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The vehicle related data developed during the orbital operations study are described. The interfacing activity findings have been realigned into the four basic vehicle systems as follows: (1) earth orbital shuttle (EOS), (2) research and applications module (RAM), (3) space based, ground based, manned and unmanned tugs, and (4) modular space station (MSS).
The accuracy of water vapor measurement required by modelers and forecasters at a number of scales of motion is discussed. Direct and indirect methods for operational use in obtaining atmospheric water vapor data are reviewed along with meteorological applications of water vapor data obtained by a space shuttle laboratory lidar system.
The cost effectiveness of utilizing the Nuclear Instrumentation Modular (NIM) and the Computer Automated Measurement Control (CAMAC) equipment for Spacelab payload instrumentation was determined. Representative shuttle sortie payloads were analyzed for applicability and commonality. Modification of NIM/CAMAC equipment was analyzed for its suitability in Spacelab environments and to determine the cost. NIM/CAMAC equipment usage requirements for Spacelab payloads were converted to pool size requirements and time-phased equipment procurement requirements. A programmatic estimate of the pool equipment costs and a management plan were prepared for the pool concept. The implementation and impact of CAMAC software were assessed.
The environmental charging of satellite surfaces during geomagnetic substorms is the apparent cause of a significant number of anomalous events occurring on geosynchronous satellites since the early 1970's. Electromagnetic pulses produced in connection with the differential charging of insulators can couple into the spacecraft harness and cause electronic switching anomalies. An investigation conducted to determine the response of the spacecraft surfaces to substorm particle fluxes makes use of a harness transient detector. The harness transient detector, called the Transient Event Counter (TEC) was built and integrated into the Canadian-American Communications Technology Satellite (CTS). A description of the TEC and its operational characteristics is given and the obtained data are discussed. The data show that the satellite surfaces appear to be charged to the point that discharges occur and that the discharge-induced transients couple into the wire harnesses.
The measurement program was conducted to define the characteristics of the Southeastern Virginia urban plume with emphasis on the photooxidant species. The measurement area was a rectangle approximately 200 km by 60 km centered in the Hampton Roads area of Tidewater Virginia. This area includes the cities of Norfolk, Virginia Beach, Chesapeake, Newport News, and Hampton. The data set presented includes aircraft measurements for ozone, nitrogen oxides, carbon monoxide, methane, and meteorological parameters such as dewpoint temperature. Surface level data for ozone are presented for 10 stations located throughout the test area. Comprehensive meteorological data from existing National Weather Service stations and special locations selected for the urban plume program are summarized.
Design and parametric data for the hydrogen oxygen engine used in the orbiter transfer vehicle are presented. The engine design is analyzed and minimum engine performance and man rating requirements are discussed. Candidate cycle performance, weight and tradeoff analysis, and cost estimates are reported.
Data pertinent to the launching of space probes, soundings rockets, and satellites presented in tables include launch date, time, and site; agency rocket identification; sponsoring country or countries; instruments carried for experiments; the peak altitude achieved by the rockets; and the apoapsis and periapsis for satellites. The experimenter or institution involved in the launching is also cited.
Under a NASA research program designated DAMVIBS (Design Analysis Methods for VIBrationS), four U. S. helicopter industry participants (Bell Helicopter, Boeing Vertol, McDonnell Douglas Helicopter, and Sikorsky Aircraft) are to apply existing analytical methods for calculating coupled rotor-fuselage vibrations of the AH-1G helicopter for correlation with flight test data from an AH-1G Operational Load Survey (OLS) test program. Bell Helicopter, as the manufacturer of the AH-1G, was asked to provide pertinent rotor data and to collect the OLS flight vibration data needed to perform the correlations. The analytical representation of the fuselage structure is based on a NASTRAN finite element model (FEM) developed by Bell which has been extensively documented and correlated with ground vibration tests.The AH-1G FEM was provided to each of the participants for use in their coupled rotor-fuselage analyses. This report describes the AH-1G OLS flight test program and provides the flight conditions and measured vibration data to be used by each participant in their correlation effort. In addition, the mechanical, structural, inertial and aerodynamic data for the AH-1G two-bladed teetering main rotor system are presented. Furthermore, modifications to the NASTRAN FEM of the fuselage structure that are necessary to make it compatible with the OLS test article are described. The AH-1G OLS flight test data was found to be well documented and provide a sound basis for evaluating currently existing analysis methods used for calculation of coupled rotor-fuselage vibrations.
While the 'Catalog Interoperability' (CI) project began as a NASA effort to facilitate identification, location, and access to data of interest to space and earth sciences researchers, it now has a membership encompassing numerous U.S. and international agencies as well as academic institutions. CI is creating a global network of interconnected directory, catalog, and inventory systems. Its directories contain brief summary information about data sets, and can either furnish automated links to other information systems yielding greater detail on matters of interest or indicate to whom requests for additional information can go.
