Control Project

Madhu Pujari

****, ****** **, ***

****,

Mississauga, L5J 3T4, ON,

CANADA.

Tel: 647-***-****

Email: *****.*******@*****.***

CAREER SUMMARY

. IT Professional with 7.00 years of experience in Real Time Embedded

Programmer and V&V expert for Embedded Systems.

. Hands-on experience in Embedded Design, Development, Unit testing,

Integration testing, Hardware and Software testing and validation,

Certification of Software, with complete SDLC knowledge.

. Well versed in C, C++, Java, Ada, ARINC429, DO178B, UNITY, AUTOLAWS,

HSITD, LAWS Language (Honeywell Proprietary).

. Involved in Formal Qualification of the software witnessing Boeing

Customers.

. Involved in certifying the software in SOI 2 and SOI 3 audits of

Boeing.

. Skilled in Vector cast testing tool, white box testing, planning test

cases, designing and analyzing code, Code Reviews, Embedded Linux(OS)

RTOS(DSPBIOS), VxWorks(RTOS), Embedded system Concepts.

. Hands on Experience with the low level drivers like ADC, I2C drivers.

. Excellent interpersonal and communication skills.

. Strong team player

. Excellent verbal and written communication skill

. Ability to work in different lines of business like Boeing, Airbus,

Gulfstream, Embraer etc

. Ability to thrive in a fast paced, and pressured environment.

TECHNICAL SKILLS

. Languages: C, C++, ADA95, LAWS (Honeywell Proprietary), Java.

. Operating Systems: DSP BIOS (RTOS), VxWorks(RTOS) Win2000, Win XP, VAX

(VMS)

. Testing Tools: VECTOR CAST, UNITY, Autolaws, HSITD, Preprocessor tool

(Honeywell Proprietary).

. Development Tools: IBM Rational Rhapsody, Code Composer Studio,

WindRiver.

. Configuration Tools: PVCS, Clear Case, SVN, VSS.

. Standards: DO-178B, DO254B, DO160F, MISRA, BHI.

. Protocols: ARINC 429, I2C, SPI, UART.

PROFESSIONAL EXPERIENCE

Honeywell,

Mississauga, ON Feb

2008 to Dec 2011

Senior Engineer

Projects Handled:

Project Name: Nitrogen Generation System - NGS

Description:

The NGS controller is responsible for - Regulation of bleed air temperature

entering the ASM by modulation of the Torque Motor Valve, Control of NGS

SOV: valve will be commanded On (regulating) or Off based on various system

states, Control of NGS OTSOV: valve will be commanded On or Off based on

various system states, Control of TCSOV (non-737): valve will be commanded

On or Off based on various system states, Control of ASM High flow valve:

valve will be commanded OPEN or CLOSED based on various system states,

Detection of over temperature conditions, Detection of loss of flow,

Low/High Speed ARINC 429 communication (for 747 and 777 only) to Central

Maintenance Computer System (CMCS)

. Involved in, Coding, Hardware and Software Integration Testing.

Software Integration Testing.

. Technology used - PVCS, Configuration Management, Polyspace, Vector

Cast

. Involved in Formal Qualification of the software witnessing Boeing

Customers.

. Involved in certifying the project in SOI 2 and SOI 3 audits of

Boeing.

Project Name: OBIGGS (On-Board Inert Gas Generation System)

Description:

A small portion of bleed air is taken from the bleed crossover duct and

routed to a pneumatically

Actuated pressure regulating and shutoff valve (PRSOV), which provides

primary on/off control of the OBIGGS. In addition, the PRSOV regulates to

approximately 35 psig in order to minimize the probability of providing

excessive pressure (and resulting flow) to the OBIGGS. The PRSOV is

commanded closed when the system is inactive (i.e. in standby, or in the

event of over temperature or overpressure conditions).

The bleed air is conditioned to 190 F using the hot side temperature

control valve

Temperature is controlled by modulating the torque motor of the TCV to

control the amount of hot air flow by-passed around the OBIGGS Heat

Exchanger. Temperature sensors at the Heat

Exchanger outlet and at the inlet of the ASM provides feedback for this

control.

