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Papers by Jean de Lafontaine

Research paper thumbnail of Evaluation of Autonomous GNC Strategies for the Roseti a Interplanetary Mission 1

IFAC Proceedings Volumes, 1992

Research paper thumbnail of Autonomous guidance and control of Earth-orbiting formation flying spacecraft: Closing the loop

Acta Astronautica, Dec 1, 2008

Previous work on autonomous formation flying guidance and control identified three key challenges... more Previous work on autonomous formation flying guidance and control identified three key challenges to overcome in order to obtain a fully autonomous guidance and control loop: an accurate but simple model of relative motion about elliptical and perturbed orbits, an efficient way of performing conflicting requirements trade-off with power-limited on-board computers, and finally an optimal or near-optimal control algorithm easy to implement on a flight computer. This paper first summarizes recent developments on each of these subject that help to overcome these challenges, developments which are then used as building blocks for an autonomous formation flying guidance and control system. This system autonomously performs trade-offs between conflicting requirements, i.e. minimization of fuel cost, formation accuracy and equal repartition of the fuel expenditure within the formation. Simulation results show that a complete guidance and control loop can be established using mainly analytical results and with very few numerical optimization which facilitates on-board implementation.

Research paper thumbnail of Robust Guidance and Control Algorithms Using Constant Flight Path Angle for Precision Landing on Mars

AIAA Guidance, Navigation, and Control Conference and Exhibit, Jun 15, 2006

This paper proposes four guidance laws aimed at reducing the most significant sources of landing ... more This paper proposes four guidance laws aimed at reducing the most significant sources of landing dispersion during atmospheric entry at Mars. The autonomous guidance algorithms rely on simple analytic and semi-analytic solutions that prescribe segments of constantflightpath angles (FPA's) that match the trajectory constraints in terms of desired final altitude, velocity and downrange. Two one-segment solutions and two two-segment solutions are presented. A nonlinear dynamic inversion of the translational dynamics and a robust attitude controller, designed with the Robust Modal Control technique, complete the guidance and control system whose performance is demonstrated through numerical simulations of a Mars entry scenario.

Research paper thumbnail of Rosetta/CNSR, ESA's planetary cornerstone mission

The Rosetta/Comet Nucleus Sample Return (CNSR) mission is described in terms of scenario, spacecr... more The Rosetta/Comet Nucleus Sample Return (CNSR) mission is described in terms of scenario, spacecraft concept, comet approach, sampling, return to Earth and Earth approach and re-entry phase. The preparatory program of ESA and NASA to provide new technologies is discussed. The prime scientific objective is to return a comet nucleus sample to Earth while preserving such fundamental properties as: the chemical and isotopic composition of the individual molecular species of remaining volatile compounds; the chemical, isotopic and structural state of the individual phases and crystals constituting higher temperature condensates and aggregates; and the preservation of complex hydrocarbon compounds and their aggregates. The sample will allow the study of the most primitive material in the solar system and the physical and chemical processes that marked the system's beginning, and hopefully will establish correspondence between interstellar matter, cometary material and primitive meteo...

Research paper thumbnail of The Generalized (μ,MU)-Iteration Illustrated by Flexible Aircraft Robust Control

IFAC Proceedings Volumes, 2004

Thanks to real-p,-analysis, the (p"Mu)-iteration generalizes the discrete multi-model approach to... more Thanks to real-p,-analysis, the (p"Mu)-iteration generalizes the discrete multi-model approach to a continuum of models, represented by LFT. The present paper proposes and explains how to generalize the (p"Mu)-iteration to take into account robust performance requirements rather than stability. Moreover, it illustrates the advantages of this approach by applying it to reduction, structuration and performance robustness improvement of a high-order controller designed for flexible aircraft robust control.

