thermal mismatch between the detector and the readout. This is the key discriminator of this project. The projected sensitivity of this array as well as the 1k pixel (4k pixel mosaic) format meets the stated requirements of future NASA instruments. This effort fits well within the scope of the SBIR Subtopic S4.01 and will be a benefit to many large and small NASA projects such as SOFIA and SAFIR.

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We propose the development of automated systems to improve radiobiology research capabilities at NASA Space Radiation Laboratory (NSRL) at Brookhaven National Laboratory (BNL). Current radiobiology experimentation at the NSRL is limited primarily by the amount of time required to manually move samples to/from the radiation target area. Additionally, the NSRL facility currently does not support processing of samples during or directly after radiation exposure, or long duration radiobiology studies. Our proposed automated system will address the above issues as follows. First, an automated sample movement system will be developed to reduce the overhead time of the current manual system of moving samples to/from the radiation target area. Second, an Online Assay System will be designed to provide immediate sample analysis, such as sample fixation and freezing, to allow a better understanding of the radiation effects on the samples. Third, the Single Loop for Cell Culture (SLCC, developed by Payload Systems Inc. for NASA) system design will be modified to support long duration radiobiology research. In addition, the system will also support animal experiments.

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This SBIR proposal is to establish a platform technology of space durable thermally/electrically conductive fabrics for space environment applications. The fabrics are based on nanoengineered fibers and yarns under development at NanoTex Corp. With increased emphasis on long term manned space missions with limited resources, there is increased need for efficient passive thermal control systems. Furthermore, the proposed fabrics are multifunctional as they will have improved strength and tenacity, designed electrical conductivity, and greater thermal stability.

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This project will focus on the strategic, routine incorporation of medium-resolution satellite imagery into operational agricultural assessments for the global crop market. Automated algorithms for rapid extraction of field-level crop area statistics from Landsat and Landsat-class imagery (including SLC-off L7 data, AWiFS, ASTER, and NPOESS/OLI) will be developed. For prototype development, the project will collaborate with the Production Estimates and Crop Assessment Division of the USDA Foreign Agricultural Service. The algorithms, based on Bayesian Probability Theory, will incorporate multiple lines of evidence in the form of prior and conditional probabilities and will implement an innovative approach to supervised image classification allowing for automated class delineation. The knowledge-based expert classifiers prototyped during Phase I will be tested and validated at selected pilot sites across the globe. The overall results of the project will enhance global agricultural production estimates by improving the timeliness and accuracy of field-level crop area estimates. It addresses the NASA SBIR subtopic by developing unique, rapid analyses for the extraction of crop area statistics from medium-resolution imagery. The developed technologies will support both the scientific and commercial applications of ES data and will be benchmarked for practical use against an international model for agricultural production estimates.

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Future advanced telescopes require active mirror compensation without the complexity of real-time adaptive control. Current wavefront correctors, while dimensionally stable, require closed loop control using a wavefront sensor and complicated electronics to maintain mirror shape. For space based systems, simplified open loop control is desirable since it reduces power and weight while greatly improving system reliability by reducing complexity and electronic parts count. Xinetics proposes a Programmable Relaxor Open-Loop Mirror using Integrated Spatial Encoders (PROMISE) that combines surface parallel actuation and micro optical encoders. The programmable relaxor open-loop mirror uses a surface parallel actuator array, made using ferroelectric micromachining originally developed for silicon based MEMS. The programmable actuator array enables the dimensionally stability and angstrom level control provided only by relaxor ferroelectrics, as has been demonstrated by the Jet Propulsion Laboratory. The integrated spatial encoder features an optical encoder that monitors dimensional change and is integrated directly between the actuator array and the surface mount interconnect. The voltage output of the optical encoder is used as a direct input to the feedback loop for the actuator circuit enabling electroactive control of the mirror surface without the necessity of an optical sensor, thereby enabling open loop control.

