Introduction to Avionic Systems Development_slides

INTRODUCTION TOAVIONIC SYSTEMS DEVELOPMENT

WORKSHOP

This Workshop provides a comprehensive overview to the process, methods, techniques and tools for the Avionic Systems design, development and integration. Main topics include:

A preliminary overview of the systems engineering concepts

A detailed analysis of the avionic system development process, including the designapproach and the activities to be performed during the entire system development cycle,from the feasibility studies to the operational clearance

A detailed description of the methods and tools that are currently used for the avionicsdevelopment and integration. Particular consideration is given to the modern modeling andsimulation methods, techniques and tools which can be used for the system development,including the system architectural design. The basic concurrent engineering concepts arealso addressed.

Quality and safety aspects.

The Workshop is designed for beginning systems engineers, but will also serve to introduce avionics fundamentals to practicing engineers of small and medium enterprises involved in the design, development and operation of avionic systems, subsystems and components.

WORKSHOP OVERVIEW

CONTENT1. INTRODUCTION TO SYSTEMS ENGINEERING

1.1. The Current Environment1.2. Definition of a System1.3. Definition of Systems Engineering1.4. The System Life Cycle

2. THE AVIONIC SYSTEM DEVELOPMENT CYCLE

2.1. Design Approach

Top Down Design ApproachBottom Up Design ApproachLife Cycle Design ApproachThe System Development ModelModel Based System Development

2.2. Development Phases

Development Cycle OverviewFeasibility StudyOperational RequirementsPreliminary System DesignDetailed System Design

CONTENT (cont d)

Equipment DevelopmentOperational Software DevelopmentDevelopment of Integration and Testing FacilitiesSystem Integration and TestingGround TestsFlight Tests

3. AVIONIC SYSTEM DEVELOPMENT METHODS AND TOOLS

3.1. Concurrent Engineering

GeneralThe System Development ProcessImproving the System Development ProcessDistributed Systems Engineering

3.2. Operational Software Development Facilities

Software Design, Coding and TestingSoftware Verification

3.3. System Integration and Testing Facilities

Integration RigsAntenna Testing

CONTENT (cont d)

Electromagnetic Compatibility TestingHIRF Testing

3.4. Modeling and Simulation Tools

Modeling and Simulation Tools for the System Architectural DesignReconfigurable SimulatorsMission SimulatorsSoftware Modeling and Automatic Code GenerationDistributed Interactive Simulation

3.5. Rapid Prototyping Tools for the HMI Design

4. QUALITY AND SAFETY ASPECTS

4.1. Quality Engineering

Total Quality ManagementQuality Systems, Standards and SpecificationsProduct and Process Quality Assurance

CONTENT (cont d)

4.2. System Configuration Management

GeneralConfiguration Change ControlSoftware Configuration

4.3. Development of Safety Critical Elements

Safety and Mission Critical FunctionsSafety EngineeringFault Tolerance Concept

1. INTRODUCTION TO SYSTEMS ENGINEERING

1.1. The Current Environment1.2. Definition of a System1.3. Definition of Systems Engineering1.4. The System Life Cycle

THECURRENT

ENVIRONMENT

SYSTEM ENGINEERING CONCEPTS, PRINCIPLES AND METHODS

CONSTANTLY CHANGINGREQUIREMENTS

CHANGINGTECHNOLOGY

LONGERACQUISITION TIMES

GREATERINTERNATIONAL COMPETITION

HIGHEROVERALL COSTS

EXTENDED SYSTEMLIFE CYCLES

MULTIPLEPRIME/SUPPLIER TEAMS

INCREASINGSYSTEM COMPLEXITY

1.1. The Current Environment

A SYSTEM CONSTITUTES A SET OF INTEGRATED COMPONENTS WORKING TOGETHER WITH THE COMMON OBJECTIVE OF FULFILLING SOME DESIGNATED USER NEED

CONSTRAINTS

- Technology- Economic- Social- Political- Environmental

RESOURCEREQUIREMENTS

- Human- Equipment- Software- Facilities- Data- Maintenance

Support

SYSTEM

INPUT

UserRequirements

(Need)

OUTPUT

A System thatwill respond to a User need in an

effective and efficient manner

1.2. Definition of a System

THE MAJOR ELEMENTS OF A SYSTEM

OperatingPersonnel

PrimeOperatingEquipment

OperatingSoftware

Data

Test andSupport

Equipment

MaintenanceElements

THE SYSTEM


EXAMPLE MODERN COMBAT AICRAFT


EXAMPLE ATTACK HELICOPTER


THE SYSTEM ENGINEERING IS THE EFFECTIVE APPLICATION OF SCIENTIFIC AND ENGINEERING EFFORTS TO TRANSFORM AN OPERATIONAL NEED INTO A DEFINED SYSTEM CONFIGURATION THROUGH THE TOP DOWN ITERATIVE PROCESS OF REQUIREMENT ANALYSIS, FUNCTIONAL ANALYSIS AND ALLOCATION, SYNTHESIS, DESIGN OPTIMIZATION, TEST AND EVALUATION AND VALIDATION

The Department of Defense (DOD) defines Systems Engineering as the Process that:

- transforms operational needs and requirements into an integrated system design solution throughconcurrent consideration of all Life Cycle needs

- ensures that system definition and design reflect the requirements for all system elements

- ensures the compatibility, interoperability and integration of all functional and physical interfaces

- characterizes and manages technical risk

1.3. Definition of Systems Engineering

SYSTEMS ENGINEERING AREAS OF EMPHASIS

A Top Down approach is required, viewing the system as a whole.An overview and an understanding of how the system components fittogether are essential.

A Life Cycle orientation is required, addressing all phases to include system design and development, production, operation, maintenace, support and retirement.

A complete effort is required relative to the initial identification of system requirements, in order to ensure the effectiveness of early decision making in the design process.

Interdisciplinary effort and team approach are required throughoutthe system design and development process.

1.3. Definition of Systems Engineering

EXAMPLE OF SYSTEM LIFE CYCLE

1.4. The System Life Cycle

SYSTEM ENGINEERING WITHIN THE SYSTEM LIFE CYCLE

THE SYSTEM ENGINEERING PROCESS IS CONTINUOUS, ITERATIVE AND INCORPORATES THE NECESSARY FEEDBACK PROVISIONS AT EACH STEP OF THE SYSTEM LIFE CYCLE

1.4. The System Life Cycle

2. THE AVIONIC SYSTEM DEVELOPMENT CYCLE


2.1.1. Top Down Design Approach2.1.2. Bottom Up Design Approach2.1.3. Life Cycle Design Approach2.1.4. The System Development Model2.1.5. Model Based System Development


2.2.1. Development Cycle Overview2.2.2. Feasibility Study2.2.3. Operational Requirements2.2.4. Preliminary System Design2.2.5. Detailed System Design

2.2.6. Equipment Development2.2.7. Operational Software Development2.2.8. Development of Integration and Testing Facilities2.2.9. System Integration and Testing2.2.10. Ground Tests2.2.11. Flight Tests

TOP DOWN DESIGN APPROACH

OPERATIONALREQUIREMENTS

SYSTEMDESIGN

COMPONENTSDEVELOPMENT

INTEGRATION

- DRIVEN BY OPERATIONAL REQUIREMENTS

- PERFORMANCE ORIENTED

- IMPLIES SIGNIFICANT DEVELOPMENT WORK AT BOTH SYSTEMAND COMPONENTS LEVELS

- PLATFORM SPECIFIC

- USED FOR SYSTEMS DEVELOPMENT AT THE UPPERTECHNOLOGY EDGE

- TYPICAL OF NEW MILITARY PROGRAMS WITH VERYDEMANDING REQUIREMENTS


BOTTOM UP DESIGN APPROACH

EXISTINGCOMPONENTS

ADAPTATION

INTEGRATION

PERFORMANCEASSESSMENT

- BASED ON REUSE OF EXISTING COMPONENTS, ACCORDING TOTHE OFF THE SHELF CONCEPT

- COST ORIENTED

- REDUCES DEVELOPMENT EFFORT, TECHNICAL RISKAND PROGRAM TIMESCHEDULE

- CAN BE EASILY ADAPTED TO DIFFERENT PLATFORMS

- CONFLICTS WITH THE NEED FOR TECHNOLOGYGROWTH

- TYPICAL OF MILITARY UPGRADE PROGRAMSWITH LIMITED BUDGETS AND SHORTTIMESCHEDULES


FUNCTIONAL DECOMPOSITION

Hierarchy Level 0(Context-Diagram)

