Field of the invention
This development, in Aerospace domain, facilitates assembler/designer to
calibrate & monitor the behavior of various parameters. Online monitoring
system reads the real time data, from electronic port and converts it. into
meaningful data. Using this meaningful data, sensors installed in the aircraft
can be checked/ calibrated.
The real time calibration interface system reads the real time data from serial
port and sends it into database of-non editable format being used for
calibration. Using this database of various parameters, sensors installed in
the aircraft can be calibrated in feedback system.
Background of the invention
There was no real time system to calibrate the aircraft sensor related
parameters mainly Analog, ARINC-429, Discrete & Frequency & to check
health of avionics system during engine run on ground. In general, parameter
values were checked by replaying the data recorded in PMM of SSFDR which
makes it a cumbersome process. Hence, this online monitoring system has
beje'ri developed to reduce the calibration time as well as to check the health
of various subsystem installed on the aircraft.
Summary of present invention
Online Monitoring system characterizes the process by which an object's
characteristics are measured (such as velocity of an aircraft), and the results
are transmitted to a distant station for display, record, and analysis purpose.
The transmission media may be air and/or space via satellite and/or copperwire
and/or fiber cable for static ground environments like power generating
plants,
Annexure -1
, Sheet 3 of 12
Online Monitoring system is developed in LabView Environment, and
comprises of followings:
1. Online Monitoring executable developed in LabView Environment
2. Rugged / Non Rugged Laptop/computer
3. RS 422/RS 485 to USB 2.0 Converter hardware. ,
4. Shielded Loom assembly
The Online Monitoring system is developed in such a fashion that it can
provide data of any avionics system based on RS-422 protocol & can
reconstruct the raw as well as Engineering Value of that system in real time
by using the complex mathematical formulas for the conversion.
Software functionality is broadly divided into three parts i.e
1. Capturing of RS 422 data,
2. Making the Frame in defined format i.e 256 words/sec
3. Data Display
Detailed Description
Online Monitoring system characterizes the process by which an object's
characteristics are measured (such asvelocity of an aircraft), and the.results
are transmitted to a distant station for-display, record, and analysis purpose.
The transmission media may be air and/or space via satellite and/or copper
-wire and/or fiber cable for static ground environments, like power generating
plants. . .
Online Monitoring supports large numbers of measurands as it;is too costly
and impractical to use separate transmission channels for each measured
quantity. The Online Monitoring system involves grouping of measurements
(such as pressure, speed, and temperature) into a format that can be
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Annexure - I
Sheet 4 of 12
transmitted as a single data stream. Once received, the data stream is
separated into the original measurement for analysis.
Design & Development of new aircraft may use this system. During initial
flight testing, an aircraft performs a variety of test maneuvers. The critical
flight data from a maneuver is transmitted to flight test engineers at a ground
station where results are viewed in real time or analyzed within seconds of
the maneuver. Real-time monitoring allows the "safety officer" to make instant
decisions on whether to proceed or terminate a test. With real-time analysis,
the flight test engineer can request a maneuver be repeated, the next
maneuver be performed, or test plan alternatives be substituted. Real-time
data is also captured to storage media, such as disk and tape, for later
analysis and archiving.
The avionics equipments mainly comprising of a Solid State Flight Data
Recorder (SSFDR), flight computer, telemetry, power supply, and support
modules. The SSFDR possesses a sensor suite including an altimeter and
accelerometer, and logs the data over the entire flight. Telemetry relays real
time FDR data to the ground.
An Online Monitoring system is often viewed as two components, the
Airborne System and the Ground System. In actuality, either or both may be
in the air or on the ground.
The Online Monitoring Software is developed in such a fashion that it can
provide the data of any avionics system based on RS-422 protocol & can
reconstruct the raw as well as Engineering Value of that system in real time
by using the complex mathematical formulas for the conversion. The
algorithm for the Online Monitoring System is developed as per Fig 5 which is
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Annexure -1
Sheet 5 of 12
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a flow chart. The experimental setup to execute the entire process has been
defined in Fig 4. The various screen shot to observe the parameters values in
various format for calibration has been explained in screen shot as defined in
Fig 1, Fig 2 & Fig3,The ultimate objective of the entire system is to have the
Online Calibration of critical or non critical parameters as well as health status
of installed subsystems moreover finding out the failure of any subsystem
further more root cause analysis rectification if any.