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Silicon carbide matrix composites can produce turbomachinery structures with 1500<SUP>o</SUP>C service temperature capability at less than one-half the weight of metallic structures. This would translate into substantial improvement in rocket (or aircraft) system performance. However, SiC composites do not have adequate long term stability under hot, humid turbine engine conditions. Thus, reliable environmental barrier coating (EBC) technology needs to be developed for SiC composites for long duration or reusable turbomachinery applications. The preceding SBIR Phase I program proved feasibility of our technology to improve environmentally durability of silicon carbide CMCs. The Phase II program will refine coating materials and processes. A comprehensive test matrix is included to assess repeatability in environmental barrier performance. Next, this technology will be used to produce representative turbine engine test articles. Surmet has teamed with a major prime contractor, so as to develop technology that is useful towards near-term NASA systems. Key environmental barrier testing work will be conducted at specialized test facility that simulates turbine engine environment. Thus, the Phase II program will provide a strong foundation for a follow-on Phase III program which will start implementation into specific NASA system(s).

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Space structures that are ultra-lightweight, and have gas barrier property, space durability, radiation resistance and high impact resistance are desirable to improve the reliability and provide a safe resting environment for astronauts and equipment operation. Some of the components currently in use such as stations or habitats use double-wall thick films with high internal pressure. Some components are in thin film form and the specific rigidity and dimensional stability needs improvement. Components of landers and vehicles are subject to dust impact. All these solid or hollow components are vulnerable in space because of the foreign object impact or radiation attack. In this Phase I project, we propose to develop ultra-lightweight, microcellular nanocomposite foams and sandwich structures that possess all the desirable properties mentioned above. The structural module can be compacted into a small volume to facilitate launching. The proposed microcellular nanocomposite foam and sandwich structures do not involve or release any toxicity and will have much higher specific mechanical properties than foams and sandwich structures processed by the conventional techniques. They can be used to either replace or supplement to the inflatable technology for improvement in reliability, durability, and safety in space operation. Preliminary research results are very encouraging.

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The Phase II program will concentrate on manufacturing of qualified low-current, light-weight, 10K ADR magnets for space application. Shielded ADR solenoidal magnets will be compared with self-shielding toriodal magnets in terms of overall weight, volume, and cooling capacity. Models of both toroidal and shielded solenoidal magnet systems will be built and tested to compare the two options at practical as well as technical levels.

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The utilization of space resources can enable sustained affordable exploration of the Moon and beyond in the nation's Exploration Initiative. The availability of low-cost, abundant indigenous electric power is critical to the aggressive implementation of space resource utilization. This power-rich space environment can be achieved by the generation of electrical power from thin film photovoltaic solar cells produced on the surface of the Moon from lunar resources. This concept of operation offers a specific advantage in the capability of continuous power growth by addition of solar cells, manufactured in situ, to an expanding power grid. Such an effective power system on the Moon would lower operational risks of future robotic and manned missions through higher reliability. In addition, such architecture has the capability to deliver power at a decreasing cost per kWh beyond the first 100 kWh or so. We propose the development of the key thin film silicon solar cell technologies needed to demonstrate the fabrication of thin-film solar cells on the surface of the Moon, and to present a preliminary design of a roving vehicle to support these operations.

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We will leverage our prior work on Adaptive Information Management (AIM) to provide a core reasoning capability for use in an interactive and quantitative evaluation aid to assist designers in developing user interfaces (UIs). We have a task-linked information representation and associated algorithms for reasoning about the information needs of a set of user tasks, the information presentation capabilities of a set of devices and formats, and the degree of match between the two. These have served as the basis of multiple, successful AIM systems in the past. In Phase I, we developed an architecture for making our core representation more interactive and subject to user guidance-- turning our AIM into a Multi-modal Advisor for Interface Design (a MAID). We demonstrated the effectiveness of the resulting evaluation algorithm in a set of 10 "walkthrough" experiments illustrating quantitative feedback on the adequacy of interface concepts for the types of procedures and displays under consideration for NASA's Crew Exploration Vehicle (CEV). In Phase 2, we propose to implement a prototype version of this approach in an integrated suite of software tools for procedure authoring and demonstrate it on a set of procedure execution displays for a NASA vehicle or platform (notionally, CEV).

