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Model-Based FDIR for Space Applications

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Fault Diagnosis and Fault-Tolerant Control and Guidance for Aerospace Vehicles

Part of the book series: Advances in Industrial Control ((AIC))

Abstract

This chapter is dedicated to space applications. Three application cases will be presented: an Earth observation satellite, a deep space mission and an atmospheric re-entry vehicle. The design method is based on H ∞ /H − tools and is associated with a suitable post-analysis process, the so-called generalized μ-analysis. It is shown that the resulting design/analysis procedure provides an iterative refinement cycle which allows the designer to get “as close as possible” to the required robustness/performance specifications and trade-offs. This chapter is dedicated to actuator fault detection and diagnosis in space applications. Fault tolerance in terms of control and guidance will also be discussed. The design method is based on H ∞ /H − and robust pole assignment tools. Three space applications will be studied:

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Notes

  1. 1.

    This case study is taken from a collaborative project supported by the French Space Agency (CNES).

  2. 2.

    The Mars Sample Return (MSR) mission is taken from a European project supported by the European Space Agency and Thales Alenia Space (France).

  3. 3.

    HL-20 vehicle: This study is taken from a collaborative project (SICVER project, see Chap. 1) with European Space Agency and EADS Astrium Space Transportation (France).

  4. 4.

    http://www.sti.nasa.gov/

  5. 5.

    MICROSCOPE is the French acronym of MICRO-Satellite à traînée Compensée pour l’Observation du Principe d’Equivalence.

  6. 6.

    The MICROSCOPE project Steering Committee has authorized the project to start a new preliminary conception phase (phase B) with cold gas micro-thrusters instead of FEEPs.

  7. 7.

    The complete database of the aerodynamic coefficients is available at http://ntrs.nasa.gov

Abbreviations

ACC:

ACCelerometer

AOCS:

Attitude and Orbit Control System

CSS:

Coarse Sun Sensor

FEEP:

Field Emission Electric Propulsion

GNSS:

Global Navigation Satellite System

GYR:

GYRoscope

IMU:

Inertial Measurement Unit

LFR:

Linear Fractional Representation

LIDAR:

LIght Detection And Ranging

LMI:

Linear Matrix Inequality

MAV:

Mars Ascent Vehicle

MDV:

Mars Descent Vehicle

MSR:

Mars Sample Return

NAC:

Narrow Acquisition Camera

NAV:

NAVigation

NEP:

Nominal Exit Point

PID:

Proportional Integral Derivative

RFS:

Radio Frequency Sensor

RLV:

Reentry Launch Vehicle

RW:

Reaction Wheel

SAM:

Sun Acquisition Mode

SDP:

Semi-Definite Programming

STR:

Star TRacker

TAEM:

Terminal Area Energy Management

TEP:

TAEM Exit Point

THR:

THuRster

TM:

Telemetry

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Authors and Affiliations

  1. CNRS, IMS Lab, The University of Bordeaux, Bordeaux, France

    Ali Zolghadri, David Henry & Jérôme Cieslak

  2. INRIA-LNE Non-A project, Parc Scientifique de la Haute Borne, Villeneuve d’Ascq, France

    Denis Efimov

  3. EYCCC Flight Control System Airbus Operations S.A.S. – St. Martin, Toulouse, France

    Philippe Goupil

Authors
  1. Ali Zolghadri
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  2. David Henry
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  4. Denis Efimov
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  5. Philippe Goupil
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Zolghadri, A., Henry, D., Cieslak, J., Efimov, D., Goupil, P. (2014). Model-Based FDIR for Space Applications. In: Fault Diagnosis and Fault-Tolerant Control and Guidance for Aerospace Vehicles. Advances in Industrial Control. Springer, London. https://doi.org/10.1007/978-1-4471-5313-9_7

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  • DOI: https://doi.org/10.1007/978-1-4471-5313-9_7

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  • Online ISBN: 978-1-4471-5313-9

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