Research paper thumbnail of Improvement of the Analytical Predictor-Corrector Guidance Algorithm Applied to Mars Aerocapture

AIAA Guidance, Navigation, and Control Conference and Exhibit, 2005

Research paper thumbnail of Planetary Landing Dynamic Test Facility: Design and Applications

AIAA Guidance, Navigation and Control Conference and Exhibit, 2008

In an effort to bridge the gap between software simulation and expensive full-scale hardware-in-t... more In an effort to bridge the gap between software simulation and expensive full-scale hardware-in-the-loop tests, an innovative Landing Dynamic Test Facility was designed and built. This facility reproduces landing trajectories in a lab environment using an industrial robot mounted on a linear rail. The facility was originally designed to validate a Lidar-based autonomous guidance, navigation and control system for Mars landing. However, its time and spatial scaling capabilities make it compatible with a variety of celestial bodies (Moon, asteroids, etc.) and sensors (e.g. camera). This paper presents the design of the facility as well as examples of its use in particular landing applications.

Research paper thumbnail of Zero-Speed Crossing Avoidance with Three Active Reaction Wheels using Set-Point Angular Momentum Management

Research paper thumbnail of Performance Assessment of a Gyroless 3-Axis Stabilised Sun Pointing Mode on a Highly Elliptical Orbit

Research paper thumbnail of Improvement to the Analytical Predictor-Corrector Guidance Algorithm Applied to Mars Aerocapture

Journal of Guidance Control and Dynamics, May 23, 2012

Research paper thumbnail of Control of mars guided entry (part II): Robust nonlinear dynamics inversion

Research paper thumbnail of Robust 2-DOF H-infinity Controller for Highly Flexible Aircraft : Design Methodology and Numerical Results

Canadian Aeronautics and Space Journal, Mar 1, 2003

Research paper thumbnail of Control of mars guided entry (part I): Robust self-scheduling modal control

Research paper thumbnail of Linearized dynamics of formation flying spacecraft on a J2-perturbed elliptical orbit

Journal of Guidance Control and Dynamics, 2007

ABSTRACT A linearized set of equations of relative motion about a J2,-perturbed elliptical refere... more ABSTRACT A linearized set of equations of relative motion about a J2,-perturbed elliptical reference orbit is developed. This model uses analytical relations that are well suited for onboard applications. The inclusion oftheJ2 perturbation in a simple analytical model can lead to formation flying guidance and control algorithms that make use ofthe naturaIJ2induced relative motion to perform maneuvers instead of constantly compensating for this perturbation. The model uses the linearized differential drift rate of mean orbit elements to predict the impact of the J2 perturbation on relative osculating spacecraft motion. tt analytically provides the relative motion in Hill coordinates at any given true anomaly using only the initial osculating relative orbit elements and the initial orbit elements of the reference trajectory. A linear time-varying state-space form of the model is also presented. Simulation results show that relative motion prediction remains accurate over several orbits.

Research paper thumbnail of Innovative Navigation Schemes for State and Parameter Estimation During Mars Entry

Journal of Guidance Control and Dynamics, 2007

ABSTRACT

Research paper thumbnail of Robust synthesis of static output feedback controller for Mars entry

Research paper thumbnail of PROBA-2: AOCS Software Validation Process and Critical Results

The PROBA-2 spacecraft is the second spacecraft designed in the context of the PRoject for On-Boa... more The PROBA-2 spacecraft is the second spacecraft designed in the context of the PRoject for On-Board Autonomy (PROBA) programme supported by the European Space Agency (ESA). Building on the ongoing success of PROBA-1, PROBA-2 will continue the in-flight demonstration of on-board autonomy by performing a Sun observation mission along with many flight and hardware experiments. Now that the Final Acceptance Review (FAR) of the Attitude and Orbit Control System (AOCS) has been completed, this paper will focus on the test activities that were conducted to qualify the software for flight and on some critical test results that were obtained.

