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Airborne Lasers and Integrated Weapon

Systems: Design, Development,

Test and Evaluation

San Jose dos Campos, 30th September 2015

NATO UNCLASSIFIED – Approved for Public Release

Prof. Roberto Sabatini, PhD, FRIN Head of Group, Intelligent Transport Systems and Aviation Program Leader

Avionics and ATM Leader, Sir L. Wackett Aerospace Research Centre

School of Aerospace, Mechanical and Manufacturing Engineering

RMIT University, Melbourne, Victoria, Australia

INVITED PLENARY SPEACH

INTRODUCTION

MILITARY REQUIREMENTS

CLDP, GBU-16 AND GBU-24 SYSTEMS DESCRIPTION

CLDP HMI, FUNCTIONS AND EMPLOYMENT

LGB SELF-DESIGNATION AND CO-OPERATIVE ATTACKS

FLIGHT TEST REQUIREMENTS AND METHODS

SOFTWARE DEVELOPMENT AND TESTING

MODELLING AND SIMULATION

FLIGHT TEST ACTIVITY

FINAL REMARKS

SCOPE OF THE PRESENTATION

XVII SIGE - Symposium of Operational Applications in Areas of Defense

29 September – 1 October 2015, San Jose dos Campos, Brazil

LOAM SYSTEM DESCRIPTION



INTRODUCTION

q Since the beginning of the 90’s, the NATO Defence Forces have been involved in

activities related with:

Laser Guided Weapons;

Laser Designation Systems.

q In the ITAF R&FTC (CSV-RSV) the Thales Convertible Laser Designation Pod

(CLDP), together with Laser Guided Bombs (LGBs), have been integrated on

TORNADO-IDS aircraft.

q A new tailored RDT&E was adopted in order to:

Reduce the costs associated with the development process; Obtain the higher possible level of efficiency.

Laser Navigation Aid and Obstacle Warning Systems

q The Laser Obstacle Avoidance and Monitoring System (LOAM) was developed

under to equip helicopters, with a focus on NH-90 (Eurocopter) rerquirements and

possible further applications to low dynamics platforms (e.g., small size UAVs).

q Modelling and Simulation were essential for correctly planning flight test activities, analysing flight test data and verifying the validity of the models/algorithms loaded in the operational aircraft software.

Store Separation Simulation;

Aerodynamic Simulation;

Guided/Unguided Weapon Simulation;

Masking Algorithms Simulation;

Aircraft Weapon Aiming Simulation;

Laser Performance Simulation;

Ballistic and Laser Safety Areas Simulation.

q Simulation Tools developed during Sub-System integration activities included thefollowing:

INTRODUCTION



LTD/LGB MILITARY REQUIREMENTS

q Initial MOD Requirements (“Lesson learned” of the “Desert Storm” operation):

COTS Bang-Bang Laser Guided Bombs; COTS Day-Night Laser Designation Pod.

q Further MOD Requirements:

Improve Sub-System Software capability; Integrate LGBs with a longer operational range and higher accuracy/hit probabilities.

q Operational Requirements for LTD and LGBs included definition of:

Specific Mission Requirements;

Functional Requirements;

Crew Members Workload;

Human-Machine Interface (HMI).



q Systems Selection Criteria (LGB’s and LTD):

Proven operational capability; Full compliance with the basic operational requirements; Low risk during the development phase; Commonality with other sub-systems and TORNADO-IDS suspension system; State-of-the-art technology in order to guarantee longer operational life;

q Selected Systems :

THALES Convertible Laser Designation Pod (CLDP); GBU-16 Laser Guided Weapon (Paveway II); GBU-24 Laser Guided Weapon (Paveway III).

LTD/LGBMILITARY REQUIREMENTS

Upgrade potentials for future applications.



q The CLDP is a system designed to provide the aircraft with day and night laserdesignation capability. It can be configured with:

CONVERTIBLE LASER DESIGNATION POD (CLDP)

q Both CLDP configurations include two sections:

Interchangeable Front Section containing a TV or TC sensor head; Common Body containing a centre section and rear cooling unit.

Television Camera (TV) for day-time missions; Thermal Camera (TC) for day/night time missions.



GBU-16 LASER GUIDED BOMB (PAVEWAY II)

q The GBU-16 (PAVEWAY II) Laser Guided Bomb consists of:

Forward Computer Control Group (CCG) including control canards and an aftwing assembly;

MK-83 1000 pound warhead.

q The Detector Unit Housing (DUH) is mounted on the front section of the CCG and isfree to gimbal in any direction (aerodynamically stabilised with the velocity vector of theweapon).

q GBU-16 guidance is provided by a system commonly referred to as “Bang-Bang”control.



q The GBU-24 (PAVEWAY III) is a laser guided munition designed to enhance Low Altitude Delivery. PAVEWAY III consist of:

Nose Mounted Guidance Unit;

Aft Wing Assembly. q The Air Force selected two 2000 pound bombs:

MK-84 2000 pound warhead;

BLU-109 high penetration warhead. q GBU-24 is a “Proportional Guidance” LGB. q The bomb has 4 Operational Modes depending on target characteristics and

desired bomb impact angle. For each mode, the GBU-24 computer unit automatically selects a suitable flight profile.

GBU-24 LASER GUIDED BOMB (PAVEWAY III)



CLDP FORMAT

Functions selected

through dedicated SKs

CLDP

CONTROL

PANEL

CLDP MAN - MACHINE INTERFACE

q CLDP main functions are selected by the Weapon System Operator (WSO).Commands and controls are located in the Tornado Rear Cockpit.

q Pod Line of Sight (LOS) controls are located both in Front and Rear Cockpit.



CLDP BASIC SUB-SYSTEM FUNCTIONS

q CLDP System Status Check

q Slave Modes

q Track Modes

q Computer Rate Track

q Masking

q Reversionary

q Pod-Aircraft Harmonization

q Video-Laser Boresight



CLDP OPERATIONAL EMPLOYMENT

q Self Designation Attacks

Aircraft acts as illuminator for the own carried LGBs.

q Co-operative Designation Attacks.

