IHS Jane’sAll the World’s AircraftUnmanned

2012-2013

Editor: Mark Daly

ISBN -13 978 0 7106 3003 2

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Contents

Alphabetical list of Advertisers .......................................................................................... [4]

Executive Overview ............................................................................................................. [7]

Users’ Charter ...................................................................................................................... [12]

Acknowledgements ............................................................................................................ [13]

Glossary ................................................................................................................................. [14]

How to use ........................................................................................................................... [30]

UNMANNEDAERIAL VEHICLES ........................................................................................... 1

AERIAL TARGETS ................................................................................................................. 281

POWER PLANTS .................................................................................................................... 359

CONTROL ANDCOMMUNICATIONS .............................................................................. 387

LAUNCHANDRECOVERY SYSTEMS ............................................................................... 415

Contractors ........................................................................................................................... 431

Alphabetical index ............................................................................................................... 441

Manufacturers’Index .......................................................................................................... 449

© IHS Global Limited 2012 IHS Jane’s All the World’s Aircraft: Unmanned 2012-2013[3]

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Boeing Phantom RayType: Technology demonstrator.Development: The company‐funded Phantom Ray project was launchedby Boeing's Phantom Works in October 2008, although not announcedpublicly until 8 May 2009. In essence, it resumes work performed on theX‐45C, the ultimate X‐45 variant developed by Boeing as its entrant in theformer joint‐service J‐UCAS programme. In October 2004, Boeingreceived a USD767 million DARPA contract for three X‐45C prototypes,the first of which should have had its public roll‐out on 2 March 2006.However, this was pre‐empted by termination of the J‐UCAS programme.The aircraft never flew and, along with the uncompleted secondprototype, was placed in storage.As announced, the X‐45C will now serve as the basis for the Phantom

Ray, as a testbed for advanced technologies. A 10‐flight flyingprogramme is envisaged over a period of about six months, supportingmissions that may include ISR, SEAD, hunter/killer and electronic attack.Also tested will be autonomous in‐flight refuelling — the X‐45C designincluded space provision in the rear fuselage for a refuelling receptacle,and this capability was to have been explored with the third X‐45C.

Description: Airframe: Stealthy, ‘arrow‐head' flying wing design withabout 55° leading‐edge sweepback and W‐planform trailing‐edge;blended fuselage, with internal bay(s); buried turbofan engine withserpentine dorsal intake; no vertical tail surfaces. Retractable tricyclelanding gear. All‐composites construction.

Mission payloads: Specific to individual test flights; details not yetannounced.

Guidance and control: Fully autonomous, including taxi, take‐off andlanding phases.

Launch: Conventional and autonomous wheeled take‐off.Recovery: Conventional and autonomous wheeled landing.Power plant: A and B: One approx 51.2 kN (11,500 lb st) General

Electric F404‐GE‐102D non‐afterburning turbofan.(A: X‐45C, B: Phantom Ray)

Phantom Ray

Dimensions, External

Overall, length..........................................................................10.97 m (36 ft 0 in)Wings, wing span....................................................................15.24 m (50 ft 0 in)

Weights and Loadings

Weight, Max T-O weight...................................................... 16,556 kg (36,499 lb)Performance

Altitude, Operating altitude...................................................12,190 m (40,000 ft)Power plant........................................................................................ 1 × turbofan

Status: Design development continued in 2009 and construction wascompleted in 2010. Phantom Ray was shipped by NASA Boeing 747Shuttle Carrier Aircraft fromSt Louis to Edwards Air Force Base, Californiain December 2010. The Phantom Ray (the successor to the X‐45) took itsmaiden flight on 27 April 2011 at NASA's Dryden Research Center atEdwards Air Force Base, Calif, US.

Contractor: The Boeing Company, Boeing Defense, Space and SecuritySt Louis, Missouri.

Boeing ScanEagleType: Endurance mini‐UAV.Development: ScanEagle is a variant of the Insitu SeaScan , built under a15‐month original agreement announced on 11 February 2002 and beingdeveloped separately by Boeing's Phantom Works in collaboration withInsitu. Boeing equipped the prototype air vehicle using its own systemsintegration, communications and payload technologies. It made its first,remotely controlled, flight in April that year and its first autonomous flighton 19 June 2002, following a pneumatic catapult launch. Made atBoeing's Boardman, Oregon, facility, the latter flight lasted 45 minutes,flying a preprogrammed course at a maximum altitude of 457 m (1,500 ft).A number of test waypoints were completed using DGPS, as well as theability to make real‐time updates to the flight plan from the GCS. The UAVwas retrieved using the patented Insitu Skyhook technique.In late January 2003, the ScanEagle made five flights, totalling more

