Cassini Thruster Calibration Algorithm Using Reaction Wheel Biasing Data

Rizvi, Farheen

doi:10.2514/1.a32523

Cited by 3 publications

(1 citation statement)

References 6 publications

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“…The Mars Cube One spacecraft performed in-space thrust estimation by measuring the total change in angular momentum of the spacecraft [4]. In a similar procedure, the thrusters onboard Cassini were calibrated during measured flight telemetry during reaction wheel biasing [5]. The University Würzburg Experimental satellite-4 also demonstrated the use of attitude control maneuvers to measure the thrust magnitude as well as direction for multiple onboard thrusters [6].…”

Section: Introductionmentioning

confidence: 99%

Segmented Reconstruction of Low-Acceleration Orbital Maneuvers

Jia-Richards

2023

Journal of Guidance, Control, and Dynamics

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This paper considers the problem of inferring the acceleration acting on a spacecraft in a near-circular orbit around a large planetary body when the acceleration is known to act in the along-track direction. A segmented approach is analyzed where the acceleration profile over a given period of time is approximated as a piecewise-constant profile. Noisy measurements of the spacecraft’s position are collected throughout the acceleration profile, from which the constant acceleration for each segment of the piecewise-constant profile can be inferred. The primary contribution of this work is an analytical approximation for the sensitivity of each measurement with respect to the constant acceleration of each segment. The resulting analytically approximated sensitivity matrix enables an analytical reconstruction of the acceleration profile given a numerically simulated reference trajectory. Applications of the segmented approach for thrust inference for both discontinuous and continuous thrust profiles are demonstrated. In particular, the reconstruction of a simulated thruster degradation profile over the course of 60 h is shown.

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Section: Introductionmentioning

confidence: 99%

Segmented Reconstruction of Low-Acceleration Orbital Maneuvers

Jia-Richards

2023

Journal of Guidance, Control, and Dynamics

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A Revised Sensitivity Model for Cassini INMS: Results at Titan

et al. 2015

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Cassini Ion Neutral Mass Spectrometer (INMS) measurements from roughly a hundred Titan encounters over the Cassini mission yield neutral and ion densities systematically lower, by factors approximately 2 to 3, than estimates from several other spacecraft systems, including the Attitude and Articulation Control System, and Navigation system. In this paper we present a new INMS instrument sensitivity model, obtained by re-analyzing (1) the capture and transmission of neutral gas through the instrument, and (2) the detector gain reduction during pre-launch testing. By correcting for an under-estimation of gas leakage out of the instrument into space by the original calibration model, and adjusting for the gain change, the new model brings INMS densities into much closer agreement with the other Cassini systems. Accordingly, the INMS ion densities are revised upward by a constant detector sensitivity correction factor of 1.55 ± 21 %, while the neutral sensitivities have a complex instrument pointing direction dependence, due (mostly) to the effect of the INMS vent and antechamber-to-closed source tube. In the special case of on-ram pointing the neutral densities are revised upward by a constant factor of 2.2 ± 23 %. The corrected neutral and ion sensitivities given here are applicable to all previously published INMS results at Titan, Enceladus and elsewhere in the Saturn system. The new model gives reliable densities at high ram angles, in some cases above 90 degrees, thereby expanding the list of Titan flybys from which INMS densities may be extracted. We apply the model to obtain accurate densities from several off-ram Titan flybys which gave unusual neutral density vs. altitude profiles, or unreasonably high densities, with the original calibration.

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Thruster-Specific Force Estimation and Trending of Cassini Hydrazine Thrusters at Saturn

Stupik

Burk

2016

AIAA Guidance, Navigation, and Control Conference

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Cassini Thruster Calibration Algorithm Using Reaction Wheel Biasing Data

Cited by 3 publications

References 6 publications

Segmented Reconstruction of Low-Acceleration Orbital Maneuvers

Segmented Reconstruction of Low-Acceleration Orbital Maneuvers

A Revised Sensitivity Model for Cassini INMS: Results at Titan

Thruster-Specific Force Estimation and Trending of Cassini Hydrazine Thrusters at Saturn

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