Data on the Open Data Network

Publishers

Refine by:Found 7,836 results

infrastructure Close
finance Close
data.nasa.gov Close
data.grandrapidsmi.gov Close
data.cityoftacoma.org Close

API
Propellant Flow Actuated Piezoelectric Rocket Engine Igniter, Phase II
data.nasa.gov | Last Updated 2018-07-19T09:03:13.000Z
Under a Phase 1 effort, IES successfully developed and demonstrated a spark ignition concept where propellant flow drives a very simple fluid mechanical oscillator to excite a piezoelectric crystal. The Phase 1 effort exceeded expectations, with the device demonstrating reliable ignition of both hydrogen and propane fuels, and achieving in excess of 1 million impact cycles (40,000 start cycles) during fatigue testing without measureable degradation. Several spin-off concepts were also identified that provide additional options for improving spark ignition system design. For Phase 2, IES proposes an accelerated, 18 month effort to refine design concepts and analysis tools, and then develop specific ignition system designs for two customer applications, with the intention of having these ignition systems demonstrated in engine ground testing during Phase 2 and ready to start flight qualification immediately following the Phase 2 effort. Both customers (United Launch Alliance and Pratt Whitney Rocketdyne) have expressed interest and commitment in participating in the Phase 2 activity, making engines and facilities available for development testing, and integrating any resulting viable products into their flight engines. The ULA application is a new gaseous bipropellant H2/O2 attitude control thruster, for which the piezoelectric igniter is ideal as a simple, direct ignition source. The PWR application is for an evolved RL-10 study currently underway, for which the piezoelectric system might be scaled up or used as a pilot igniter for a torch, or make use of another spin-off concept that was identified during the Phase 1 effort. The timing of this Phase 2 effort coincides perfectly with near term needs of both these customers, as well as for other small engine applications in work to replace catalytic hydrazine engines with bi-propellant engines that will require a simple and reliable ignition source.
API
EPOXI 103P/HARTLEY2 ENCOUNTER - MRI CALIBRATED IMAGES V1.0
data.nasa.gov | Last Updated 2018-07-19T02:46:12.000Z
This dataset contains calibrated images of comet 103/P Hartley 2 acquired by the Medium Resolution Visible CCD (MRI) from 05 September through 26 November 2010 during the Hartley 2 encounter phase of the EPOXI mission. Clear-filter and CN images of the comet were acquired throughout this phase; OH, C2, and dust continuum images were only acquired for several days spanning closest approach.
API
Networked Instrumentation Element
data.nasa.gov | Last Updated 2018-07-18T20:30:39.000Z
Armstrong researchers have developed a networked instrumentation system that connects modern experimental payloads to existing analog and digital communications infrastructures. In airborne applications, this system enables a cost-effective, long-range, line-of-sight network link over the S and L frequency bands that supports data rates up to 10 megabits per second (Mbps) and a practically unlimited number of independent data streams. The resulting real-time payload link allows researchers to make in-flight adjustments to experimental parameters, increasing overall data quality and eliminating the need to repeat flights.Work to date: The team has developed and flight-tested the 10 Mbps bi-direction aircraft-to-ground, line-of-sight network. A follow-on project, Space-Based Range Demonstration and Certification (SBRDC) Flight Demonstration #2, involved integration of this system with a phased-array antenna and controller to provide a 10 Mbps over-the-horizon network downlink. This prototype system was further refined into a more operational system that provided the Airborne Research Test System (ARTS) aboard the Full-Scale Advanced Systems Testbed (FAST) access to thousands of parameters from the heavily instrumented aircraft. Engineers were able to view ARTS network data output in the control room, without replacing any aircraft instrumentation or ground equipment.&nbsp; Additionally, four streams of network data from onboard hot-film sensors was recorded onboard and transmitted to the control room.Looking ahead: Work has begun to design a new system that incorporates state-of-the-art transceiver technology. The new system is expected to allow a five-fold improvement in throughput, to 40 Mbps.Benefits<ul><li>Flexible: Expands the utility of existing airborne platforms with legacy communications systems by supporting state-of-the-art payloads that leverage current network technology</li><li>Economical: Achieves a bi-directional, line-of-sight network without the need to replace existing communications infrastructure</li><li>Flight efficient: With real-time control of experimental parameters, reduces the need for repeat flights</li></ul>Applications<ul><li>Secure local line-of-sight communications</li><li>Global space-based communications via satellite links</li></ul>
API
WRANGLER: Capture and De-Spin of Asteroids and Space Debris
data.nasa.gov | Last Updated 2018-07-19T08:31:35.000Z
WRANGLER will accomplish these functions by combining two innovative technologies that have been developed by TUI: the GRASP deployable net capture device, and the SpinCASTER tether deployer/winch mechanism. Successful testing of both technologies in a microgravity environment has established these technology components at mid-TRL maturity. The leverage offered by using a tether to extract angular momentum from a rotating space object enables a very small nanosatellite system to de-spin a very massive asteroid or large spacecraft. The WRANGLER system is suitable for an incremental development program that will validate the technology through an affordable test flight in which a nanosatellite launched on a rideshare opportunity would capture and de-spin the upper state used to launch it.