than 20 hours, as a communications relay platform in a US Navy exercise('Giant Shadow') in the Bahamas. Small‐scale production has ensued, asdescribed under the 'Status' heading below. Boeing has quoted potentialapplications as including persistent ISR, US Navy SEAL operationsescort, low‐cost sea lane protection, sentinel and sentry guard duty,battlefield communications relay network node, and convoy support.In June 2003, Boeing and Insitu signed a longer‐term contract to

continue their collaboration and begin production of the ScanEagle, threeA models of which are understood to have been completed at that time.On 15 September 2003, Boeing announced that in recent flights two ofthese had been launched simultaneously, the first completing a 15.2‐hourendurance flight while, in its latter stages, being monitored by the other,which relayed real‐time video to the GCS. At that time the three A modelshad completed a total of 70 sorties. Persistent ISR was demonstratedbetween December 2003 and June 2004 during US Joint ForcesCommand's exercise 'Forward Look III', providing imagery and targetingto UAVs and other airborne assets, ground stations, command centresand ships at sea. In August 2004, a Boeing‐owned aircraft completed a 16hour 45 minute flight off the US west coast in Puget Sound, Washington,after launch from a fishing boat, thought to be the longest flight up to thattime by a UAV launched and retrieved at sea; and in December 2004another ScanEagle successfully demonstrated high‐speed wirelesscommunications relay (voice and video).ScanEagles have participated in a number of military demonstrations,

experiments and exercises, some of which are described under the'Status' heading below.

Description: Airframe: Mainly cylindrical fuselage; mid‐mounted,sweptback wings with tall endplate fins and rudders; pusher engine.Modular internal avionics bay. No landing gear. Folding‐wing version forair launch under study in 2006.

X‐45C underside detail (IHS Global Limited/Patrick Allen) 1097072

X‐45C mockup at the 2004 Farnborough International Air Show(IHS Global Limited/Patrick Allen) 1097073 ScanEagle handling (USMC) 1151558

214 Unmanned aerial vehicles > United States > Boeing Phantom Ray – Boeing ScanEagle

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Saeghe 2: More advanced version. Telecommand and telemetry linksbetween air vehicle and GCS; GPS navigation. Same airframe as Saeghe1. Specification data apply to this version.

Saeghe 2

Dimensions, External

Overall

length....................................................................................2.81 m (9 ft 2¾ in)height....................................................................................0.70 m (2 ft 3½ in)

Fuselage, length.......................................................................2.66 m (8 ft 8¾ in)Wings, wing span.....................................................................2.60 m (8 ft 6¼ in)

Weights and Loadings

Weight, Max launch weight............................................................. 60 kg (132 lb)Performance

Altitude, Service ceiling...........................................................3,355 m (11,000 ft)Speed, Max level speed............................................135 kt (250 km/h; 155 mph)Radius of operation, max, mission.......................... 27 n miles (50 km; 31 miles)Endurance...................................................................................................45 minPower plant................................................................................1 × piston engine

Status: In production and service.As of May 2011, the Fars News Agency announced that the Iranian

Army plans to increase the range of its home‐madeUAS and also equip itsreconnaissance unmanned aircraft with missile‐launching systems,according to an Iranian commander.

Speaking to the Fars News Agency, Lieutenant Commander of theIranian Army’s Self‐Sufficiency Jihad, Rear Admiral Farhad Amiri referredto Iran’s capability in designing and building different types of unmannedaircraft, and explained that UAS are usually used for collecting intelligence

and information, wiretapping, photography and shooting footage, butthey can also be used for other purposes on the basis of their power andcapabilities. “For example, in naval missions we need long‐range UAS orwe need the unmanned aircraft which have the capability to launchmissiles, each of which needs its own special technology. Of course, allthese (projects) are on our working agenda in a move to satisfy our needsduring the next two years,” he added.

SOURCE IS UASVISION.COM from FARS NEWS AGENCYCustomers: Iranian armed forces. Possibly also exported.

Contractor: Qods Aviation IndustriesTehran.

IsraelRafael Black Sparrow

Type: Air‐launched ballistic target.Development: The Black Sparrow programmewas funded jointly by the USBallistic Missile Defense Organization (BMDO) and the Israeli MissileDefence Organisation (IMDO) in 1996 in order to develop a high‐fidelity,threat‐representative ballistic target for Israel's Theatre Missile Defence(TMD) requirements. It simulates the Scud‐B ballistic missile and has fulltelemetry and test range safety capabilities.

Description:Mission payloads:Modular warhead simulator, which can beadapted to emulate various warhead threats such as high explosive andbulk chemical for lethality analysis.

Guidance and control: The target simulates the trajectory (velocityand altitude profiles) and the thermal and RCS signatures of the Scud‐Bballistic missile, being able to simulate such re‐entry manoeuvres asballistic and barrel roll. Its telemetry supports full data for interceptor testanalysis.

