Absolute-stability test for discrete systems.
Numerical absolute stability test for nonlinear discrete systems using bilinear transformation
Siljak, D.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Matching flow characteristics of standard shutoff valves eliminates need for custom fabricated valves
Standard high pressure valves are used in low pressure fluid system testing when a substantial system pressure increase is required. The flow-vs-valve stroke is matched with that of the valves being replaced. Some correction to the plug contour may be necessary.
Bevan, A. F.↗
Apollo support equipment. Digital test command system models C14-264 through C14-268 - Maintenance handbook
Explore the source record for details and available documents.
Source record↗
System for testing pressure probes using a simple sinusoidal pressure generator
Pressure probe response determined by sinusoidal pressure generator
Englund, D. R., Jr.↗
A study of voltage breakdown in spacecraft systems from test and flight experience
Voltage breakdown in spacecraft electronic circuitry during tests and flight conditions
Mercy, K. R.↗
Testing electronic systems for aerospace
Multiterminal electronic networks computerized fault detection based on linearized Taylor expansion algorithm
Neu, E. C.↗
A plan for application system verification tests. The value of improved meteorological information, volume 2
For abstract, see volume 1 N77-12634.
Source record↗
A plan for application system verification tests--The value of improved meteorological information: Executive summary
For abstract, see volume 1 N77-12634.
Source record↗
DSN system performance test Doppler noise models; noncoherent configuration
The newer model for variance, the Allan technique, now adopted for testing, is analyzed in the subject mode. A model is generated (including considerable contribution from the station secondary frequency standard), and rationalized with existing data. The variance model is definitely sound; the Allan technique mates theory and measure. The mean-frequency model is an estimate; this problem is yet to be rigorously resolved. The unaltered defining expressions are noncovergent, and the observed mean is quite erratic.
Bunce, R.↗
Hybrid random-sound test-control system
Controller develops gain-control signals by comparing detected sound levels in each band with reference set levels. By eliminating multiplexing network and single clock used in digital system, design allows servocontrol rate for each band to be adjusted independently.
Woodbury, R. C.↗
Preliminary design and development of a reflectance spectrometer instrument
An improved design for the reflectance spectrometer is described to be used on various terrestrial body missions. These improvements were made on the original Lunar Polar Orbiter design. These include a larger entrance mirror, rectangular aperture, multiple optical beams, spatial resolution, and a bandwidth extension to 5 microns. In addition, detailed electronic designs were produced for a charge amplifier and an amplifier/demodulator/integrator. Design of a microprocessor driven test system was begun. Laboratory tests were performed on a tuning fork chopper.
Mccord, T. B.↗
Rubidium frequency standard test program for NAVSTAR GPS
Test data of the RFS Program in the Production phase and computer automation are presented, as an essential element in the evaluation of the RFS performance in a simulated spacecraft environment. Typical production test data will be discussed for stabilities from 1 to 100,000 seconds averaging time and simulated time error accumulation test. Also, design considerations in developing the RFS test systems for the acceptance test in production are discussed.
Koide, F.↗
Block 1, phase 1 very long baseline interferometry implementation
The Block 1, phase 1 VBLI System, implemented in the Deep Space Network and currently undergoing system testing, is discussed. The system can be characterized as the modification of existing equipment and the addition of new software in the 64 m subnet and the addition of new hardware and software in the Network Operations and Control Center. It is to be operational to support Voyager project navigation requirements and is to provide, on a weekly basis, the information related to station clock synchronization, UT1, and polar motion.
Wilcher, J. H.↗
The large scale microelectronics Computer-Aided Design and Test (CADAT) system
The CADAT system consists of a number of computer programs written in FORTRAN that provide the capability to simulate, lay out, analyze, and create the artwork for large scale microelectronics. The function of each software component of the system is described with references to specific documentation for each software component.
Gould, J. M.↗
Leak Tester for Cryogenic Flowlines
Gas chromatography measures leakage into cavity surrounding joint under test. System surrounds joint being tested with sealed cavity. Presence of leakage gas in cavity monitored by gas chromatograph. Leakage rate found by multiplying relative leakage gas concentration by mass flow rate of purge as into cavity.
Mortensen, G. D.↗
Propulsion control technology
A brief discussion of digital jet engine control systems is given. Performance tests, systems integration, and redundancy are discussed.
Beattie, E. C.↗
SRB thermal protection systems materials test results in an arc-heated nitrogen environment
The external surface of the Solid Rocket Booster (SRB) will experience imposed thermal and shear environments due to aerodynamic heating and radiation heating during launch, staging and reentry. This report is concerned with the performance of the various TPS materials during the staging maneuver. During staging, the wash from the Space Shuttle Main Engine (SSME) exhust plumes impose severe, short duration, thermal environments on the SRB. Five different SRB TPS materials were tested in the 1 MW Arc Plasma Generator (APG) facility. The maximum simulated heating rate obtained in the APG facility was 248 Btu/sq ft./sec, however, the test duration was such that the total heat was more than simulated. Similarly, some local high shear stress levels of 0.04 psia were not simulated. Most of the SSME plume impingement area on the SRB experiences shear stress levels of 0.02 psia and lower. The shear stress levels on the test specimens were between 0.021 and 0.008 psia. The SSME plume stagnation conditions were also simulated.
Wojciechowski, C. J.↗