Aircraft acts as illuminator for partner(s) aircraft.

q CLDP Target/Navigation Fixing.

CLDP can be used as a sensor for 2D/3D Navigation/Target Fixing purposes.



SELF DESIGNATION ATTACK

1

2

3

4

1 - Approach phase

5

2 - Bomb Release

4 - Laser illumination 3 - Escape manoeuvre

5 - End of attack



CO-OPERATIVE ATTACK

1 - Approach phase

4 - Laser illumination

2 - Break-off point

3 - Controlled turn manoeuvre

2

1

3

4





LTD/LGB SEQUENCE OF OPERATIONS

TEST REQUIREMENTS

q Areas of Testing:

Test RequirementsMathematical ModelsAnalysis Tools

Flight mechanics (handling/vibration); Store separation ( LGB’s);

Software development; Avionics and Sub-systems functions verification.

Data Acquisitionand

Telemetry System



FLIGHT MECHANICS TESTING

q Handling

Typical maneuvers were performed to verify aircraft stability and control at theselected flight conditions identified through mathematical models.

q Vibration

Activity needed to measure the actual vibration levels induced on CLDP andAdapter under the selected flight conditions and aircraft external stores configurations.



STORE SEPARATION TESTING

q LGB Jettison and Releases performed at the selected flight conditions to:

Confirm the store separation predicted by mathematical models;

Verify any possible mechanical interference between ‘dressing’ and TORNADO suspension system;

Verify aerodynamic influence on unguided store trajectory;

Acquire data for optimising ballistic constants;

Optimise attack profiles.



SOFTWARE DEVELOPMENT AND TESTING

q Development of Avionics Softwarerequired moving into the followingprocess:

SW

Definition

SW

Requirement

Specification

SW

Coding

Ground

Tests

Limits ?

Queries ?

Yes

No

Flight

Trials

Limits ?

Queries ?

Yes

No

In Flight

Final Demo

SW

Delivery

No

Yes

No

Software Definition ;

Software Coding ;

Software Testing .



SIMULATION

q Store Separation Simulation

q Aerodynamic Simulation

q Unguided Weapon Ballistics

q Masking Analysis and Simulation

q Weapon Aiming Simulation

q Guided Weapon Simulation

q CLDP Performance Simulation

q Ballistic and Laser Safety Areas



STORE SEPARATION SIMULATION

Program based on the application of 3D Euler Code, to evaluate and update the airloadson the separating store.



AERODYNAMICS SIMULATION

CAD-CATIAand

CFD codes

Complete/Reliable Aerodynamic Calculations



LGB WEAPON BALLISTIC SIMULATION

q Guided Weapon Ballistics Program (GWBP)

Program capable of computing the guided LGB weapon trajectory. GWBP outputs are: - bomb flight conditions where the target enters into the seeker field of view; - bomb flight conditions when the las er starts to fire; - bomb flight condition where the bomb starts the guided trajectory; - bomb flight conditions along the guided trajectory; - impact point with respect the spot laser; - bomb time of flight.

q Unguided Weapon Ballistics Program (UWBP)

The UWBP was developed at RSV in order to compute unguided ballistic tables for any type of bomb released by any type of aircraft, and to define attack release conditions. The output ballistics tables consisted of the following parameters:

- bomb range; - bomb time of flight; - bomb impact angle; - bomb impact velocity; - bomb depression angle relative to the aircraft at time of release.



MASKING PROFILES SIMULATION

CAD Simulation was used for defining the Masking Function logic according to theaircraft shape and external stores configurations.

ROOT

LO

RO

LSW

TANKLI

RI

E/NCL

E/N

A/C MASKS SEMICLEAN 2

TANK

E/N

GBU2 4

GBU24

E/N

E/N

E/N

CLEAN

LEGEN D :

E/N = Empty / N o Py lo n

TA N K = 1 5 0 0 LT Ta nk

GBU 2 4 = GBU 2 4 R ea l Wea po n

C BLS = BD U 3 3 B/B o r M K 1 0 6

= D o n't C a re

TANK

RS (light)

CBLS

GBU1 6

RS (heavy) E/N

GBU1 6

SEMICLEAN 1

E/N

RSW



ATTACK PROFILES SIMULATION

An Attack Profiles Simulation (APS) tool was developed for monitoring the LOS components (Azimuth and Elevation) during A/C manoeuvres, in an Hammer/Aitoff Diagram where mask and pre-mask profiles were plotted.



q For Weapon Aiming assessment purposes, a simulation program was developed atRSV. The program used the same models adopted by the TORNADO MainComputer (MC) for execution of the various attacks.

TORNADO WEAPON AIMING SIMULATION

q Two GBU-24 software modules were developed covering specific sub-tasks:

a module for selecting the appropriate set of envelope constants dependingon aircraft flight/release conditions;

a second module, based on neural networks algorithms, for calculating therelease range envelope for a successful bomb release.



CLDP PERFORMANCE SIMULATION

q The models used for performance calculations were:

Geometric Model

Laser Range Equation

Atmospheric Propagation Models

Reflection Models




Geometric Model________________________________________________




Laser Range Equation_________________________________________




Atmospheric Propagation Models______________________________




Reflection Models___________________________________________

Lambert Model

Phong Model



BALLISTIC SAFETY AREAS

A software tool was developed capable of producing “Safety Traces”. This tool was able to manage “dive”, “level”, as well as “loft” attacks with any input entry conditions, type of bomb and error vector.

The program output was the Safety Trace border on the ground, obtained by takinginto account the worst case simulated impacts.



