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Radiative lifetimes measured by phase shift method for near and vacuum UV emission systems excited in low pressure barium, carbon and silicon fluoride gases
Water or bromotrifluoromethane content required in propellant Aerozine-50 /A-50/ spill to inert against ignition in air, considering fire extinguishment
Performance testing of SNAP 8 boiler
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Friction and wear tests were performed with rubbed carbon monofluorides derived from different types of carbon. Best results were given by fluorated artificial graphite and coke. The coefficient of friction is practically independent of the fluorine-to-carbon ratio x where 0 x 1, but wear decreases by a factor of 6 as x tends toward 1. For a range of variation of the severity factor (PV) expressed in Newtons/cm. sec (where P is the average pressure and V the velocity) contained between 1,000 and 200,000, the wear measured with carbon monofluoride is significantly lower than that obtained with MoS2. A transfer film or third body which protects the surfaces is formed with carbon monofluoride, and beyond 400 C, thick and fragile oxide coatings are also formed.
Experimental subjects wore goggles that restricted monocular vision to a luminous line fixed relative to the head, and they were exposed on one occasion to a straight-ahead acceleration of an aircraft and on another occasion to a tilting chair. The magnitude of change of direction of the resultant acceleration was the same on both occasions, but the perceived movement of the luminous line from the two stimuli was very different. In response to the aircraft stimulus, the oculogravic illusion was experienced and the luminous line was perceived as tilting relative to the subject, in response to the tilting chair stimulus, the line was perceived as remaining fixed relative to the subject. It was concluded that the oculogravic illusion, as experienced in the aircraft (and previously in centrifuges), is a true illusion and not merely a fact of physics.
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A summary of the activities which led to defining deterioration rates of the CF6 family of engines, a description of what was learned, and an identification of means of conserving fuel based upon the program findings are presented. The program to define the deterioration levels and modes for the CF6 family of engines involved four distinct phases: analysis of inbound engine test results, analysis of airline cruise data, analysis of airline test cell data resulting from testing of refurbished engines, and inspection of engine hardware.
Qualification testing of Combustion Engineering's AMDATA Intraspect/98 Data Acquisition and Imaging System that applies to the redesigned solid rocket motor field joint capture feature case-to-insulation bondline inspection was performed. Testing was performed at M-111, the Thiokol Corp. Inert Parts Preparation Building. The purpose of the inspection was to verify the integrity of the capture feature area case-to-insulation bondline. The capture feature scanner was calibrated over an intentional 1.0 to 1.0 in. case-to-insulation unbond. The capture feature scanner was then used to scan 60 deg of a capture feature field joint. Calibration of the capture feature scanner was then rechecked over the intentional unbond to ensure that the calibration settings did not change during the case scan. This procedure was successfully performed five times to qualify the unbond detection capability of the capture feature scanner. The capture feature scanner qualified in this test contains many points of mechanical instability that can affect the overall ultrasonic signal response. A new generation scanner, designated the sigma scanner, should be implemented to replace the current configuration scanner. The sigma scanner eliminates the unstable connection points of the current scanner and has additional inspection capabilities.
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It was concluded that the P-40 cell performed well in the -23.5 deg. C to 71 deg. range with resistive loads from 1.35 ohms to 675 ohms. Storage with subsequent discharge: tests performed to date show little self-discharge up to 2 years. And good pulse capability with 3, 2, and 1 ohm loads at 0, 24, and 49 deg. C.
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