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Avionic Systems Engineering Training Crash Course

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Introduction:

Avionic Systems Engineering Training Crash Course Hands-on

Avionic Systems Engineering Training Crash Course covers a comprehensive training of theories, technical, certification requirements, and the technologies applied in the today and future avionic systems. By taking this training course, you will fully understand all the systems involved in the avionic technology, plus you will be introduced to DO-178C and DO-254.

Duration: 4 days

Avionic Systems Engineering Training Crash Course Related Courses

Customize It!

● We can adapt this Avionic Systems Engineering Training Crash Course to your group’s background and work requirements at little to no added cost.
● If you are familiar with some aspects of this Avionic Systems Engineering Training Crash Course, we can omit or shorten their discussion.
● We can adjust the emphasis placed on the various topics or build the Avionic Systems Engineering Training Crash Course around the mix of technologies of interest to you (including technologies other than those included in this outline).
● If your background is nontechnical, we can exclude the more technical topics, include the topics that may be of special interest to you (e.g., as a manager or policy-maker), and present the Avionic Systems Engineering Training Crash Course in manner understandable to lay audiences.

Audience / Target Group

Avionic Systems Engineering Crash Course is a 4-day course designed for:

● Design engineers
● Manufacture engineers and managers
● Support engineers
● Application engineers
● Systems engineers
● Safety engineers
● Software/hardware engineers
● Quality assurance or certification personnel
● All other professional engineers and managers involved in avionic systems onto air-vehicles.
● Participants are required to have an engineering or science background.

Avionic Systems Engineering Training Crash Course - Objectives:

Upon the completion of Avionic Systems Engineering Crash Course, the attendees are able to:

● Understand and explain how avionic systems and its components work
● Describe and evaluate the basic performance requirements and essential components of all the main avionic systems to be found in modern civil and military air-vehicles
● Understand the criteria for and derive the functionality of avionic system elements within the fully integrated ‘systems of systems’
● Formulate and incorporate avionic systems from requirements definition, through concept development to final execution within their operating role
● Understand and use the architectural rules and the design process to be used to certificate safe and reliable avionic systems
● Explain avionic certifications
● Advanced systems
● System design and development
● Understand and implement DO-178C, DO-254 requirements
● Understand various data bus systems

Avionic Systems Engineering Training Crash Course - Course Content:

Overview of Avionic Systems and Systems Engineering Processes

What is avionic systems engineering?
Terminologies
Background
Applications
Guidance and standards
Systems integration
Systems interaction
Flight control systems
Engine control systems
Fuel systems
Hydraulic systems
Electrical systems
Pneumatic Systems
Environmental condition systems
Emergency systems
Rotary wing systems
Military radar systems
DO-178b/c
RTCA DO-178B/C / EUROCAE ED-12B/C
Software Considerations in Airborne Systems and Equipment Certification
Software certification standard for airborne systems on commercial aircraft
Various software life cycle processes
DO-254
DO-254 Design Assurance Guidance for Airborne Electronic Hardware
Aircraft electronic systems assurance of electronic airborne equipment safely
Line replaceable units
Circuit board assemblies
Application specific integrated circuits (ASICs)
Programmable logic devices

Flight Control Systems

Principles of flight control
Flight control surfaces
Primary flight control
Secondary flight control
Commercial aircraft
Primary flight control
Secondary flight control
Flight control linkage systems
Push-pull control rod system
Cable and pulley system
High lift control systems
Trim and feel
Flight control actuation
Simple mechanical/hydraulic actuation
Mechanical actuation with electrical signaling
Multiple redundancy actuation
Mechanical screwjack actuator
Integrated Actuator Package (IAP)
Advanced actuation implementations
Civil system implementations
Top-level comparison
Airbus implementation
Fly-By-Wire control laws
A380 flight control actuation
Boeing 777 implementation
Boeing 787 Implementation
Military Aircraft Implementation
Interrelationship of flight control, guidance and flight management

Engine Control Systems

Engine/airframe interfaces
Engine technology and principles of operation
The control problem
Engine indications
Engine oil systems
Engine off takes
Reverse thrust
Engine control on modern civil aircraft

Fuel Systems

Characteristics of fuel systems
Description of fuel system components
Fuel quantity measurement
Fuel system operating modes
Integrated civil aircraft systems
Fuel tank safety
Polar operations – cold fuel management

Hydraulic Systems

Hydraulic circuit design
Hydraulic actuation
Hydraulic fluid
Fluid pressure
Fluid temperature
Fluid flow rate
Hydraulic piping
Hydraulic pumps
Fluid conditioning
Hydraulic reservoir
Warnings and status
Emergency power sources
Proof of design
Aircraft system applications
Civil transport comparison
Airbus A320
Boeing
Landing gear systems

Electrical Systems

Electrical power evolution
Aircraft electrical system
Power generation
Primary power distribution
Power conversion and energy storage
Secondary power distribution
Typical aircraft dc system
Typical civil transport electrical system
Electrical loads
Emergency power generation
Recent systems developments
Electrical Load Management System (ELMS)
Variable Speed Constant Frequency (VSCF)
VDC Systems
More-Electric Aircraft (MEA) 227
Recent electrical system developments
Electrical systems displays
MIL-STD-1553
MIL-STD-1760
MIL-STD-1773

Pneumatic Systems

Use of bleed air
Engine bleed air control
Bleed air system indications
Bleed air system users
Pitot static systems