LASER SAFETY AREAS

q A simulation tool was implemented at RSV for laser missions planning andoptimisation. The program was based on the following calculations:

- Laser Characteristics - Aircraft Position and Velocity - Reflection Point Position - Observer Position

Exposure Time Calculation

NOHD Calculation

NOHD >

Distance Observer-Reflection Point +

Reflection point-aircraft

Safe Scenario

Unsafe Scenario

TRUE

FALSE

Nominal Ocular Hazard Distance (NOHD)

Buffer Zone (BZ)

Hazard Area (HA)

Extended Buffer Zone (EBZ)



LASER SAFETY AREAS

Hazard Area___________________________________________________



Buffer Zone_________________________________________________

LASER SAFETY AREAS



Extended Buffer Zone___________________________________________

LASER SAFETY AREAS




Functional assessment was carried out at the Air Force Sardinia Test Range (PISQ)and included:

‘Dry Attack’ Flights – performed over the PISQ Sea Range (Salto di Quirra);

‘Hot Attack’ Flights – performed over the PISQ Ground Range (Piana del Cardiga).



Self Designation Reversionary





Sardinia Test Range currently immediate actions:

PISQ Ground Range ‘Evacuation of Personnel’ – Safety

Safety Officer Monitoring (PISQ Control Room) – Safety and ATC Coordination

Real-time Telemetry Link for CLDP Video – Safety and Accuracy

Sardinia Test Range upgrades (PILASTER):

Laser Spot Tracking System (SAPD) – Safety and Pointing Accuracy

IR Laser Signal Measuring System (IRSM) – Performance Evaluation

Real-Time Encrypted Telemetry Link (ETL) – Safety, Comms and Accuracy

Ground Soft Target – Test/Training “Dry/Hot Attacks” w/o LGB Delivery

Ground Hard Target – Test/Training “Hot Attacks” with LGB Delivery

Control Room Upgrade – SAPD, IRSM and ETL Management



MOST HELICOPTER AND UAV CRASHES ARE DUE TO IMPACT AGAINST

OBSTACLES WHICH ARE SCARCELY VISIBLE EVEN

IN DAYLIGHT AND IN GOOD WEATHER CONDITIONS

NEED TO AUGMENT HELICOPTER LOW-LEVEL AND NAP-OF-THE-EARTH

NAVIGATION CAPABILITY

OBSTACLE AVOIDANCE SYSTEMS



LASER OBSTACLE WARNING/AVOIDANCE

WARNING TIME • 10 SECONDS

FLIGHT CONDITIONS

DETECTION • ANY OBSTACLE ALONG FLIGHT PATH • EXPECIALLY WIRES

HMI • TYPE OF OBSTACLE • LOCATION • AVOIDANCE ADVICE

• STRAIGHT FLIGHT (UP TO 260 Km/h)

• TURN (UP TO ABOUT 30 deg)

• TERRAIN FLIGHT

• DAY/NIGHT NVD



OPERATIONAL REQUIREMENTS

LASER “RADAR” SOLUTION

LOAM LASER OBSTACLE

AVOIDANCE & MONITORING

REQUIREMENTS MAGNETIC

OWS THERMAL

OWS MILLIMETRIC RADAR OWS

LASER RADAR OWS

Wire detection only energized

wires only energized

wires

all wires preferably perpendicular to flight trajectory

all wires

Detection range short short as required as required Coverage Area small as required as required as required

Obstacle position, distance and type

determination accuracy

insufficient good for position

and type , no distance provided

medium very high

Performance/weather/ flight speed

dependency good poor good good

False alarm rate high low very low very low Installability medium medium medium medium

Base technology status

mature mature state-of-art state-of-art



OBSTACLES TYPE • WIRES (5 mm)

• PYLONS, POLES, TREES

• BUILDING, WALLS

FLIGHT ENVELOPE

INSTALLATION PLATFORMS

• ANY TYPE OF HELICOPTER AND SMALL UAV • STAND ALONE / INTEGRATED MODES

EYE-SAFETY • STANAG 3606 CLASS I

• STRAIGHT FLIGHT (UP TO 260 Km/h)

• TURN (UP TO ABOUT 30 deg)

• LANDING, TAKE OFF



LOAM TECHNICAL REQUIREMENTS

• SCAN BY LASER BEAM THE AREA AROUND THE FLIGHT TRAJECTORY

• OBSTACLES DETECTION AND CLASSIFICATION THROUGH ECHOES ANALYSIS

• DELIVERY OF WARNING AND INFORMATION TO THE CREW

• COMMUNICATE WITH OTHER ON-BOARD EQUIPMENT

SENSOR HEAD UNIT

• SELF TEST

CONTROL PANEL UNIT

LOAM FUNCTIONS



PARAMETERS PERFORMANCE

Vertical FOV > 30°

Horizontal FOV > 40°

LOS range Az 20°

LOS range El 20°

Instantaneous FOV < 2 mrad

Scan efficiency per one frame 1:15

Scan efficiency per 0,5 sec. 1:20

Max range 2000 m

Min range < 50 m

Range resolution < 1.5 m

Scanning time 0.5 s

Detection probability per 1 sec. > 99.5 %

False Alarm Rate < 1 per 2 flight hours

SUBSYSTEMDIMENSION

width x height x depth

Sensor Head Unit 320 x 239 x 419 mm

Control Panel Unit 146 x 38.1 x 165 mm

Display Unit (optional)4 ATI or3x4 ATI

Warning Unit (optional) 90 x 22 x 100

SUBSYSTEM WEIGHT (Kg)

Sensor Head Unit 24

Control Panel Unit 0.5

Display Unit (optional) 1.7

Warning Unit (optional) 0.5

PERFORMANCE



visibility 800 m

visibility 1500 m

visibility 2000 m

90

75

60

45

30

15 0

-15

-30

-45

-60

-75

-90 1000 900 800 700 600 500 400 300 200 100 0

Detection range for wires, d=5mm

90

75

60

45

30

15 0

-15

-30

-45

-60

-75

-90 1000 900 800 700 600 500 400 300 200 100 0

Detection range for wires, d=10mm

PERFORMANCE



TELESCOPE

SUB-ASSY

TX

OPTICS

DETECTOR

SUB-ASSY

LASER

ASSY

SCANNER CONTROL

&

PREPROCESSING ASSY

Blanking signal POWER SUPPLY &

POWER MOTORS

ASSY 28 Vdc

On/Off

Motors control signals

PROCESSING ASSY

HMD PROCESSING & VDU

VIDEO ASSY

MIL-STD 1553

ARINC 429

RS232 Test Link

GYROSCOPE

ASSY

OPTICAL

ASSY

WMC discrete

WOW (TBD)

