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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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Experimental verification of scale factors for parawing opening characteristics with dimensional ratios from 1/1.3 to 1/3
Electromagnetic compatibility verification for Centaur and Surveyor space vehicles
OGO-3 and ATS-1 data used in experimental verification of drift shell splitting in distorted magnetosphere
Experimental verification of surface vehicle dynamics
Apollo/Saturn V automatic checkout test verification and debug program using real time computer simulation with digital space vehicle system model
Operational reliability verification of Apollo real time mission program and testing structure, discussing environment, processing, controls, response criteria, etc
Test and operations plan for functional verification unit of photoheliograph to be used with Apollo telescope mount
Verification of entry monitor system line patterns for Apollo Project
Coastal areas remote sensing instrumentation and techniques, discussing data handling and analysis and ground verification of color and multispectral imagery
On-line optimization of maintenance and verification schedules for complex system safety insurance
Redundant functional element, together with basic elements of system, constitutes a redundant system with primary and backup capability for performing particular functions with increased reliability. Methodology is applicable to design of a verification system for hypothetical complex communication system.
Verification experiment design for satellite-borne geodetic altimeter operating over seas
Interpretation of sequence of diffuse plasma resonance observed in space for verification of weak turbulence theory
Procedures for development and verification of complex software used in space shuttle data management system
Checkout and verification of space shuttle system redundant components without disrupting systems
Numerical and scale modeling interaction for spacecraft thermal design verification
Redundancy verification of parallel systems related to element MTBF and decision maker perspective involving acceptance risk of system failure
The results of the booster verification wind tunnel test are presented. These tests were conducted in a 14 x 14-inch trisonic wind tunnel utilizing a .0035 scale model. The nominal Mach numbers tested were 0.6, 0.9, 0.95, 1.0, 1.05, 1.20, 1.50, 2.0, 2.74, 3.00, 4.50 and 5.0. The angle of attack range was +5 to 40 deg. The yaw data was obtained over a range of -10 to +10 deg at fixed angles of attack of 0, 6, 15, 25, and 30 deg. The Reynolds number range was 4.2 to 6.9 million per foot. Results include elevon and canard effectiveness in pitch, and rudder, aileron, body flap, and tail effectiveness in yaw.