- API data.nasa.gov | Last Updated 2019-12-12T23:50:14.000Z
CAL_LID_L2_05kmCPro-Prov-V3-40 data are CALIPSO Lidar Level 2 Cloud Profile data. The Lidar Level 2 Cloud Profile data product contains cloud profile data and ancillary data. The cloud profile product is produced at 5 km horizontal resolution and is written in HDF. Note that there is no atmospheric volume characterization associated with the cloud profile products. Also, the 1064 calibration scheme assumes that both the extinction and the backscatter from clouds are spectrally independent. Consistent with this assumption, extinction and backscatter profiles will be reported for clouds only at 532 nm. Additionally, it is important to note that the aerosol profile product extends upward to 30.1 km, while the cloud profile product ceases at 20.2. Therefore, users interested in polar stratospheric clouds will need to order the aerosol profile data product. The science algorithms used to produce the V3.40 CALIOP data products are identical to those used to generate the V3.01 and V3.02 products; however, some of the ancillary data used in the V3.40 analyses is different. All CALIOP data products rely on meteorological data provided by NASA's Global Modeling and Assimilation Office (GMAO). The V3.01 and V3.02 data products were produced using the GMAO's GEOS 5.2 data products. Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations (CALIPSO) was launched on April 28, 2006 to study the impact of clouds and aerosols on the Earth's radiation budget and climate. It flies in the international A-Train constellation for coincident Earth observations. The CALIPSO satellite comprises three instruments, the Cloud-Aerosol LIdar with Orthogonal Polarization (CALIOP), the Imaging Infrared Radiometer (IIR), and the Wide Field Camera (WFC). CALIPSO is a joint satellite mission between NASA and the French Agency, CNES.
- API data.nasa.gov | Last Updated 2020-01-29T03:39:20.000Z
<p>The primary objective of this activity is to develop, design, and test (DD&T) the QUAD-core siTARA (QUATARA) computer to distribute computationally intensive processes such as: communication, sensors, attitude determination, attitude control, cameras, robotic manipulators, and science payloads. An example of the current state-of-the art for a COTS CubeSat flight computer is, a 16 bit 80 MHz Microchip dsPIC33 microcontroller capable of managing the satellite attitude determination, control system, communication system, power, and science payloads. Adding more capability to these COTS flight computers required the development, under a previous CIF proposal, of the Modular Attitude Determination System (MADS) board. MADS lessened the I/O load from the flight computer so it could focus on higher priority tasks such as managing a Real-Time Operating System (RTOS) or carrying out an attitude control algorithm. The MADS board utilized a 16 bit 80 MHz Texas Instruments ARM Cortex-M4 Stellaris microcontroller to execute the attitude determination algorithm independently of the dsPIC33 flight computer. Once the MADS board processes the data, the dsPIC33 receives the estimated states and determines the desired attitude control.</p><p>The addition of cameras, proximity sensors, robotic manipulators, thruster systems, complex science payloads and video guidance systems, would cause current CubeSat flight computers to be overwhelmed. Because of the desire to expand the capabilities of CubeSats, the innovation of the QUATARA architecture enhances the capabilities of data handling and computer processing by replacing the 16 bit 80 MHz microcontrollers with four 64 bit 1 GHz microprocessors. The QUATARA allows for tasks to be processed at a faster rate not only because of the difference in clock speed between the platforms but also because of the fact that there are four individual microprocessors which can run these tasks independently without the need to serialize the execution of the code like in a single microcontroller.</p><p>The QUATARA computer aims to be fault-tolerant by means of a software voting scheme to guard against the effects of Single Event Effects (SEE) such as Single Event Upsets (SEU). Each ‘node’ (Gumstix Computer-On-Modules (COM)) of the QUATARA computer will be connected to its own set of sensors and actuators. These individual nodes will collect their respective data and share it between themselves over a data bus (such as RS-485). Once each node has all the data from all of the other nodes it will process it and come up with a result. This result can then be used to determine if a node is considered as ‘failed’ and that node then needs to be disabled, (this can be done by ignoring future data received from that node or by completely shutting it off). In the case a node is lost a support node is available to be switched in for the failed node. This support node will focus on low priority tasks, (such as housekeeping), if it is not required as a voting node. Synchronization between the nodes can be maintained by having a precise timing source on each of the processors, (such as a ticking timer interrupt routine), that ticks at a set time interval. This timing information will be passed between the nodes and the tick rate of the interrupt routine will be modified as required to ensure that all of the nodes data remains in sync.</p>