WU P

(optional)

WU C

(optional)

WIN

DO

W

ELECTRONIC

MECHANIC

OPTIC

SCANNER

ASSEMBLY

CP

(helicopter)

HMD/C

HMD/P

VID

EO

RS

422

FLIR

VDU

VID

EO

VID

EO

RS

422

VID

EO

EXTERNAL

SYSTEM ARCHITECTURE



LOAM EQUIPMENT MAKES USE OF

ERBIUM FIBER 1.55 µm LASER

LOAM EQUIPMENT OPERATION IS ACCORDING TO

STANAG 3606 CLASS I(1)

(1) Class I lasers produce radiation that causes no biological damage

LASER SAFETY



Sensor Head Unit

Control Panel Unit

Display Unit

(for test)

HARDWARE



Laser

Beam expander

Scanning control

& Processing board

Telescope

Power supply

HARDWARE (2)



Entrance window

Scanning mirror

Electrical connector

HARDWARE (3)



• BASED ON A SWASHING

MIRROR CONCEPT • LIGHT WEIGHT

• HIGH RELIABILITY

• HIGH ACCURACY

LINE OF SIGHT ORIENTATION

• AUTOMATIC FOV LOS RANGE ORIENTATION

• ± 20O IN AZIMUTH (1° step)

• ± 20O IN ELEVATION (20° step)

300

V-FOV

400 H-FOV

SCAN PATTERN

• 40.000 LASER SPOTS

• DRAWN BY SCANNED ELLIPSES

• CAPABILITY TO DETECT OBSTACLES REGARDLESS

THEIR ORIENTATION

• OPTIMIZED FOR WIRE DETECTION

• PRESERVE OBSTACLE SHAPE

DURING HELICOPTER MOTION

SCANNER



SCANNER



OBSTACLE CLASSIFICATION

OBSTACLE PRIORITYZATION

• CLASS “WIRE” (HORIZONTAL THIN STRUCTURE “WIRE LIKE”)

• CLASS “TREE/POLE” (VERTICAL SINGLE STRUCTURE “TREE OR PILON LIKE”)

• CLASS “EXTENDED OBSTACLE”

(BIDIMENSIONAL STRUCTURE “BUILDING OR HILL LIKE”)

OBSTACLE DETECTION

• ECHO DETECTION (AVALANCHE PHOTODIODE, VARIABLE GAIN AMPLIFIER)

• PRE PROCESSING

(SINGLE ECHO POSITION/DISTANCE ANALYSIS)

• PROCESSING

(PREPROCESSED ECHOES GLOBAL ANALYSIS)

• BASED ON OBSTACLE RANGE AND FLIGHT PATH

• SELECTABLE PHYSICAL ENVELOPE

• NEAREST OBSTACLE AND/OR OBSTACLE POSITIONED WITHIN THE

FLIGHT PATH HIGHTEST PRIORITY

DETECTION AND CLASSIFICATION



DETECTION AND CLASSIFICATION



VISUAL WARNINGS

• OBSTACLES ARE DISPLAYED WITH THREE

TYPES OF SYMBOLS (Classes)

• OBSTACLE SYMBOLS ARE VISUALIZED ON A SCREEN REPRESENTING LOAM FOV

• OBSTACLE POSITIONED ACCORDING TO

LOAM REFERENCE FRAME

• RELEVANT RANGE AND MAX. PRIORITY

MARK DISPLAYED

AUDIO WARNINGS

• ANALOG SIGNAL TO DIRECTLY DRIVE

HEADPHONE SET

• DIGITAL SIGNAL TO TRIGGER ON BOARD

SOUND GENERATOR

CLASS

WIRE

SIMBOL

CLASS

EXTENDED

SYMBOL

CLASS

TREE

SYMBOL

MODULATED SOUND

SYNTHETIC

PRESENTATION OF

OBSTACLES

WARNING DELIVERY OPTIONS



70º 70°

40°

70°

Scenario (Altitude)

Manned

operations Autonomous operations

Nominal Pilot (AC 90-48c)

Auto LOS BLOS

Low 2.5 0.5 1 1.5

Medium 3.5 1 2 2.5

High 4.0 1 2.5 3

DETECTION RANGE (NM)

FAA Requirements



UAV INTEGRATION ARCHITECTURE

DISPLAY OPTIONS



Safety Line



WR / PL

DISPLAY OPTIONS



ALL



3D



3D / FLIR



PPI





IMPACT WARNING

COMMUNICATION LINES (MIL-BUS-1553B, RS422 SERIAL LINK, ARINC 429)

• OBSTACLE INFORMATION TRANSMISSION Obstacle Class, Priority, Position (Az , El & Distance

according to LOAM reference system, useful for evasive manoeuvre)

• SYSTEM STATUS TRANSMISSION

• EXTERNAL COMMANDS RECEIVE

AUTO TEST FUNCTIONS

• POWER ON BIT: AUTOMATICALLY ACTIVATED ON POWER ON

• INTERRUPTIVE BIT: ACTIVATED ON PILOT’S REQUEST

• CONTINUOUS BIT: PERIODICALLY EXECUTED DURING NORMAL OPERATION CBIT

IBIT

• VIDEO OUTPUT FLIR with obstacle symbols superimposed available

COMMS & AUTO-TEST



DISPLAY

UNIT

INHIBIT

LASER EMISSION

RETURN ECHOES

HEAD SET

POWER SUPPLY

POWER SUPPLY CONTROL

PANEL UNIT

SENSOR UNIT

e.g., NH300

INTEGRATION



DISPLAY

UNIT

INHIBIT

LASER EMISSION

RETURN ECHOES

HEAD SET

POWER SUPPLY

POWER SUPPLY CONTROL

PANEL UNIT

SENSOR UNIT

IMU

ARINC 429

e.g., AB212/AB412 and Small UAV

PTHROUGH DL IN UAV

INTEGRATION (2)



INHIBIT

POWER SUPPLY

MISSION BUS 1553B

CWG

MFD

MC IRS

AR

INC

429

EWS FLIR RS422 (PROVISION)

e.g., EH101 and UAV

LASER EMISSION

RETURN ECHOES

DISPLAY

UNIT

CONTROL

PANEL UNIT

THROUGH DATALINK IN UAV

SENSOR UNIT

INTEGRATION (3)



INHIBIT

LASER EMISSION

RETURN ECHOES

POWER SUPPLY

MISSION BUS 1553B

WMC

MFD

LOAM

SENSOR UNIT IRS1,2

EWS

CONTROL

PANEL UNIT

HSM/D P HSM/D C

VIDEO (OPTIONAL)

VIDEO (OPTIONAL)

ARINC 429

RS422

RS422

VDU VIDEO

WU P

OPT.

