Engineering Papers⌕ Search

Engineering topics

Bhat, R. S.

Publications and source records attributed to Bhat, R. S..

12 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS2012

Navigation of the Twin GRAIL Spacecraft into Science Formation at the Moon

On February 29, 2012 the twin NASA Gravity Recovery And Interior Laboratory (GRAIL) spacecraft, Ebb and flow, achieved precise synchronized formation for collecting highly sensitive lunar gravity data. This was accomplished after performing a total of 27 propulsive maneuvers between the two spacecraft (13 on Ebb, 14 on Flow) over six months. Each 300 kg GRAIL spacecraft independently flew a 3.8-month, low-energy trajectory to reach the Moon after separation from the launch vehicle on September 10, 2011. The space craft were captured into 11.5 hr co- planar polar orbits after performing Lunar Orbit Insertion (LOI) maneuvers on New Years Eve (Dec 31, 2011) and New Years Day (Jan 1, 2012), respectively for Ebb, and Flow. Once captured, each spacecraft performed clusters of period reduction maneuvers to bring their orbit periods down to just less than 2 hrs. Finally, the orbiters we replaced into science formation by performing five strategic maneuvers (2 on Ebb, 3 on Flow). These maneuvers ensured 3 months of orbit life time with mean altitudes of 55 km and separations of 82-217 km by targeting the orbits' eccentricity vectors to specific locations. This paper will discuss the navigation strategy and performance of the twin GRAIL spacecraft from the September 10, 2011 launch through the end of the Prime Mission Science Phase in June 2012.

lunar gravity↗
NASA NTRS2003

Phase curve and albedo of asteroid 5534 Annefrank

Seventy-two images of the S-class asteroid 5535 Annefrank, acquired on 2 November 2002 at target ranges of 11,415??8.5 km, were transmitted to Earth as a part of an engineering readiness test of the Stardust mission. Forty-four of these were used to create a phase curve extending to 134, the largest angle yet achieved for any S-class asteroid. Flux fell by more than six magnitudes between the extrapolated 0 and 134. A maximum illuminated cross section of 16 km2 was seen at a phase angle of 47.2. Assuming a camera efficiency of 75%, a broadband (470?? nm) geometric albedo of 0.24 was derived for Annefrank.

Solar system comets small bodies↗
NASA NTRS1998

TOPEX/Poseidon orbit maintenance for the first five years

The TOPEX/Poseidon orbit maintenance strategy was changed following launch to include the effects of observed unmodeled, and hence anomalous, along-track accelerations. The anomalous force causes the semi-major axis, a, to either increase (called "boost") or decrease ("deboost" or "decay") depending on the satellite attitude and solar array pitch angle offset. Although this force is the most uncertain parameter in ground track prediction, it has been used as a passive technique for orbit maintenance, thereby reducing the number of propulsive maneuvers, enhancing maneuver spacing, and to place maneuvers at convenient times. This passive technique was first demonstrated in May 1993. The TOPEX/Poseidon orbit has been uniquely maintained using both passive (non-propulsive) and active (propulsive) maneuvers. Furthermore, the orbit has been maintained using only the passive technique since the ninth orbit maintenance maneuver on January 15, 1996. Only nine orbit maintenance maneuvers have been required to maintain the ground track, including verification site over flights, since achieving the operational orbit on September 21, 1992 (mission requirement: 95% within +/- l km). During this period, a has varied within 7,714,429 +/- 7 m, while the inclination i periodically fluctuated in the range 66.0408 deg. +/- 0.0040 deg. The frozen orbit (required e < 0.001 and omega approximately equals to 90 deg.) has been maintained without any dedicated eccentricity maneuvers. The frozen eccentricity vector has completed two periodic cycles and it is currently tracing its third cycle (period approximately equals 26.7 months).

Bhat, R. S.↗
NASA NTRS1993

TOPEX/POSEIDON Orbit Acquisition Manuever Sequence

TOPEX/POSEIDON....was launched...on August 10, 1992...The Project wanted to achieve operational orbit as soon as possible in order to begin oceanographic data acquisition through altimeters. A sequence of six manuevers was implemented to acquire the operational orbit following injection...

TOPEX TOPEX/POSEIDON manuever sequence design↗
NASA NTRS1993

TOPEX/POSEIDON Orbit Acquisition Manuever Sequence

A sequence of six manuevers was implemented over a 42-day period following the launch of the TOPEX/POSEIDON satellite on August 10, 1992 to acquire an orbit compatible with oceanographic data acquisition requirements as soon as possible...

TOPEX TOPEX/POSEIDON orbit manuevers↗
NASA NTRS1990

TOPEX/POSEIDON orbit maintenance maneuver design

The Ocean Topography Experiment (TOPEX/POSEIDON) mission orbit requirements are outlined, as well as its control and maneuver spacing requirements including longitude and time targeting. A ground-track prediction model dealing with geopotential, luni-solar gravity, and atmospheric-drag perturbations is considered. Targeting with all modeled perturbations is discussed, and such ground-track prediction errors as initial semimajor axis, orbit-determination, maneuver-execution, and atmospheric-density modeling errors are assessed. A longitude targeting strategy for two extreme situations is investigated employing all modeled perturbations and prediction errors. It is concluded that atmospheric-drag modeling errors are the prevailing ground-track prediction error source early in the mission during high solar flux, and that low solar-flux levels expected late in the experiment stipulate smaller maneuver magnitudes.

Bhat, R. S.↗