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Quality control testing is presented for various lots of resin matrix composites. The tests conducted were filler test, resin test, fabric test, and prepreg test for lots 1, 3, 4, and 5. The results of the tests are presented in chart forms.
Quality control tests are presented for resin matrix and carbon-carbon composites. Tests performed are filler test, resin test, prepregs test, and fabric test. The test results are presented in chart form.
Test results for FM 5055B Lot No. 1 for filler testing, resin testing, fabric testing, and prepreg testing are presented in tabular and graphic format.
Test results for FM 5055B Lot No. 3 for filler testing, resin testing, fabric testing, and prepreg testing are presented in tabular and graphic format.
Test results for FM 5064 J (HITCO) Lots No. 1 (H) - 4 (H) for filler testing, resin testing, fabric testing, and prepreg testing are presented in tabular and graphic format.
Test results for FM 5839 Lot No. 4 for filler testing, resin testing, fabric testing, prepreg testing are presented in tabular and graphic format.
Filler testing, particle analysis, resin testing, fabric testing, and prepreg testing results for FM 5834 Lot 2 are presented in graphs and tables.
Test results for FM 5064J Lot No. 5 (H) for filler testing, resin testing, fabric testing, and prepreg testing are presented in tabular and graphic format.
Test results for FM 5055B Lot No. 4 and 5 for filler testing, resin testing, fabric testing, and prepreg testing are presented in tabular and graphic format.
Test results for FM 5839 Lot No. 1, 2, 3, 5, and 2R for filler testing, resin testing, fabric testing, and prepreg testing are presented in tabular and graphic format.
Filler testing, particle analysis, resin testing, fabric testing, and prepreg testing results for FM 5055B Lot 2 are presented in graphs and tables.
The Space Shuttle Redesigned Solid Rocket Motor (RSRM) Certification Program provides confidence that the RSRM and its components/subsystems meet or exceed Mission Oriented Requirements when manufactured per design requirements and specified/approved processes. Certification is based on documented results of tests, analyses, inspections, similarity, and demonstrations. Evidencing information is provided to certify that each RSRM component/subsystem satisfies design, mission related requirements and objectives.
This report contains post-test information for the Space Shuttle Orbiter Crew Hatch Jettison Test OA362 which was conducted in the Texas A&M Low Speed Wind Tunnel from 6/15/87 to 6/22/87. The test objective was to verify that the crew hatch, once jettisoned, would clear the orbiter under various simulated flight conditions. Several model hatches were used with the 0.0405-scale orbiter (Model 16-0). The model's angle of attack was set at 10, 15, and 20 degrees while the sideslip had values of minus 5, 0, and plus 5 degrees. The full scale Qbars that were simulated were 105, 128, 160, and 210 psf. In the hatch jettison mechanism itself, the plunger pressure was varied to achieve horizontal velocities of 3, 5, 7, and 20.1 feet per second model scale, and the plunger location was varied to achieve a variety of rotational velocities. The orbiter model was subjected to 122 runs with 13 different hatches. Of these, 60 were good runs.
The Hatizyo Hydrographic Observatory, which is one of the essential magnetic observatories in Japan, was established in 1979 and is currently operated by the Hydrographic Department, Maritime Safety Agency. This is the annual report compiled from the results of magnetic observations carried out at the observatory in 1994. As to the instruments used for magnetic observations, the digital recording variometer was replaced by a fluxgate magnetometer in 1986, and one set each of the proton and fluxgate magnetometers was additionally installed in January and October 1992, respectively.
The Hatizyo Hydrographic Observatory, which is one of the essential magnetic observatories in Japan, was established in 1979 and is currently operated by the Hydrographic Department, Maritime Safety Agency. This is the annual report compiled from the results of magnetic observations carried out at the observatory in 1993. As to the instruments used for magnetic observations, the digital recording variometer was replaced by a fluxgate magnetometer in 1986, and one set each of the proton and fluxgate magnetometers was additionally installed in January and October 1992, respectively.
Concentrations of Ir have been measured in 87 sediment samples from Ocean Drilling Program Site 1096 in search of evidence of fallout from the impact of the Eltanin asteroid, which occurred at 2.15 Ma, approx. 1300 km northwest of the site. An additional six samples were measured from a unique sand layer and adjacent sediments that are dated at approx. 1.6 Ma. These 93 sediment samples are all silts and muds that were deposited on a continental rise drift of the Antarctic Peninsula. No evidence of the Eltanin impact deposit was found in this study.
This document provides the results from a study into the apparent factors and causes of violations of restricted airspace, particularly temporary flight restrictions (TFRs) and air defense identification zones (ADIZs). By illuminating the reasons for these violations, this study aims to take the first step towards reducing them. The study assesses the basic characteristics of restricted airspace violations as well as the probable causes and factors contributing to violations. Results from the study imply most violations occur where the restriction has been in place for a significant amount of time prior to the violation. Additionally, the study results imply most violations are not due to the pilot simply being unaware of the airspace at the time of violation. In most violations, pilots are aware of the presence of the restricted airspace but have incorrect information about it, namely, its exact boundaries or procedures for authorized penetration. These results imply that the best means to reduce violations of restricted airspace is to improve the effectiveness of providing pilots the details required to avoid the airspace.
With the recent interest in Martian exploration using Unmanned Aerial Vehicles (UAVs), an experimental study was conducted to investigate rotor performance at Martian atmospheric conditions. Both simulation and testing of rotors is vital for evaluating rotor performance and behavior, especially for operations at Martian atmospheric densities and pressures. One critical test that has not been performed to date is helicopter forward flight testing at Martian atmospheric densities. To achieve this, a test was conducted in a tunnel facility that could be evacuated to the atmospheric pressure and density of Mars. A 40-inch-diameter rotor, roughly approximating the scale of the proposed Mars Helicopter (MH) design by the NASA Jet Propulsion Laboratory (JPL), was tested in forward flight at Mars’ atmospheric pressure at the NASA Ames Planetary Aeolian Laboratory (PAL). In this forward flight testing, the drive system of the Martian Surface Wind Tunnel (MARSWIT) was never turned on; all wind speeds read were generated either through the rotor spinning or from facility effects. The goal of this experiment was to collect rotor thrust, rotational speed, power, torque, and acoustics measurements. Subsequently, these results can be used for correlation with simulated cases using a mid-fidelity Computational Fluid Dynamics (CFD) simulation. As expected, rotor thrust and power are drastically reduced at air densities 100 times lower than at sea level on Earth. In addition, Reynolds number effects seem to play a vital role at reduced pressure that cannot be neglected in the simulation.