Year: 1967
Type: conference-paper
Abstract: The navigation and guidance analysis of a Mars probe possibly to be launched from a manned spacecraft during M a r s flyby missions in 1975 and 1976 is presented.The study is initiated with the probe and spacecraft separation at the M a r s sphere of influence and is terminated with the probe arrival at a specified entry altitude and the spacecraft arrival at M a r s periapsis.The relative state between the probe and spacecraft is assumed to be perfectly known so that the uncertainty covariance matrix for the probe is equivalent to that of the spacecraft.certainties are reduced by processing onboard sextant o r theodolite measurements with a Kalman filter.dispersions between 1 and 6 n. mi.can be obtained with one o r two midcourse velocity corrections totaling between 10 and 150 fps depending on (1) M a r s radius uncertainty;(2) instrument accuracy; (3) sighting frequency; (4) type, number, and timing of corrections; and (5) the accuracy of their execution.dispersions ranged from 0.13" to 0.21" for the same range in velocity-correctionvector magnitude and for the same parameter variations as indicated for the spacecraft.The spacecraft position and velocity un-The results of the study indicate that spacecraft periapsis-altitude The probe entry flight-path-angle I
DOI: 10.2514/6.1967-546
Author: V. BOND
Institution: Johnson Space Center
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W2091536610