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The NASA test airplane, B-52B-008, was a carrier for drop tests of the shuttle booster recovery parachute system. The purpose of the test support by Boeing was to monitor the vertical loads on the pylon hooks. The hooks hold the Drop Test Vehicle to the B-52 pylon during drop test missions. The loads were monitored to assure the successful completion of the flight and the safety of the crew.
NASA s Aviation Safety Program was created for the purpose of making a significant reduction in the incidents of weather related aviation accidents by improving situational awareness. The objectives of that program are being met in part through advances in weather sensor technology, and in part through advances in the communications technology that are developed for use in the National Airspace System. It is this latter element, i.e., the improvements in aviation communication technologies, that is the focus of the Weather Information Communications project. This report describes the final flight test results completed under the WINCOMM project at the NASA Glenn Research Center of the 1090 Extended Squitter (1090ES) and VDL Mode 3 (VDL-3) data links as a medium for weather data exchange. It presents the use of 1090ES to meet the program objectives of sending broadcast turbulence information and the use of VDL-3 to send graphical weather images. This report provides the test requirements and test plans, which led to flight tests, as well as final results from flight testing. The reports define the changes made to both avionics and ground-based receivers as well as the ground infrastructure to support implementation of the recommended architecture, with a focus on the issues associated with these changes.
Test Acceptance Report for Test PG-28 at the Oregon State University High Temperature Test Facility. The purpose of this test is to investigate the impact on Lower Plenum thermal profiles and mixing due to changes in the system mass flow rate in an integral test facility scaled to General Atomics’ Modular High Temperature Gas Reactor (MHTGR) design.
Test Acceptance Report for Test PG-30 at the Oregon State University High Temperature Test Facility. The purpose of this test is to investigate the impact on Lower Plenum thermal profiles and mixing due to changes in the system mass flow rate in an integral test facility scaled to General Atomics’ Modular High Temperature Gas Reactor (MHTGR) design.
Test Acceptance Report for Test PG-31 at the Oregon State University High Temperature Test Facility. The purpose of this test is to examine the progression of the Pressure Vessel Bottom Break with Restored Forced Convection Cooling transient in an integral test facility scaled to General Atomics’ Modular High Temperature Gas Reactor (MHTGR) design.
Test Acceptance Report for Test PG-33 at the Oregon State University High Temperature Test Facility. The purpose of this test is to examine long term passive cooling in an integral test facility scaled to General Atomics’ Modular High Temperature Gas Reactor (MHGTR) design.
The RELAP5-3D computer code has been used to perform a pre-test prediction for Test PG-26 in the High Temperature Test Facility at Oregon State University. Test PG-26 will simulate a pressurized conduction cooldown transient following a trip of the primary coolant system gas circulator. The facility is initialized with a steady-state power of 700 kW and prototypic core inlet and outlet helium coolant temperatures of 259 and 687°C, respectively. Sensitivity calculations addressed the flow coastdown time, the reactor cavity cooling system flow rate and temperature, and decay power.
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A shock test of the electron-proton spectrometer structural test unit was conducted. The purpose of the shock test was to verify the structural integrity of the electron-spectrometer design and to obtain data on the shock response of the electronics and electronic housing. The test equipment is described and typical shock response data are provided.
Qualification tests of the electron-proton spectrometer test unit are presented. The tests conducted were: (1) functional, (2) thermal/vacuum, (3) electromagnetic interference, (4) acoustic, (5) shock, (6) vibration, and (7) humidity. Results of each type of test are presented in the form of data sheets.
The detection, location, and identification of suspected underground nuclear explosions (UNEs) are global security priorities that rely on integrated analysis of multiple data modalities for uncertainty reduction in event analysis. Vegetation disturbances may provide complementary signatures that can confirm or build on the observables produced by prompt sensing techniques such as seismic or radionuclide monitoring networks. For instance, the emergence of non-native species in an area may be indicative of anthropogenic activity or changes in vegetation health may reflect changes in the site conditions resulting from an underground explosion. Previously, we collected high spatial resolution (10 cm) hyperspectral data from an unmanned aerial system at a legacy underground nuclear explosion test site and its surrounds. These data consist of visible and near-infrared wavebands over 4.3 km 2 of high desert terrain along with high spatial resolution (2.5 cm) RGB context imagery. In this work, we employ various spectral detection and classification algorithms to identify and map vegetation species in an area of interest containing the legacy test site. Here, we employed a frequentist framework for fusing multiple spectral detections across various reference spectra captured at different times and sampled from multiple locations. The spatial distribution of vegetation species is compared to the location of the underground nuclear explosion. We discover a difference in species abundance within a 130 m radius of the center of the test site.
A three-phase helical induction electromagnetic pump, designed for the boiler-feed pump of a potassium Rankine-cycle space power system, was built and tested. The pump was tested over a range of potassium temperatures from 900 to 1400 F, flow rates from 0.75 to 4.85 lb/sec, developed pressures up to 340 psi, net positive suction heads (NPSH) from 1 to 22 psi, and NaK coolant temperatures from 800 to 950 F. The maximum efficiency at the pump design point of 3.25 lb/sec flow rate, 240 psi developed pressure, 1000 F potassium inlet temperature, and 800 F NaK coolant temperature was 16.3 percent. The tests also showed successful operation of the pump at an NPSH as low as 1.5 psi without cavitating.
Two near optimum full-scale Viking aeroshell prototypes (140 deg ring-stiffened conical shells), differing only in base ring size, were designed and tested under uniform pressure to buckling failure. Part I describes the computerized design procedure which iterates between a design program based on approximate equations to determine skin and ring gages and ring spacings, and a sophisticated system of shell of revolution programs for more accurate analysis as a basis for redesign. Part II discusses fabrication techniques, test procedures, and test results. Both buckling and prebuckling data are compared with the theoretical predictions of Part I. Appropriate buckling knockdown factors for this type of construction are identified. Measured strains in skin and rings agreed well with theoretical predictions and the buckling pressure was in close agreement with the design ultimate pressure.
The structural test unit of the electron-proton spectrometer was tested to a random vibration spectra and to a sinusoidal resonant search to comply with the requirements of a verification plan for the spectrometer. The test item consisted of mass simulated electronic and printed circuit boards mounted in a flight type electronic housing. The arrangement, center of gravity, and weight were as proposed for flight units.