WU C

OPT.

WOW (TBD)

e.g., NH90

FLIR

VIDEO

INTEGRATION (4)



LOAM FOV Centre

Platform Instantaneous

Direction of Flight

Platform axis

HMI OPTIMISATION



Altimetric Format

2-D Format

Platform

Instantaneous

Direction of Flight

HMI2 Optimization

DETECTION PERFORMANCE M&S and TEST



MINIMUM DETECTION PERFORMANCE ANASYSIS



GROUND TEST



Clear Weather Rain

V=10km V=12.5km V=15km Light Medium Heavy

SNRP 4.90104 4.95104 5.02104 3.14104 1.83104 1.45104

SNRE 3.35104 3.80104 4.27104 2.87104 2.47104 2.13104

Predicted and Measured Signal-to-Noise Ratios

NEPDRRP

deLLAESNR

D

W

R

rTrp

2

24

EP = output laser pulse energy

A = receiver aperture

LT = transmission losses (including beam shaping)

Lr = reception losses (including optical filter)

= atmospheric extinction coefficient

dW = wire diameter

= wire reflectivity

PD = pulse duration

R = obstacle range

= beam divergence

D = initial beam diameter

NEP = noise equivalent power



Display Unit

(for test)

Control Panel Unit

Sensor Head Unit

NH-300

FLIGHT TEST



MCU

AB-212

FLIGHT TEST (2)



AB412

EH101

A129

SMALL UAV

UNMANNED HELICOPTERS

SENSOR

UNIT

CONTROL

UNIT

Future Activities



We have presented the activities carried out for integrating the Convertible Laser Designation Pod and GBU-16/GBU-24 Laser Guided Bombs on the TORNADO-IDS.

A new tailored test philosophy was adopted, consisting in a continuous interaction between ground test, flight test and simulation.

Extensive use of simulation tools allowed a full aerodynamics and safe-separation investigation, weapon aiming analysis, masking characterisation, preliminary performance estimation, laser hazards determination and laser/ballistic safety assessment.

The adopted test philosophy, introduced considerable improvements in the data gathering and analysis activities, reducing costs and saving time. Therefore an increase of efficiency was experienced, with consequent optimisation of the overall development process.

FINAL REMARKS



• Laser Obstacle Detection & Collision Avoidance is a mature

technology for low-to-mid dynamics platforms

• The LOAM systems was successfully integrated on various

helicopters and is been tested on UAVs

• A number of low, medium and high-level avionics integration

architectures have been developed

• HMI2 aspects were deeply investigated both in manned and

unmanned configurations

• Ground and flight test activities validated the obstacle

detection, classification and avoidance algorithms

• Future activities will address additional manned and unmanned

aircraft applications with mid-to-high dynamics



FINAL REMARKS (cont.)

Airborne Lasers and Integrated Weapon

Systems: Design, Development,

Test and Evaluation

INVITED PLENARY SPEACH

Questions and Discussion

[1] R. Sabatini and M. A. Richardson, RTO AGARDograph AG-300 Vol. 26: Airborne Laser Systems Testing

and Analysis: NATO Science and Technology Organization, 2010.

[2] R. Sabatini, "Tactical Laser Systems Performance Analysis in Various Weather Conditions", presented at

the E-O Propagation, Signature and System Performance under Adverse Meteorological Conditions

Considering Out of Area Operations, Sensors and Electronics Technology (SET) panel, NATO Research

and Technology Organization (RTO), Naples, Italy, 1998.

[3] R. Sabatini and G. B. Palmerini, RTO AGARDograph AG-160 Vol. 21: Differential Global Positioning

System (DGPS) for Flight Testing: NATO Research and Technology Organization, 2008.

[4] R. Sabatini, F. Guercio, and S. Vignola, "Airborne Laser Systems Performance Analysis and Mission

Planning", in RTO-MP-46 - Advanced Mission Management and Systems Integration Technologies for

Improved Tactical Operations, Systems Concepts and Integration (SCI) panel, NATO Research and

Technology Organization (RTO), Florence, Italy, 1999.

[5] R. Sabatini, F. Guercio, G. Campo, and A. Marciante, "Laser Guided Bombs and Convertible Designation

Pod Integration on Italian TORNADO-IDS", presented at the 31st Annual Symposium of the Society of

Flight Test Engineers, Turin, Italy, 2000.

[6] R. Sabatini, F. Guercio, G. Campo, and A. Marciante, "Simulation and Flight Testing for Integration of a

Laser Designation Pod and Laser Guided Bombs on Italian TORNADO-IDS", in RTO-MP-083 -

Integration of Simulation with System Testing, Systems Concepts and Integration (SCI) panel, NATO

Research and Technology Organization (RTO), Toulouse, France, 2001.

[7] R. Sabatini and M. A. Richardson, "A new approach to eye-safety analysis for airborne laser systems

flight test and training operations", Optics and Laser Technology, vol. 35, pp. 191-198, 2003. DOI:

10.1016/S0030-3992(02)00171-8

References



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[9] R. Sabatini and M. A. Richardson, "Novel atmospheric extinction measurement techniques for aerospace

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10.1016/j.infrared.2012.10.002

[10] T. Elder and J. Strong, "The infrared transmission of atmospheric windows", Journal of the Franklin

Institute, vol. 255, pp. 189-208, 1953

[11] R. M. Langer, "Report on Signal Corps Contract No. DA-36-039-SC-72351", 1957.