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To address NASA's need for an instrument for robotic in situ geochemical exploration of the solar system, Physical Optics Corporation (POC) proposes to develop a new hybrid Laser Induced Breakdown Spectroscopy (LIBS) and Raman Spectroscopy (LIBRA) standoff chemical analysis system. This 0.03 m^3, <10 kg, <15 W passively cooled system will offer high specificity in trace chemical detection through LIBS/Raman sensor fusion to minimize false alarm rate (<1 in one million). Its hermetically sealed, monolithic, space-qualified design will ensure the survivability of LIBRA through launch and extended operation on planet surfaces. In Phase I, POC demonstrated the feasibility of LIBRA by assembling and testing a proof-of-concept tabletop (0.020 m^3 sensing head; 0.025 m^3 power supply) prototype with a technology readiness level (TRL) of ~4, capable of up to 5 m standoff detection and identification of inorganic, organic, and mineral samples, including compounds associated with the origins of life, of interest to NASA solar system exploration missions. In Phase II, POC will optimize the system design and develop and fabricate a fully functional LIBRA prototype system to meet the needs of NASA solar system exploration programs. Prototype test data will lead to an engineering design for a space-rover-operable prototype.

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Silicone coatings are the system of choice for inflatable fabrics used in several space, military, and consumer applications, including airbags, parachutes, rafts, boat sails, and inflatable shelters. Commercial silicone coatings with improved mechanical, thermal and physical gas barrier properties are needed for a broad range of space, military, and commercial applications. The phase I program has demonstrated that addition of small amounts of nanostructured additives enhances tear strength, tensile strength, and hardness without significantly degrading other important properties, thermal stability, puncture resistance and air permeability of commercial silicone coatings. It was also shown that properties of coatings are strongly correlated with the chemistry and composition of nanostructured additives. The significance of the Phase I innovation is that commercially used coating formulations were utilized as the starting material, making it easier to be adopted in practice. Success in Phase I has enabled us to put together a strong Phase II team, composed of commercial silicone coating applicators, an airbag assembly developer, and a large supplier of silicone coating formulation. The focus of the Phase II program will be to develop nanostructured additives for several different types of commercial silicone coatings to meet their specific application needs. Additionally, nanostructured additive technology will be scaled up, and prototype airbags will be fabricated.

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Payload Systems Inc. and the MIT Space Systems Laboratory propose Self-assembling, Wireless, Autonomous, Reconfigurable Modules (SWARM) as an innovative approach to modular fabrication and in-space robotic assembly of large scale systems. Fabrication of modular components yields fabrication savings associated with large production volume and automated integration and test. In-space assembly permits staged deployment on an as-needed, as-afforded basis. It also decouples stowed launch geometry from deployed operational geometry. The SWARM concept uses formation flown spacecraft, containing multiple universal docking ports, to dock with modular elements and maneuver them to dock with other, similar elements. In the process, systems can be assembled that are much larger than what can be fit or folded into a launch vehicle fairing, or what can be launched on a single vehicle. Furthermore, such modularity will allow jettison of failed components, upgrade of obsolete technology, and amortization of design costs across multiple missions. In Phase I, we demonstrated the feasibility of this approach for a simplified telescope assembly on the flat-floor at MSFC. In Phase II, we will develop the hardware and software elements necessary to demonstrate, on a flat-floor, the modular assembly and reconfiguration of systems representative of trans-planetary spacecraft and large telescope assembly.