API
Microwave Enhanced Freeze Drying of Solid Waste, Phase II
data.nasa.gov | Last Updated 2018-07-19T13:25:18.000Z
The development of advanced methods for Microwave Enhanced Freeze Drying of Solid Waste (MEFDSW) is proposed. Methods for the recovery of relatively pure water as a byproduct of freeze drying will also be fully developed. The Phase II project will result in the design, assembly, thorough testing, and delivery of a technology demonstrator prototype which may be employed over a broad range of mission scenarios. The prototype system will recover water initially contained within the wastes and stabilize the residue with respect to microbial growth. The dry waste may then be safely stored or passed on to the next solid waste treatment process. Using microwave power in a closed microwave cavity, water-ice present in the frozen solid waste can be selectively and rapidly heated. This results in a more energy efficient lyophilization process, and therefore hardware based upon this technology will have a lower Equivalent System Mass (ESM) than currently available systems.
API
NextSTEP Hybrid Life Support
data.nasa.gov | Last Updated 2018-07-19T07:04:42.000Z
NextSTEP Phase I Hybrid Life Support Systems (HLSS) effort assessed options, performance, and reliability for various mission scenarios using contractor-developed analysis tools and databases. A large scale GreenWall plant growth prototype was also fabricated. The prototype was scaled to accommodate a NASA Exploration Life Support Salad Crop Diet for a crew of four. NextSTEP Phase II baseline efforts encompass two tasks that will result in a high fidelity GreenWall-based HLSS testbed scaled to commercial habitat modules.The first task will include testing and refinement of the GreenWall subsystems, and the Phase I GreenWall prototype will be upgraded to a high fidelity testbed to allow testing of HLSS technologies at a habitat scale. The second task will include refinement of the Life Support Multidimensional Assessment Criteria (LSMAC) alternative evaluation factors as the salad production architecture is further developed and HLSS life support technologies are further characterized.The GreenWall plant growth system will also undergo further assessment for its ability to provide radiation shielding using modelling software available from NASA, allowing different materials and hardware configurations to be assessed. Additonal Phase II work includes Parabolic Flight Testing used to develop media-free water and nutrient delivery technologies that are logistically feasible for large scale plant growth systems in space.
API
Lightweight and Compace Multifunction Computer-Controlled Strength and Aerobic Training Device, Phase I
data.nasa.gov | Last Updated 2018-07-19T09:03:34.000Z
TDA Research proposes to develop a computer-controlled lightweight and compact device for aerobic and resistive training (DART) to counteract muscular atrophy and bone loss and to improve the overall wellness of astronauts operating in microgravity. The DART will be able to provide resistive loads up to 350 lbf and will accurately simulate the load profile of a mass in a 1-g environment. It will also be capable of applying custom load profiles such as eccentric overloading. In aerobic training mode, the DART will simulate the loads of a rowing machine with loads up to 175. The system will computer-controlled and can automatically calibrate to a user's range of motion. The total weight of the device will be less than 20 lbs and have a compact form factor to enable integration into a small crew module. By using a regenerative energy recovery system, the average power consumption of the DART will be less than 100 W during an exercise session. TDA is able to build on previous experience building exercise equipment for NASA and develop the DART in a short timeframe. TDA will prove the feasibility of providing effective aerobic and resistive training with a single device that is lightweight and compact in Phase I. At the end of Phase I a prototype will be delivered to NASA for evaluation. In Phase II we will advance the technology and provide the second generation prototype to NASA for testing on the International Space Station.
API
Extreme Environment Hybrid Gearbox Technology, Phase II
data.nasa.gov | Last Updated 2018-07-19T08:49:57.000Z
Nearly all mechanism applications require some form of gearbox. Wet lubricated gearbox technologies are limited to the relatively narrow temperature ranges of their lubricants. Dry lubricated gearboxes have proven to be problematic with poor life and reliability characteristics. Testing has shown that dry lubricated rolling elements can be made to work reliably provided they are operated at conservative contact stresses, however when dry film lubrications are tested under the sliding conditions in conventional transmissions they are no longer reliable. During the Phase I SBIR Rocketstar Robotics developed the preliminary design of a transmission that consists of all rolling elements and has eliminated all of the sliding elements that exist in conventional gearing. The transmission operates at contact stress values that are conservative and within the envelope proven through previous testing to provide reliable performance in rolling elements. The resulting transmission can be provided in a range of sizes and offers considerable torque capability within a reasonable envelope while operating within conservative rolling contact stress regimes at operating temperatures from near absolute zero to over 500C. The development and test of a successful prototype could revolutionize the torque transmission industry and open the door to mechanisms operations over a much broader temperature range than is now possible. Rocketstar Robotics proposes that the design be carried through the detailed design phase which includes detailed analysis models and that multiple prototypes be built of two different size transmissions. The units would then be tested for performance and life over the extremes of temperature from near cryogenic to 500C operation. Rocketstar will build 3 small 100 in-lb units and 3 large 400 in-lb units for testing along with spare splines to allow development testing with multiple DFL types. One of each unit will be delivered to NASA.
