Microscopic Object Classification through Passive Motion Observations with Holographic Microscopy
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It is shown how the gravity-gradient effect may be utilized to design a long-lived, earth-pointing satellite attitude control system which requires no fuel supplies, attitude sensors or active control equipment. This two-body system is provided with a magnetic hysteresis damper which effectively damps out oscillations (librations) about the local vertical. The long rods, which must be extended in space from coiled up metal tapes, provide the required large moments of inertia and possess adequate rigidity and sufficient strength to endure the rigors of the extension process. The system is compatible with the requirements of multiple satellite launchings from a single last-stage vehicle. Analysis indicates that the gravitational torques are sufficient to keep the disturbing effects of solar radiation pressure, residual magnetic dipole moments, orbit eccentricity, rod curvature, eddy currents, and meteorite impacts within tolerable limits. It is believed that the high-performance, earth-pointing system described and analyzed in this paper represents an essential step in the development of high-capacity communications satellites requiring long life.
Engineering study and analysis of water vapor mass transfer in space suit
Volumetric flow rate of gas is maintained at a constant value independent of temperature by passing the gas through a parallel or series combination of turbulent flow and laminar flow restrictors. By proper combination of restrictors, the flow rate may be automatically made to vary as an increasing or decreasing function of temperature.
Design of three-axes seismographic system for Apollo lunar landing mission
Effects of variations in orbital altitude, lens radius of curvature, and lens included angle on physical characteristics of gravity gradient stabilized lenticular satellite configurations
Eddy-current damper and gravity-gradient rod development
Flexure rigidity and tensile strength of Dacron- glass yarn and fiberglass
Radio observations of Mercury, Venus, Mars, Saturn and Uranus compared with other observational method results
Bounds for decay times of pendulum damper vibrating in plane containing spin axis of space vehicle
Damping technique effect on performance of gravity-gradient satellite stabilization, noting means of creating restoring torques
Attitude errors of inertially coupled gravity gradient satellite with solar radiation pressure as dominant disturbance, noting slot problems in stabilized package accommodating damper motion
Feasibility of forming thin film resistors and capacitors by cold substrate deposition