Evaluation of concepts for reuse of large booster nozzles.
Large booster nozzle reuse, discussing design, refurbishment, performance, costs and test evaluation
Bailey, R. L.↗
SEARCH · Engineering Papers
Results for “test and evaluation”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Inchfab – A ultra-low-cost micro and nanofabrication platform (CRADA Final Report)
Inchfab Inc. is developing an ultra-low cost suite of micro- and nanofabrication platforms which allows greater process flexibility and short development cycles. In traditional manufacturing environments, virtually all fabrication happens on 6-12” substrates–which requires prohibitively expensive fabrication facilities (“fabs”). By scaling the substrate size down to 1-2”, Inchfab reduces the capital cost and physical footprint of a fab by two to three orders of magnitude, while still retaining a similar level of performance. Additionally, the design of the Inchfab will allow users to develop fully-customizable fabrication processes, accommodating non-traditional materials and process diversity. Ultimately, the Inchfab platform will enable innovative device designs which currently have limited possibility of being realized. This CRADA project worked on preliminary research to test the feasibility of the Inchfab platform by utilizing equipment at Berkeley Lab to evaluate test samples and characterize equipment performance.
42 ENGINEERING↗
Study of monopropellants for electrothermal thrusters: Analytical task summary report
The feasibility of operating small thrust level electrothermal thrusters is determined with monopropellants other than MIL-grade hydrazine. The work scope includes analytical study, design and fabrication of demonstration thrusters, and an evaluation test program where monopropellants with freezing points lower than MIL-grade hydrazine are evaluated and characterized to determine their applicability to electrothermal thrusters for spacecraft attitude control. Results of propellant chemistry studies and performance analyses indicated that the most promising candidate monopropellants to be investigated are monomethylhydrazine, Aerozine-50, 77% hydrazine-23% hydrazine azide blend, and TRW formulated mixed hydrazine monopropellant (MHM) consisting of 35% hydrazine-50% monomethylhydrazine-15% ammonia.
Kuenzly, J. D.↗
Noise measurements at Stockton airport obtained during engineering evaluation of two-segment approaches in a DC-8-61 aircraft
A series of noise measurements were made during engineering evaluation tests of the two segment approach using a DC-8-61. The two approaches evaluated were: (1) ILS, 2.9 deg glide slope using 50 deg flaps; and (2) two segment 5.5 deg/2.9 deg glide slope, using 50 deg flaps and lower segment intercept altitude of 575 feet. Measurements were made at twelve sites underneath and to the side of the flight path.
Glass, R. E.↗
Wide Panel Testing Technique for Evaluating Repair Weld Strengths
This paper describes a new tensile testing technique for evaluating the overall effect of a repair weld on the strength of a welded joint. Previously, repair weld strengths have been evaluated using one-inch width tensile specimens, but this technique does not capture all of the effects that result from a repair. The new technique involves testing of "wide panel" tensile specimens which contain the full length of a repair weld within a longer initial weld, allowing the specimen to capture the combined effects of residual stresses, local strength degradation, and load redistribution around a repair. The development of strains in the repair area of standard aluminum alloy specimens and new high-performance aluminum-lithium alloy specimens was observed and evaluated using photoelastic material. The results of this evaluation show an increased sensitivity to repair welding residual stresses in the aluminum-lithium alloy specimens.
Rogers, Patrick R.↗
The development and flight test of an electronic integrated propulsion control system
Advanced technical features of the electronic integrated propulsion control system (IPCS) and flight evaluation tests of IPCS (F-111E with TF30-P-9 engines as test vehicle) are described. Nine baseline flight tests and 15 IPCS flight tests were conducted. Instrumentation, data acquisition and data processing systems, software maintenance procedures, flight test procedures, flight safety criteria, flight test results, and ground and flight testing of the aircraft system are described. Advantages conferred by IPCS include: faster accelerations (both gas generator and afterburner performance), better thrust and flight control, reduced flight idle thrust, reduced engine ground trim, extended service ceiling, automatic stall detection, and stall recovery detection.
Johnson, H. J.↗
Model Test Bed for Evaluating Wave Models and Best Practices for Resource Assessment and Characterization
A wave model test bed is established to benchmark, test and evaluate spectral wave models and modeling methodologies (i.e., best practices) for predicting the wave energy resource parameters recommended by the International Electrotechnical Commission, IEC TS 62600-101Ed. 1.0 ©2015. Among other benefits, the model test bed can be used to investigate the suitability of different models, specifically what source terms should be included in spectral wave models under different wave climate conditions and for different classes of resource assessment. The overarching goal is to use these investigations to provide industry guidance for model selection and modeling best practices depending on the wave site conditions and desired class of resource assessment. Modeling best practices are reviewed, and limitations and knowledge gaps in predicting wave energy resource parameters are identified.
13 HYDRO ENERGY↗
Investigation of test methods, material properties, and processes for solar cell encapsulants
A study of potentially useful low cost encapsulation materials for the Flat-Plate Solar Array project is discussed. The goal is to identify, evaluate, test and recommend encapsulant materials and processes for the production of cost-effective, long life solar cell modules. Technical investigations included studies of aging and degradation of candidate encapsulation materials, continued identification of primers for durable bonding of module interfaces, continued evaluation of soil resistant treatments for the sunlit surface of the module and testing of corrosion protective coatings for use low cost mild steel substrates.