External Data Sink

External Data Source

Bottom-Up

Top-Down

Hierarchy Level 1

Hierarchy Level 2



GENERATORSHIGH LEVEL CONTROLS

STATUS

MISSION AVIONICS

SENSOR(S) SENSORSCONTROL

SENSORSINTERFACE

HORIZONTALENGINE

CONTROLHORIZONTAL

ENGINE

NGIRI

DIRECTION

STATUS

VERTICALENGINE

CONTROLVERTICALENGINE

NGIRI

STATUSPROVISION

BASICAVIONICS

VROT

VOICE

MISSION DATA

VOICE

TO AIRTRAFFIC CONTROL

ELECTRICAL POWER GENERATIONAND DISTRIBUTION SYSTEM

EPGDS CONTROL

HIGH LEVEL CONTROLS

STATUS

PNEUMATIC SYSTEM

ACTUATORS PS CONTROL

HIGH LEVEL CONTROLS

STATUS

UNDERCARRIAGE SYSTEM

ACTUATORS US CONTROL

VIDEO

DATA

GROUNDSTATION

NAUTILUS ETF AVIONICS FUNCTIONAL ARCHITECTURE LEVEL ZERO


NAUTILUS ETF AVIONICS FUNCTIONAL ARCHITECTURE LEVEL ONE

BASIC AVIONICS

HORIZONTALENGINES

VERTICALENGINES

NGIRI

DIRECTION

STATUS

NGIRI

STATUS

VROT

GROUNDSTATION

VOICE

DATA

AIR TRAFFICCONTROL

HIGH LEVELCONTROLS

STATUS

EPGDS

PROVISION

MISSIONAVIONICS

HIGH LEVELCONTROLS

STATUS

HIGH LEVELCONTROLS

STATUS

PS

USVOICE

VIDEO

COMMUNICATIONSSUBSYSTEM

UTILITIESCONTROL

SUBSYSTEM

FLIGHTCONTROLS

SUBSYSTEM

NAVIGATIONSUBSYSTEM

FLIGHT MANAGEMENTSUBSYSTEM

AUTOPILOT

MONITORING ANDRECORDINGSUBSYSTEM

VISIONSUBSYSTEM

VIDEO

DATA

MISSION DATA

TO COMMUNICATIONSSUBSYSTEM

FROM NAVIGATIONSUBSYSTEM

FROM ALL SUBSYSTEMS

LIFE CYCLE DESIGN APPROACH

THE SYSTEM ENGINEERING PROCESS MUST ENSURE THAT THE USER REQUIREMENTS ARE MET IN AN EFFECTIVE AND EFFICIENT MANNER ACROSS THE ENTIRE SYSTEM LIFE CYCLE, INCLUDING DEVELOPMENT, PRODUCTION AND OPERATIONAL USE.

SYSTEM DESIGN REQUIREMENTS

- FUNCTIONS

- PERFORMANCE

- MAN/MACHINE INTERFACE

- COST/EFFECTIVENESS

- ENVIRONMENTAL REQUIREMENTS

- RELIABILITY

- MAINTAINABILITY

- TESTABILITY

- SAFETY

- SURVIVABILITY

- VULNERABILITY

- RECONFIGURABILITY

- HUMAN FACTORS

- PRODUCUBILITY

- SERVICEABILITY

- LIFE CYCLE COST


THE V SYSTEM DEVELOPMENT MODEL

HW / SW Design

SystemAcceptance

System Integration & Test

Module Integration & Test

Requirements Analysis

System Modification

SystemsAnalysis &

Design

Test Scenarios

Test Scenarios

Test Scenarios

HW / SWImplementation

& Unit Test


DEVELOPMENT CYCLE OVERVIEW

OperationalRequirements

SystemPreliminary

DesignReview

SystemFinal

DesignReview

SystemTest

ReadinessReview

Installationon Aircraft

FlightRelease

OperationalClearance

PreliminaryDesign

DetailedDesign

Equipment Development

Software Development

Development of Integrationand Testing Facilities

GroundTests

Flight Tests

System Integration and Testing


FEASIBILITY STUDYINPUT

- OPERATIONAL REQUIREMENTS

ACTIVITIES

- IDENTIFICATION OF RISK AREAS

OBJECTIVE

- RISK REDUCTION

- IDENTIFICATION OF THE VARIOUS POSSIBLETECHNOLOGICAL AND DESIGN APPROACHES

- EVALUATION OF THE CANDIDATES IN TERMS OF PERFORMANCE,EFFECTIVENESS, LOGISTIC REQUIREMENTS AND LIFE CYCLE ECONOMIC CRITERIA

- INITIATION OF RESEARCH ACTIVITIES, IF REQUIRED, WITH THE OBJECTIVE OFDEVELOPING NEW METHODS/TECHNIQUES FOR SPECIFIC APPLICATIONS

- SELECTION OF AN OVERALL TECHNICAL APPROACH ANDRECOMMENDATION TO THE CUSTOMER

OUTPUT

- FINALIZED OPERATIONALREQUIREMENTS

- AGREED OVERALL TECHNICALAPPROACH


OPERATIONAL REQUIREMENTS

THE OPERATIONAL REQUIREMENTS REFLECT THE NEEDS OF THE USER RELATIVE TO SYSTEM UTILIZATION AND THE ACCOMPLISHMENT OF A MISSION.

TYPICAL OPERATIONAL REQUIREMENTS FOR MILITARY AIRCRAFT

- OPERATIONAL DEPLOYMENT: NUMBER OF SITES, GEOGRAPHICAL DISTRIBUTION, QUANTITY

- MISSION TYPES: AIR SUPPORT, INTERDICTION, INTERCEPTION, AIR DEFENSE, ETC.

- MISSION PROFILE: FLIGHT PATH, RANGE, ALTITUDE

- MISSION SCENARIO: TERRAIN, TARGETS, THREATS, ETC.

- OPERATIONAL FUNCTIONS: NAVIGATION, WEAPON AIMING, MAN/MACHINE INTERFACE, STORE MANAGEMENT, ETC.

- UTILIZATION REQUIREMENTS: OPERATING HOURS, DUTY CYCLE, OPERATIONAL LIFE, ETC.

- EFFECTIVENESS REQUIREMENTS: RELIABILITY, MAINTAINABILITY, TESTABILITY, VULNERABILITY, ETC.

- ENVIRONMENT: TEMPERATURE, VIBRATION, ELECTROMAGNETIC COMPATIBILITY, ETC.

- PERFORMANCE: NAVIGATION ACCURACY, WEAPON DELIVERY ACCURACY, REACTION TIME, WEIGHT, ETC.


PRELIMINARY SYSTEM DESIGN

OPERATIONALREQUIREMENTS

REQUIREMENTSANALYSIS

SYSTEMFUNCTIONAL

DESIGN

SUBSYSTEMFUNCTIONAL

DESIGN

SUBSYSTEMDESIGN

SYSTEMREQUIREMENTS

DOCUMENTS

SUBSYSTEMREQUIREMENTS

DOCUMENTS

HARDWARE/SOFTWARECOMPONENTS

DEFINITION

ITERATIONS

ITERATIONS

ITERATIONS

OBJECTIVES OF THE PRELIMINARY SYSTEM DESIGN PHASE

- CONVERSION OF THE OPERATIONAL REQUIREMENTSINTO AN INTEGRATED SYSTEM DESIGN SOLUTION

- DEFINITION OF THE SYSTEM FUNCTIONAL ARCHITECTURE,HARDWARE/SOFTWARE PARTITIONING AND SYSTEMPHYSICAL ARCHITECTURE


AVIONIC SYSTEM SPECIFICATION

SCOPE

APPLICABLE DOCUMENTS

OPERATIONAL REQUIREMENTS

Mission Types

Mission Profiles

Mission Scenario

Utilization Requirements

General

System Functional Architecture

FUNCTIONAL AND PERFORMANCEREQUIREMENTS

GeneralSystem Moding

Subsystems Definition

Flight Management SubsystemAutopilotCommunications SubsystemVision SubsystemUtilities Control SubsystemMonitoring and Recording Subsystem


Functional Interface

External InterfaceInternal Interface

Navigation SubsystemFlight Controls Subsystem

System Performance RequirementsNavigation AccuracyCommunications Subsystem PerformanceVision Subsystem PerformanceSystem Readiness for Operations

PHYSICAL REQUIREMENTS

Hardware ConfigurationHardware Preliminary ArchitectureEquipment FunctionsSystem Intercommunication


Physical Characteristics

System WeightSystem VolumeInstallation Requirements

Electrical Power Supply Requirements

Electrical Power Supply CharacteristicsPower Consumption

Cooling Requirements

Cooling Air CharacteristicsAir Mass Flow

SAFETY AND MISSION CRITICALITYDESIGN REQUIREMENTS

Basic Definitions

Safety/Flight Critical FunctionsMission Critical Functions

Basic Design Requirements

Safety/Flight Critical Failure Rate

Software Development Environment

Software Development ToolsHost SystemSoftware Integration and Verification Facilities

Software Design/Architecture

Software Design MethodologiesSoftware ArchitectureSoftware Development PhasingVerification of Software

