Huygens probe entry and descent trajectory analysis and reconstruction techniques

Atkinson, D. H.; Kazeminejad, B.; Gaborit, V.; Ferri, F.; Lebreton, Jean‐Pierre

doi:10.1016/j.pss.2004.11.005

Cited by 11 publications

(5 citation statements)

References 18 publications

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“…Under appropriate conditions: i.e. (1) the probe must be spin-stabilised, (2) the Servo (or any other highly-sensitive accelerometer) can only sense decelerations in the descent-axis, and (3) group velocity of gravitational waves must be much smaller than probe's entry velocity (<100 cm.s -1 in Titan's case, [Strobel, 2006]) versus entry velocity of ~ 6 km.s -1 [Atkinson, et al, 2005. ]), the chances of detecting such a tidal wave must improve.…”

Section: Accepted Manuscriptmentioning

confidence: 99%

Huygens HASI servo accelerometer: A review and lessons learned

Hathi

Ball

Colombatti

et al. 2009

Planetary and Space Science

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The Servo accelerometer constituted a vital part of the Huygens Atmospheric Structure Instrument (HASI): flown aboard the Huygens probe, it operated successfully during the probe's entry, descent, and landing on Titan, on 14 th January 2005. This paper reviews the Servo accelerometer, starting from its development/assembly in the mid-1990s, to monitoring its technical performance through its seven-year long in-flight (or cruise) journey, and finally its performance in measuring acceleration (or deceleration) upon encountering Titan's atmosphere.The aim of this article is to review the design, ground tests, in-flight tests and operational performance of the Huygens Servo accelerometer. Techniques used for data analysis and lessons learned that may be useful for accelerometry payloads on future planetary missions are also addressed.The main finding of this review is that the conventional approach of having multiple channels to cover a very broad measurement range: from 10 -6 g to the order of 10 g (where g = Earth's surface gravity, 9.8 m/s 2 ), with on-board software deciding which of the channels to telemeter depending on the magnitude of the measured acceleration, works well. However, improvements in understanding the potential effects of the sensor drifts and ageing on the measurements can be achieved in future missions by monitoring the 'scale factor' -a measure of such sensors' sensitivity, along with the already implemented monitoring of the sensor's offset during the in-flight phase.

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Section: Accepted Manuscriptmentioning

confidence: 99%

Huygens HASI servo accelerometer: A review and lessons learned

Hathi

Ball

Colombatti

et al. 2009

Planetary and Space Science

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“…he use of measurements taken during entry, descent, and landing (EDL) is an established method for accurate post-flight reconstruction of a vehicle's trajectory during entry into a planetary atmosphere. [1][2][3][4][5] Many data types, such as inertial acceleration measurements from accelerometers, are commonly available for use in these analyses. Further, methods exist to leverage the data collected to create an estimate of the atmospheric profile encountered by the vehicle.…”

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confidence: 99%

Statistical Reconstruction of Mars Entry, Descent, and Landing Trajectories and Atmospheric Profiles

Christian

Verges

Braun

2007

AIAA SPACE 2007 Conference &Amp; Exposition

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“…To study the parachute descent trajectory, several studies [3][4][5][6][7][8] analyze the whole descent process such as the entry, descent, and landing trajectories of pay load. These analyses consist of performing a simulation of the atmospheric entry phase to predict deceleration peaks, descent attitudes, and terminal conditions.…”

Section: Introductionmentioning

confidence: 99%

“…Because the parachute is usually made of very flexible material, this assumption may be different from application of the parachute in real life due to the breathing phenomenon [10][11][12], however, this assumption will greatly simplify the model. This reduced model always correctly reproduces the most relevant features of the trajectory of the decelerator system and has been applied to many parachute trajectory models [3][4][5][6][7][8]. In parachute body fixed coordinate frame, the governing equations of a six degree rigid body parachute are written as…”

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confidence: 99%

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Numerical Formulation of Parachute Payload Decelerator System and its Animation with Moving Background

Jianhua

Qian

2015

2015 International Conference on Virtual Reality and Visualization (ICVRV)

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In order to study the parachute payload performance during the steady descent phase, a twelve degree freedom rigid parachute-payload with elastic suspension model is established, and its trajectory will be displayed with animation. The parachute and payload usually cannot be observed clearly for its comparatively small scale model during animation. In this paper, the reference background is built to provide references for the moving parachute.

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Huygens probe entry and descent trajectory analysis and reconstruction techniques

Cited by 11 publications

References 18 publications

Huygens HASI servo accelerometer: A review and lessons learned

Huygens HASI servo accelerometer: A review and lessons learned

Statistical Reconstruction of Mars Entry, Descent, and Landing Trajectories and Atmospheric Profiles

Numerical Formulation of Parachute Payload Decelerator System and its Animation with Moving Background

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