ARIANE 5 FLIGHT 501 FAILURE GARIMELLA SUDHEER EE 585: Fault Tolerant Computing - PowerPoint PPT Presentation

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ARIANE 5 FLIGHT 501 FAILURE GARIMELLA SUDHEER EE 585: Fault Tolerant Computing

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Weather conditions at launch time were acceptable. The launch was initiated at 09h 33mn 59s( Local Time) ... One Major anomaly was gradual development of ... – PowerPoint PPT presentation

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Title: ARIANE 5 FLIGHT 501 FAILURE GARIMELLA SUDHEER EE 585: Fault Tolerant Computing


1
ARIANE 5FLIGHT 501 FAILUREGARIMELLA
SUDHEEREE 585 Fault Tolerant Computing
2
THE FAILURE
  • General Description
  • Weather conditions at launch time were
    acceptable.
  • The launch was initiated at 09h 33mn 59s( Local
    Time).
  • Nominal behavior of the launcher up to
    H036seconds.
  • Failure of the back up Inertial reference system
    followed by failure of actual inertial system.

3
ANOMOLIES OBSERVED
  • One Major anomaly was gradual development of
    variations in the hydraulic pressure of actuators
    of the main engine nozzle.
  • This anomaly was observed at H022 seconds
  • These variations had a frequency of approximately
    10Hz.

4
ANALYSIS OF FAILURE
  • In general flight control system of the Ariane 5
    is of standard design.
  • The attitude of the launcher and its movements in
    space are measured by an Inertial Reference
    system (SRI).
  • The design of Ariane 5 SRI is practically the
    same as that of an Ariane 4 SRI in particular to
    software.

5
ANALYSIS OF FAILURE (CONT)
  • Launcher started to disintegrate at H039seconds.
  • The disintegration occurred due to software
    exception of On board computer.
  • The software exception was caused during
    conversion of 64 bit floating point to 16 bit
    signed integer value.

6
COMMENTS
  • The primary cause for failure scenario are
    operand error when converting the horizontal bias
    variable BH.
  • Lack of protection of this conversion which
    caused the SRI computer to stop.

7
OTHER WEAKNESSES
  • The review has covered following areas.
  • - The design of the electrical system
  • - Embedded on board software in subsystem other
    than the Inertial frame of reference system.
  • -The on board computer and the flight program
    software

8
CONCLUSIONS
  • The failure of Ariane 501 was caused by the
    complete loss of guidance and attitude
    information.
  • This loss of information was due to
    specifications and design errors in the software
    of inertial reference system.

9
REFERENCES
  • ARIANE 5 FLIGHT 501 FAILURE
  • Report by chairman of enquiry board
  • Prof.J.L.LIONS.
  • http//www.arianespace.com
  • http//www.ima.umn.edu/arnold/disasters/ariane.ht
    ml
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