DESIGN AND CONSTRUCTION Environmental Conditions

Temperature/Altitude

OPERATIONAL SOFTWARE DESIGNREQUIREMENTS

Mission Critical Failure RateFailure Tolerance RequirementsRedundancy and Reconfiguration Concept

AVIONIC SYSTEM SPECIFICATION (cont d)

UmidityVibrationsShockSalt FogOthers


AVIONIC SYSTEM SPECIFICATION (cont d)

Electromagnetic Compatibility

Radiated and Conducted EmissionsSusceptibility to Radiated and ConductedEmissions

Lightning Protection

LOGISTIC SUPPORT REQUIREMENTS

Reliability

SYSTEM TESTING, QUALIFICATION ANDCERTIFICATION REQUIREMENTS

System Testing and Qualification

Avionics System Test ConceptEquipment Testing and QualificationSoftware VerificationSystem Integration and TestingOn Aircraft Ground TestingFlight Testing

System Certification

Maintainability

Testability

PRELIMINARY SYSTEM DESIGN

EXAMPLE INTEGRATED NAVIGATION SUBSYSTEM

ALTITUDEDATA

GENERATION

INERTIALDATA

GENERATION

GPSDATA

GENERATION

TERRAINREFERENCENAVIGATION

KALMANFILTER

NAVIGATION COMPUTING

TERRAIN DATA

AIRCRAFT POSITION

FUNCTIONAL ARCHITECTURE

RADARALTIMETER TRN

NAVIGATIONCOMPUTER

PHYSICAL ARCHITECTURE ALTERNATIVE 1

AVIONIC BUS

RADARALTIMETER INS GPS TRN

AVIONIC BUS

PHYSICAL ARCHITECTURE ALTERNATIVE 2

INS/GPS(INCLUDING

KALMAN FILTER)

NAVIGATION COMPUTER(INCLUDING

KALMAN FILTER)


DETAILED SYSTEM DESIGN

OBJECTIVES- PRODUCE DETAILED DEVELOPMENTSPECIFICATIONS AND ASSOCIATED DOCUMENTSIN ORDER TO START PARALLEL DEVELOPMENT OF THESYSTEM COMPONENTS AND OF THE INTEGRATION ANDTESTING FACILITIES

- SELECT EQUIPMENT SUPPLIERS

INPUT- RESULTS OF THE PRELIMINARYSYSTEM DESIGN

ACTIVITIES

- SELECTION OF EQUIPMENT SUPPLIERS

- DETAILED DEFINITION OF EQUIPMENT CHARACTERISTICS, INCLUDING FUNCTIONS, PERFORMANCE,FUNCTIONAL, ELECTRICAL AND MECHANICAL INTERFACES, CONTROLS AND DISPLAYS, PHYSICALREQUIREMENTS, ENVIRONMENTAL REQUIREMENTS, PRODUCT REQUIREMENTS, ETC.

- PREPARATION OF EQUIPMENT DEVELOPMENT SPECIFICATIONS AND ASSOCIATED DOCUMENTS

- DETAILED DEFINITION OF THE SOFTWARE REQUIREMENTS FOR THE OPERATIONAL FLIGHT SOFTWARE OF THEMISSION COMPUTER/COMPUTERS. PREPARATION OF THE SOFTWARE REQUIREMENTS SPECIFICATIONS AND OFTHE ASSOCIATED DOCUMENTS

- DETAILED DEFINITION OF THE DESIGN REQUIREMENTS FOR THE SYSTEM INTEGRATION ANDTESTING FACILITIES. PREPARATION OF THE RELEVANT SPECIFICATIONS AND ASSOCIATEDDOCUMENTS

OUTPUT- EQUIPMENT DEVELOPMENT SPECIFICATIONS ANDASSOCIATED DOCUMENTS

- SOFTWARE FUNCTIONAL REQUIREMENTS ANDASSOCIATED DOCUMENTS

- SYSTEM INTEGRATION AND TESTING FACILITIESSPECIFICATIONS AND ASSOCIATED DOCUMENTS


EQUIPMENT DEVELOPMENT

DEVELOPMENT AND PRODUCTION OF AVIONIC EQUIPMENT ARE USUALLY SUBCONTRACTED TO SELECTED SUPPLIERS

DESIGN REALIZATION OFA MODELSREALIZATION OF

B MODELSREALIZATION OF

C MODELSPRELIMINARY

QUALIFICATION

EQUIPMENTDEVELOPMENTSPECIFICATION

DESIGNDOCUMENTATION

ENGINEERING MODELSRETAINED BY THE SUPPLIER

FOR DEVELOPMENT ACTIVITIES

REPRESENTATIVE MODELSDELIVERED FOR SYSTEM

INTEGRATION AND TESTING

FLYABLE MODELSFOR INSTALLATIONON THE AIRCRAFT

PRELIMINARY DECLARATIONOF DESIGN AND PERFORMANCE

FOR FIRST FLIGHT

FINALQUALIFICATION

FINAL DECLARATIONOF DESIGN ANDPERFORMANCE

SUPPLIERS ACTIVITIES

ALL B AND C EQUIPMENT MODELS ARE SUBJECT TO ACCEPTANCE TESTING BEFORE DELIVERY


EQUIPMENT DEVELOPMENT

THE DEVELOPMENT ACTIVITIES PERFORMED BY THE EQUIPMENT SUPPLIERS ARE TECHNICALLY MONITORED BY EQUIPMENT ENGINEERS

EQUIPMENT ENGINEERS MAIN ACTIVITIES

- PREPARATION AND UPDATING OF THE EQUIPMENT SPECIFICATIONS

- TECHNICAL MONITORING OF THE EQUIPMENT DEVELOPMENT IN ORDER TO ENSURE COMPLIANCE WITH THE SPECIFIEDREQUIREMENTS

- IDENTIFICATION AND EVALUATION OF IMPACTS ON THE AVIONIC SYSTEM RESULTING FROM POSSIBLE DEVIATIONSFROM THE EQUIPMENT SPECIFICATIONS

- APPROVAL OF ALL DEVIATIONS FROM THE SPECIFICATIONS AND/OR MODIFICATIONS TO THE EQUIPMENT

- ANALYSIS AND APPROVAL OF ALL TECHNICAL DOCUMENTS PRODUCED BY THE SUPPLIERS

- TECHNICAL LIASON WITH THE SUPPLIERS

- SUPPORT TO SYSTEMS AND SOFTWARE ENGINEERS


OPERATIONAL FLIGHT SOFTWARE DEVELOPMENT

EXAMPLE OPERATIONAL FLIGHT SOFTWARE ARCHITECTURE

BASIC SOFTWARE

EQUIPMENTMANAGEMENT

NAVIGATIONSENSORS

DISPLAYS ANDCONTROLS

WEAPONS

OTHERS

DATA BASE

MISSION DATA

WEAPONS DATA

EQUIPMENTDATA

HUD HANDLER

HUD MODING

HUD FORMATS

MFD HANDLER

MFD MODING

MFD FORMATS

DATA HANDLER

NAVIGATIONCOMPUTATIONS

WEAPONAIMING

COMPUTATIONS

STORESMANAGER

MODECONTROLLER SCHEDULER

THE OPERATIONAL FLIGHT SOFTWARE IS THE APPLICATION SOFTWARE RESIDENT IN THE AIRCRAFT MISSION COMPUTERS PERFORMING THE AVIONIC FUNCTIONS REQUIRED IN ORDER TO FULFILL THE MISSION REQUIREMENTS


OPERATIONAL FLIGHT SOFTWARE DEVELOPMENT

SOFTWAREFUNCTIONAL

REQUIREMENTS

SOFTWAREREQUIREMENTS

ANALYSISSOFTWARE

PRELIMINARYDESIGN

SOFTWAREDETAILED

DESIGN CODING ANDUNIT TESTING UNIT

INTEGRATIONAND TESTING

CSCIQUALIFICATION

TESTINGSOFTWAREREQUIREMENTS

ANALYSISSOFTWARE

PRELIMINARYDESIGN

SOFTWAREDETAILED

DESIGN CODING ANDUNIT TESTING UNIT

INTEGRATIONAND TESTING

CSCIQUALIFICATION

TESTING

CSCI/HWCIINTEGRATIONAND TESTING

SYSTEMFINAL

DESIGNREVIEW

SOFTWARESPECIFICATION

REVIEW

PRELIMINARYDESIGNREVIEW

CRITICALDESIGNREVIEW

SOFTWARETEST

READINESSREVIEW

SYSTEMTEST

READINESSREVIEW

SOFTWAREREQUIREMENTSSPECIFICATION

INTERFACEREQUIREMENTSSPECIFICATION

SOFTWAREARCHITECTURE

SOFTWAREDESIGN

DESCRIPTION

INTERFACEDESIGN

DESCRIPTION

DATA BASEDESIGN

DESCRIPTION

SYSTEMQUALIFICATION

TESTING

SOFTWARETEST

DESCRIPTION

SOFTWARETEST

REPORT

SOFTWARETEST

DESCRIPTION

SOFTWARETEST

REPORT

CSCI = COMPUTER SOFTWARE CONFIGURATION ITEM

HWCI = HARDWARE CONFIGURATION ITEM


DEVELOPMENT OF INTEGRATION AND TESTING FACILITIES

THE INTEGRATION AND TESTING ACTIVITIES AT SYSTEM/SUBSYSTEM LEVELS REQUIRE COMPLEX FACILITIES, CAPABLE OF SUPPORTING THE SYSTEM INTEGRATION AND TESTING ACCORDING TO THE HARDWARE IN THE LOOP METHODOLOGY WITH PILOT INTERACTION IN A REPRESENTATIVE ENVIRONMENT

