SEARCH · Search NASA
Results for “MINITRACK”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
NASA minitrack interferometer refraction corrections
Influence of atmospheric refraction on minitrack interferometer system and correction procedures for computation accuracy
Recovery of thrust magnitude from minitrack data for the SERT-2 spacecraft
An estimation of the thrust magnitude of the Space Electric Rocket Test (SERT) engine is obtained. This estimation is based on changes in the SERT-2 spacecraft orbit as determined from tracking data by using a revised definitive orbit determination system which includes the effect of thrust upon the motion of a spacecraft in general and the SERT-2 satellite in particular. The results of these computations are found to be in good agreement with values of acceleration as determined by an on-board accelerometer. A discussion of the mathematical model used to obtain the numerical results is also presented.
136 MHz interferometer error due to galactic nucleus.
Extraneous interfering signals are discussed which limit the basic accuracy of the 136 MHz Minitrack radio-interferometer system providing electrical phase data from which direction cosines for determining spacecraft orbits are generated. In particular, the fundamental error due to interference caused by the passage of the galactic nucleus is investigated. An expression is developed for the lower bound of the phase error when the noise source is not uniformly distributed across the Minitrack's zenith-pointed fan beam. In addition, the threshold of the Minitrack input power levels is determined below which the electrical phase is no longer determined unambiguously. The effect of the passage of the galactic nucleus coincident with the presence of a spacecraft is analyzed, and the corresponding phase error established.
The effects of tracking station coordinate uncertainties on GEOS-2 orbital accuracy
Laser and minitrack observational data from GEOS-2 collected during the period April 23, 1971 to May 1971, have been used for the purpose of assessing the influence of tracking station location on the accuracy of orbit determination. These data were processed using a unified set of coordinates for the tracking station locations. Concurrently, these data were processed using nonunified station locations referred to a variety of geodetic datums. The resultant orbits based on the two different sets of station locations were compared and relative differences in the position of the satellite were determined. Differences between the two groups of orbits fitted over four-day data spans ranged from 250 meters to 500 meters for orbits derived from laser data only. For orbits observed from Minitrack data alone the relative differences in GEOS-2 spacecraft position ranged from 50 meters to 190 meters. Utilizing the laser data alone in each arc, definitive orbits were computed using the unified and nonunified station location coordinates. The differences in the satellite position in the overlap region when using the unified laser station coordinates ranged from 25 meters to 150 meters, whereas when using the nonunified laser station coordinates the differences in position ranges from 180 to 650 meters.
Project Vanguard Magnetic-Field Instrumentation and Measurements
The Vanguard III Satellite, 1959 Eta, placed in orbit on September 18, 1959, contained a proton precessional magnetometer for magnetic-field studies of exceptional accuracy. Throughout the 85 days of battery life, the instrumentation functioned according to plan. Measurements of the absolute total field were obtained in the meridian belts of Minitrack stations at altitudes 510 to 3750 kilometers and at latitudes +/- 33.4 degrees. Surface magnetic observatories were operated at eight of the Minitrack stations to furnish correlative information. This paper reviews briefly the instrumentation employed in these experiments, and the data collection and reduction procedures. Emphasis is given to results from a preliminary analysis. Specifically, this analysis bears on the accuracy of computed fields, the stability of the earth's field in space, the Capetown anomaly, and magnetic-storm effects.
TRACKING AND DATA ACQUISITION
Tracking and data acquisition from spacecraft using minitrack network
Obtaining Data from Space
Ground support of nasa space programs - tracking and command techniques - minitrack, deep space stations, mercury network, data processing centers
SPACECRAFT TRACKING AND DATA ACQUISITION
Spacecraft tracking and data acquisition - baker- nunn camera network, minitrack, deep space network and manned space network
New knowledge of the earth's atmosphere from the aeronomy satellite /explorer xvii/
Data on atmosphere of earth obtained from Explorer XVII satellite with Minitrack Optical Tracking System /MOTS/
NASA/MOTS optical observations of the ANNA 1B satellite
ANNA 1B beacon satellite photographic tracking by Minitrack Optical Tracking System
Saturn antenna systems SA-5, volume 1
Antenna radiation patterns for Saturn I /Sa-5/ launch vehicle very high frequency telemetry system and minitrack-VOT system
The evolution of the Satellite Tracking And Data Acouisition Network /STADAN/
Evolution of Satellite Tracking and Data Acquisition Network /STADAN/ from pre-IGY AND Minitrack facilities
Study of GSFC radio frequency interference design guideline for aerospace communications systems Final report
Tracking errors caused by radio frequency interference to Minitrack system, and analysis of phase locked loop with interference
Mean elements of GEOS-1 and GEOS-2
A combined analytical-numerical procedure for determining precise mean orbital elements is presented and applied to the orbits of GEOS-1 and GEOS-2. The precision of the mean semi-major axes of these orbits is a few tens of centimeters when optical flash data is used to determine two-day orbital arcs. Four-day Minitrack orbits give mean semi-major axes of a few meters precision. The mean orientation parameters are obtained to a precision of about 0.1 sec (about 3m) or better from the optical orbits. This precision is adequate for determinations of tidal parameters, particularly in the case of GEOS-2, where the tidal perturbation of the inclination is 10 sec.
Mean elements of GEOS 1 and GEOS 2.
A combined analytical-numerical procedure for determining mean orbital elements is presented and applied to the orbits of GEOS 1 and GEOS 2. The precision of the mean semi-major axes of these orbits is a few tens of centimeters when optical flash data are used to determine 2 day orbital arcs. Four day Minitrack orbits give mean semi-major axes of a few meters precision. The mean orientation parameters determined from the optical data are obtained to a precision of about 0.1 sec.
Mission operations and data systems
A communications system for performing the basic functions of mission operations, orbit and attitude determination, and data processing is described. A block diagram is provided to show the relationships of these functions with the spacecraft in orbit and the experiments to be conducted on board the spacecraft. Specific areas of application are discussed as follows: (1) software operating systems for the ATS-F satellite testing and ground support, (2) inversion of the RAE-1 satellite (Explorer 38 satellite) in orbit, (3) ALSEP differential Doppler tracking, (4) minitrack calibration using satellite data, (5) angles-only orbit extraction, and (6) image processing system performance prediction and product quality evaluation techniques. Block diagrams of the various systems are provided to show the steps involved in the operations.