[12] W. E. K. Middleton, "Vision through the Atmosphere", University of Toronto Press1952.

[13] American National Standard Institute ANSI Z136.1, “Safe Use of Laser”, 1976.

[14] American National Standard Institute ANSI Z136.4, “Laser Safety Measurements and Instrumentation”,

1990.

[15] STANAG 3606 - 5th ed., "Evaluation and Control of Laser Hazards", 1991.

[16] International Electrotechnical Commission IEC 825 – (Amendment 2), “Radiation Safety of Laser

Products, Equipment Classification, Requirements and User’s guide”, 1993.

[17] Italian Regulation DL 04.12.1992 - n. 475, “Attuazione della direttiva 89/686/CEE relativa ai dispositivi di

protezione individuale”, 1992.

References



[18] Italian Standard CEI - 76/2 - 2nd ed., "Apparecchi Laser - Sicurezza delle Radiazioni, Classificazione dei

Materiali, prescrizioni e Guida per l'Utilizzatore", 76/2 - ed. II, 1993.

[19] Italian Military Safety Standard SMD-W-001 - 2nd ed., “Regolamento Interforze di Sicurezza per l’Impiego

degli Apparti Laser”, 1995.

[20] UK Ministry of Defence – Ordnance Board D/OB/2407/2, JSP390 – Military Laser Safety, 1998.

[21] R. Sabatini and M. A. Richardson, "Innovative methods for planetary atmospheric sounding by lasers", in

proceedings of AIAA Space 2008 Conference, San Diego, CA, USA, 2008. DOI: 10.2514/6.2008-7670

[22] R. Sabatini, M. A. Richardson, H. Jia, and D. Zammit-Mangion, "Airborne laser systems for atmospheric

sounding in the near infrared", in proceedings of SPIE 8433, Laser Sources and Applications, Photonics

Europe 2012, Brussels, Belgium, 2012. DOI: 10.1117/12.915718

[23] A. Gardi and R. Sabatini, "Unmanned aircraft bistatic lidar for CO2 colum density determination", in

proceedings of IEEE Metrology for Aerospace Conference 2014, Benevento, Italy, 2014

[24] R. Sabatini, E. Roviaro, and M. Cottalasso, "Development of a Laser Collision Avoidance System for

Helicopters: Obstacle Detection/Classification and Calculation of Alternative Flight Paths", in RTO-MP-

092 - Complementarity of Ladar and Radar, Sensors & Electronics Technology (SET) panel, NATO

Research and Technology Organization (RTO), 2002.

[25] R. Sabatini, A. Gardi, and M. A. Richardson, "LIDAR Obstacle Warning and Avoidance System for

Unmanned Aircraft", International Journal of Mechanical, Industrial Science and Engineering, vol. 8, pp.

62-73, 2014

References



[26] R. Sabatini, A. Gardi, S. Ramasamy, and M. A. Richardson, "A laser obstacle warning and avoidance

system for manned and unmanned aircraft", in proceedings of IEEE Metrology for Aerospace

Conference 2014, Benevento, Italy, 2014

[27] R. Sabatini, C. Bartel, A. Kaharkar, and T. Shaid, "Design and integration of vision based sensors for

unmanned aerial vehicles navigation and guidance", in proceedings of SPIE 8439, Optical Sensing and

Detection II, Photonics Europe 2012, Brussels, Belgium, 2012. DOI: 10.1117/12.922776

[28] R. Sabatini, M. A. Richardson, M. Cantiello, M. Toscano, P. Fiorini, H. Jia, et al., "Night Vision Imaging

Systems design, integration and verification in military fighter aircraft", in proceedings of SPIE 8439,

Optical Sensing and Detection II, Photonics Europe 2012, Brussels, Belgium, 2012. DOI:

10.1117/12.915720

[29] R. Sabatini, C. Bartel, A. Kaharkar, T. Shaid, L. Rodriguez Salazar, D. Zammit-Mangion, et al., "Low-cost

navigation and guidance systems for unmanned aerial vehicles - part 1: vision-based and integrated

sensors", Annual of Navigation, vol. 19, pp. 71-98, 2012. DOI: 10.2478/v10367-012-0019-3

[30] R. Sabatini, S. Ramasamy, A. Gardi, and L. Rodriguez Salazar, "Low-cost sensors data fusion for small

size unmanned aerial vehicles navigation and guidance", International Journal of Unmanned Systems

Engineering, vol. 1, pp. 16-47, 2013. DOI: 10.14323/ijuseng.2013.11

[31] R. Sabatini, M. A. Richardson, M. Cantiello, M. Toscano, and P. Fiorini, "A novel approach to night vision

imaging systems development, integration and verification in military aircraft", Aerospace Science and

Technology, 2014. DOI: 10.1016/j.ast.2013.08.021

[32] R. Sabatini, C. Bartel, A. Kaharkar, T. Shaid, and S. Ramasamy, "Navigation and Guidance System

Architectures for Small Unmanned Aircraft Applications", International Journal of Mechanical, Industrial

Science and Engineering, vol. 8, pp. 733-752, 2014

References



[33] L. Rodriguez Salazar, R. Sabatini, A. Gardi, and S. Ramasamy, "A Novel System for Non-Cooperative

UAV Sense-and-Avoid", in proceedings of European Navigation Conference 2013 (ENC2013), Vienna,

Austria, 2013

[34] S. Ramasamy, R. Sabatini, and A. Gardi, "Avionics Sensor Fusion for Small Size Unmanned Aircraft

Sense-and-Avoid", in proceedings of IEEE Metrology for Aerospace Conference 2014, Benevento, Italy,

2014

[35] R. Sabatini, T. Moore, and C. Hill, "A new avionics-based GNSS integrity augmentation system: Part 1 -

Fundamentals", Journal of Navigation, vol. 66, pp. 363-384, 2013. DOI: 10.1017/S0373463313000027