THE TECHNICAL CHARACTERISTICS OF THE INTEGRATION AND TESTING FACILITIES ARE STRONGLYRELATED TO:

A) THE SPECIFIC AIRCRAFT CHARACTERISTICSB) THE SPECIFIC AVIONIC SYSTEM ARCHITECTURE AND CONFIGURATIONC) THE SPECIFIC EQUIPMENT HARDWARE

THE REALIZATION OF THE INTEGRATION AND TESTING FACILITIES REQUIRES SPECIFIC DESIGN AND DEVELOPMENT


SYSTEM INTEGRATION AND TESTING

THE SCOPE OF THE INTEGRATION AND TESTING ACTIVITIES IS TO VERIFY THAT THE FUNCTIONS AND PERFORMANCE OF THE INTEGRATED AVIONIC SYSTEM COMPLY WITH THE REQUIREMENTS OF THE AVIONIC SYSTEM SPECIFICATION

STATIC TESTS

- ELECTRICAL INTEGRATION

- STATIC STIMULATION OF EQUIPMENT, IN ORDER TO VERIFY CORRECT STATIC OPERATION

- MODIFICATION OF SELECTED PARAMETERS

- INJECTION OF ERROR CONDITIONS

- VERIFICATION OF DIGITAL, DISCRETE AND ANALOG EQUIPMENT INTERFACES


SYSTEM INTEGRATION AND TESTING

DYNAMIC TESTS

THE DYNAMIC TESTS ALLOW THE VERIFICATION OF THE GLOBAL SYSTEM FUNCTIONS AND PERFORMANCES, OPERATING IN DYNAMIC CONDITIONS IN A REPRESENTATIVE ENVIRONMENT

OPEN LOOP DYNAMIC SIMULATIONTHE INTEGRATED SYSTEM IS STIMULATED BY COMPUTER GENERATED SIGNALS, ACCORDING TO PREDEFINED MATHEMATICAL MODELS

CLOSED LOOP DYNAMIC SIMULATION

THE INTEGRATED SYSTEM IS STIMULATED BY AN AIRCRAFT SIX DEGREES OF FREEDOM MATHEMATICAL MODEL,CONTROLLED BY PILOT COMMANDS.

THE CLOSED LOOP SIMULATION RUNS ACCORDING TO THE FOLLOWING OPERATIONAL MODES:

A) CLOSED LOOP SIMULATION WITH PILOT IN THE LOOP

THE LOOP IS CLOSED BY THE ACION OF THE PILOT/OPERATOR WITHIN THE MANEUVERS LIMITATIONSIMPOSED BY THE AIRCRAFT OPERATIONAL FLIGHT ENVELOPE

B) CLOSED LOOP SIMULATION WITH SIMULATED PILOT (DETERMINISTIC TESTS)

A MATHEMATICAL MODEL GENERATES A PREDEFINED FLIGHT PATH. THIS MODE ALLOWS TESTS REPEATABILITY.


GROUND TESTS

THE SCOPE OF THE GROUND TESTING ACTIVITIES IS TO VERIFY THE CORRECT INTEGRATION OF THEAVIONIC SYSTEM ON THE AIRCRAFT IN TERMS OF:

A) MECHANICAL, ELECTRICAL AND FUNCTIONAL INTERFACESB) COMPATIBILITY WITH OTHERS AIRCRAFT SYSTEMS.

POST INSTALLATION TESTING

- VERIFICATION OF THE AVIONIC SYSTEM FUNCTIONALITY WHEN INSTALLED ON THE AIRCRAFT

- VERIFICATION OF AVIONIC SYSTEM INTERFACES WITH OTHERS AIRCRAFT SYSTEMS

- USUALLY PERFORMED BY USING SPECIFIC TEST SOFTWARE PACKAGES

- PERFORMED ON ALL AIRCRAFTS


GROUND TESTS

ANTENNA TESTING

- VERIFICATION OF CORRECT OPERATION OF TRANSMITTING AND RECEIVING ANTENNAS ASSOCIATED TO AVIONIC EQUIPMENT

- ANTENNAS RADIATION PATTERNS ARE MEASURED WITH EXTENSIVE LABORATORY TESTING ON SCALED MODELS INANECHOIC CHAMBERS. ADDITIONAL TESTS ON PROTOTYPES AIRCRAFTS.

HAZARD FROM ELECTROMAGNETIC RADIATION TO ORDNANCE (HERO) TESTING

- VERIFICATION OF IMPACTS ON AIRCRAFT SYSTEMS RESULTING FROM EXTERNAL ELECTROMAGNETIC EMISSIONS

ELECTROMAGNETIC COMPATIBILITY TESTING

- VERIFICATION OF MUTUAL COMPATIBILITY OF AVIONIC EQUIPMENT AMONG THEMSELVES FOR ELECTROMAGNETICRADIATED AND CONDUCTED EMISSIONS

- VERIFICATION OF COMPATIBILITY OF AVIONIC EQUIPMENT WITH OTHERS AIRCRAFT SYSTEMS FOR ELECTROMAGNETICRADIATED AND CONDUCTED EMISSIONS

- BASICALLY PERFORMED ON PROTOTYPES AIRCRAFTS


FLIGHT TESTS

THE SCOPES OF THE FLIGHT TESTING ACTIVITIES ARE:

A) PERFORM THE FINAL INTEGRATION OF THE AVIONIC SYSTEM ON THE AIRCRAFT IN THE ACTUAL OPERATING CONDITIONS

B) DEMONSTRATE THAT THE AVIONIC SYSTEM COMPLIES WITH THE OPERATIONAL REQUIREMENTS

THE FINAL INTEGRATION OF THE AVIONIC SYSTEM ON THE AIRCRAFT REQUIRES EXTENSIVE FLIGHT CHAMPAINS ON PROTOTYPESAIRCRAFTS, IN ORDER TO COVER THE FOLLOWING MAIN ASPECTS:

A) ENVIRONMENT: VIBRATION, TEMPERATURE, ALTITUDE, HUMIDITY, ETC.B) COOLING: AIR FLOW, AIR TEMPERATURE AND PRESSURE, ETC.C) POWER SUPPLY: AIRCRAFT POWER SUPPLY CHARACTERISTICS, NORMAL AND ABNORMAL CONDITIONS, TRANSIENTS, ETC.D) ELECTROMAGNETIC COMPATIBILITY: RADIATED AND CONDUCTED EMISSIONS, COMPATIBILITY BETWEEN TRANSMITTING

AND RECEIVING EQUIPMENT, ETC.E) FUNCTIONALITY: FINAL VERIFICATION OF THE AVIONIC SYSTEM FUNCTIONALITY.

ACTUAL AIRCRAFT OPERATING CONDITIONS


FLIGHT TESTS

OPERATIONAL FUNCTIONS AND PERFORMANCE

DEMONSTRATION OF THE COMPLIANCE TO THE OPERATIONAL REQUIREMENTS FOR:

A) OPERATIONAL FUNCTIONS: NAVIGATION, WEAPON AIMING, COMMUNICATIONS, STORES MANAGEMENT, SELF PROTECTION, ETC.

B) OPERATIONAL PERFORMANCE: NAVIGATION ACCURACY, TARGET DETECTION RANGE AND ACCURACY, WEAPON AIMING ACCURACY, WEAPON DELIVERY ACCURACY, COMMUNICATIONS RANGE AND COVERAGE, THREAT DETECTION RANGE AND COVERAGE, ETC.

MAN/MACHINE INTERFACE

DEMONSTRATION OF THE COMPLIANCE TO THE OPERATIONAL REQUIREMENTS FOR:

A) OPERATIONAL PROCEDURES: SYSTEM MODING, SUBSYSTEM MODING, EQUIPMENT OPERATION AND CONTROL, ETC.

B) DISPLAYS FORMATS AND SYMBOLOGY: HEAD UP DISPLAY, HEAD DOWN MULTIFUNCTION DISPLAYS, CONTROL AND DISPLAY UNITS, DEDICATED PANELS, ETC.