A compilation is provided of measured sonic boom signature data derived from 39 supersonic flights (43 passes) of the XB-70 airplane over the Mach number range of 1.11 to 2.92 and an altitude range of 30500 to 70300 ft. These tables represent a convenient hard copy version of available electronic files which include over 300 digitized sonic boom signatures with their corresponding spectra. Also included in the electronic files is information regarding ground track position, aircraft operating conditions, and surface and upper air weather observations for each of the 43 supersonic passes. In addition to the sonic boom signature data, a description is also provided of the XB-70 data base that was placed on electronic files along with a description of the method used to scan and digitize the analog/oscillograph sonic boom signature time histories. Such information is intended to enhance the value and utilization of the electronic files.
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Data obtained by NASA VGH and V-G recorders on several Lockheed Electra airplanes operated over three domestic routes have been analyzed to determine the in-flight accelerations, airspeed practices, and landing accelerations experienced by this particular airplane. The results indicate that the accelerations caused by gusts and maneuvers are comparable to corresponding results for piston-engine transport airplanes. Oscillatory accelerations (apparently caused by the autopilot or control system) appear to occur about one-tenth as frequently as accelerations due to gusts. Airspeed operating practices in rough air generally follow the trends shown by piston-engine transports in that there is no significant difference between the average airspeed in rough or smooth air. Placard speeds were exceeded more frequently by the Electra airplane than by piston-engine transport airplanes. Generally, the landing-impact accelerations were higher than those for piston-engine transports.
This Crew Debrief Data provides support for design and development of vehicles, hardware, requirements, procedures, processes, issue resolution, lessons learned, consolidation and trending for current Programs; and much of the data is also used to support development of future Programs.
In-situ measurements of cloud Total Water Content and ice particle Median Mass Diameter have been previously collected during the High Altitude Ice Crystal – High Ice Water Content (HAIC-HIWC) and HIWC RADAR I flight campaigns. These measurements have been provided to an Ice Crystal Icing Aviation Rulemaking Advisory Committee to assess Title 14 Code of Federal Regulations (14CFR) Part 33 Appendix D, and recommend possible changes to the envelopes contained therein. Since then, NASA and the FAA have completed three additional flight campaigns in similar clouds. This article examines these new measurements and any impact they might have on Appendix D assessment. The addition of the new flight campaign data had little effect on previous estimates of the properties of high total water content regions of clouds. Some new information on the occurrence of graupel particles may be important to some ice crystal icing applications.
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Observations with the Infrared Astronomy Satellite (IRAS) and with the International Ultraviolet Explorer (IUE) satellite have stimulated the need for machine-readable data bases at infrared and ultraviolet wavelengths along with associated software. This paper describes the generation of three such data sets at the Astronomical Data Center (ADC) of the NASA-Goddard Space Flight Center (GSFC): the Catalog of Infrared Observations, the Combined List of Astronomical Sources, and the Bibliographical Index of Objects Observed by IUE 1978-82. The discussion is divided by spectral regime and includes summaries of the data products developed in each category.
To comply with U.S. Nuclear Regulatory Commission (NRC) regulations, licensees and entities authorized under Title 10 of the Code of Federal Regulations (CFR) Part 26 Section 26.3 (§ 26.3) are required to have fitness-for-duty (FFD) programs. Under § 26.3, the expectation of these FFD programs is to provide reasonable assurance that individuals who are granted unescorted access to nuclear power reactor protected areas and Category I fuel cycle facility material control areas are trustworthy, will perform their tasks in a reliable manner, are not under the influence of any substance, legal or illegal, that may impair their ability to perform their duties, and are not mentally or physically impaired from any cause that can adversely affect their ability to safely and competently perform their duties. Pacific Northwest National Laboratory (PNNL) was tasked with developing a performance monitoring program to risk inform NRC inspection and policy regarding quantitative FFD performance data. To meet this need, PNNL developed methodologies that could be implemented within a performance monitoring program. Throughout this report, these methodologies are referred to as comparative metrics. The NRC provided PNNL with 2016–2019 data from annual reporting forms and single positive test forms provided by licensees and other entities. For most of the comparative metrics, the analyses required customized processing, such as creating filtering fields, adding data fields and summaries, and joining datasets. The comparative metrics developed include: random testing rate, random policy violation rate, pre-access policy violation rate, subversion attempt rate, and number of policy violations by labor category. The comparative metrics can be used for parsing and visualizing FFD program data and monitoring FFD performance at the labor category, facility, licensee, and industry levels to risk inform NRC inspection and policy with regard to the FFD data currently collected from licensees and other entities that implement Part 26 requirements. Furthermore, these developed comparative metrics allow a more in-depth look at the FFD programs for the industry to discern trends and patterns that may warrant changes at an industry level and to inform policy decisions. These analyses should be refreshed as new FFD data become available.