Research paper thumbnail of Development of the PROBA Attitude Control and Navigation Software

Research paper thumbnail of A semianalytic satellite theory for orbital decay predictions

Journal of the Astronautical Sciences

ABSTRACT

Research paper thumbnail of Orbit lifetime prediction and safety considerations

Research paper thumbnail of Evaluation of Autonomous GNC Strategies for the Roseti a Interplanetary Mission 1

IFAC Proceedings Volumes, 1992

Research paper thumbnail of Autonomous guidance and control of Earth-orbiting formation flying spacecraft: Closing the loop

Acta Astronautica, Dec 1, 2008

Previous work on autonomous formation flying guidance and control identified three key challenges... more Previous work on autonomous formation flying guidance and control identified three key challenges to overcome in order to obtain a fully autonomous guidance and control loop: an accurate but simple model of relative motion about elliptical and perturbed orbits, an efficient way of performing conflicting requirements trade-off with power-limited on-board computers, and finally an optimal or near-optimal control algorithm easy to implement on a flight computer. This paper first summarizes recent developments on each of these subject that help to overcome these challenges, developments which are then used as building blocks for an autonomous formation flying guidance and control system. This system autonomously performs trade-offs between conflicting requirements, i.e. minimization of fuel cost, formation accuracy and equal repartition of the fuel expenditure within the formation. Simulation results show that a complete guidance and control loop can be established using mainly analytical results and with very few numerical optimization which facilitates on-board implementation.

Research paper thumbnail of Robust Guidance and Control Algorithms Using Constant Flight Path Angle for Precision Landing on Mars

AIAA Guidance, Navigation, and Control Conference and Exhibit, Jun 15, 2006

This paper proposes four guidance laws aimed at reducing the most significant sources of landing ... more This paper proposes four guidance laws aimed at reducing the most significant sources of landing dispersion during atmospheric entry at Mars. The autonomous guidance algorithms rely on simple analytic and semi-analytic solutions that prescribe segments of constantflightpath angles (FPA's) that match the trajectory constraints in terms of desired final altitude, velocity and downrange. Two one-segment solutions and two two-segment solutions are presented. A nonlinear dynamic inversion of the translational dynamics and a robust attitude controller, designed with the Robust Modal Control technique, complete the guidance and control system whose performance is demonstrated through numerical simulations of a Mars entry scenario.

Research paper thumbnail of Rosetta/CNSR, ESA's planetary cornerstone mission

The Rosetta/Comet Nucleus Sample Return (CNSR) mission is described in terms of scenario, spacecr... more The Rosetta/Comet Nucleus Sample Return (CNSR) mission is described in terms of scenario, spacecraft concept, comet approach, sampling, return to Earth and Earth approach and re-entry phase. The preparatory program of ESA and NASA to provide new technologies is discussed. The prime scientific objective is to return a comet nucleus sample to Earth while preserving such fundamental properties as: the chemical and isotopic composition of the individual molecular species of remaining volatile compounds; the chemical, isotopic and structural state of the individual phases and crystals constituting higher temperature condensates and aggregates; and the preservation of complex hydrocarbon compounds and their aggregates. The sample will allow the study of the most primitive material in the solar system and the physical and chemical processes that marked the system's beginning, and hopefully will establish correspondence between interstellar matter, cometary material and primitive meteo...

Research paper thumbnail of The Generalized (μ,MU)-Iteration Illustrated by Flexible Aircraft Robust Control

IFAC Proceedings Volumes, 2004

Thanks to real-p,-analysis, the (p"Mu)-iteration generalizes the discrete multi-model approach to... more Thanks to real-p,-analysis, the (p"Mu)-iteration generalizes the discrete multi-model approach to a continuum of models, represented by LFT. The present paper proposes and explains how to generalize the (p"Mu)-iteration to take into account robust performance requirements rather than stability. Moreover, it illustrates the advantages of this approach by applying it to reduction, structuration and performance robustness improvement of a high-order controller designed for flexible aircraft robust control.