C) ALL ERGONOMIC ASPECTS


FLIGHT TESTS

FLIGHT TEST INSTRUMENTATION

FLIGHT TEST INSTRUMENTATION (FTI) IS INSTALLED ON BOARD OF PROTOTYPES AIRCRAFTS FOR DATA COLLECTION, COMPRESSION AND RECORDING FOR POST FLIGHT ANALYSIS AND EVALUATION.

RECORDED DATA INCLUDE:

A) FLIGHT AND NAVIGATION DATA: AIRCRAFT ATTITUDE, ALTITUDE, SPEED, POSITION, ETC.B) ENVIRONMENTAL DATA: VIBRATION, TEMPERATURE, ETC.C) EQUIPMENT INPUT/OUTPUT DATA: DIGITAL, DISCRETES, ANALOGS, ETC..

FLIGHT BACK UP ACTIVITIES

THE FLIGHT TESTS ARE SUPPORTED BY PARALLEL FLIGHT BACK UP ACTIVITIES PERFORMED ON THE INTEGRATION ANDTESTING FACILITIES.

THIS ALLOWS TO:

A) REPRODUCE RECORDED SITUATIONS, IN ORDER TO ANALYZE AND EVALUATE THE MALFUNCTIONS DETECTED DURING THE FLIGHTS

B) IDENTIFICATION AND TEST OF CORRECTIVE ACTIONS FOR THE MALFUNCTIONS DETECTED DURING THE FLIGHTS.


3. AVIONIC SYSTEM DEVELOPMENT METHODS AND TOOLS


3.1.1. Definition3.1.2. System Design and Analysis3.1.3. Interactive Simulation3.1.4. System Verification


3.2.1. Software Design, Coding and Testing3.2.2. Software Verification


3.3.1. Integration Rigs3.3.2. Antenna Testing3.3.3. Electromagnetic Compatibility Testing3.3.4. HERO Testing


3.4.1. Modeling and Simulation Tools for the System Architectural Design3.4.2. Reconfigurable Simulators3.4.3. Mission Simulators3.4.4. Software Modeling and Automatic Code Generation3.4.5. Distributed Interactive Simulation


GENERAL

COMPUTERIZED DESIGN AIDS

- SIMULATION METHODS

- MATHEMATICAL PROGRAMMING METHODS

- STATISTICAL TOOLS

- DATA BASE MANAGEMENT MODELS

- SPECIALIZED ENGINEERING TOOLS

- PROJECT MANAGEMENT AIDS



TimeRequirements-Analysis

SystemsAnalysis &

Design

HW/SWDesign

HW/SWImplementation

ModuleIntegration & Test

SystemIntegration & Test

System Acceptance

System Engineers

Test Engineers

Mechanical Engineers

Software Engineers

Electrical Engineers

THE SYSTEM DEVELOPMENT PROCESS


Time

System Engineers

Test Engineers


Software Engineers


Requirements-Analysis

SystemsDesign & Analysis

HW/SWDesign

HW/SWImplementation

ModuleIntegration & Test

SystemIntegration & Test

System Acceptance

System Engineers

Test Engineers


Software Engineers


Time

IMPROVING THE SYSTEM DEVELOPMENT PROCESS

DISTRIBUTED SYSTEMS ENGINEERING

DISTRIBUTEDSYSTEMS

ENGINEERING

SYSTEMDESIGN

PROJECTREVIEWS

ENGINEERINGANALYSIS

TESTPREPARATION

AND EXECUTION

SIMULATIONS

DISTRIBUTED SYSTEM DESIGN AND ANALYSISDISTRIBUTION AND COLLABORATIVE EVALUATION OF ANALYSIS AND SIMULATION RESULTS

DISTRIBUTED DESIGN REVIEWS

CONSOLIDATION OF THE SYSTEM DESIGN IN A DISTRIBUTED REVIEW TEAM

DISTRIBUTED SYSTEM VERIFICATIONSUPPORT TO PREPARATION, EXECUTION AND EVALUATION OF SYSTEM TESTS


OPERATIONAL FLIGHT SOFTWARE DEVELOPMENT FACILITY

- INCLUDES A SET OF SOFTWARE TOOLS COVERING ALL PHASES OF THE DEVELOPMENT PROCESS

- INCLUDES A HOST SYSTEM WITH A SUFFICIENT NUMBER OF WORK PLACES TO SUPPORT THE DEVELOPMENT EFFORT

- SUPPORTS THE ENTIRE SOFTWARE LIFE CYCLE IN ACCORDANCE WITH THE APPLICABLE MILITARY STANDARDS(MIL STD 498 MILITARY STANDARD SOFTWARE DEVELOPMENT AND DOCUMENTATION)

GRAPHIC SOFTWARE DEVELOPMENT FACILITY

- DEFINES, DEVELOPS AND MAINTAINS THE FORMATS AND SYMBOLOGY OF THE HEAD UP DISPLAY AND OF THE HEAD DOWNMULTIFUNCTION DISPLAYS

- ALLOWS RAPID PROROTYPING OF DISPLAYS FORMATS AND SYMBOLOGY ON HOST COMPUTER

- ALLOWS AUTOMATIC CODE GENERATION FOR TARGET COMPUTER

SOFTWARE VERIFICATION STATION

- SUPPORTS THE HARDWARE/SOFTWARE INTEGRATION OF THE OPERATIONAL FLIGHT SOFTWARE IN A REPRESENTATIVEENVIRONMENT

- ALLOWS THE VERIFICATION OF THE OPERATIONAL FLIGHT SOFTWARE FUNCTIONALITY IN A SIMULATED DYNAMICENVIRONMENT, INCLUDING AIRCRAFT AND AVIONIC EQUIPMENT SIMULATORS


- ALLOWS TO TEST AND EVALUATE THE INTEGRATED AVIONIC SYSTEM FUNCTIONS, PERFORMANCE ANDINTEGRATION ASPECTS

- SUPPORTS THE VALIDATION OF THE OPERATIONAL FLIGHT SOFTWARE BEFORE FLIGHT

- SUPPORTS THE FINAL TESTING OF THE INTEGRATED SYSTEM BEFORE FLIGHT AND THE PREPARATIONOF THE FLIGHT RELEASE DOCUMENTS

- SUPPORTS THE AVIONIC SYSTEM INTEGRATION AND TESTING ACTIVITIES ON GROUND ACCORDINGTO THE HARDWARE IN THE LOOP AND PILOT IN THE LOOP CONCEPTS

- PROVIDES AN EFFECTIVE MEAN OF TRAINING PILOTS ON THE USE OF THE AVIONICS AND ON THERELATED FLIGHT AND ATTACK PROCEDURES

FUNCTIONS OF AN AVIONICS INTEGRATION RIG

AN AVIONICS INTEGRATION RIG CAN BE EXPANDED TO PROVIDE AN OVERALL MISSION SIMULATION CAPABILITY IN A COMPLEX TACTICAL SCENARIO


COCKPIT MOCK UP

EQUIPMENT BENCH

OPERATIONAL ENVIRONMENTSIMULATOR

AIRCRAFT SIMULATOR

DATA ACQUISITION ANDSTIMULATION SYSTEM

IMAGE GENERATOR

TERRAIN DATA BASETACTICAL SCENARIO SIMULATOR

GRAPHICS CONTROL

STRUCTURE SIMULATION SYSTEM

PROJECTION SYSTEM

SCREEN

STRUCTUREWIRING

POWER SUPPLYPROJECTOR

STRUCTUREWIRING

POWER SUPPLY

STRUCTUREWIRING

POWER SUPPLY

AVIONICEQUIPMENT

NON AVIONICEQUIPMENT

DYNAMICS/BASIC SENSORSAVIONIC EQUIPMENT SIMULATORS

INTERFACE WITH REAL EQUIPMENTDATA ACQUISITION AND STIMULATION

SOFTWARE SERVICES

NON AVIONIC EQUIPMENT SIMULATORS

DISCRETES

ANALOGS

DISCRETES

ANALOGS

LAN

LAN

DIGITAL

DISCRETES ANALOGS

REAL DISPLAYSAND INDICATORS

REAL CONTROLS

AVIONICS INTEGRATION RIG CONFIGURATION



ANTENNA TESTING

The design of airborne antennas and their location on the aircraft are essential for the overall system performance. The radiation patterns of the antennas can be significantlyaffected by the aircraft structure. Interference problems can also occur from couplingfrom an onboard transmitting antenna to a receiving antenna. Extensive testing activitiesmust therefore be carried out to ensure the desired installed performance.

Computational antenna modelling on structures

Measurements on subscale models of the airframe

Full scale ground measurementsOperational flight testing to verify properinstallation, functional performance and electromagnetic compatibility with the aircraft systems

OVERVIEW

HW / SW Design

SystemAcceptance




SystemsAnalysis &

Design

Test Scenarios

Test Scenarios

Test Scenarios


& Unit Test

MODELING AND SIMULATIONTOOLS FOR

SYSTEM DESIGN

SOFTWARE MODELINGAUTOMATIC CODE GENERATORS

INTEGRATION RIGSMISSION SIMULATORS

RECONFIGURABLE SIMULATORSMISSION SIMULATORS



SYSTEM DEVELOPMENT PROBLEMS

- Systems today are becoming more and more complex.

