Multilayer plated wire shows promise as memory device

Multilayer plated wire memory system surpasses planar thin film memories because of its high speed, simplicity, and high output. The device consists of 5 mil Be-Cu wire plated with Ni-Fe alloy about 1 micron thick crossed orthogonally by word lines

Engineering study for a mass memory system for advanced spacecrafts Final report, 1 Dec. 1969 - 1 Jul. 1970

Mass memory system for advanced spacecraf

Design and develop a MOS magnetic memory Final report, 11 Mar. - 11 Sep. 1966

Interface problems between plated wire magnetic memory and MO

Spaceborne memory organization, phase 1 Final report

Application of associative memories to data processing for future space vehicle

Multiprocessing techniques for unmanned multifunctional satellites Final report,

Simulation of on-board multiprocessor for long lived unmanned space satellite contro

Reconfigurable G and C computer study for space station use. Volume 1 - Technical summary Final report, 29 Dec. 1969 - 31 Jan. 1971

Technical summary of reconfigurable guidance and control computer for space station application - Vol.

Computer recommendations for an automatic approach and landing system for V/STOL aircraft. Volume 1 - Computer recommendations

Evaluation of digital computer for V/STOL aircraft automatic approach and landing syste

Miniature space-borne memory monthly technical report no. 2, jan. 4 - 31, 1965

High temperature testing of adhesives and metal protective platings - construction of memory syste

Spaceborne memory organization Interim report

Associative memory applications in unmanned space vehicle

Precision Pointing Control System (PPCS) system design and analysis

The precision pointing control system (PPCS) is an integrated system for precision attitude determination and orientation of gimbaled experiment platforms. The PPCS concept configures the system to perform orientation of up to six independent gimbaled experiment platforms to design goal accuracy of 0.001 degrees, and to operate in conjunction with a three-axis stabilized earth-oriented spacecraft in orbits ranging from low altitude (200-2500 n.m., sun synchronous) to 24 hour geosynchronous, with a design goal life of 3 to 5 years. The system comprises two complementary functions: (1) attitude determination where the attitude of a defined set of body-fixed reference axes is determined relative to a known set of reference axes fixed in inertial space; and (2) pointing control where gimbal orientation is controlled, open-loop (without use of payload error/feedback) with respect to a defined set of body-fixed reference axes to produce pointing to a desired target