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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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At least 181 records · Page 10

All sources NASA NTRS DOE OSTI

NASA NTRS1971

Application of recent panel flutter research to the space shuttle. Part 2 - Influence of edge clips and flow angularity

Parameters contributing to aeroelastic problems in thermal protection of space shuttle

Bohon, H. L.↗

NASA NTRS1973

Aerodynamic characteristics of a 55 deg clipped-delta-wing orbiter model at Mach numbers from 1.60 to 4.63

Wind tunnel tests to determine the supersonic aerodynamic characteristics of a delta wing space shuttle orbiter model were conducted. The model was tested at Mach numbers from 1.60 to 4.63, at nominal angles of attack from minus 2 degrees to plus 30 degrees, nominal sideslip angles of minus 4 degrees to plus 10 degrees, and Reynolds numbers from 1.8 to 2.5 times one million per foot.

Blair, A. B., Jr.↗

NASA NTRS1976

Effect of Reynolds number on the aerodynamic stability and control characteristics of a 55 deg clipped-delta-wing orbiter configuration at supersonic Mach numbers

A wind-tunnel investigation has been conducted at Mach numbers from 1.60 to 4.63 for Reynolds numbers varying from approximately 0.8 million to 10.0 million (based on body length) to determine the Reynolds number effects on the static longitudinal and lateral aerodynamic stability and control characteristics of two scale models of the Grumman H-33 space shuttle orbiter. The results indicate that for the Reynolds number range investigated, there are no Reynolds number effects on the longitudinal or lateral aerodynamic characteristics of either model with zero control deflections and only negligible effects with control deflections. The roll control is constant for both models with the possible exception of a slight increase with increases in Reynolds number up to 2.0 million at the lower Mach numbers. This very small Reynolds number effect is much more apparent for the smaller model and disappears with increasing Mach and Reynolds numbers.

Blair, A. B., Jr.↗

NASA NTRS1982

Static and unsteady pressure measurements on a 50 degree clipped delta wing at M = 0.9

Pressures were measured with Freon as the test medium. Data taken at M = 0.9 is presented for static and oscillatory deflections of the trailing edge control surface and for the wing in pitch. Comparisons of the static measured data are made with results computed using the Bailey-Ballhaus small disturbance code.

Hess, R. W.↗

NASA NTRS1986

Clip-On Extensometer

Flexural clamp eliminates problems of operator variability. Extensometer opens and closes like clothespin and placed easily on specimen. Dimensions of block specimen are 1 by 1 by 2.2 inches (2.54 by 2.54 by 5.59 centimeters). By constructing central flexure units of various widths, one adapts extensometer to handle specimens ranging from thin strips to those many inches thick. New design reduces measurement errors caused by variability among test operators.

Holmes, A. M. C.↗

NASA NTRS1988

A CLIPS prototype for autonomous power system control

The model of the system assumes a constant power source and loads (experiments) whose power demands exceed the supply. Experiments are described by their name, power consumption, time for a complete run, present status and the state of the load. The power consumption of each load is set at a constant level but can be dynamically modified by the operator. The status specifies if the experiment is running, paused, completed or failed. The state compensates for the lack of actual feedback sensor data, by signifying the stability of the load. Experiments are scheduled to keep as many running as possible with the current system limitations. A graphics oriented user interface is embedded into the rule-based system to enable an operator to easily experiment with the system.

Vezina, James M.↗

NASA NTRS1991

Passive acquisition of CLIPS rules

The automated acquisition of knowledge by machine has not lived up to expectations, and knowledge engineering remains a human intensive task. Part of the reason for the lack of success is the difference in the cognitive focus of the expert. The expert must shift his or her focus from the subject domain to that of the representation environment. In doing so this cognitive shift introduces opportunity for errors and omissions. Presented here is work that observes the expert interact with a simulation of the domain. The system logs changes in the simulation objects and the expert's actions in response to those changes. This is followed by the application of inductive reasoning to move the domain specific rules observed to general domain rules.

Kovarik, Vincent J., Jr.↗

NASA NTRS1991

A CLIPS based personal computer hardware diagnostic system

Often the person designated to repair personal computers has little or no knowledge of how to repair a computer. Described here is a simple expert system to aid these inexperienced repair people. The first component of the system leads the repair person through a number of simple system checks such as making sure that all cables are tight and that the dip switches are set correctly. The second component of the system assists the repair person in evaluating error codes generated by the computer. The final component of the system applies a large knowledge base to attempt to identify the component of the personal computer that is malfunctioning. We have implemented and tested our design with a full system to diagnose problems for an IBM compatible system based on the 8088 chip. In our tests, the inexperienced repair people found the system very useful in diagnosing hardware problems.

Whitson, George M.↗

NASA NTRS1956