- Static documentation is insufficient for describing dynamic behavior.

- Functional groups have a lack of communication.- System requirements can be misinterpreted.

- Individuals interpret requirements differently.- Missing requirements.- Ambiguous requirements.- Conflicting requirements.

System Development Time

Cost

($$) of

Err

ors


SystemAcceptance




Requirements Models(Use Cases)

System Modification

System - / Performance - Model

TEST/PARAMETER-DATABASE

Test Scenarios Test Scenarios


& Unit Test

HW / SW Design

SystemsAnalysis &

Design

MODELING AND SIMULATION TOOLS FOR THE SYSTEM ARCHITECTURAL DESIGN


SystemFunctional

Design

RequirementsDocument

System Requirements

Document

Subsystem Design *HW/SW Requirements

SpecificationDocument

* Concurrent Engineering Task

SubsystemFunctionalDesign *

HW Design & Build SW Design & Implementation

Subsystem Requirements

Document

Links providing Traceabilityto original Requirements

Test Scenarios /Test Vectors

Test/ParameterDatabase

Executable Use Case Models



- Requirements Model

- Analyze each requirement and derive new system requirements.- Develop use-case models of the requirements.

- Functional Model

- Build and validate a functional description of the entire system.- Concerned with functional decomposition of a system, building a complete definition of the

system interfaces, and behavioral descriptions of the functions.- Functional decomposition is modeled independent of the physical architecture.

- Executable specification to describe dynamic behaviour.

- System validation performed early in the design process.

- Early detection of design errors.

- Model based design.

- removes ambiguous requirements.- resolves conflicting requirements.

- Communication channels are opened.



TEST DATABASE

- Tests need to be defined at each stage of the development cycle.

- At every level of the systems hierarchy, before progressing to thenext level, the model should be tested to validate the systemrequirements.

- Stimuli and responses should be recorded and applied during eachphase of development.

- Tests recorded on the virtual system can be applied to the physicalsystem.



MODELING AND SIMULATION CONCEPT FOR SYSTEM DESIGN

GRAPHICAL MODELING AND

DESIGN

SIMULATION AND ANALYSIS

GENERATE CODE

VALIDATE AND DEBUG DESIGN

EXECUTABLE SPECIFICATIONS

PROTOTYPES



PI_Controller

Vehicle_Dynamics



User Interface View

Panel

TargetPilot

Use Case 1

UC_1_1_3 Select Weapon

UC_1_1_4 Perform prerelease calcsUC1_1_1 Process

and store TGT position data

UC1_1 TGT Acquisition

UC1_1_12 Groundstab LDP

to TGT

Use Case 1

Use Case View

Use

Cas

e D

iagr

am

Use Case Scenario View

Sequ

ence

Dia

gram

Time-continuous Behavioral View

Time-

cont

inuou

s Diag

ram

State-based Behavioral View

Statec

hart

Statemate

Functional / Architectural View

Activity Char

t



- System Design Automation Tool.

- Allows the user to:

- Graphically model a design.

- Uses a graphical modeling language.

- Perform system analysis.

- Allows early validation of the systems behavior and functionality.

- Create a rapid prototype of the system.

- C/Ada and VHDL/Verilog Code can be generated for a design.- Panels can be created as a user interface to your simulation.



FROM USE CASES TO SYSTEM DESIGN

Identify Use Cases (done in RQ Analysis)

Identify Subsystems

Assign Requirements (Use Cases) to Subsystems

Define Subsystem Interfaces

Synthesize High Level Architecture- Functional System Design- System-Level COTS Analysis

Refine Subsystems- HW / SW Partitioning

Hierarchy Level 0(Context-Diagram)

ExternalData Sink

External Data Source

Hierarchy Level 1 Top-Down

Hierarchy Level 2



ENCAPSULATION OF ACTIVITIES

Statechart

Activity Chart



Hierarchy Level -1

Hierarchy Level 0 and 1

Hierarchy Level 2



Mini-Spec Continuous Diagrams( VisSim )

Truthtables

C-Code:User written or

SE-Tool generated( Matrix_x, Simulink, )

Statemachines(Statechart)



Interactive SimulationGenerating Events and/or changing Conditions and Data manually via a Monitor Window or a Graphic User Interface

- Animation of Statecharts and Activity Charts - Play-back File (Simulation Control Language (SCL-) Format)- Trace-File (Output: Spread Sheet, Waveform Display)

SIMULATION MODES

Batch SimulationUsers may write their own Simulation Control Program (SCP) on the Basis of a recorded Playback File

Testbench Simulation

By defining a Statechart to be a Testbench this Chart will beinterpreted as a Concurrent State Machine to the entire System.

- Stimulation and Monitoring of the System via the Broadcasting Mechanism- Application: Test Program Generation, FMEA, linear Plant Models



Aerospace Typical Applications

Avionics

Flight SurfacesPassenger

CabinSystems

Hybrid

DiscreteLogical

Behavior

Time/ContinuousControl Law

Behavior

MATRIXX/BetterState

Simulink/StateFlowStatemate MAGNUM/VisSim


Example Hybrid Systems

Discrete LogicSystems

Exterior Car LightingDigital Displays

Time-Continuous / Control Law Systems

Engine ControllerFlight Surfaces

Physical Systems

Hybrid SystemsAutopilot

TransmissionHVAC


The essential concept behind model checking is to (mathematically) prove whether a given model (a set of system requirements or a simulation model) satisfies a certain specification property.

Define a formal model of the system that issubject to verification by creating a model of the system in a language that fits the model checker's input language.


Provide a particular system property thatshould be proved. In other words, a question aboutthe system's behavior is formulated that should beanswered by the model checker.

Invoke the model checking tool and receive a notification whether the given system property wasfulfilled or not. In case the system property couldnot be verified, a counterexample is generated tofinger-point to the source of error in the simulationmodel.

MODEL CHECKING


RECONFIGURABLE SIMULATORS FOR THE SYSTEM DESIGN

RECONFIGURABLE SIMULATORS CAN BE USED IN THE SYSTEM DESIGN PHASE FOR EARLY PRELIMINARY ANALYSIS AND EVALUATION OF POSSIBLE DESIGN ALTERNATIVES IN A REPRESENTATIVE ENVIRONMENT

- FRONT PANEL GENERAL LAYOUT

- DISPLAYS FORMATS AND SYMBOLOGY

- SYSTEM/SUBSYSTEMS MODING

- AVIONICS CONTROL PROCEDURES

- FLIGHT AND MISSION PROCEDURES

- MAN/MACHINE INTERFACE PROCEDURAL ASPECTS


MISSION SIMULATORS FOR THE SYSTEM DESIGN


MISSION SIMULATORS FOR THE SYSTEM DESIGN

MISSION SIMULATORS CAN STRONGLY SUPPORT THE SYSTEM DESIGN BY PROVIDING AN EFFECTIVE MEAN FOR ANALYZING AND EVALUATING THE AVIONIC SYSTEM BEHAVIOUR IN AN EARLY STAGE OF THE DEVELOPMENT

MAIN AREAS OF UTILIZATION

- EARLY VERIFICATION OF THE AVIONIC SYSTEM FUNCTIONALITY AND PERFORMANCE

- EARLY VERIFICATION OF COMPLIANCE TO THE OPERATIONAL REQUIREMENTS IN A HIGHLYREPRESENTATIVE ENVIRONMENT

- EVALUATION OF THE MAN/MACHINE INTERFACE CHARACTERISTICS IN A HIGHLY REPRESENTATIVEENVIRONMENT

- DEFINITION AND EVALUATION OF FLIGHT AND MISSION PROCEDURES IN A HIGHLYREPRESENTATIVE TACTICAL SCENARIO

- EARLY VERIFICATION OF COMPLIANCE TO THE OPERATIONAL REQUIREMENTS WITH THE FINAL USER


MISSION SIMULATOR FUNCTIONAL BLOCK DIAGRAM

TACTICALSCENARIO

SIMULATOR

VISUALSIMULATOR

AIRCRAFTSIMULATOR

PILOTINTERFACE

SENSORSSIMULATORS

AVIONICEQUIPMENT

SIMULATORS

REALAVIONIC

EQUIPMENTSOFTWARESERVICES


AVIONIC SYSTEM

SCENARIO DATA

STATUS STATUS

COMMANDS

PROJECTIONSYSTEM

GRAPHICS

PLATFORMDATA

STATUS

COMMANDSAND CONTROLS


MISSION SIMULATOR PHYSICAL CONFIGURATION

COCKPIT MOCK UP


AIRCRAFT SIMULATOR

DATA ACQUISITION ANDSTIMULATION SYSTEM

IMAGE GENERATOR

TERRAIN DATA BASETACTICAL SCENARIO SIMULATOR

GRAPHICS CONTROL

STRUCTURE

SIMULATION SYSTEM

PROJECTION SYSTEM

SCREEN

STRUCTUREWIRING

POWER SUPPLYPROJECTOR

STRUCTUREWIRING

POWER SUPPLY

DYNAMICS/BASIC SENSORSAVIONIC EQUIPMENT SIMULATORS

DATA ACQUISITION AND STIMULATION

SOFTWARE SERVICES

NON AVIONIC EQUIPMENT SIMULATORS

DISCRETES

ANALOGS

LAN

LAN

DIGITAL

DISPLAYSINDICATORS

CONTROLS


AIRCRAFT SIMULATOR

THE AIRCRAFT SIMULATOR IS A HIGH FIDELITY SIX DEGREES OF FREEDOM AERODYNAMIC MODEL SIMULATING IN REAL TIME THE FLIGHT CHARACTERISTICS AND HANDLING OF THE AIRCRAFT. IT ALSO SIMULATES SOME AIRCRAFT SYSTEMS AND EQUIPMENT.