Launch: Air‐launched.Recovery: Expendable. Design incorporates a fully redundant flight

termination system to meet the range safety requirements governingmissile interceptor tests.

Black Sparrow

Dimensions, External

Overall

length...................................................................................4.85 m (15 ft 11 in)width...................................................................................0.526 m (1 ft 8¾ in)

Weights and Loadings

Weight, Max launch weight..................................................... 1,275 kg (2,810 lb)

Status: Black Sparrow has been proven in missile defence engagementscenarios with the Israeli Arrow weapon system. By 2005 it was fullydeveloped and market‐ready, having successfully completed a series offly‐out and interception tests. The Black Sparrow was selected by theFrench DGA for testing the SAMP/T system.

Contractor: Rafael Armament Development Authority LtdHaifa.

ItalySelex Galileo Locusta

Type: Expendable target or subtarget.

Development: Described as “a mini‐UAV secondary aerial target”,development of the Locusta began in 2004 as a 'live' target for tacticalmissiles and air defence artillery. It was designed to be deployed either asa subtarget payload for the Mirach 100/5 target or, alternatively, as astand‐alone target launched fromother types of host aircraft. In the formerapplication, one Locusta is carried under each wing of the Mirach parenttarget. Locusta can simulate incoming threats from both surface‐to‐airand air‐to‐air missiles. It can also be configured for such operational rolesas decoy and jamming.

Description: Airframe: Cylindrical body with ogival nosecone and ventralengine air intake. Four front‐mounted fins in cruciform configuration andfour larger tailfins in X configuration. Mainly carbon fibre construction.

Mission payloads: Modular payloads include radar cross‐sectionaugmentors (S‐band and Ku‐band) and IR augmentors.

Guidance and control: Flight profiles are mainly autonomous, butground controller can monitor the mission and, if the target survives a

The Qods Saeghe 2 in flight 0087738

The Black Sparrow air‐launched target (Rafael) 1122521 Black Sparrow on an Israeli Air Force F‐15 (Rafael) 1128968

Model of Locusta wing‐mounted on a Mirach 100/5(IHS Global Limited//Patrick Allen) 1327047

308 Aerial targets > Iran – Italy > Qods Saeghe – Selex Galileo Locusta

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POWER PLANTS

AustriaRotax 582

Type: In‐line water‐cooled two‐cylinder two‐stroke.Description: Rotary‐valve piston engine with electronic dual ignition,

integrated water pump and thermostat, exhaust system, carburettors andrewind starter. Effective compression ratio 5.75:1. Fuel grade RON 91(leaded or unleaded), in 50:1 mixture with super two‐stroke motor oil.Weight quoted includes twin carburettors and exhaust system. TBO is300 hours.

Specifications

Dimensions

Bore...............................................................................................76 mm (2.99 in)Stroke............................................................................................64 mm (2.52 in)Capacity.............................................................................. 580.7 cc (35.44 cu in)

Weights

Dry weight.................................................................................... 36.0 kg (79.4 lb)Performance

T‐O rating (6,500 rpm)...............................................................48.0 kW (64.4 hp)Max rpm........................................................................................................6,800Generator performance.........................................................155 W at 6,000 rpmVoltage............................................................................................................13.5

Status: In service, remains in production (2010). UAV applications haveincluded the Gnat 750, Prowler II, Sperwer A and Ugglan.

Contractor: BRP‐Rotax GmbH & Co KGGunskirchen.

Rotax 912Type: Air/liquid‐cooled, horizontally opposed four‐cylinder four‐stroke.Development: Introduced 1988.Description: This small piston engine has air‐cooled barrels and

liquid‐cooled heads, electric starting, dry sump forced lubrication and acompression ratio of 9.0:1 (912 UL) or 10.5:1 (912 S and ULS). Ignition isby breakerless dual‐condenser discharger. The engine has a 2.27:1reduction gear; a 2.43:1 reduction gear is optional. Fuel is leaded orunleaded Mogas (RON 90) or Avgas 100LL. Weights quoted includecarburettors, intake silencer, exhaust system and gearbox. TBOincreased from 1200 hours to 1500 hours in 2003.

Specifications

Dimensions

Bore: 912 UL, A and F...............................................................79.5 mm (3.13 in)912 S and ULS..........................................................................84 mm (3.31 in)

Stroke: all......................................................................................61 mm (2.40 in)Capacity: 912 UL, A and F............................................... 1,211.2 cc (73.91 cu in)912 S and ULS................................................................ 1,352 cc (82.50 cu in)

Weights

Dry weight: 912 UL, A and F...................................................... 55.4 kg (122.1 lb)912 S and ULS....................................................................... 56.6 kg (124.8 lb)

Performance

Max (5 min) rating at 5,800 rpm

912 UL, A and F.....................................................................59.6 kW (79.9 hp)912 S and ULS.......................................................................73.5 kW (98.6 hp)

Normal operation at 5,500 rpm

912 UL, A and F.....................................................................58.0 kW (77.8 hp)912 S and ULS.......................................................................69.0 kW (92.5 hp)

Max rpm........................................................................................................5,800Generator performance at 5,500 rpm..........................................................250 WVoltage............................................................................................................13.5

Status: In service and remains in production (2010). Applications haveincluded I‐Gnat, Perseus, Predator, Raptor Demonstrator and TheseusUAVs.

