| ON THE DYNAMICS OF A SATELLITE STABILIZED BY WIRES. |
FEB 1966 |
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| Authors:
Robert R. Newton; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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 | The attitude of a satellite can be made stable in all three libration angles by a suitable arrangement of wires rather than rigid members to give the necessary vertical extent. In one stabilization method, four wires are connected to the main satellite body at points as far apart as possible. The other ends of the wires are connected to a small mass, yielding a pyramidal configuration. This paper analyzes the ... |
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| AN OBSERVATION OF THE SATELLITE PERTURBATION PRODUCED BY THE SOLAR TIDE. |
JUN 1965 |
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| Authors:
Robert R. Newton; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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| By analysis of perturbations in the inclinations of two nearly polar satellites, we have found a reasonable value for the tidal number k that is effective for the total of earth and ocean tides, for the semidiurnal solar tide. Similar methods can be applied to the lunar tide. The amount of tidal friction is not found accurately. We believe that the error in the friction is produced by a perturbation ... |
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| MEASUREMENTS OF THE DOPPLER SHIFT IN SATELLITE TRANSMISSIONS AND THEIR USE IN GEOMETRICAL GEODESY, |
NOV 1964 |
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| Authors:
Robert R. Newton; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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| This paper describes a type of equipment that is being developed to measure the time integral of the Doppler frequency received from a satellite, for use in geometrical geodesy. Experimental results of the instrumentation errors obtained with prototype equipment are given, and it is shown that the errors compare favorably with those from the Doppler tracking stations in the TRANET System. Some geometric results obtained with tracking stations located withing ... |
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| ORBITAL ELEMENTS FROM THE DOPPLER TRACKING OF FOUR SATELLITES, |
NOV 1964 |
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| Authors:
Robert R. Newton; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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| Tables of orbital elements are presented for the satellite 1963 49B for which no elements have been previously published. These elements were determined with the interim gravity model. They do not being with the first perigee passage of the satellite (N = O). It has been determined from the early elements of the satellite that it wwas subject, for perhaps its first 200 revolutions, to a fluctuating force with a ... |
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| CHARACTERISTICS OF THE GEOS A SPACECRAFT, |
NOV 1964 |
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| Authors:
Robert R. Newton; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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| This paper describes the GEOS A spacecraft that will be launched by the National Aeronautics and Space Administration in the late summer of 1965. Characteristics of the optical beacons, the Doppler beacons, and of the timing signals are given in detail. (Author) |
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| DAMPING OF A GRAVITATIONALLY STABILIZED SATELLITE, |
APR 1963 |
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| Authors:
Robert R. Newton; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
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| The librations of a prolate, axially symmetric satellite can be coupled to the longitudinal oscillations of a spring-mass system connected to the satellite. The oscillations of the spring can be heavily damped; thus the librations can be damped. The coupling for librations in the plane of the orbit is linear in the libration amplitude, and hence is effective for all amplitudes. Coupling for librations normal to the orbital plane is ... |
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Reports by Author
