Communicating Navigation Data Inside the Cassini-Huygens Project: Visualizations and Tools

Wagner, Sean V.; Gist, Emily M.; Goodson, Troy; Hahn, Yungsun; Stumpf, Paul W.; Williams, P.

doi:10.2514/6.2008-6748

Cited by 5 publications

(3 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The dispersion on the S/C initial state is performed by sampling the position and velocity errors from the ICPS injection covariance. The maneuver's execution error is implemented using the Gates model [27]. The model is used to generate Gaussian randomly sampled execution errors for a specific commanded ∆V, both in magnitude and in pointing.…”

Section: Flight Path Control Analysismentioning

confidence: 99%

Design and Analysis of the Cis-Lunar Navigation for the ArgoMoon CubeSat Mission

et al. 2022

View full text Add to dashboard Cite

In the framework of the Artemis-1 mission, 10 CubeSats will be released, including the 6U CubeSat ArgoMoon, built by the Italian company Argotec and coordinated by the Italian Space Agency. The primary goal of ArgoMoon is to capture images of the Interim Cryogenic Propulsion Stage. Then, ArgoMoon will be placed into a highly elliptical orbit around the Earth with several encounters with the Moon. In this phase, the navigation process will require a precise Orbit Determination (OD) and a Flight Path Control (FPC) to satisfy the navigation requirements. The OD will estimate the spacecraft trajectory using ground-based radiometric observables. The FPC is based on an optimal control strategy designed to reduce the dispersion with respect to the reference trajectory and minimize the total ΔV. A linear approach was used to determine the optimal targets and the number and location of the orbital maneuvers. A covariance analysis was performed to assess the expected OD performance and its robustness. The analysis results show that the reference translunar trajectory can be successfully flown and the navigation performance is strongly dependent on the uncertainties of the ArgoMoon’s Propulsion Subsystem and of the orbit injection.

show abstract

Section: Flight Path Control Analysismentioning

confidence: 99%

Design and Analysis of the Cis-Lunar Navigation for the ArgoMoon CubeSat Mission

et al. 2022

View full text Add to dashboard Cite

show abstract

“…Details of this maneuver cancellation process can be found in Ref. 17. Table 6 highlights all of the cancelled maneuvers from the past year of the Equinox Mission.…”

Section: Maneuver Cancellationsmentioning

confidence: 99%

Cassini Maneuver Experience: Ending the Equinox Mission

Ballard

Arrieta

Hahn

et al. 2010

AIAA/AAS Astrodynamics Specialist Conference

Self Cite

View full text Add to dashboard Cite

The Cassini-Huygens spacecraft was launched in 1997 on a mission to observe Saturn and its many moons. After a seven-year interplanetary cruise, it entered a Saturnian orbit for a four-year Prime Mission in 2004 and began a two-year Equinox Mission in 2008. It has been approved for another seven-year mission, the Solstice Mission, starting in October 2010. This paper highlights significant maneuver activities performed from July 2009 to June 2010. We present results for the 45 maneuvers during this time. The successful navigation of the Cassini orbiter can be attributed in part to the accurate maneuver performance, which has greatly exceeded pre-launch expectations.

show abstract

“…In order for the Cassini-Huygens maneuver team to provide information for project management to determine if cancellation of a maneuver was the appropriate course of action, tools were developed that would quantify what would happen with and without a particular maneuver. Thus, the maneuver cancellation analysis software was developed [3]. The maneuver cancellation analysis software runs every time the maneuver team designs a maneuver solution for the ensuing encounter.…”

mentioning

confidence: 99%

Flyby Error Analysis Based on Contour Plots for Cassini Tour

Stumpf

Gist

Goodson

et al. 2009

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

The maneuver cancellation analysis consists of cost contour plots employed by the Cassini maneuver team. The plots are two-dimensional linear representations of a larger six-dimensional solution to a multimaneuver, multiencounter mission at Saturn. This realization and the use of the tool itself is just one of the many significant engineering achievements that have come from the Cassini project. After inserting the cost contour capability with an enhancement (taking account of asymptote changes), a tool that was originally only used for analysis could be used for operations once the accuracy of the plots was determined to be acceptable for operations. The plots have been used extensively since the enhancement. By using contours plotted in the B plane with B R and B T components, it is possible to view the effects on V for various encounter positions in the B plane. The plot is used in operations to help determine if the approach maneuver (ensuing encounter minus three days) and/or the cleanup maneuver (ensuing encounter plus three days) can be cancelled and is a linear check of an integrated solution. The plots have also been used to bias the targets of encounters to save V. Nomenclature B = B vector or B plane B R = vertical axis of the B plane B T = horizontal axis of the B plane C3 = excess velocity or characteristic energy G x;y = grid point value on the contour plot for an approach maneuver, m=s G x;y;c = grid point value on the contour plot for a cleanup maneuver, m=s i = leg index J x;y = V calculation of a B plane grid point for an approach maneuver, m=s J x;y;c = V calculation of a B plane grid point for a cleanup maneuver, m=s K = K matrix, a maneuver capability matrix M = the B plane mapping R = R vector of the B plane r o = nominal trajectory apoapsis maneuver location S = the incoming asymptote T = T vector of the B plane T n = nth encounter of Titan V1 = the magnitude of the velocity for a cleanup maneuver, m=s V2 = the velocity magnitude for an apoapsis maneuver, m=s B A = asymptote change B plane state vector B RT = grid variation vector B xy = the variations in the B plane with a perturbed trajectory B R y = y component of grid points in the B plane B T x = x component of grid points in the B plane r = difference in the apoapsis maneuver location for a perturbed trajectory V = change in velocity, m=s V REF = change in velocity given in the reference trajectory, m=s

show abstract

Communicating Navigation Data Inside the Cassini-Huygens Project: Visualizations and Tools

Cited by 5 publications

References 7 publications

Design and Analysis of the Cis-Lunar Navigation for the ArgoMoon CubeSat Mission

Design and Analysis of the Cis-Lunar Navigation for the ArgoMoon CubeSat Mission

Cassini Maneuver Experience: Ending the Equinox Mission

Flyby Error Analysis Based on Contour Plots for Cassini Tour

Contact Info

Product

Resources

About