Willis, P. B.↗
Evaluation of Candidate Millimeter Wave Sensors for Synthetic Vision
The goal of the Synthetic Vision Technology Demonstration Program was to demonstrate and document the capabilities of current technologies to achieve safe aircraft landing, take off, and ground operation in very low visibility conditions. Two of the major thrusts of the program were (1) sensor evaluation in measured weather conditions on a tower overlooking an unused airfield and (2) flight testing of sensor and pilot performance via a prototype system. The presentation first briefly addresses the overall technology thrusts and goals of the program and provides a summary of MMW sensor tower-test and flight-test data collection efforts. Data analysis and calibration procedures for both the tower tests and flight tests are presented. The remainder of the presentation addresses the MMW sensor flight-test evaluation results, including the processing approach for determination of various performance metrics (e.g., contrast, sharpness, and variability). The variation of the very important contrast metric in adverse weather conditions is described. Design trade-off considerations for Synthetic Vision MMW sensors are presented.
Alexander, Neal T.↗
Development of a Heterogeneous sUAS High-Accuracy Positional Flight Data Acquisition System
Recently, a heterogeneous FDAS, consisting of a diverse range of instruments was developed to support acoustic flight research programs at NASA Langley Research Center. In addition to a conventional GPS to measure latitude, longitude and altitude, the FDAS also utilizes a small, light-weight, low-cost DGPS system to obtain centimeter accuracy to measure the distance traveled by sound from a sUAS vehicle to a microphone on the ground. Acoustic flight testing using the FDAS installed on several different sUAS platforms has been conducted in support of the NASA CAS DELIVER and ERA ITD projects (Reference 1). The first FDAS prototype was assembled and implemented in the acoustic/flight measurement system in December 2014 to support DELIVER acoustic flight tests. Evaluation of the system performance and results from the data analyses were used to further test, develop and enhance the FDAS over a six-month period to support acoustic flight research for the ERA.
McSwain, Robert G.↗
Laboratory test methods for evaluating the fire response of aerospace materials
The test methods which were developed or evaluated were intended to serve as means of comparing materials on the basis of specific responses under specific sets of test conditions, using apparatus, facilities, and personnel that would be within the capabilities of perhaps the majority of laboratories. Priority was given to test methods which showed promise of addressing the pre-ignition state of a potential fire. These test methods were intended to indicate which materials may present more hazard than others under specific test conditions. These test methods are discussed and arranged according to the stage of a fire to which they are most relevant. Some observations of material performance which resulted from this work are also discussed.
Hilado, C. J.↗
Saturn IB program. Test report for flexible hose, 1/4-inch, 3000-psig Aeroquip corporation part number 675003-4-0420, NASA DRAWING number 75M11337-4-0420
Performance evaluation tests on flexible pressure hose in Saturn ground support equipment
TEST PROGRAM↗
Energy Efficient High-Pressure Turbine Leakage Technology Report
The leakage test program was one of such supporting technology programs structured to provide guidance to the Energy Efficient Engine High Pressure Turbine Component Design Effort. Leakage reduction techniques were identified and evaluated. Test models were used to simulate component leak paths and to evaluate leakage reduction techniques. These models simulated the blade/disk attachment, the vane inner platform attachment, and the vane outer platform attachment combined with the blade outer airseal. Disk blade attachment testing indicated that leakage in this area could be reduced to very low levels by paying careful attention to the tolerances along the contact surface between the blade vibration damper and the blade platform contact surface. The aim of feather seal testing was to achieve a goal for an effective leakage gap of one mil (.001 inch) per inch of feather seal length. Results indicated that effective gaps even below the goal level were achievable by (1) maintaining close tolerances between feather seals and their slots to minimize end gaps and limit seal rotation, (2) avoiding feather seal overlap, and (3) minimizing feather seal intersections. W seals were shown to be effective leakage control devices. Wire rope, in its present state of development, was shown not to be an effective sealing concept for application to the component design.
Gardner, W. B.↗
A GENERIC MICROGRID CONTROLLER
The main objective of this project was to develop and test a Generic Microgrid Controller (GMC) that provides (1) seamless islanding and reconnection of the microgrid, (2) efficient, reliable, and resilient operation of the microgrid with the required power quality, whether islanded or grid-connected, (3) existing and future ancillary services to the larger grid, (4) the capability for the microgrid to serve the resiliency needs of participating communities, (5) communication with the electric grid utility as a single controllable entity, and (6) increased reliability, efficiency and reduced emissions. The GMC developed under this project was designed to facilitate the deployment of microgrids, to be easily adapted to various microgrid configurations, and reduce up-front engineering costs associated with the design and development of microgrid controllers. Specifically, the GMC: 1. Provides a control structure amenable to accommodating an array of microgrid configurations and a portfolio of functional requirements; 2. Possesses a high level architecture that can readily be adopted by commercial suppliers; 3. Supports unlimited nesting of conforming microgrid control schemes; 4. Integrates into a full-featured Energy Management System (EMS) as a module. A select set of microgrids, operating a variety of microgrid configurations, served as “collaborating microgrid partners” in the project and assured thereby that the GMC developed under this program can readily be applied to microgrids of different sizes, and equipped with various resources, attributes, and equipment. Collaborating microgrid partners included the UCI Medical Center), the Port of Los Angeles, Port of Long Beach, and the Irvine Ranch Water District. The objectives of the project were achieved in two phases: (Phase I) Research, Development and Design (“Design”), and (Phase II) Testing, Evaluation, and Verification (“TEV”). In Phase I, specifications were developed for the GMC and a detailed test plan was established to test the functional requirements of the GMC. The GMC addresses two core functions, transition and dispatch, as well as several optional higher level functions such as economic dispatch, and renewable and load forecasting.