AIRCRAFT SIMULATOR MAIN SIMULATION MODELS

- AERODYNAMIC SYSTEM

- FLIGHT CONTROLS SYSTEM

- FLIGHT MANAGEMENT SYSTEM

- AUTOPILOT SYSTEM

- NAVIGATION SYSTEM

- AIR DATA SYSTEM

- AMBIENT SYSTEM

- WINDS SYSTEM

- ELECTRICAL SYSTEM

- HYDRAULIC SYSTEM

- ENGINE SYSTEM

- AUTOTHROTTLE SYSTEM


THE TACTICAL SCENARIO SIMULATOR ALLOWS THE DEFINITION OF INTERACTIVE TACTICAL SCENARIOS WITHIN USER DEFINED SYNTHETIC ENVIRONMENTS. ONCE THE SCENARIOS ARE GENERATED, THE SIMULATOR RUNS THEM IN REAL TIME, ENABLING FREE PLAY PARTICIPATION MIXED IN WITH THE PREDEFINED ENTITY BEHAVIOR RULES.

TACTICAL SCENARIO SIMULATOR


TERRAIN DATA BASE


IMAGE GENERATOR


DATA ACQUISITION AND STIMULATION SYSTEM


ImplementationTesting

MechanisticDesign

DetailedDesign

CodingUnit

TestingIntegration

Testing

ValidationTesting

IterativePrototypes

DesignObject-oriented SW Engineering

System Modification

Kno

wle

dge

Bas

e

HW/SW RequirementsSpecification

Test Scenarios

RequirementsSpecification

Function drivenSystems Engineering

RequirementsCapture & Analysis

A-D-I-T Cycles

SystemsAnalysis & Design

A-D-I-T Cycles

SystemAcceptance

Test Scenarios

SOFTWARE MODELING AND AUTOMATIC CODE GENERATION


+TypePP_DATA PP_DATA

+setPP_DATA(TypePP_DATA iPP_DATA)

CALC_AVG_SIGMA

+ACQ_DATA : OMBoolean

+setACQ_DATA(OMBoolean iACQ_DATA)+RESTART_ACQ()

DATA_ACQUISITION

+PB_ON_OFF : OMBoolean+PB_DISP : int

+setPB_ON_OFF(OMBoolean iPB_ON_OFF)+setPB_DISP(int iPB_DISP)

SIGNAL_GENERATOR

+A_DAT : double

+setA_DAT(double iA_DAT)+SEND_PP_DATA()

PRE_PROCESSING

+DISP_REQUEST : OMString+AV_VAL : double+SIGMA : double

+setDISP_REQUEST(OMString iDISP_REQUEST)+setAV_VAL(double iAV_VAL)+setSIGMA(double iSIGMA)

DATA_EVALUATION

DISPLAY

1

1

1 1

1

1

1

1

1

1

1

EXAMPLE OF SOFTWARE MODELING OBJECT MODEL DIAGRAM


Transition labels = Notes

EXAMPLE OF SOFTWARE MODELING STATECHARTS


CODE GENERATION AND DEBUGGING


DISTRIBUTED INTERACTIVE SIMULATION

DISTRIBUTED INTERACTIVE SIMULATION FACILITIES SUPPORT INTERACTION AND COLLABORATIVE WORKING BETWEEN GEOGRAPHICALLY DISTRIBUTED FACILITIES FOR NUMERICAL SIMULATION AND REAL TIME SIMULATION, INCLUDING HARDAWARE IN THE LOOP AND/OR MAN IN THE LOOP

NETWORK

COMMUNICATIONS

SIMULATION ANDVIRTUAL REALITY

MIDDLEWARE

SUPERVISOR GROUPWARE

HARDWARE INTHE LOOP

MAN INTHE LOOP

NUMERICALMODELS

SUPERVISIONAND CONTROL

VIDEOCONFERENCE ANDCOLLABORATIVE WORKING


DISTRIBUTED INTERACTIVE SIMULATION

ENGINEERING: COLLABORATIVE WORK BETWEEN DISTANT ENGINEERING TEAMS

SYSTEM VALIDATION: VALIDATION OF COMPLEX SYSTEMS WITH DISTRIBUTED TEST FACILITIES

TRAINING: TRAINING AND MISSION REHEARSAL USING REMOTE RESOURCES

RTIHLA-RTI

RTI RTI RTI

UserInteraction

DSI

Logger

DSI

RTI RTI

DSI

DSI

Tank Simulator

DSI

DSI

Aircraft Simulator

THE RAPID PROTOTYPING IN THE MAN/MACHINE INTERFACE DESIGN

ADVANCED TACTICAL FIGHTER COCKPIT LAYOUT TYPICAL HEAD DOWN DISPLAY FORMAT


THE RAPID PROTOTYPING IN THE MAN/MACHINE INTERFACE DESIGN

THE RAPID PROTOTYPING TOOLS ARE USED IN THE AEROSPACE INDUSTRY FOR DESIGNING, RAPID PROTOTYPING, TESTING AND DEPLOYING MAN/MACHINE INTERFACES. THEY ENABLE THE DEVELOPMENT OF DYNAMIC, INTERACTIVE, REAL TIME GRAPHICAL MAN/MACHINE INTERFACES FOR COMPLEX APPLICATIONS SUCH AS THE COCKPIT LAYOUTS AND THE DISPLAYS AND CONTROLS FORMATS AND SYMBOLOGY

RAPID DESIGN, GENERATION, TESTING AND DOCUMENTATION OF VIRTUAL MAN/MACHINE INTERFACE OBJECTS FOR MISSION CRITICAL, SAFETY CRITICAL AND SIMULATION APPLICATIONS

AUTOMATIC CODE GENERATION FOR THE DEVELOPMENT ENVIRONMENT

AUTOMATIC CODE GENERATION FOR REAL TIME EMBEDDED TARGET

AUTOMATIC GENERATION OF QUALIFIABLE SOURCE CODE WHICH IS COMPILED FOR THE DEVELOPMENT ENVIRONMENT AND FOR REAL TIME EMBEDDED TARGETS


4. QUALITY AND SAFETY ASPECTS


4.1.1. Total Quality Management4.1.2. Quality Systems, Standards and Specifications4.1.3. Product and Process Quality Assurance

4.2. System Configuration Control

4.2.1. Configuration Identification4.2.2. Configuration Change Control4.2.3. Software Configuration4.2.4. Configuration Audits


4.3.1. Safety and Mission Critical Functions4.3.2. Safety Engineering4.3.3. Fault Tolerance Concept

TOTAL QUALITY MANAGEMENT: THE TOTAL INTEGRATED MANAGEMENT APPROACH THAT ADDRESSES SYSTEM/PRODUCT QUALITY DURING ALL PHASES OF THE LIFE CYCLE AND AT EACH LEVEL IN THE OVERALL SYSTEM HIERARCHY

- TOTAL CUSTOMER SATISFACTION

- CONTINUOUS IMPROVEMENT ON A DAY TO DAY BASIS APPLIED TO ENGINEERING, PRODUCTIONAND SUPPORT PROCESSES AND FUNCTIONS

- INDIVIDUAL UNDERSTANDING OF PROCESSES, EFFECTS OV VARIATION AND PROCESS CONTROL METHODS.INDIVIDUAL EMPLOYEES MUST BE KNOWLEDGEABLE OF VARIOUS PROCESSES AND THEIR INHERENTCHARACTERISTICS

- TOTAL ORGANIZATIONAL APPROACH, INVOLVING EVERY GROUP IN THE ORGANIZATION. INDIVIDUALEMPLOYEES MUST BE MOTIVATED AND SHOULD BE RECOGNIZED AS BEING KEY CONTRIBUTORS TOMEETING QUALITY OBJECTIVES

QUALITY ENGINEERING IS A PART OF THE SYSTEM ENGINEERING PROCESS

- QUALITY PLANNING: THE DEVELOPMENT OF A TOTAL QUALITY MANAGEMENT PLAN MUST BE ACCOMPLISHEDDURING CONCEPTUAL DESIGN AND UPDATED AS REQUIRED

- QUALITY IN DESIGN: SIMPLICITY, FLEXIBILITY, STANDARDIZATION, ROBUSTNESS


TOTAL QUALITY MANAGEMENT


A Quality System is an organizational structure with responsibilities, procedures, processes, and resources that implements a management function to determine and enforce quality principles. A Quality System encompasses Quality Assurance and Quality Control.