[36] R. Sabatini, T. Moore, and C. Hill, "A new avionics-based GNSS integrity augmentation system: Part 2 -

Integrity flags", Journal of Navigation, vol. 66, pp. 501-522, 2013. DOI: 10.1017/S0373463313000143

[37] R. Sabatini, T. Moore, and C. Hill, "Avionics-based integrity augmentation system for mission- and

safety-critical GNSS applications", in proceedings of 25th International Technical Meeting of the Satellite

Division of the Institute of Navigation 2012, (ION GNSS 2012), Nashville, TN, 2012, pp. 743-763

[38] K. Chircop, D. Zammit-Mangion, and R. Sabatini, "Bi-objective pseudospectral optimal control

techniques for aircraft trajectory optimisation", in proceedings of 28th Congress of the International

Council of the Aeronautical Sciences 2012 (ICAS2012), Brisbane, Australia, 2012, pp. 3546-3555

[39] W. Camilleri, K. Chircop, D. Zammit-Mangion, R. Sabatini, and V. Sethi, "Design and validation of a

detailed aircraft performance model for trajectory optimization", in proceedings of AIAA Modeling and

Simulation Technologies Conference 2012 (MST2012), Minneapolis, MN, USA, 2012. DOI:

10.2514/6.2012-4566

References



[40] S. Ramasamy, R. Sabatini, A. Gardi, and Y. Liu, "Novel flight management system for real-time 4-

dimensional trajectory based operations", in proceedings of AIAA Guidance, Navigation, and Control

Conference 2013 (GNC2013), Boston, MA, USA, 2013. DOI: 10.2514/6.2013-4763

[41] R. Sabatini, “Performance Prediction and Flight Testing of Tactical Laser Systems.” 1st NATO Tactical

Leadership Program (TLP) Conference. Invited Plenary Paper. Florenne (Belgium), January 2000.

[42] R. Sabatini, “Aviation Electro-Optical Sensor Systems.” Chosun University. Gwangju (South Korea),

October 2013.

[43] R. Sabatini, “Avionics RADAR and Electro-Optical Sensor Systems." Cranfield University Tutorial.

Cranfield (United Kingdom), March 2013.

[44] R. Sabatini, “Airborne Laser Systems Performance Modelling, Safety Analysis and flight Testing.” Italian

Air Force Production Test Pilot School Seminar. Rome (Italy), May 2006.

[45] R. Sabatini, “Laser Beam Propagation in the Atmosphere – Flight Test and Remote Sensing

Applications.” University of Rome “La Sapienza” and ITAF Research and Flight Test Centre Seminar.

Rome (Italy), February 2005.

[46] R. Sabatini, “Innovative Infrared Non-destructive Test (IR-NDT) Techniques.” University of Rome “La

Sapienza” Research Seminar. Rome (Italy), February 2004.

[47] R. Sabatini, “Laser Systems Safety Analysis for Airborne Applications: Mathematical Models and

Simulation Results.” University of Rome "La Sapienza" and ITAF Research and Flight Test Centre

Seminar. Rome (Italy), May 2001.

References



[48] R. Sabatini. “Mathematical Models and Simulation Results for Eye-safe Laser Attacks and Test/Training

Missions Planning with High Power/Low Divergence Ground Laser Systems.” Technical Report – ITAF

Research and Flight Test Centre (CSV-RSV). 2005.

[49] R. Sabatini. “Laser Beam Propagation in the Atmosphere – Flight Test and Remote Sensing

Applications.” Research Report – ITAF Research and Flight Test Centre. 2005.

[50] R. Sabatini. “AMX Night Vision Goggles (NVG) Compatible Systems Development: Final Report for the

Certification Authorities.” Technical Report – ITAF Research and Flight Test Centre (CSV-RSV). 2004.

[51] R. Sabatini, I. Bruni and E. Pederzolli. “AMX Night Vision Goggles (NVG) Compatible Systems

Development: Ground and Flight Test Campaign.” Test Report – ITAF Research and Flight Test Centre

(CSV-RSV). 2004.

[52] R. Sabatini, I. Bruni and F. Martiradonna. “AMX Night Vision Goggles (NVG) Compatible Systems

Development: NVG/Helmet, Cockpit and External Lights Modifications.” Technical Report – ITAF


[53] R. Sabatini. “Development and Initial Ground/Flight Test of the SELEX-COMMUNICATIONS Laser

Obstacle Warning System (LOAS) Technology Demonstrator.” Technical Report – ITAF Research and

Flight Test Centre (CSV-RSV). 2003.

[54] R. Sabatini. “Developed of a Laser Test Range for the Italian Air Force: Design, Development, Test and

Evaluation – Final Report.” Technical Report – ITAF Research and Flight Test Centre (CSV-RSV).

2003.

[55] R. Sabatini, A. Pellegrini and M. Locatelli. “Operational Test and Evaluation of the MB-339CD (Full

Digital) Avionics and Armament Systems – Final Operational Clearance (FOC) Version.” ITAF Research

and Flight Test Centre (CSV-RSV). 2002.

References



[56] R. Sabatini and E. Dati. “Laboratory Experimental Activities with Near Infrared Cameras, Integrating

Spheres, Piro-electric Probe Sensors and the SELEX-Communications RALM-01 Laser Warning

Receiver to Support the Development of the PILASTER Laser Test Range.” Technical Report – ITAF

Research and Flight Test Centre (CSV-RSV/RC). 2002.

[57] R. Sabatini and M. Locatelli. “MB-339CD Night Vision Imaging System (NVIS) Development:

Operational Requirements and Viable Technical Solutions.” Technical Report – ITAF Research and

Flight Test Centre (CSV-RSV). 2002.

[58] R. Sabatini. “TORNADO-ECR Night Vision Goggles (NVG) Compatible Systems Development: Final

Report for the Certification Authorities.” Technical Report – ITAF Research and Flight Test Centre (CSV-

RSV). 2001.

