FIELD OF THE INVENTION
This invention relates to audio & visual warning for FDR system and, more particularly,
10 for health of the FDR system in the form of audio and visual warning.
BACKGROUND OF THE INVENTION
Flight data recorders are monitoring and recording instruments, carried aboard an
15 aircraft, which systematically monitor and store the instantaneous values of various aircraft
parameters. Early recorders were analog electromechanical devices which periodically marked,
in analog form, the value of a given airplane parameter on a moving wire or other permanent
storage medium. The time of occurrence of the parameter was also suitably scribed into the
medium opposite the mark for the sensed parameter. Subsequently, digital flight data recorders
20 have been developed which operate by converting each analog aircraft parameter into a
corresponding digital signal, and storing the digital signals on a permanent storage medium
such as magnetic tape.
Fault Indication is glow through fault lamp on a/c in case of built in test (BIT) failure.
25 When FDR detects that any of the tests for BIT has failed for five times, it sets the software
system error flag in turn one of the port of micro-controller set to indicate the warning as failure
signal.
The FDR failure results in the Reset to Micro-controller & returns it to the start of
30 program. If the fault has cleared, FDR run normally. If the fault persists, FDR again Reset & go
through its start-up-sequence maximum for 5 times. Even if fault persists after 5 times, FDR not
reset further & go ahead to record parameters along with fault. No recording of data occur
during reset cycle. A discrete is available for forcing a fault for testing fault-generating circuit.
35 FDR System monitors the aircraft data/ parameters against the preset threshold value
stored in the recording unit and provide the real time visual & audio warning.
SUMMARY OF PRESENT INVENTION
40 The present invention, therefore, is directed to audio & visual warning for FDR.
An aspect of the present invention is System is to monitor the aircraft data/ parameters
against the preset threshold value stored in the recording unit and provide the real time visual &
audio warning.
A further aspect of the invention is that invention assists the pilot to monitor the health of
FDR also prompts the pilot in air through audio & visual warnings whenever the aircraft exceeds
the specified/predefined limits of critical parameters such as Engine RPM & other aircraft design
5 parameters
This system constitutes one important feature in control unit (CU) in FDR. This unit
apart from providing junction between FDR & external milking units, it basically provides audio &
visual warnings to warn the pilot in air about the exceedence limits & inform ground crew
members about the non-serviceability of the equipment. This system acts as maintenance
10 panel & is situated in the Cockpit and forms the main interface between the maintenance crew
and the FDR.
Front panel of CU consists of status indication lights, tone generators & self-test button
for providing the audio & visual warnings to the pilot either on demand or by continuously
monitoring the health of the system & providing useful alerts to the pilot when the aircraft is
15 airborne.
BRIEF DESCRIPTION OF THE DRAWINGS
The features and advantages of the present invention become more apparent and
descriptivein the descriptionwhen considered together with figures/flow charts presented:
20
Figure 1: isa Block Diagram of Audio & Visual Warning Interfaced with FDR& CU
Figure2:is a Block Diagram of Visual Warning
Figure 3: is a Flow Diagram ofAudio warning
25 DETAILED DESCRIPTION
Flight Data Recorder/Cockpit Voice Recorder (FDR/CVR) has been designed to
investigate the causes of crash. The FDR/CVR consists of a data acquisition & recording unit.
Further the present invention highlights the concept of placing an audio & visual warning system
30 inside the Control panel of FDR/CVR that helps the pilot/ground crew to ensure the
serviceability of FDR/CVR. Presently the control unit facilitates self-test function for Flight Data
Recorder/Cockpit Voice Recorder (FDR/CVR) to ensure the health of system & also interfaces
to Headset jack to verify the pilot, co-pilot, area microphone and the third crew audio Channel
outputs. Control Unit provides junction between FDR/CVR and external milking units. External
35 milking units down load data from FDR/CVR through this control unit.