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The research proposed targets airframe noise (AFN) prediction and reduction. AFN originates from complex interactions of turbulent flow with airframe components that are extremely difficult to compute efficiently and accurately. In Phase I the feasibility of an innovative generalized lattice Boltzmann equation (GLBE) approach as a computational aeroacoustics (CAA) tool was evaluated. A subgrid scale (SGS) with wall damping was introduced into the GLBE to enable large eddy simulations. GLBE results on wall turbulence statistics compared well with direct numerical simulations and experiments. The GLBE approach, which uses multiple relaxation times, was significantly more stable than, and as computationally efficient as, the more common single-relaxation time LBE at high Reynolds numbers. It was also computationally competitive with finite-difference methods on single processors, but GLBE had the major advantage of scaling near-linearly on large parallel computers. GLBE computations also accurately reproduced the tonal frequencies for cross-flow over a single, and a pair of cylinders, and feedback-generated tonal frequencies for flow over cavities, which are CAA benchmarks for AFN. With feasibility demonstrated in Phase I, further developments of GLBE, including innovative use of wall-layer models, dynamic SGS models, improved boundary condition implementation and grid refinement strategies in Phase II would enable simulations of very high Reynolds number CAA problems of complex geometry with high fidelity. The GLBE approach developed will then be interfaced to an existing far-field acoustics prediction code to efficiently address AFN in configurations of interest, including high-lift systems and landing gear.

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The runway safety issue has been on the Most Wanted list of the National Transportation Safety Board since the list's inception in 1990. The FAA has responded by implementing two ground surveillance technologies at major U.S. airports to reduce the risk of runway incursions. However, both technologies route information through air traffic control (rather than directly to pilots), which significantly delays safe responses. Several flight deck technologies that communicate information directly to pilots are currently in development. However, there is a need for tools to rapidly test the technologies early in the design process and measure their impact on pilot performance prior to implementation. The Aptima/George Mason University team proposes to develop two technologies that can be used together or independently to evaluate performance of flight deck technologies aimed at improving runway safety. We will deliver a computational cognitive model (Adaptive Control of Thought-Runway Safety; ACT-RS) that realistically emulates pilot performance, thus reducing the need for human pilots early in the design process. In addition, we will deliver a measurement tool (Performance Measurement Engine) that can measure the impact of the flight deck technology on the performance of ACT-RS and human pilots, making it useful across the technology lifecycle.

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Various Earth Science fields require well-calibrated field radiometers whose calibrations must be tracked and verified in the field. NASA has long recognized requirement. However, these activities require specialized light sources that typically require high power, are bulky and difficult to use in the field, and do not work with all types of radiometers. We propose a next-generation portable, ultra-stable, lightweight and highly versatile light source based on light-emitting diodes (LEDs). Recent advances in LEDs include higher power, efficiency, and a wider range of wavelengths (from UV to IR). These advances, coupled with LEDs' inherent suitability for electronic feedback stabilization, make them excellent candidates for more compact and power-efficient calibration sources. During Phase I we showed that we can implement light sources with the desired characteristics, using current technology. We identified and tested LED devices, measurement and stabilization techniques, and physical configurations. In Phase II we will build prototypes and implement a program for test and evaluation, and refine the design based on test results. At the conclusion of Phase II we will be ready to produce and sell a commercial version.

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Solid rocket motor cases are subject to a variety of external environmental and loading conditions from cradle-to-grave. These conditions can significantly impact the performance and decrease safety of the rocket motor. Fueling of the rocket motor adds an additional complexity in that inspection of the interior becomes impossible while creating the possibility of disbonds between the case and fuel. These factors can have potentially catastrophic consequences for the space vehicle performance. Acellent Technologies is currently developing structural health monitoring systems to address this issue. The TRL at completion of the current technology development is anticipated to be TRL 5-6. The proposed program focuses on maturing the technology to a TRL level 7 for implementation on existing and future space transportation vehicles. The development will be conducted in close collaboration with ATK-Thiokol who fully support the developmental and commercialization efforts.

