FIELD OF THE INVENTION
The present invention relates to ARINC429 parameter which is the most commonly
used avionics data bus in aircrafts. The feature of this invention that testing
methodology of ARINC429 data through RS422.
BACKGROUND OF THE INVENTION
Earlier in the aviation field ,the parameter like analog, discrete and frequency are
sufficient to provide the information from various sub-system of aircraft .But as the
system getting advance and digital , it required a different data bus which can
handle with these critical parameter. ARINC429 data bus is one of these data bus
which is best suitable for aviation application.
Generally the data transmitted from the test equipment has been stored in buffer
and the only method to verify the data through emulator through reading the buffer
but we are unable to read the data in real time. So the facility of RS422 data bus
are very useful in this situation that we can read the data in real time and check the
possibility of loosing the data. ARINC 429 is suitable where labels are known and
where sampling rate of parameters are known and overall traffic of data is
comparatively less.
SUMMARY OF PRESENT INVENTION
In accordance with one aspect of present invention is to provide a procedure that
facilitates testing method of ARINC429 data through RS422
In accordance with second aspect of present invention is to provide a procedure
which can communicate upto the 4 ARINC429 channels.
Briefly, the present invention is a testing methodology for ARINC429 parameter
from the various aircraft sensors in through RS422 databus on realterm software.
Annexure‐II
An advantage of the present invention is that a ARINC429 data can be checked
online while acquiring the data through various sensors and data loss can be
minimized through this facility.
BRIEF DESCRIPTION OF THE DRAWINGS
The features and advantages of the present invention will become more apparent
and descriptive in the description when considered together with figures/flow
charts presented:
Fig. 1 shows setup of ARINC429 data verification through RS422.
Fig. 2 shows Flow chart diagram of Acquiring the ARINC429 Labels.
Fig.3 shows the real term data structure.
DETAILED DESCRIPTION
Referring to Fig 1, shows the setup of ARINC429 data verification through RS422.
For transmitting the ARINC429 data from test equipment , the test equipment need
to be configured with labels, parity, data, SDI, SSM. Sampling rate of each
parameter is also need to be configured means the rate at which parameter will be
transmitted. A method to ensure the data transmitting from test equipment to
system is through emulator with the help of emulator, read the buffer and verified
all the data transmitted from test equipment. With the emulator the data transmitted
from the test equipment in run time cannot be checked. So, a unique facility of data
verification is data available in buffer is transmitted on RS422 data bus and the
data can be visualize on serial data capturing tool like realterm in run time. If there
is any data loss then it can be found easily. On Realterm, there is facility which can
be used to observe the data as per requirement of user.
Referring to Fig 2, Labels loading of each ARINC parameter has been done after
configuring the control register in label loading mode for each ARINC channel so
that during recording, the coming label can be checked with loaded labels and
when mismatch occurs then the particular label can be ignored. Enable the
Receive interrupt Selection Register and the Receive interrupt Enable Register for
the generating the interrupt for ARINC429 channels.
Annexure‐II
ARINC Receive interrupt enable Register:
D15 D14 D13 D12 D11 D10 D9 D8 D7 D6 D5 D4 D3 D2 D1 D0
EN
CH
16
EN
CH
15
EN
CH
14
EN
CH
13
EN
CH
12
EN
CH
11
EN
CH
10
EN
CH
9
EN
CH
8
EN
CH
7
EN
CH
6
EN
CH
5
EN
CH
4
EN
CH
3
EN
CH
2
EN
CH
1
Enable = 1
Disable = 0
D0 to D7 bits generate interrupt for ARINC int #1
D8 to D15 bits generate interrupt for ARINC int #2
ARINC Receive interrupt selection Register:
D15 D14 D13 D12 D11 D10 D9 D8 D7 D6 D5 D4 D3 D2 D1 D0
HF
16
or
NE
16
HF
15
or
NE
15
HF
14
or
NE
14
HF
13
or
NE
13
HF
12
or
NE
12
HF
11
or
NE
11
HF
10
or
NE
10
HF
9
or
NE
9
HF
8
or
NE
8
HF
7
or
NE
7
HF
6
or
NE
6
HF
5
or
NE
5
HF
4
or
NE
4
HF
3
or
NE
3
HF
2
or
NE
2
HF
1
or
NE
1
Annexure‐II
‘0’ = Half Full(HF) ‘1’ = Not Empty(NE or Rx ready)
D0 for CH1 and D15 for CH16
Referring to Fig 3, displays the window of Realterm in which the ARINC429 data
comes in this pattern. After the regular interval the data repeated itself according
the configuration of ARINC429 transmission setup. We can verify the data online
easily and check if there is possibility of missing of any data.

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. We Claim

1. Testing methodology of ARINC429 data through RS422, comprising:
- An embedded hardware with at least one processor for running the ARINC 429 channels acquisition executable,
- Relevant memory like Random Access Memory (RAM) and/or Non-volatile Random Access Memory (NVRAM) and/or Read Only Memory for storing program and scratch calculations &
- Respective looms/cables .

2. The system according to claim 1, further comprising of
- A signal conditioner circuit to receive electrical signals corresponding to ARINC 429 data and provide digital data as per ARINC 429 specification.

3. The system according to claim 1 & 2, capable of acquiring the ARINC parameter through various sensors.

4. The system as per claim 1 & 2, is not limited to airborne applications alone but can be used for commercial application.

5. The system as per claim 1 & 2, is qualified for working in extreme weather conditions like high temperature, low temperature, vibration, shock, acceleration etc. ,TagSPECI:As per Annexure-II