Introduction to Bose Chaudhuri Hocquenghem codes
Bose-Chaudhuri-Hocquenghem codes for correcting random errors
RANDOM ERROR↗
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Results for “error correction”
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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The effect of channel errors on data compression
Synchronization and error correcting codes effect on data compression
Davisson, L. D.↗
On the solution of algebraic equations over finite fields.
Error correcting codes decoding by solving algebraic equations over finite fields
Berlekamp, E. R.↗
A learning technique for Volterra series representation.
System identification learning method based on pattern recognition involving on-line error correction procedure for Volterra series system representation
Roy, R. J.↗
Comparisons between topside and ground-based soundings.
Electron density profiles from topside ionograms compared to ground based sounding results, discussing error corrections
Jackson, J. E.↗
Self testing and repairing computer - A concept
STAR computer has five redundant modular function units, fixed store, arithmetic, memory, input, and output. Each unit is connected to a diagnostic control unit, each is coded for error detection and error correction. Separation into function units permits assembly of many different systems from the set of units.
Avizienis, A. A.↗
Cyclic codes and exponential sums
Cyclic codes for error correction noting connection with exponential sum theorems
Mceliece, R. J.↗
Navigation for the Apollo 12 lunar landing
Apollo 12 navigation for pinpoint lunar landing, correcting errors in downtrack position in guidance computer near powered descent initiation time
Schiesser, E. R.↗
Study of potential applications of digital techniques to the Apollo unified S-band communications system, phase 2 Final report
Digital data processing and error correcting code techniques applied to Apollo unified S band communication system
Source record↗
Self-testing and repairing computer Patent
Self testing and repairing computer comprising control and diagnostic unit and rollback points for error correction
Avizienis, A. A.↗
Altimeter bias recovery from range and angle observations
Error correction for GEOS-C altimeter system from range and angle observations
Berbert, J. H.↗
Adaptive telemetry systems Final report, 1 May 1968 - 1 Feb. 1971
Error correcting codes and data compression techniques for PCM adaptive telemetry systems - abstracts
Wintz, P. A.↗
On the Blizard decoding algorithm
Blizard decoding algorithm for binary linear error correcting codes
Welch, L. R.↗
Cyclic and multiresidue codes for arithmetic operations
Cyclic and multiresidue AN codes, determining single error correcting range
Garcia, O. N.↗
On the construction of a class of majority- logic decodable codes
Majority-logic decodable block codes construction by combining shorter length codes, obtaining correctable error bounds
Kasami, T.↗
Decoding binary block codes on Q-ary output channels
Error correcting binary block code decoding on Q-ary output channels /weighted erasure decoding/, considering applications
Weldon, E. J., Jr.↗
Rate 1/2 convolutional codes with complementary generators
Rate 1/2 convolutional error correcting binary codes with complementary generators, discussing synthesis and search procedure for largest free distance
Bahl, L. R.↗
Propulsion requirements for communications satellites.
The concept of characteristics thrust is introduced herein as a means of classifying propulsion system tasks related particularly to geosynchronous communications spacecraft. Approximate analytical models are developed to permit estimation of characteristic thrust for injection error corrections, orbit angle re-location, north-south station keeping, east-west station keeping, spin axis precession control, attitude rate damping, and orbit raising applications. Performance assessment factors are then outlined in terms of characteristic power, characteristic weight, and characteristic volume envelope, which are related to the characteristic thrust. Finally, selected performance curves are shown for power as a function of spacecraft weight, including the influence of duty cycle on north-south station keeping, a 90 degree orbit angle re-location in 14 days, and finally comparison of orbit raising tasks from low and intermediate orbits to a final geosynchronous station. Power requirements range from less than 75 watts for north-south station keeping on small payloads up to greater than 15 KW for a 180 day orbit raising mission including a 28.5 degree plane change.
Isley, W. C.↗