Once conditioned, the bleed air passes through a filter to coalesce

particulate and aerosol matter that may be present in the bleed air. Dust

and sand particles will be captured, as well as oil, hydraulic fluid, and

water from the system. This will prevent excessive contamination built up

within the ASM membrane fibers, which can result in lower flow, and higher

oxygen levels in the Nitrogen Enriched Air (NEA).

The filtered, conditioned air then passes through the ASM, which removes

all gases except N2

This is based on a molecular size difference, where only N2 is small enough

to pass through the ASM membrane fibers.

For secondary over temperature protection (when the PRSOV fails open), a

solenoid valve

(OTSOV) is installed upstream of the ASM. This valve is actuated by a

thermo-switch which trips at approximately 265 deg F and closes the valve.

This valve can also be commanded to close by the OBIGGSC.

. Involved in, Hardware and Software Integration Testing. Software

Integration Testing.

. Technology used - C, PVCS, Configuration Management, Polyspace, Vector

Cast

. Involved in Formal Qualification of the software witnessing Boeing

Customers.

Honeywell Technologies Solutions, Bangalore Feb 2006

to Feb 2008

Senior Engineer Dec 2011 to Feb

2012

Project Name: A350 XWB Cabin Pressure Control Systems (CPCS)

Description:

The A350XWB Cabin Pressure Control System (CPCS) consists of two

electrically actuated Outflow Valves (OFV), which are installed in the

forward and aft a/c lower skin. The OFVs are controlled by two Outflow

valve Control Units (OCU) installed in the triangle area near the forward

and aft cargo door. Both OCUs measure the actual cabin pressure, calculate

the target cabin pressure and control the OFVs to vary the airflow

discharged through the valves in order to increase or decrease the fuselage

internal air pressure according to the demands of the aircraft operation.

In addition the system comprises one pneumatic Overpressure Relief Valve

(ORV) installed in the rear pressure bulkhead and two Negative Relief

Valves (NRV) installed in the forward LH and RH skin.

The System BITE and CPIOM Gateway partitions hosted on the CPIOM

communicate with the OCU modules over dedicated ARINC 429 transmit and

receive links. In addition they communicate with the SACU and other

aircraft systems over the ADCN (AFDX) network. The CRDC Gateway

functionality receives data from the OCU MON partition and SACU over

dedicated ARINC429 transmit links. The CRDC communicates with the CPIOM and

other aircraft systems over AFDX.

. Involved in design, coding, unit testing

. Technology used - C Language, PVCS, Clear case for Configuration

Management. Polyspace

Project Name: Pack Zone Temperature Control (PZTC)

Description:

The air conditioning and temperature control system will consist of two

controllers, two air conditioning packs and three zone trim valves each

controller will consist of three sections

1. A digital section which will provide automatic control of one pack and

up to two of the three zones. Control will be performed by a

microprocessor using software which will implement the requirements

outlined herein.

2. Fault monitoring of the SRADA based on discrete input signals.

3. An independent analog circuit, with back-up zone and pack inputs,

which will provide standby, pack Control in the event of a failure of

automatic control.

For each controller/pack combination, one will be designated as "left" and

the other as "right". Under normal Operating conditions, in the absence of

system faults, both controller/pack combinations will provide pack and Zone

control. One controller will be responsible for controlling the flight deck

and one zone. The other Controller will control the remaining zone and

provide a spare control for the flight deck in the event that a System

component failure renders the primary flight deck control inoperable.

Control of the flight deck trim valve is switched between left and right

controllers using a Customer Furnished Equipment (CFE) relay. If loss of

one zone duct loop occurs, the zone temperature errors will be averaged to

produce a duct demand in order to provide a reasonable response to all

zones. If the digital pack control in the left controller fails, the analog

standby pack of the right controller will be switched in to control the

left pack. Similarly, the analog standby pack of the left controller will

control the right pack in the event of a failure of the digital Section of

the right pack controller. The analog standby pack of either controller

will select its pack demand from the standby pack demand signal generated

from the digital section of its own controller, provided this Signal

(standby pack demand) has not failed. If the standby pack demand signal has

failed, the analog standby pack will select its own analog standby pack

demand signal for generation of the standby pack Temperature Control Valve

(TCV) drive signal.

. Involved in unit & integration testing (white box testing).

. Technology used - Ada language, PVCS, Clear case for Configuration

Management.

. Involved in Formal Qualification of the software witnessing Boeing

Customers.

. Involved in certifying the project in SOI 3 audits of Boeing.