[59] R. Sabatini, M. Toscano and M. Cantiello. “TORNADO-ECR Night Vision Goggles (NVG) Compatible

Systems Development: Ground and Flight Test Campaign.” Test Report – ITAF Research and Flight Test

Centre (CSV-RSV). 2001.

[60] R. Sabatini and F. Martiradonna. “TORNADO-ECR Night Vision Goggles (NVG) Compatible Systems

Development: NVG/Helmet, Cockpit and External Lights Modifications.” Technical Report – ITAF


[61] R. Sabatini, F. Guercio and S. Vignola. “Laser Systems Safety Analysis for Airborne Applications:

Mathematical Models and Simulation Results.” Technical Report - ITAF Research and Flight Test Centre

(CSV-RSV). 2001.

References



[62] R. Sabatini. “Developed of a Laser Test Range for the Italian Air Force: Laser Systems Performance

Prediction, Safety Analysis and Hardware/Software Developments.” Technical Report – ITAF Research


[63] R. Sabatini and E. Dati. “Construction of a Near Infrared Laser Scatterometer and Laboratory

Measurements of the Bidirectional Reflectance Distribution Function (BRDF) of Various Materials and

Paints.” Technical Report – ITAF Research and Flight Test Centre (CSV-RSV/RC). 2000.

[64] R. Sabatini, F. Simei, M. Vitale and P. Cuppone. “Integration of the Convertible Laser Designation Pod

(CLDP) on the TORNADO-IDS Aircraft with Advanced System SW TORNADO ADA (ASSTA) version 1.”

Flight Test Report – ITAF Research and Flight Test Centre (CSV-RSV). 2000.

[65] R. Sabatini. “Developed of a Laser Test Range for the Italian Air Force: Definition of the Operational

and Technical Requirements.” Technical Report – ITAF Research and Flight Test Centre (CSV-RSV).

1999.

[66] R. Sabatini, M. Vitale, M. Mutti and P. Cuppone. “TORNADO-IDS Night Vision Goggles (NVG)

Compatible Systems Development: Ground and Flight Test Campaign.” Test Report – ITAF Research


[67] R. Sabatini, M. Vitale and F. Martiradonna. “TORNADO-IDS Night Vision Goggles (NVG) Compatible

Systems Development: NVG/Helmet, Cockpit and External Lights Modifications.” Technical Report –

ITAF Research and Flight Test Centre (CSV-RSV). 1999.

[68] R. Sabatini, S. Vignola and F. Guercio. “Mathematical Models and Simulation Tools for Eye-safe Laser

Attacks and Test/Training Missions Planning with Airborne Laser Systems.” Technical Report – ITAF


References



[69] R. Melosi and R. Sabatini. “Laboratory Measurements of PAVEWAY Laser Guided Bomb Seeker-heads

Minimum Detectable Power Densities.” Technical Report – ITAF Research and Flight Test Centre (CSV-

RSV/RC). 1997.

[70] R. Sabatini. “Mathematical Models for Calculating the Range Performance of the THALES-Optronics

Convertible Laser Designation Pod (CLDP) in Various Operational Scenarios and Weather Conditions.”

Technical Report – ITAF Research and Flight Test Centre (CSV-RSV). 1995.

[71] Kneizys F.X., Shuttle E.P., Abreau L.W., Chetwynd J.H., Anderson G.P., Gallery W.O., Selby J.E.A., and

Clough S.A., “Users Guide to LOWTRAN 7”. Air Force Geophysical Laboratory Report AFGL-TR-88-

0177. Hansom AFB (MA). 1988.

[72] Hudson R.D., “Infrared Systems Engineering”. Wiley & Sons. 1969.

[73] Strohbehn J.W. et al., “Laser Beam Propagation in the Atmosphere“. Topics in Applied Physics Series –

Vol. 25. Sprienger-Verlag. 1978.

[74] Keith G.G., Otten L. J., and Rose W.C., “Aerodynamic Effects”. ERIM-SPIE IR&EO Systems Handbook

(Vol. 2 – Chapter 3). Second Printing. 1996.

[75] La Rocca A.J. and Turner R.E., “Atmospheric Transmittance and Radiance: Methods of Calculations”.

Environmental Research Institute of Michigan Ann Arbor. 1975.

[76] Weichel H., “Laser Beam Propagation in the Atmosphere”. SPIE Optical Engineering Press. Second

Printing. 1990.

[77] Langer R.M., Signal Corps Report n° DA-36-039-SC-72351. May 1957.

References



[78] R. Sabatini, M. A. Richardson, A. Gardi and S. Ramasamy, “Airborne Laser Sensors and Integrated

Systems.” Progress in Aerospace Sciences. 2015.

[79] R. Sabatini, F. Cappello, S. Ramasamy, A. Gardi and R. Clothier, “An Innovative Navigation and

Guidance System for Small Unmanned Aircraft using Low-Cost Sensors.” Aircraft Engineering and

Aerospace Technology, 2015.

[80] F. Cappello, R. Sabatini, S. Ramasamy, "Low-Cost Multi-Sensor Data Fusion for Unmanned Aircraft

Navigation and Guidance." In press, Journal of Science and Engineering Investigations, Vol. 4, Issue

43, August 2015.

[81] A. Gardi and R. Sabatini, " Design and Development of a Novel Bistatic DIAL Measurement System for

Aviation Pollutant Concentrations." International Journal of Science and Engineering Investigations, Vol.

4, Issue 41, June 2015. http://www.ijsei.com/papers/ijsei-44115-10.pdf

[83] R. Sabatini, A. Gardi and S. Ramasamy, “A Laser Obstacle Warning and Avoidance System for

Unmanned Aircraft Sense-and-Avoid.” Applied Mechanics and Materials, Vol. 629, pp. 355-360, October

2014. DOI: 10.4028/www.scientific.net/AMM.629.355

[84] A. Gardi, R. Sabatini and S. Ramasamy, “Bistatic LIDAR System for the Characterisation of Aviation-

Related Pollutant Column Densities.” Applied Mechanics and Materials, Vol. 629, pp. 257-262, October

2014. DOI: 10.4028/www.scientific.net/AMM.629.257

References



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