Quality Assurance

Quality Control

A management system for programming and coordinating the quality maintenanceand improvement efforts of the various groups in a design and/or manufacturing organization, so as to permit design and/or production in compliance withregulatory and customer requirements.

Conduct and direct supervision of the quality tasks (inspection of product) toensure that the quality requirements of the product are achieved.

QUALITY SYSTEMS, STANDARDS AND SPECIFICATIONS



Quality and reliability are critical values for the aerospace industry. In an environmentwhere the mistakes or failure of products or services can be fatal, the effectiveoperation of a quality management system plays an essential role in helping to reduce risks and provide a reliable framework for organizations to provide a product or service.

Quality management systems have been used in the aerospace industry for many years. Efforts by members of the aerospace industry to establish a single common qualitymanagement system resulted in AS9100, 9110, 9120. They are used and supported by the world's leading aerospace companies and also throughout their supply chain partnerships.

AS9100 - Quality Management System Requirements for Design and/or Manufacture of Aerospace Products

AS9110 - Quality Management System Requirements for MaintenanceOrganizations

AS9120 - Quality Management System Requirements for StockistDistributors



AS 9100 has been endorsed by all major Aerospace regulators, including:

Federal Aviation Administration (FAA) U.S. Department of Defense (DoD) National Aeronautics and Space

Administration (NASA).

The AS9100 is the quality management standard specifically written for the aerospace industry. Itprovides organizations with a comprehensive quality management system focused on areas direclyimpacting product safety and reliability.

Configuration managementRequires that management discipline be applied over the life cycle of a product to provide visibility and control of its functional and physical characteristics

DesignEnsures that design responsible organizations have a robust design process to meet safety and reliability requirements demanded by the Aerospace industry

PurchasingRequires effective controls over the organizations entire supply chain

Product RealizationEnsures that each phase of product realization, fromplanning procuring and manufacturing to shipment iscontrolled for delivery of product conforming to customerrequirements

Product Monitoring/MeasurementDefines requirements for product validation prior toshipment.


GENERAL

ONCE A CONFIGURATION BASELINE HAS BEEN ESTABLISHED, IT IS ESSENTIAL THAT ANY VARIATIONS OR CHANGES WITH RESPECT TO THAT BASELINE BE TIGHTLY CONTROLLED. THE PROCESS OF CONFIGURATION IDENTIFICATION, THE CONTROL OF CHANGES AND MAINTAINING THE INTEGRITY AND CONTINUITY OF DESIGN ARE ACOMPLISHED THROUGH THE CONFIGURATION MANAGEMENT

PRELIMINARYDESIGN

DETAILEDDESIGN

DEVELOPMENT PRODUCTION OPERATIONALUSE

FUNCTIONALBASELINE

ALLOCATEDBASELINE

PRODUCTBASELINE

UPDATED PRODUCTBASELINE

CLASS 1 CHANGESDESIGN CHANGES AFFECTING FORM AND/OR FIT AND/OR FUNCTION AND/OR ANY OTHER SYSTEM SPECIFICATION REQUIREMENT

CLASS 2 CHANGESDESIGN CHANGES RELATIVELY MINOR IN NATURE AND NOT AFFECTING THE SYSTEM SPECIFICATION REQUIREMENTS

CONFIGURATION CHANGE CONTROL


SOFTWARE CONFIGURATION


The Software Configuration Management (SCM) process identifies the functional and physicalattributes of software at various points in time, and performs systematic control of changes to the identified attributes for the purpose of maintaining software integrity and traceability throughout the software development life cycle.

It identifies four procedures that must be defined for each software project to ensure that a sound SCM process is implemented.

Configuration identification is the process of identifying the attributes that define every aspect of a configuration item. These attributes are recorded in configuration documentation and baselined. Baselining an attribute forces formal configuration change control processes to be effected in the eventthat these attributes are changed.

Configuration change control is a set of processes and approval stages required to change a configuration item's attributes and to re-baseline them.

Configuration status accounting is the ability to record and report on the configuration baselinesassociated with each configuration item at any moment of time.

Configuration audits are broken into functional and physical configuration audits. They occur eitherat delivery or at the moment of effecting the change. A functional configuration audit ensures thatfunctional and performance attributes of a configuration item are achieved, while a physicalconfiguration audit ensures that a configuration item is installed in accordance with the requirementsof its detailed design documentation.

- FLIGHT CONTROL SENSORS, PROCESSING AND DISPLAYS

- TERRAIN FOLLOWING/TERRAIN AVOIDANCE SENSORS ANDCONTROL

- STORES MANAGEMENT CRITICAL FUNCTIONS

EXAMPLE TACTICAL AIRCRAFTTYPICAL SAFETY/FLIGHT CRITICAL FUNCTIONS

EXAMPLE TACTICAL AIRCRAFTTYPICAL MISSION CRITICAL FUNCTIONS

- NAVIGATION SENSORS, PROCESSING AND DISPLAYS

- ATTACK SENSORS, PROCESSING AND DISPLAYS

- COMMUNICATIONS

- STORES MANAGEMENT NON CRITICAL FUNCTIONS

- TACTICAL SITUATION MANAGER

- ELECTRONIC WARFARE

SAFETY/FLIGHT CRITICAL FUNCTIONSFUNCTIONS WHICH ARE ESSENTIAL TO SAFE OPERATION OF THE AIRCRAFT. FAILURES TO THESE FUNCTIONS MIGHT LEAD TO A HAZARD FOR THE PILOT OR FOR THE AIRCRAFT.

SAFETY/FLIGHT CRITICAL FUNCTIONS MUST BE SUBJECT TO RIGOROUS FAULT TOLERANT AND INTEGRITY DESIGN PHILOSOPHIES.

MISSION CRITICAL FUNCTIONSFUNCTIONS WHICH RELATE DIRECTLY TO THE MISSION OF THE AIRCRAFT. FAILURES TO THESE FUNCTIONS MIGHT LEAD TO THE MISSION ABORT.A LOWER DEGREE OF FAULT TOLERANCE AND INTEGRITY CAN BE ACCEPTED FOR THE MISSION CRITICAL FUNCTIONS.


SAFETY AND MISSION CRITICAL FUNCTIONS

SAFETY IS A SYSTEM DESIGN CHARACTERISTIC. IT IS ESSENTIAL THAT THE SAFETY REQUIREMENTS BE APPROPRIATELY INTEGRATED INTO THE OVERALL SYSTEM ENGINEERING PROCESS

SAFETY PROGRAM TASKS

- PROGRAM MANAGEMENT TASKS

- SYSTEM SAFETY PROGRAM PLAN

- REVIEW AND CONTROL OF SUPPLIERS/SUBCONTRACTORS

- SYSTEM SAFETY PROGRAM REVIEWS

- DESIGN AND ANALYSIS TASKS

- FAULT TREE ANALYSIS

- HAZARD ANALYSIS

- RISK ANALYSIS

- DATA COLLECTION, ANALYSIS, FEEDBACK AND CORRECTIVE ACTIONS

- TEST AND EVALUATION TASKS

- SAFETY TRAINING PROGRAM

- SAFETY TEST AND EVALUATION


SAFETY ENGINEERING

THE CRITICAL SYSTEMS MUST BE DEVELOPED ACCORDING TO THE FAULT TOLERANCE CONCEPT. THE FAULT TOLERANCE IS THE ABILITY OF A SYSTEM TO PROVIDE ITS FUNCTION AND TO CONTINUE OPERATION AFTER ONE OR MORE FAULTS HAVE OCCURRED.

FAULT TOLERANCE TECHNIQUES

- FAULTS MUST BE DETECTED, IDENTIFIED AND ISOLATED- REDUNDANT SYSTEM RESOURCES MUST BE AVAILABLE AND BE RECONFIGURED

TO PROVIDE CONTINUING OPERATION- MONITORS, VOTERS AND SWITCHING MECHANISMS ARE REQUIRED TO RECOGNIZE

FAULTS AND TO PROVIDE RECONFIGURATION PATHS

- THE RECOVERY MECHANISMS MUST BE AUTONOMOUS, ALLOWING GRACEFULDEGRADATION

- ALL FAILURES THAT MIGHT LEAD TO A HAZARD MUST BE DETECTED


FAULT TOLERANCE CONCEPT

Documents

Introduction to Avionic Systems Development_slides