Engineering topics
Meyer, R.
Publications and source records attributed to Meyer, R..
Aviation applications of NASA's global differential GPS system
In this article we describe the aviation applications of the system, and describe the extensive flight tests and the performance validation methodology.
Demonstration of decimeter-level real-time positioning of an airborne platform
We demonstrate the ability of the NASA Global Differential GPS System to support 10 to 20 cm accurate real-time airplane positioning, anywhere in the world, independent of local navigational aids or infrastructure.
Recent results and activities of the IGS analysis center at JPL
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Computer-based instruction and reference documentation system for the orbit determination program
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Shuttle/TDRSS Ku-band downlink study
Assessing the adequacy of the baseline signal design approach, developing performance specifications for the return link hardware, and performing detailed design and parameter optimization tasks was accomplished by completing five specific study tasks. The results of these tasks show that the basic signal structure design is sound and that the goals can be met. Constraints placed on return link hardware by this structure allow reasonable specifications to be written so that no extreme technical risk areas in equipment design are foreseen. A third channel can be added to the PM mode without seriously degrading the other services. The feasibility of using only a PM mode was shown to exist, however, this will require use of some digital TV transmission techniques. Each task and its results are summarized.
An analytical procedure for evaluating shuttle abort staging aerodynamic characteristics
An engineering analysis and computer code (AERSEP) for predicting Space Shuttle Orbiter - HO Tank longitudinal aerodynamic characteristics during abort separation has been developed. Computed results are applicable at Mach numbers above 2 for angle-of-attack between plus or minus 10 degrees. No practical restrictions on orbiter-tank relative positioning are indicated for tank-under-orbiter configurations. Input data requirements and computer running times are minimal facilitating program use for parametric studies, test planning, and trajectory analysis. In a majority of cases AERSEP Orbiter-Tank interference predictions are as accurate as state-of-the-art estimates for interference-free or isolated-vehicle configurations. AERSEP isolated-orbiter predictions also show excellent correlation with data.
On the use of piecewise-linear functions in suboptimal feedback control laws
Suboptimal feedback control law for second order nonlinear systems with quadratic performance index, determining power series coefficients