API
Inflatable Air Beam Standard Interface Connector
data.nasa.gov | Last Updated 2018-07-19T10:53:04.000Z
The project will develop a system of 3D-printed connectors that can be used as a kit of parts to connect inflatable air beams to form a variety of spacecraft interior outfitting components.  Examples of inflatable IVA structures that can be assembled include crew quarters, waste & hygiene compartment, crew medical restraint system, splints, science payload racks, stowage and other equipment racks, science glove box, recreational devices, other portable devices, work surfaces and other workstations, support braces, other secondary structures, etc.  This inflatable technology can enable such hardware to be packaged in much smaller volumes for delivery in logistics flights or potentially to be integrated within inflatable spacecraft, increasing trade space options.  Crew can also reconfigure spacecraft in-flight, using the ability to 3D-print custom connectors to redesign living spaces or create entirely new interior architectures to respond to mission developments or psychosocial needs. The Habitabiltiy Design Center has already prototyped scale models of inflatable crew stations and initial prototypes of a standard interface connector.  These connectors have demonstrated basic capability, but are too large relative to the airbeams for pracitcal use.  We have a notional reduced size connector and will use this concept as a starting point, to fabricate and test under operational inflation pressures.  Pending initial success, we will fabricate various connectors to provide several linear and angled connections.  This will form the basic building block for assembly of a variety of crew stations and support hardware. This research addresses HAT Needs Numbers 12.1.a and 12.1.b and provides steps towards several HAT-specified performance targets:  Bladder Material Selection: The potentially frequent cycles of inflation and deflation experienced by IVA inflatable structures will require bladder material and seal interfaces capable of resisting puncture, tear, flex cracking, or other damage due to folding, handling, or stowage temperatures.  Predictive Modeling of Deployment Dynamics: Inflation or deflation may involve imparted torques and loads that require IVA inflatable structures to be anchored to the spacecraft secondary structure prior to the initiation of inflation or deflation.  Lightweight Structures and Materials Optimization to Realize Structural System Dry Mass Savings (Minimum of 20-25%) and Operational Cost Savings: The inflatable air beam and connector technology offers significant dry mass savings over traditional IVA structural materials.  Structural mass savings for an individual crew quarters is expected to be in excess of 75% over ISS crew quarters. The intended product deliverable of this activity includes three airbeams of at least 12-inch length and no less than one each of the following: 90-degree connector, 45-degree connector, 180-degree connector, 90-degree five-airbeam connector, 60-degree three-airbeam connector.  Additionally, a test report and CAD models for each connector will constitute deliverables of this activity. Upon completion of this initial ICA effort, we will be able to demonstrate use of the airbeams in conjunction with existing Logistics to Living Modified Cargo Transfer Bags (MCTBs) to demonstrate deployable partitions as an initial example case.  This demonistration will be helpful in explaining the potential for continued investment to reduce both mass and habitability risks.  We will continue to pursue research funding for further development and will also pursue options to directly engage exploration programs to generate solutions for their specific mission architectures.
API
FY15 GRC CIF Enabling Hybrid Aerospace Structures
data.nasa.gov | Last Updated 2018-07-19T08:06:03.000Z
Novel Processing Approach to Enable Hybrid Material System Designs for Turbine and Rocket EnginesDemonstrate feasibility of using electron beam melting (EBM) for a hybrid disk, where a state-of-the-art powder metallurgy alloy (LSHR) is bonded to single-crystal Ni-alloy (LDS). The successful completion of this effort will demonstrate that direct deposition is a viable technique to successfully fabricate hybrid components of two dissimilar materials that typically are bonded to create the final structure.These type of dissimilar metal bonds is a technology that has yet to be demonstrated using additive manufacturing (AM). Only recently have monolithic advanced nickel-based superalloys AM builds been observed and reported in the literature. No known work has been published of satisfactory fabrication of even monolithic high strength powder metal disk alloys, which have been verified to be durable for rotating, fatigue-critical hardware. If successful, the work here would establish the proof-of-concept of an AM hybrid disk, as well as platform for the creation of new hybrid components.