The present invention assists the pilot to monitor the health of FDR/CVR also prompts
the pilot in air through audio & visual warnings whenever the aircraft exceeds the
specified/predefined limits of critical parameters such as Engine RPM & other aircraft design
parameters. This system constitutes one important feature in control unit in FDR/CVR. This unit
40 apart from providing junction between FDR/CVR & external milking units, it basically provides
audio & visual warnings to warn the pilot in air about the exceedence limits & inform ground
crew members about the non-serviceability of the equipment. This system acts as Maintenance
Panel & is situated in the Cockpit and forms the main interface between the maintenance crew
and the FDR/CVR.
Front panel of CU consists of status indication lights, tone generators & self-test button
for providing the audio & visual warnings to the pilot either 5 er on demand or by continuously
monitoring the health of the system & providing useful alerts to the pilot when the aircraft is
airborne.
• Discrete Inputs:
10 􀀹 FAULT_ FDR : OPEN/GND
􀀹 FAULT_CVR :OPEN/GND
Note: These are the inputs signals which need to be indicated through respective LEDs.
• Discrete Outputs
15
􀀹 PUSH_TO_TEST : OPEN/GND
Note: These are the inputs signals from switches and these signals are given to FDR.
The System monitors the aircraft data /parameters against the preset threshold value
20 stored in the recording unit & provide the real time visual & audio warning/caution as below:
1. Audio warnings (in flight), which activates whenever the predefined vital parameters
exceeds the safe envelope of that parameter. The warning comprises of a high density
intermittent audio tone of predefined audio tone beeps for the safe limits both lower & higher
value. The system generates separate warning based on whenever the parameter falls
25 below the lower limit & separate warning when the parameter crosses the upper limit.
2. The system generates visual warnings (In flight) which continuously ON whenever the most
critical parameter as defined by the design team cross the specified limit.
3. All real time warnings/caution is reversible in nature.
4. A mute command option inside the cockpit allows the pilot to reset the audio warning/tone
30 in the case of emergency as required by the crew.
5. The threshold value/limit for the real time warnings can be set & redefined by the pilots as
per their operational requirements.
6. A separate switch helps the pilot during flight to mark an indent input in order to highlight the
specific second of data during recording phase. The indents are filtered & displayed
35 separately in the ground for purpose of investigations.

WE CLAIMS:-
Accordingly, the description of the present invention is to be considered as illustrative only and is for the purpose of teaching those skilled in the art of the best mode of carrying out the invention. The details may be varied substantially without departing from the spirit of the invention, and exclusive use of all modifications which are within the scope of the appended claims is reserved. The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:
1. Audio & Visual warning system for FDR comprising; monitoring system aircraft parameters against the preset threshold value stored in the recording unit and provides the real time visual & audio warning/ caution; said warning means visual & audio which is decided on the basis of health of FDR; said Threshold values means acceptable limit set for each aircraft parameters on which the warning is decided; said FDR means Flight Data acquisition & recording system and warning is decided on the basis of stored aircraft parameter and health of the FDR; said control units means a panel in the aircraft which interfaced with FDR as well as warning signals;
2. The audio & visual warning system of claim 1 wherein the Audio warnings (in flight), which activates whenever the predefined vital parameters exceeds the safe envelope of that particular parameter.
3.The audio & visual warning system of claim 1 wherein said warning comprises of a high density intermittent audio tone of predefined audio tone beeps for the safe limits both lower & higher value. The system generates separate warning based on whenever the parameter falls below the lower limit & separate warning when the parameter crosses the upper limit.
4.The audio & visual warning system of claim 1 wherein said warning generateS visual warnings (In flight) which is continuously ON whenever the most critical parameter as defined by the design cross the specified limit.
5. The audio & visual warning system as claimed in any of the preceding claims wherein all real time warnings/caution is reversible in nature.
6.The audio & visual warning system as claimed in any of the preceding claims wherein a mute command option inside the cockpit allows the pilot to reset the audio warning/tone in the case of emergency as required by the crew.
7. The audio & visual warning system as claimed in any of the preceding claims wherein the threshold value/limit for the real time warnings set & redefined by the pilots as per their operational requirements.
8.The audio & visual warning system as claimed in any of the preceding claims wherein a separate switch helps the pilot during flight to mark an indent input in order to highlight the specific second of data during recording phase. The indents are filtered & displayed separately in the ground for purpose of investigations. ,TagSPECI:As per Annexure-II