A design study of a 350 kWe out-of-core nuclear thermionic converter system
Out-of-core nuclear thermionic converter system for high power levels
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Out-of-core nuclear thermionic converter system for high power levels
Developing structure, payload, communication and data handling subsystems for ERTS
Developing attitude control, orbit adjust, thermal, power, electrical integration, integration test and launch support subsystems for ERTS
Component parametric data and initial integrated analyses for potassium turboalternators for spacecraft
V/STOL concepts for short haul commercial aircraft compared for gross weight, operating cost, gust sensitivity and noise levels
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Parametric data of heat exchanger size and weight for nuclear reactor Brayton cycle space power systems
Modifications to reduce fan-compressor noise level of DC-8 aircraft - Part 2
Storage effects on performance of silver zinc and silver cadmium batteries
Nuclear Brayton cycle heat exchanger and duct assembly
Space shuttle high pressure, hydrogen oxygen auxiliary propulsion subsystem designs, weight sensitivities, and operating performances
Modifications and computational tasks required for aeroelastic capability in NASTRAN
Development of requirements for auxilary propulsion system used with baseline orbiter and booster of space shuttle system
Development and characteristics of space shuttle auxiliary propulsion system based on vehicle configuration and vehicle/mission requirements
The feasibility and the noncontact operation of the self-acting seal was demonstrated over a range of simulated gas turbine engine conditions from 200 to 500 ft/sec sliding speed. Sealed pressure differentials were 50 to 300 psi and sealed temperatures were 150 to 1200 F. Low leakage (about 1/10 that of conventional labyrinth seals) was exhibited in two endurance runs (200 and 338 hr) at 400 ft/sec, 200 psi and 1000 F (gas temperature). For these endurance runs, the self-acting pad wear was less than 3.8 micrometers (0.00015 in.); this low wear was attributed to the noncontact operation of the primary seal. Operating problems identified were fretting wear of the secondary seal and erosion of the primary seal by hard particles.
Skew test data are presented on a tape recorder transport with a double capstan drive for a 100 KHz tone recorded on five tracks simultaneously. Phase detectors were used to measure the skew when the center channel was the 100 KHz reference.
The means of storing multispectral, high resolution sensor data on an Earth observing satellite are studied. It is concluded that this is best done digitally on a multi-track, longitudinal, magnetic tape recorder. The machine proposed will store 8 X 10 to the 10th power bits of data on 1040 m of 51 mm-wide magnetic tape mounted on two co-planar reels.
The sampling probe to measure the free stream gas composition in a hypersonic wind tunnel is described. Using a free expansion of the continuum flow, a series of sampling inlet-pumping stages is evaluated. Mass analysis is carried out with a quadrupole mass spectrometer employing a crossed electron beam, molecular beam ion source, and an off-axis electron multiplier. The spatial distribution of the sampled molecular flux and the pumping requirements are evaluated for varying inlet conditions of gas density and flow velocity. The signal-to-noise ratio of the molecular beam formed by this series of coaxial inlets is also determined. The signal-to-noise ratio of the unscattered flux is sufficiently high that an unambiguous determination of the beam composition and of the free stream gas properties can be made. The magnitude of the detected signal is sufficiently high that measurement of trace constituents two orders of magnitude below the primary beam signal can be made.