Research paper thumbnail of Improvement of the Analytical Predictor-Corrector Guidance Algorithm Applied to Mars Aerocapture

AIAA Guidance, Navigation, and Control Conference and Exhibit, 2005

Research paper thumbnail of Planetary Landing Dynamic Test Facility: Design and Applications

AIAA Guidance, Navigation and Control Conference and Exhibit, 2008

In an effort to bridge the gap between software simulation and expensive full-scale hardware-in-t... more In an effort to bridge the gap between software simulation and expensive full-scale hardware-in-the-loop tests, an innovative Landing Dynamic Test Facility was designed and built. This facility reproduces landing trajectories in a lab environment using an industrial robot mounted on a linear rail. The facility was originally designed to validate a Lidar-based autonomous guidance, navigation and control system for Mars landing. However, its time and spatial scaling capabilities make it compatible with a variety of celestial bodies (Moon, asteroids, etc.) and sensors (e.g. camera). This paper presents the design of the facility as well as examples of its use in particular landing applications.

Research paper thumbnail of Zero-Speed Crossing Avoidance with Three Active Reaction Wheels using Set-Point Angular Momentum Management

Research paper thumbnail of Performance Assessment of a Gyroless 3-Axis Stabilised Sun Pointing Mode on a Highly Elliptical Orbit

Research paper thumbnail of Improvement to the Analytical Predictor-Corrector Guidance Algorithm Applied to Mars Aerocapture

Journal of Guidance Control and Dynamics, May 23, 2012

Research paper thumbnail of Control of mars guided entry (part II): Robust nonlinear dynamics inversion

Research paper thumbnail of Robust 2-DOF H-infinity Controller for Highly Flexible Aircraft : Design Methodology and Numerical Results

Canadian Aeronautics and Space Journal, Mar 1, 2003

Research paper thumbnail of Control of mars guided entry (part I): Robust self-scheduling modal control

Research paper thumbnail of Linearized dynamics of formation flying spacecraft on a J2-perturbed elliptical orbit

Journal of Guidance Control and Dynamics, 2007

ABSTRACT A linearized set of equations of relative motion about a J2,-perturbed elliptical refere... more ABSTRACT A linearized set of equations of relative motion about a J2,-perturbed elliptical reference orbit is developed. This model uses analytical relations that are well suited for onboard applications. The inclusion oftheJ2 perturbation in a simple analytical model can lead to formation flying guidance and control algorithms that make use ofthe naturaIJ2induced relative motion to perform maneuvers instead of constantly compensating for this perturbation. The model uses the linearized differential drift rate of mean orbit elements to predict the impact of the J2 perturbation on relative osculating spacecraft motion. tt analytically provides the relative motion in Hill coordinates at any given true anomaly using only the initial osculating relative orbit elements and the initial orbit elements of the reference trajectory. A linear time-varying state-space form of the model is also presented. Simulation results show that relative motion prediction remains accurate over several orbits.

Research paper thumbnail of Innovative Navigation Schemes for State and Parameter Estimation During Mars Entry

Journal of Guidance Control and Dynamics, 2007

ABSTRACT

Research paper thumbnail of Robust synthesis of static output feedback controller for Mars entry

Research paper thumbnail of PROBA-2: AOCS Software Validation Process and Critical Results

The PROBA-2 spacecraft is the second spacecraft designed in the context of the PRoject for On-Boa... more The PROBA-2 spacecraft is the second spacecraft designed in the context of the PRoject for On-Board Autonomy (PROBA) programme supported by the European Space Agency (ESA). Building on the ongoing success of PROBA-1, PROBA-2 will continue the in-flight demonstration of on-board autonomy by performing a Sun observation mission along with many flight and hardware experiments. Now that the Final Acceptance Review (FAR) of the Attitude and Orbit Control System (AOCS) has been completed, this paper will focus on the test activities that were conducted to qualify the software for flight and on some critical test results that were obtained.

Research paper thumbnail of Development of the PROBA Attitude Control and Navigation Software

Research paper thumbnail of A semianalytic satellite theory for orbital decay predictions

Journal of the Astronautical Sciences

ABSTRACT

Research paper thumbnail of Orbit lifetime prediction and safety considerations