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In this phase I SBIR program, a team led by Advanced Ceramics Research Inc. (ACR) propose a novel, low-cost manufacturing process for multi-functional polymer composite components with improved lightning strike mitigation and EMI shielding capabilities. The proposed program will develop and demonstrate a process for manufacturing complex-geometry composite parts with tailored lightning strike mitigation capability based on design requirements. This process is a natural extension of the ACR water-soluble tooling process for fabricating complex-geometry polymer composite parts as well as filament wound composite tanks. For the proposed phase I program, the ACR-led team will use a novel process to create a highly conductive surface capable of providing the necessary lightning strike protection and EMI shielding. The ACR team will evaluate the new approach with two different space qualified matrix polymers with graphite fibers and compare the surface conductivity with baseline composite systems.

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Advanced bipropellant engines are needed for ARES/ORION vehicle maneuvering and future deep space science missions. Currently, an iridium-lined rhenium combustion chamber is the state-of-the-art for in-space propulsion applications. An example of an in-space engine that incorporates an iridium-lined rhenium thruster is Aerojet's HiPAT apogee engine. This engine uses monomethyl-hydrazine (MMH, CH3N2H3) as fuel and nitrogen tetroxide (N2O4, specifically MON-3) as oxidizer. To increase performance of bipropellant engines, improved chamber materials are needed that will allow higher operating conditions (pressure and temperature) and better resistance to oxidation. Therefore, Plasma Processes, Inc. and its partner, Aerojet, propose to develop hafnium oxide-iridium lined rhenium combustion chambers that will simplify engine design and allow higher operating conditions. As a result, a lower cost, higher performance bipropellant space engine will be produced.

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This proposed program will focus on life management needs for new and emerging composite material systems and built-up structures in "young" aircraft. Both wide area inspection of fuselage and wing structures and characterization of adhesive bonds in built-up structures are addressed. JENTEK will develop both (1) hybrid methods in which spatially registered, digital images, produced by two or more sensing modalities are combined, and (2) a new method called Magneto-Thermography, invented by JENTEK, which offers both wide area inspection advantages and potential for characterization of adhesive bonds in built-up composite and metal structures. In one implementation of a hybrid method for graphite fiber/epoxy composites, the MWM-Array could sense and locate fiber damage and fiber movement under loads, while thermography could sense both fiber and matrix damage, allowing discrimination between fiber breakage, fiber/matrix disbonding, matrix cracking, and disbonding in built-up structures. Magneto-Thermography will use the demonstrated capability of the MWM-Array to monitor temperatures of buried fibers and to monitor temperatures at buried interfaces to replace IR cameras with MWM-Arrays in thermographic methods. This will enable both wide area inspection of thick composites and enhanced characterization of adhesive bonds in built-up structures, for foam layers, and other aerospace and space applications.

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The Gimbal-stabilized Compact Hyperspectral Imaging System (GCHIS) fully integrates multi-sensor spectral imaging, stereovision, GPS and inertial measurement, gimbal-stabilization, and gimbal-pointing-and-tracking capabilities into a compact light weight package. Advanced adaptive Kalman filter and attitude calibration algorithms are embedded for precision inertial measurement and real-time platform stabilization, motion compensation, and pointing control. Innovative multi-thread-coded, fully concurrent execution software is implemented with the latest multi-core CPU, which makes operation of GCHIS seamless. GCHIS concurrently acquires pushbroom hyperspectral imagery and multispectral snapshot stereo pairs. It features: 1) at least a 1392 pixel swathwidth and 5nm spectral resolution in the VNIR range for hyperspectral imaging; 2) at least 2600 x 1920 pixel frame size for four band multispectral imaging; 3) 12 bit digitization depth for all imaging components; 4) about 20lbs complete instrument mass; and 5) 1/100 degree platform stabilization/pointing accuracy. GCHIS has a fast data rate for high resolution and large area coverage. GCHIS can deliver one-foot resolution orthorectified hyperspectral imagery and inch level resolution multispectral stereo imagery. With gimbaled stabilization and programmable pointing, GCHIS is highly resistant to air turbulence and can handle diverse flight profiles, e.g. non-linear corridors and block areas, high and low altitudes, re-visiting or repeated measurement for change detection, and etc.