Environmental Control Systems

The need for a controlled environment
The International Standard Atmosphere (ISA)
Environmental control system design
Cooling systems
Humidity control
The inefficiency of present systems
Air distribution systems
Cabin noise
Cabin pressurization
g tolerance
Rain dispersal
Anti-misting and de-misting
Aircraft icing

Emergency Systems

Warning systems
Fire detection and suppression
Emergency power sources
Explosion suppression
Emergency oxygen
Passenger evacuation
Crew escape
Computer-controlled seats
Ejection system timing
High speed escape
Crash recorder
Crash switch
Emergency landing
Emergency system testing
Rotary Wing Systems

Special requirements of helicopters
Principles of helicopter flight
Helicopter flight control
Primary flight control actuation
Key helicopter systems
Helicopter auto-flight control
Active control technology
Advanced battlefield helicopter
Tilt rotor systems

Advanced Systems

STOL Manoeuvre Technology Demonstrator (SMTD)
Vehicle Management Systems (VMS)
More-electric aircraft
More-electric engine
Stealth
Joint Strike Fighter (JSF)
Integrated Flight and Propulsion Control (IFPC)
Vehicle management system
More-electric aircraft
More-electric actuation
More-electric engine
Impact of stealth design
Technology developments/demonstrators

System Design and Development

SEMP and ConOps
Systems analysis and design
Development processes
System design
Key agencies and documentation
Design guidelines and certification
Techniques
Key elements of the development process
Major safety processes
Functional Hazard Analysis (FHA)
Preliminary System Safety Analysis (PSSA)
System Safety Analysis (SSA)
Common Cause Analysis (CCA)
Requirements capture
Top-down approach
Bottom-up approach
Fault Tree Analysis (FTA)
Dependency diagram
Failure Modes and Effects Analysis (FMEA)
DFMEA and PFMEA applied
FMECA and FTA
Component reliability
Analytical methods
In-service data
Dispatch reliability
Markov analysis
Reliability and safety engineering
Development processes
The product life cycle
Concept phase
Definition phase
Design phase
Build phase
Test phase (qualification phase)
Operate phase
Disposal or refurbish
Development program
‘V’ diagram
Extended Operations (ETOPS)

Avionics Technology

The nature of microelectronic devices
Processors
Memory devices
Digital data buses
A 429 data bus
MIL-STD-1553B
ARINC 629 data bus
COTS data buses
Data bus integration of aircraft systems
COTS data buses – IEEE 1394 468
Fiber optic buses
Avionics packaging standards
Typical LRU architecture
Integrated modular avionics

Military Avionics

Military communications
Radar
Sonar
Electro-Optics
ESM/DAS
Aircraft networks

Avionics Protocols in Military

Aircraft Data Network (ADN): Ethernet derivative for Commercial Aircraft
Avionics Full-Duplex Switched Ethernet (AFDX): Specific implementation of ARINC 664 (ADN) for Commercial Aircraft
ARINC 429: Generic Medium-Speed Data Sharing for Private and Commercial Aircraft
ARINC 664: See ADN above
ARINC 629: Commercial Aircraft (Boeing 777)
ARINC 708: Weather Radar for Commercial Aircraft
ARINC 717: Flight Data Recorder for Commercial Aircraft
IEEE 1394b: Military Aircraft
MIL-STD-1553: Military Aircraft
MIL-STD-1760: Military Aircraft
TTP – Time-Triggered Protocol: Boeing 787 Dreamliner, Airbus A380, Fly-By-Wire Actuation Platforms from Parker Aerospace
TTEthernet – Time-Triggered Ethernet: NASA Orion Spacecraft

Fundamentals of DO-178C

Introduction to DO-178B and Do-178C
DO-178B vs. DO-178C
DO-178/DO-254 certification process
DO-178/DO-254 project planning and management
DO-178/DO-254 master plan
DO-178/DO-254 need analysis and requirements
Software life cycle processes
Software life cycle definition
Transition criteria between processes
Software development plan
Software life cycle environment planning
Software development standards
Review of the software planning process software considerations in System life cycle processes
System considerations in software life cycle processes
Software plan development and certification
Software development, design, coding and testing techniques
DO-178C criticality levels
Software design, testing, verification and validation processes
Software planning process objectives
Software planning process activities
Software plans
Plan for Software Aspects of Certification (PSAC)
Software Quality Assurance Planning (SQAP)
Software Configuration Management Planning (SCMP)
Software Development Planning (SDP)
Requirements, design, code, and integration
Software Verification Planning (SVP)
Reviews, tests, and analysis
Programmable hardware plan development and certification
Software and programmable hardware verification and validation
Recommended templates and recommendations
Hardware design life cycle
Tool qualification
Cost estimation and metrics
Software aspects of certification
Compliance determination

Fundamentals of DO-254

DO-254 compliance
System safety and Design Assurance Level (DAL)
Application of DO-254 by EASA and FAA
DO-254 hardware design lifecycle objectives and data
Integral/supporting processes
Validation and verification
Configuration management
Process assurance
Tool qualification
COTs cores and IPs
Single event upset and SRAM parts
Functional Failure Path (FFP)
Elemental analysis
Advanced verification techniques
Plan for Hardware Aspects of Certification (PHAC)
Requirements capture
Conceptual design
Detailed design
Implementation and production transition

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Time Frame: 0-3 Months4-12 Months

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