- API data.nasa.gov | Last Updated 2020-01-29T04:12:36.000Z
Current-day capabilities for performing post operations analysis (POA) of air traffic operations at airports, airlines and FAA facilities are mostly limited to creating reporting type of analysis results which compare mean values of key performance indicators against the respective expected nominal levels (e.g., average daily delay). This single point comparison method does not directly enable a POA analyst to identify the root-cause for a particular observed inefficiency, nor does it help in identifying a solution for mitigating that inefficiency. This SBIR develops a machine learning based approach for improving POA and for potentially making it more autonomous. We call this tool Collective Inference based Data Analytics System for POA (CIDAS-P). CIDAS-P will provide airport, airline, FAA and NASA personnel with a fast, flexible and streamlined process for analyzing the day-of-operations, rapidly pinpointing exact causes for any observed inefficiencies, as well as recommending actions to be taken to avoid the same inefficiencies in the future. It does this by developing an innovative, collective inference algorithm for cross-comparing performance of the same facility on different days as well as cross-comparing performance across different facilities. The algorithm leverages sophisticated probabilistic modeling techniques that consider the subtle nuances by which cross-facility and cross-day operational scenarios differ to enable apples-to-apples comparisons across traffic scenarios and identify what works well and what does not in similar situations. User acceptance of NASA Trajectory Based Operations research products stands to benefit from CIDAS-P because CIDAS-P's automated recommendations can help identify and fix problems with these products early on in their deployment life-cycle.
- API data.nasa.gov | Last Updated 2020-01-29T04:04:16.000Z
slowed rotor / compound (SL/C) aircraft offer VTOL combined with fixed-wing flight-efficiencies. They are safer than any other type aircraft -- with much lower acquisition, maintenance and operational cost than helicopters and tiltrotors. Carter Aviation Technologies began developing SL/C aircraft in 1994 and began flying a prototype, the CarterCopter Technology Demonstrator (CCTD) in 1998. This proposal, using CCTD data, will provide a prototype 2-seat SR/C, VTOL aircraft that meets NASA?s PAVE goals. Reduced community noise is provided by a computerized propeller, designed for quietness, which operates at low tip-speeds and is protected by tail-booms. The non-stalling autorotating rotor provides low tip-speeds, eliminates the helicopter ?dead man zone? and provides the equivalent of an emergency parachute. Low cost per seat mile is provided by simplified construction, reduced parts count and high flight-efficiency. During VTOL and low-speed flight, SR/C aircraft fly like an autogyro having the same hp to weight ratio. Autogyros are the easiest aircraft to learn to fly safely. Pilot workload is simplified by an automated tilting pylon that keeps the wings in best L/D, an automated boosted collective and automated rotor flapping controls. The landing gear absorbs 24 ft/sec impacts. Only the tilting pylon is untested.
- API data.nasa.gov | Last Updated 2020-01-29T03:27:38.000Z
The Phase I effort successfully demonstrated the feasibility of a terrain guided automated precision landing sensor using an innovative multi-field-of-view stereo motion system with a novel real time terrain mapping algorithm. The objective of the Phase II proposal is to develop a complete prototype and characterize the performance of the LandingNav sensor system in all of the relative motion environments anticipated for the descent of the Lunar Surface Access Module. The result of the Phase II work will be a comprehensive flight characterization of the new landing navigation system and a closed loop demonstration of the multi-camera stereo vision unit working with the feature detection and terrain mapping to avoid hazards.
- API data.nasa.gov | Last Updated 2020-01-29T04:12:30.000Z
Extravehicular Activity (EVA) systems are critical to every foreseeable human exploration mission for in-space microgravity EVA and for planetary surface exploration. Innoflight proposes developing a Compact Wireless EVA Communications System (CWECS) as a replacement and advancement of the Space-to-Space EVA Mobility Unit (EMU) Radio (SSER). The CWECS goals are to: (a) provide backward-compatibility with the existing SSCS network and SSER; (b) provide enhanced communication between the EMU and space vehicle (or ISS or future space habitat) via 802.11n, including high-speed telemetry from the EMU to the spacecraft; and (c) provide body area network (BAN) coverage for wireless biomedical devices and sensors within the EMU. The Phase II will leverage Innoflight's DeSCReeT IF-SDR architecture, which uses cutting edge radiation-tolerant components as the foundation of a software-defined radio (SDR), and transform it into an integrated unit supporting SSCS, 802.11n and BAN. The end result of the Phase II will be a brass-board CWECS that demonstrates compatibility with the selected waveforms.
