This development, in Aerospace domain, facilitates assembler/designer to make
the system testing more reliable & to observe the deviation from realistic range or
user range.
BACKGROUND OF THE INVENTION
There was no method earlier to simulate the actual flight condition through test
rig’s to test the system at ground. In general, aircraft sensor related parameters
mainly Analog, ARINC-429, Discrete & Frequency were being checked as per
the test rig predefined inputs rather than actual values recorded during flight
operation which results into poor & less accurate testing of system in the defined
user range. Hence, dynamic generation from recorded sortie files was required.
SUMMARY OF PRESENT INVENTION
In accordance with one aspect of present invention, the system for dynamic
generation of various parameters is developed in LabView Environment and
comprises of followings:
1. Dynamic Generation 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
5. Analog Output Card with 16 bit resolution
6. Frequency Output Card with 16 bit resolution
7. ARINC Bus Tool with analyzer
Annexure-II
8. Controller
In accordance with second aspect of present invention, the System for dynamic
generation is developed in such a fashion that it can generate the parameters as
per the sortie file well within range due to precise specification of hardware being
used & executables provides data of any avionics system based on RS-422
protocol & can reconstruct the raw of sortie file in Engineering Value by using the
complex mathematical formulas for the conversion.
Executable functionality is broadly divided into following parts i.e
1. Reading the data from Sortie File & making of frame i.e 512 bits/sec
2. Converting the raw data in engineering values
3. Generation of Parameters as per the converted engineering values
4. Capturing of RS 422 data
5. Comparing the data of sortie file & captured data
6. Result Display
BRIEF DESCRIPTION OF THE DRAWINGS
The figures for dynamic generation of various parameters developed in LabView
platform are illustrated below.
The Fig 1 shows the block diagram for reading, generation, reception &
deceleration of results of parameters.
The Fig 2 shows the testing flow.
The Fig 3 Shows Signal Flow diagram.
Annexure-II
DETAILED DESCRIPTION
The system for dynamic generation of various parameters is developed as per
the components defined above. Random recorded sortie is taken from various
flight becomes the reference for the dynamic generation. That sortie is being
read by the dynamic generator & the data of entre file is formatted into a frame of
512 bits/sec which tells the no. of bits a system can handle per second.
The raw data into the engineering values is converted according to the complex
mathematical formulas for the conversion. Once the engineering data is
available, it is fed to the concern hardware means there are 512 bits/sec so there
would be 256 parameters having 2 bits, so the value at one location out of 256
location in entire frame would decide the type of parameters, if it is analog then
converted value would be fed to Analog Output module , if location is referenced
to discrete parameters then it would be fed to discrete output module, if location
is referenced to tacho parameters then it would be fed to frequency generator & if
it is referenced to ARINC parameters then it would be fed to ARINC Bus tools.
Hence, the concern hardware role is defined as per frame format & the signals
are generated according to its engineering value of the location. All the
generated parameters by the hardware can be monitored at BIBO i.e. break in
break out box as shown in fig 1.
The data would be available on telemetry to compare with fed or sortie file data,
In receiver RS 422 to USB Converter will convert the RS 422 type of protocol
data in USB 2.0 format which is being received in Rugged Laptop. Finally, it is
being monitored using dynamic generation module developed in LabView
Platform.
Dynamic Generator functionality is broadly divided into following parts i.e
1. Reading the data from Sortie File & making of frame i.e 512 bits/sec
Annexure-II
2. Converting the raw data in engineering values.
3. Generation of Parameters as per the converted engineering values
4. Capturing of RS 422 data
5. Comparing the data of sortie file & captured data
6. Result Display
So as shown in figure-2 the data received from telemetry is being compared with
the sortie file data & the result is being declared on the behalf of tolerance
defined for that particular parameter & in case of digital data the tolerance
becomes zero or sometime LSB (Least Significant Bit). A log file is generated in
non editable format with time & date for the record of the system.

WE CLIAMS:-
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 System for dynamic generation, comprising :
- Rugged / Non Rugged Laptop/computer
- RS 422/RS 485 to USB 2.0 Converter hardware.
- Shielded Loom assembly
- Dynamic Generation executable developed in LabView Environment
- Analog Output Card with 16 bit resolution
- Frequency Output Card with 16 bit resolution
- ARINC Bus Tool with analyzer &
- Controller

2. The system according to claim 1, capable of generating engineering value with at least one sensor data 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 from previously recorded sortie file or any other sortie file.

4. The system according to claim 1, used primarily to test Solid State Flight Data Recorder for dynamic testing beyond the predefined range of test rig.

5. The system according to claim 1, used to compare & deceleration of result for parameters in a frame format consisting of atleast 64words/sec.

6. The system according to claim 1 & 3, used to improve the reliability of Solid State Flight Data Recorder. ,TagSPECI:As per Annexure-II