Infosys Technologies Limited, Mysore

Feb 2012 to Till Date

Engineering Lead

Projects Handled:

Project Name: Cased Hole Architecture Program (CHAP) Telemetry

Description:

The Cased Hole Down hole Architecture Project (CHAP) System consists of

Surface Data Acquisition system, Line Control Panel, 1000V DC Max Power

Supply, Wireline communication, Telemetry Subsystem (Acquisition Control

Module consists of Power Supply Unit, CHAP System Controller and Flash

Memory Unit), Arcnet Communication interface, CRAL connected via the STIC

(Standard Tool Interface Card), the 3504 legacy instruments (RPM, GR1, GR2

and GR3) connected via the XOVER (Cross Over Sub for legacy wireline

instruments) sub.

The main purpose of this new architecture is to integrate common

measurements and functions into a single module: borehole pressure,

borehole temperature, CCL (Casing Collar Locator), gamma ray,

accelerometer, telemetry or battery, memory, and power conditioning

The ACM is the core part of the CHAP telemetry system. Acquisition and

Control Module (ACM) comprises of a pressure bulkhead, CCL, CHAP System

Controller (CSC), Wireline and Temperature/Pressure Board, Power and Arcnet

Board, Memory Controller, Memory Cooler Heat Sink and Peltier cooler, and a

GR.

The FMC (Flash Memory Controller) which is connected to the CSC will

perform the following functions

Receive messages from the CSC (CHAP System Controller) via MCBSP link.

Store certain message payload to flash memory in redundant fashion with

ECC. Facilitate the reading of the flash memory contents via USB or MCBSP.

Control the temperature of the flash memory chips via the Peltier cooler.

Maintain readings of its own analog inputs and digital states and provide

them to the CSC for monitoring purposes. Store bad block information,

memory block allocation for each file, and statistics such as total

minute's time above 150 degrees C in EEPROM. Perform wear leveling across

flash memory blocks by virtualizing the block numbers so that the entire

flash memory address space is used evenly over the course of use.

. Involved in design of requirements, Software Architecture, coding,

unit testing

. Technology used - C Language, Code Composer Studio, DSPBIOS (RTOS),

VSS (Configuration Management tool).

EDUCATION

. Post Graduation Diploma in Embedded Systems Design Embedded Systems

(DESD)

CDAC, Trivandrum in Feb 2006.

. Bachelor of Technology in Electronics and Communication Engineering

from JNTU University Hyderabad in April 2005

CERTIFICATIONS

. Certified as Competent Communicator from Toastmaster's International

US.

. Six Sigma Green Belt Certified.

ACCOLADES

Individual Excellence Award

. For fantastic support on the PZTC program to complete the UT activities,

SOI3 Audit preparations and presentation and completing the FQT with

ease.

Individual Excellence Award

. For dedicated efforts and excellent support to complete block 6.5

activities on time.

Individual Excellence Award

. For commendable efforts and dedication in training the team which is

completely new and achieving the project deadline with very high

quality

Customer Award

. His dedication, perseverance & consistency in contributions towards

A380-SEPDS project which resulted in successful & timely certification

of S6.3 software and wide acclamation by all Honeywell & Airbus

stakeholders.

Team excellence award

. Consistently meeting the customer expectation in software design and

verification activities for the NGS program, team has performed at the

highest levels under very challenging circumstances.

Team excellence award

. For the successful completion of NGS 6.0 release and the excellent

team work towards the successful completion of SOI-2 and SOI-3 audits

from Boeing.

Team Excellence Award

. Sustained customer focus, excellent team collaboration,

multidisciplinary, highly commendable effort enabled successful

completion of V&V activities with uncompromising quality on S1.2, S4,

S5, S6.2 & S6.3 releases amidst challenging schedule.

Team Excellence award

. Delighting the partner consistently i.e. obtaining consistently high

PVI rating.

Spot Award

. Excellent support for Block 6.4 Test developments and FQT activities.

Spot Award

. For efficiently training and handling the team completely new on H/SI,

remarkable efforts in achieving the status on H/SI.

Spot Award

. Madhu has provided a major contribution for P8-MMA project during the

deadline of the project.

Spot Award

. Dedicated efforts and strong commitment to meet aggressive H/SI

schedule in Block 6.1 and Block 6.3.

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