(Name of the Invent
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Annexure -1
1. Anubhav Garg Sheet 6 of 12
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File Edit View Project Operate Tools Window Help Tclcmcu
Replay "j»n>ii<@i"i .f>
SELECTION OF PARAMETERS
I ARINC-429
Heading (HDG) Jo"
Pitch (PATT) fO |
Roll (RATT) Jo___^_"[
Pressure altitude (ALT) |cT
GPW5-
JRMALJ* j
GPWS INOP
TCASACTIVE
Indicated air speed (IAS) | 0 7T
Outsidel air temp. (OAT) Jc'["_
Vt. Beam Deviation (VBD1)JO
Hz. Beam Deviation (HBD1) |o_
ACTIVE
'-'-^-----^
J NORMALj
Vt. Beam Dev.( VBD 2)
Hz. Beam Dev.( HBD 2)
NAV rece. freq. (NAVF2)
I
j 1 oo_
TCAS/Mode S # l
TCAS/Mode S #2
TCAS System status
M. Beacon Passage (MBP1)
NAV receiver freq. (NAVF1) j 100
DME Distance (DMED) JfXO
DME Ground speed JcT
Drift Angle (DANG) Fo.00
Present LAT J o _ j ^N
Present LON Jo
DATE dd JO*"
GPS Ground Speed fo
mm | 0 \ jyy
Outer MKR
Midlde MKR
Inner MKR
M. Beacon Passage (MBP2)
Outer MKR.
Midlde MKR
Inner MKR
EM
Fig1- Selection of ARINC Parameters
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Annexure -1
1. Anubhav Garg Sheet 7 of 12
.&; m o n i t o r i n g . vi .Tools
Fjle Edit View Project Operate lools Window yelp n^ni
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SELECTION OF PARAMETERS
ANALOG
VOLTAGE Table Engg. Value Unit
f
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!
K
Radio Altitude
Torque RH Engine
Toruqe LH Engine
Normal Acceleration
Longtitudinal Accel.
Lateral Acceleration
Elevator Surface Position
Yaw Trim
Roll Trim
Pitch Trim
Analog Spare #3
Rudder Paddle Position
Left Alieron Surface Position
Right Aileron Surface Position
Spare
Flap Position
FREQUENCY
fj j! RPM (LH) HZ
! RPM (RH)HZ
Jo RPM (LH) %
J ; RPM (RH) °/o
I
EVENT MARKER
O F F j
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RADIO KEYING-PILOT
OFfy
RADIO KEYING-COPILOT
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LH PROP. MODE
NORMAL I
RH PROP. MODE
NORMA ZJ
LH ENG OIL PRESS
NORMAL
RH ENG OIL PRESS
NORMAL
AIR/GROUND STATUS
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DISCRETE
NLG POSITION
PRIMARY NAV SYS
LH AC BUS
RH AC BUS
PITOT HEATING
INLET DE-ICE
PROPELLER DE-ICING
GROUND OP SWITCH E -OPEN t J
51
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H
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DISCRETE SPARE 1
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MASTER WARNING
STALL WARNING
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LH ENG FIRE J..^ ..N.s. O. ^_^—J*
RH ENG FIRE
DC BUS 1
DC BUS 2
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Fig2- Selection of Analog, Discrete & Frequency Parameters
Annexure -1
1. Anubhav Garg Sheet 8 of 12
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Table Control
1 PSA 2 RALY 1 3
606 | 0 0
0 1 0 1 0
3S5W 3* 3s
0
49
0
"6'5'CA'N1 '
0
81PotRef28
0
97
0
0 ° 50HDG 51
0 |0
^6'6"P'AYV i' 6'7
0
82 RALT 1
0
98 RALT 1
o
0
83
0
99 HDG 1
0
1 13 CAN 111 115 IAS 1
0
I^VF'SB
0
145
0
161 C A "N
0
177
0
0
130
0
146 PALT 1
0
162
0
178
0
0
131
0
147
0
163 VBD 1
0
1 7 9 MBP 1
0
193 DMEO 194 195 VBD 1
o |o |o
209
0
225 NAVF 1
0
241 PALT 1
0
0
226
0
242
0
0
227
0
243
0
m
Tools Window Help
4 5RDP
0 |0
0 1 0
36 3?
