Engineering Papers⌕ Search

NASA NTRS · 20150007340

Using Onboard Telemetry for MAVEN Orbit Determination

Abstract

Determination of the spacecraft state has been traditional done using radiometric tracking data before and after the atmosphere drag pass. This paper describes our approach and results to include onboard telemetry measurements in addition to radiometric observables to refine the reconstructed trajectory estimate for the Mars Atmosphere and Volatile Evolution Mission (MAVEN). Uncertainties in the Mars atmosphere models, combined with non-continuous tracking degrade navigation accuracy, making MAVEN a key candidate for using onboard telemetry data to help complement its orbit determination process.

Explore related subjects

Keep this discovery

Explore connections, maps & timelines

BibTeXRIS

Lam, Try, Trawny, Nikolas, Lee, Clifford. 2013-08-11. Using Onboard Telemetry for MAVEN Orbit Determination. https://ntrs.nasa.gov/citations/20150007340

Cite the original work for its findings. Save a collection to share your selection of sources.

KEEP EXPLORING

Related reports

Preliminary Node Separation Orbit Determination Analysis for the HelioSwarm Observatory

The HelioSwarm Observatory is a nine-spacecraft swarm design, consisting of one Hub and eight Node spacecraft co-orbiting the Earth in a ~13.7-day orbit. Each Node separates from the Hub during the Node Commissioning Phase, and the Nodes’ sole source of tracking is inter-satellite relative ranging with the Hub. This study characterizes how soon the relative ranging should occur post-separation to maintain a reasonable knowledge of the Nodes’ position relative to the hub and quantifies how often, and at what measurement cadence, relative ranging needs to occur during the early days of commissioning.

orbit determination↗

Independent Navigation Team Contribution to New Horizons' Pluto System Flyby

The New Horizons spacecraft made it closest approach to Pluto on 14 July 2015. The most significant challenge of this mission was that the Pluto system ephemeris was initially known with a precision of ~1000 km. This needed to be improved significantly on approach in order to meet the science requirements. During the final six months leading to the flyby, a JPL Independent Navigation (INAV) Team was included in the ephemeris knowledge update process as a cross-check on the Project Navigation (PNAV) Team's results. This paper discusses the INAV team's experiences and challenges navigating New Horizons through the Pluto planetary system encounter.

orbit determination↗

Trajectory Dispersion Control for the Cassini Grand Finale Mission

The Cassini Grand Finale Mission, which consists of 22 ballistic orbits, will begin on April 22, 2017 after the last targeted Titan flyby. It will end on September 15, 2017 when the spacecraft dives into Saturn's atmosphere and be permanently captured. High volumes of unique science data from various onboard instruments are expected from the mission. To ensure its success and facilitate science planning, the trajectory dispersion needs to be controlled below 250 km (root-mean-square spatial deviation at the 68th percentile level) for a few segments of trajectory in the mission. This paper reports the formulation and solution of this dispersion control problem. We consider various sources of uncertainties including flyby error, orbit determination error, maneuver execution error, thruster firing control error, and uncertainty in Saturn's atmospheric model. A non-linear Monte Carlo Trajectory Dispersion tool is developed and employed for the analysis. It is found that a total of three Orbit Trim Maneuvers with a 99% (Delta)V usage of less than 2 m/s will adequately control the trajectory.

orbit determination↗