Some aspects of the distribution of meteoric flux about an attractive center.
Investigation of factors influencing rate of meteoroid impact on satellite
SPACECRAFT MOTION↗
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A determination of earth equatorial ellipticity from seven months of syncom 2 longitude drift.
Earth equatorial ellipticity measurements from longitude drift observations of stationary Syncom II satellite
EARTH SHAPE↗
An approximate solution of the equations of motion for arbitrary rotating spacecraft
Approximate analytical solution for motion of arbitrary rotating spacecraft with variable disturbance functions
ROTATING BODY↗
Analysis of lunar and solar effects on the motion of close earth satellites
Lunar and solar effects on motion of close earth satellites
SATELLITE PERTURBATION↗
Flight control for a manned orbital space station.
Flight control system for manned orbital space station using momentum storage devices and reaction control to counteract gravity effects and aerodynamic disturbances
SATELLITE PERTURBATION↗
Motion of a spinning satellite during the deployment of n asymmetrical appendages.
Motion of spinning satellite during deployment of n asymmetrical appendages, noting Pioneer spacecraft
SPIN STABILIZATION↗
Motion of a spinning satellite during the deployment of asymmetrical appendages.
Motion of spinning satellite during deployment of n asymmetrical appendages, noting Pioneer spacecraft
PIONEER SPACE PROBE↗
Effects of the solar and lunar tides on the motion of an artificial earth satellite
Effects of solar and lunar tides on motion of artificial earth satellite
SOLAR EFFECT↗
The structural and librational dynamics of a satellite deploying flexible booms or antennas.
Structural and librational dynamics of satellite deploying flexible booms or antennas
LIBRATIONAL MOTION↗
Motion and stability of a spinning spring-mass system in orbit.
Motion and stability of spinning spring-mass system in orbital plane with equation linearization
GRAVITY GRADIENT SATELLITE↗
The influence of material elasticity on satellite motions.
Material elasticity effects on planar librational motion of rigid satellite under action of gravity gradients
GRAVITY GRADIENT SATELLITE↗
Application of the Delaunay Method to the Artificial Satellites of the Moon
Perturbations in motion of three fictitious moon satellites
Lemekhova, E. N.↗
Geophysical implications of satellite determinations of the earth's gravitational field.
Gravitational field variations determined from satellite orbit perturbations, suggesting stiff lower mantle as source
Kaula, W. M.↗
Computer derivation of short-period lunar perturbations
Short period lunar perturbation on satellites by computer program with Fortran statements, considering errors, program output and table driven algebraic processors
Cherniack, J. R.↗
Earth-reflected radiation pressure
Satellite orbit perturbation due to earth reflected or reradiated solar radiation pressure
Smith, D. E.↗
Tesseral resonance on IMP-4 orbit
Tesseral harmonics of Explorer 34 satellite orbit perturbation in time of perigee passage due to third harmonic of earth gravitational field
Lowrey, B. E.↗
Tidal parameters from the variation of inclination of GEOS-1 and GEOS-2
Analysis of the luni-solar tidal perturbations of the inclination of GEOS-1 and GEOS-2 has yielded the values 0.22 and 0.31 respectively for the apparent second degree Love number. For GEOS-1 a new purely numerical method involving osculating elements was employed. For GEOS-2 it was necessary to analyze the variations of the mean elements because of the very long period (450 days) of the dominant solar tidal perturbation. The disparate values indicate that the simple second degree zonal harmonic model of the tidal potential is accommodating other effects in addition to those caused by the solid earth tides. A recent paper by Lambeck et al. (1973) indicates that ocean tide effects have significant perturbations on satellite orbits and cannot be neglected.
Douglas, B. C.↗
A unified approach for the application of general perturbation theories to the artificial satellite problem
An Encke-type method is developed as well as a variation of parameters method, both of which use a non-Keplerian reference orbit. The regularized time is used in the numerical integration and the optimum value of n is found for each type of orbit investigated. Accuracy and computation time comparisons are made with a classical Cowell method. It should be noted that the element formulations developed and tested were found to be exceptionally numerically stable in the sense that it was possible to achieve numerical consistency order of very long integration periods - a property not available with the Cowell formulation - and therefore these formulations may be helpful for high precision calculations.
Alfriend, K. T.↗