0 |0
52 S3
0 |0
68 69 RTSP
0
84 YTSP
0
1 0 0 ALP
0
0
85 DGND
0
101 RDP
0
1 16 1 17 RALT 1
0
132
0
148 ACL
0
164
0
180
0
0
133 RDP
0
149 RALT 1
0
1 65 RDP
0
181 RALT 1
0
1 96 19"7
0 |0
2^2" A d . iib
0
228 ALP
0
2,44
0
0
229 ALP
0
245 FSPR2
0
4
6 ASPR3
0
22
0
TS
° S4
° 70PotRef5
0
86ETR
0
102 RALP
0
1 1 8 DGND
0
134
0
150 OS 1
0
i eVcTsV"'
0
182 RAH
0
198
•
SELECTION OF PARAME
J RAW
7 PALT dl RALT
? 0
0 | 0
0 0
55 56
o |o
71 PALT 72 RALT
0 •
87 DATE
0
103 PALT
0
0
88 DATE
0
104 RALT
0
119 DANG 120 GPWS
0
135 PALT
0
151
0
11 T6"7"P"ATT,~
0
183
0
0
•L£3'6lRVT"
0
152 CAL
0
168 RALT
0
184
0
199 PAL"T 200 RALT
0 | 0 | 0
2l4
0
230
0
"246 R*RlH
0
r
2 * 5 216
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1?31 tfKLY"'
0
247
0
0
232 RALT
0
248
0
ibJ
9PTSP 10
0 | 0
25 Y1M2 26 CA'L
0 | 0
0 |0
57 58 OAT
TERS
1 1 CAN 12
0 0 •
27 23 IAS
0 | 0
VS A I Y W KtY
0 | 0
59 CAN 60
0 |0 0 •
73 ELP ^7*4 '
0
89 ALT l
0
105 ELP~
0
0
90 GNDS
0
106
0.
121 TCAS 122
0
T S V A L V "
0
153
0
0
138 HDG 1
0
154
0
169 170 MBP
0
185
0
0
.166 RALP
0
201 C AN 2 0 2 HBD 1
| 0
2 1 / 218 CAL
0 1
~2~3~3 R'TSP
0
249
0
0
234
0
250
0
U,75"GND"S~
0
91
0
107 CAN
0
0
13ETLH
°
° V5
0
61
0
Ve'VA's' '"77"
0
92
0
108 TCAS
0
123 124
0
T 3 9
0
155 CAN
0
171
0
187
0 •
0
140
0
156 PALT 1
0
172
0
188
0
203 CAL 2 04 LAT
0 | 0 '
219 220 GMI
o-
235
0
251
0
0
236
0
252 GPWS
0
0
93
0
109 PALT 1
0
125 PALT 1
0
1 4 1 ASPR 2
0
157 FP
0
173
0
189 RLH
0
205 LAT
zVi GW
0
237
0
253
0
14
° 30
0
0
62 OAT 1
o
78 B T ' I ) B T '2
0
94 RALP
0
1 10
0
126 RALT 1
0
142 NAVF 1
0
1S8
0
174
0
190 BT3/BT4
0
206 ELP
o
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0
238
0
254
0
M = 3
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Replay
15 16 PALT l|f A
° 31 VBD
0
0
63
° 79 V8D
0
95 FSPR1
0
1 1 1
0
127
0
143'
0
159
0
""75VAYP' '
0
191 RALT 1
0
26?
0
2^3 "ON
0
2~39~DA"NG
0
255 CSM
0
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o 1
1
64 ELP |
1
60 NAVF |
0 |
96 IAS 1
^ J
1 1 2 PALT 1
o 1
128 1
1
144 ALT 1 1
1
160
1
176 |
° 1 192 HBD l | 1
208 |
1
224 |
1
240 NAVF
1
256 1
0 \^r
1
1
. JJ3. ; m
a
R
Fig3- Selection of Raw Values
Annexure -1
1. Anubhav Garg Sheet 9 of 12
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Rugged
Ground Power
Supply
>
RS 232 to
USB 2.0
Converter
Interface. Health
Monitoring
System
R S 4 8 5 / RS
422 to USB 2.0
Converter
Aircraft's
Parameters to be
Calibrated
Fig 4:-Setup for Dynamic Calibration of Flight Parameter in Real Time
1. Anubhav Garg
Annexure -1
Sheet 10 of 12
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Start
Click on Dynamic
Calibration
, i . L U I
Wait for Self Test
FAIL
PASS
Read the RS 422/RS
485 frame
Perform the curve fitting with respect
to set data & read back data
I
Program the Parameters through
RS 232 & compare the result of
set data & read back data
Fig 5:-Flow Chart

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.
We claim
1. The Online Monitoring system, comprising:
• Online Monitoring executable developed in Lab View Environment
• Rugged / Non Rugged Laptop/computer
• RS 422/RS 485 to USB 2.0 Converter hardware.
•> Shielded Loom assembly
2. The system according to claim 1, capable of interfacing with at least
one sensor available on aircraft like temperature, pressure using at
least one dedicated interface and/or at least one standard interface.
3. The system according to claim 1, further capable of capturing
aircraft/vehicle data and conversion in real-time on ground/in water.
4. The system according to claim 1, used primarily to calibrate
aircraft/vehicle sensors in real-time and capable of curve fitting in,
polynomial degree for at least one sensor data available on aircraft like
temperature, pressure using at least one dedicated interface,and/or at
least one standard interface. However, offline calibration can-also be
performed.
5. The system according to claim 1, used to obtain parameters in a frame
format consisting of at least 64words/sec.
6. the system according to claim 1 & 4, used to improve the precision of
measurement for various parameters of aircraft.