- API data.nasa.gov | Last Updated 2020-01-29T03:55:30.000Z
The objective of this Phase II project is to develop and demonstrate a compact and reliable oscillator technology for the frequency band from 100 ? 250 GHz for use in terahertz local oscillators and transmitters. The new oscillators rely on MMIC technology that is reliable and robust, offers the best overall performance and will be suitable for volume production and commercialization. These oscillators meet immediate needs for NASA's Earth Science program, specifically for terahertz radiometers for studies of the atmosphere and climate change. The oscillators are also useful for a wide range of other scientific, military and emerging commercial applications. The Phase I study demonstrated the feasibility of the new oscillators through the development and demonstration of an oscillator at 146 GHz suitable as a driver for an 874 GHz cloud ice radiometer being developed at NASA/GSFC. This new component greatly exceeds the performance of any other commercially available oscillator technology while maintaining a compact size, power efficiency and all solid-state construction. The Phase II research is focused on achieving greater power for higher frequency terahertz sources, improving power efficiency, achieving more compact integration of the subcomponents and extending the basic design concept throughout the 100 ? 250 GHz band.
- API data.nasa.gov | Last Updated 2020-01-29T04:04:12.000Z
Deployable Space Systems (DSS) will focus the proposed Phase 2 SBIR program on the hardware-based development and TRL advance of a highly-modularized and extremely-scalable solar array (Mega-ROSA) that provides immense power level range capability from 100kW to many Megawatts in size. Mega-ROSA will enable extremely high power spacecraft applications, including: Solar Electric Propulsion (SEP) spacecraft, SEP space-tug, and large-scale Planetary and Human Exploration missions because of its ground-breaking stowed packaging efficiency, high deployed stiffness / strength, low-cost and straightforward ground test capability. The innovative and synergistic Mega-ROSA solutions, to be validated to a TRL 6 level during the proposed Phase 2 program, will enable future high power missions through low cost (25-50% cost savings depending on PV and blanket technology), high specific power (>200 W/kg to 400 W/kg BOL at the wing level depending on PV and blanket technology), extremely compact stowage volume (>50 kW/m3 for very large arrays), high deployment reliability, platform simplicity (low parts count and reduced potential failure modes), high deployed strength/stiffness (>5X stiffer and stronger than rigid panel arrays of similar sizes), high voltage capability, scalability to ultra-high power (100kW to several Megawatts), and operability in unique environments (high/low illumination, high/low sun intensity and high radiation).
- API data.nasa.gov | Last Updated 2020-01-29T04:11:27.000Z
Polymeric composite materials that are currently utilized in aircraft structures are susceptible to significant damage from lightning strikes. Enhanced electrical and thermal conductivity in these polymeric composites could eliminate this damage. The addition of this multifunctional capability to composites will result in lower manufacturing costs and weight reductions in future aircraft since the addition of coatings, conductive mesh, or expanded foil materials can be eliminated. A combined materials and engineering approach will be utilized to accomplish this objective by modifying a high performance composite system with a combination of conductive nano and micron size filler materials. The large difference between the two filler sizes will create a stratified composite structure that consists of the conductive micron size particles residing in the interlayer region of the composite with the nanomaterials dispersed evenly throughout the matrix and in the fiber tows. Using this approach, these composites will have the same or better balance of mechanical properties as current state-of-the-art composite systems but also have the added functionality of a conductive interlayer and network to eliminate damage from lightning strikes. The Technology Readiness Level will be between 3 and 4 after the Phase 1 program.
- API data.nasa.gov | Last Updated 2020-01-29T03:45:33.000Z
SCCAQ Energy, LLC (SCCAQ), in collaboration with Temple University and Infinia Technology Corporation (ITC), is pleased to propose a Stirling Kilopower Innovative Prototype (SKIP) that is ideally suited for use with fission-based Space Nuclear Power Systems (SNPS) and/or Nuclear Electric Propulsion (NEP) systems. SKIP adapts the ongoing development of a 400-W free-piston Stirling (FPS) engine for terrestrial applications to meet NASA needs for SNPS. This proposal is specifically addressed to STTR Topic T3 (Space Power and Energy Storage), with an emphasis on Subtopic T3.01. The proposed effort will be supported by Temple University SEEE lab personnel and will heavily leverage engineering support from Infinia Technology Corporation (ITC). This proposal is based on adapting newly developed 400-W engine at ITC to current NASA needs for an extremely reliable, robust, and high performance space power engine for Kilopower fission thermal conversion, among other potential power system heat sources. The key change that is needed to develop a SKIP demonstration unit is to modify the heater head to be suitable for interface with a space reactor system as a heat source.