24 POWER TRANSMISSION AND DISTRIBUTION↗
Propulsion-airframe interactions predictability
An illustration of the possible magnitude of the transonic performance prediction problem is shown. These results derived from a careful and systematic set of tests run on a jet effects model, an aerodynamic and force model, and a pressure model, evaluated test techniques and wind tunnel effects. The results were then carefully compared with flight test data where significant discrepancies in zero-lift drag were observed. A vigorous review of the test techniques identified a number of potential error sources. Some of these were thought to be aircraft roughness and protuberances, tunnel anomalies, sting/model support corrections, and hot gas effects. In addition, there were questions on model metric splitline location and magnitude of corrections for scale and Reynolds number. Flight test inlet/engine characteristics were thought to differ, also, from those of the calibration settings in the ground facilities.
Smith, R. H.↗
Space shuttle Production Verification Motor 1 (PV-1) static fire
All inspection and instrumentation data indicate that the PV-1 static test firing conducted 18 Aug. 1988 was successful. With the exception of the intentionally flawed joints and static test modifications, PV-1 was flight configuration. Fail-safe flaws guaranteeing pressure to test the sealing capability of primary O-rings were included in the aft field joint, case-to-nozzle joint, and nozzle internal Joint 5. The test was conducted at ambient conditions, with the exception of the field joints and case/nozzle joints which were maintained at a minimum of 75 F. Ballistics performance values were within specification requirements. The PV-1 motor exhibited chamber pressure oscillations similar to previously tested Space Shuttle redesigned solid rocket motors, particularly QM-7. The first longitudinal mode oscillations experienced by PV-1 were the strongest ever measured in a Space Shuttle motor. Investigation into this observation is being conducted. Joint insulation performed as designed with no evidence of gas flow within unflawed forward field joints. The intentionally flawed center and aft case field joint insulation performance was excellent. There was no evidence of hot gas past the center field joint capture feature O-ring, the case-to-nozzle joint primary O-ring, or the aft field joint primary O-ring. O-ring seals and barriers with assured pressure at the flaws showed erosion and heat effect, but all sealed against passage of hot gases with the exception of the aft field joint capture feature O-ring. There was no evidence of erosion, heat effect, or blowby on any O-ring seals or barriers at the unflawed joints. Nozzle performance was nominal with typical erosion. Post-test examination revealed that the forward nose ring was of the old high performance motor design configuration with the 150-deg ply angle. All nozzle components remained intact for post-test evaluation. The thrust vector control system operated correctly. The water deluge system, CO2 quench, and other test equipment performed as planned during all required test operations.
Source record↗
Cyclic hot firing results of tungsten-wire-reinforced, copper-lined thrust chambers
An advanced thrust liner material for potential long life reusable rocket engines is described. This liner material was produced with the intent of improving the reusable life of high pressure thrust chambers by strengthening the chamber in the hoop direction, thus avoiding the longitudinal cracking due to low cycle fatigue that is observed in conventional homogeneous copper chambers, but yet not reducing the high thermal conductivity that is essential when operating with high heat fluxes. The liner material produced was a tungsten wire reinforced copper composite. Incorporating this composite into two hydrogen-oxygen test rocket chambers was done so that its performance as a reusable liner material could be evaluated. Testing results showed that both chambers failed prematurely, but the crack sites were perpendicular to the normal direction of cracking indicating a degree of success in containing the tremendous thermal strain associated with high temperature rocket engines. The failures, in all cases, were associated with drilled instrumentation ports and no other damages or deformations were found elsewhere in the composite liners.
Kazaroff, John M.↗
Phased Array Ultrasonic Evaluation of Space Shuttle Main Engine (SSME) Nozzle Weld
This viewgraph presentation gives an overview of the phased array ultrasonic evaluation of the Space Shuttle Main Engine (SSME) nozzle weld. Details are given on the nondestructive testing evaluation approach, conventional shear wave and phased array techniques, and an x-ray versus phased array risk analysis. The field set-up was duplicated to the greatest extent possible in the laboratory and the phased array ultrasonic technique was developed and validated prior to weld evaluation. Results are shown for the phased array ultrasonic evaluation and conventional ultrasonic evaluation results.
James, Steve↗