Contractor: BRP‐Rotax GmbH & Co KGGunskirchen.

Rotax 914Type: Air/liquid‐cooled, horizontally opposed, turbocharged four‐cylinder

four‐stroke.Development: The 914 is essentially a turbocharged version of the Rotax

912.Description: Generally as for Rotax 912, except that 2.43:1 reduction gear

is standard. Weight quoted includes suspension frame, exhaust systemand gearbox.

Features include automatic wastegate control; dry sump forcedlubrication with separate oil tank; automatic adjustment by hydraulic valvetappet; twin carburettors; dual electronic ignition; electric starter;propeller speed reduction unit; engine mount assembly; air intake system;and exhaust system. Compression ratio 9.0:1. Leaded or unleadedMogas (RON 95) or Avgas 100LL. TBO increased from 1000 hours to 1200hours from 2003.

The 48 kW (64.4 hp) Rotax 582 UL (BRP-Rotax)) 1195373

The Rotax 912 UL flat‐four (BRP-Rotax) 1195374

The Rotax 914 UL flat‐four (BRP-Rotax) 1195375

359

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SwitzerlandRUAG OPATS

Type: Automatic landing positioning sensor.Development: The Object Position and Tracking System (OPATS ‐

previously known as RAPS) was developed as a major element of a UAVlanding system. As such, it was designed to alleviate the high cost oftraining ground‐based pilots and to improve the safety and reliability ofUAV landing procedures. OPATS was originally developed for use with theRanger AV and can facilitate the automatic and safe landing of ‘any' typeof UAV, irrespective of its size.

Description: OPATS consists of a motorised sensor platform mounted on atripod, an electronic unit and a battery pack platform. It is deployed inclose vicinity to the landing area, remote from the GCS. It can be fullyoperated from the GCS, connected by fibre optic video and computercommunications links. The air vehicle is equipped with two parallel,lightweight, 60 mm (2.4 in) diameter passive retro reflectors mounted onthe air vehicle's nose or wings. A laser radar and TV camera on the OPATSplatform point towards the approaching UAV, illuminating it by IR lightpulses, which are echoed back to the OPATS by the retroreflectors. Fromthese echoes, OPATS determines UAV distance and azimuth or elevationangles, while the TV camera gives the operator visual information. Duringthe landing approach, OPATS continuously measures UAV positions (at a‘high rate' of 40 m/s) and transmits them to the GCS, where they are usedas feedback in the automatic landing servo control loop; this enables theUAV to be precisely guided on to a predetermined landing point. OPATSoperating modes comprise ‘manual point’ (manual pointing for search ortracking purposes), ‘auto point’ (GCS directed pointing), ‘scan’ (anautomatic function over a 200 × 120 mrad window), ‘auto track’ (postacquisition automatic tracking) and ‘standby’ (system powered up, nolaser emission).

Specifications

Weights

Weight, incl batteries.....................................................................142 kg (313 lb)Performance

Measuring range: in azimuth.....................................................300° (5,236 mrad)in elevation....................................................−35 to +55° (−611 to +960 mrad)

Distance: tracking mode............................................35–3,500 m (115–11,500 ft)search mode........................................................150–3,500 m (492–11,500 ft)

Position measurementinterval..........................................................................................................40 msAngle measurementsaccuracy...................................................................... ±1 mrad (0.5 mrad typical)Distance measurementsaccuracy..........................................................................................±1.5 m (4.9 ft)Temperature: operating.........................................−35 to +60°C (−31 to +140°F)storage...............................................................−35 to +71°C (−31 to +160°F)

Power supply..............................................................................24 V DC (battery)Operating time........................................................6–20 h (single battery charge)Lateral object speed........................................................................... 20°/s (max)Lateral object acceleration...........................................................................5°/s2Object radial speed........................... distance accuracy requirement dependent

Status: Over time, the OPATS automatic landing positioning sensor hascontinued to be promoted. OPATS is used with a ‘diverse range of UAVsworldwide' (including RUAG's Ranger surveillance AV) and as of 2010, 90OPATS systems were in service with more than 20 different end‐users.

Contractor: RUAG AviationEmmen.

United Arab EmiratesAdcom ADCOM‐3D

Type: UAV Flight Control Unit (FCU).Description: Adcom describes the ADCOM‐3D FCU as making use of the

‘latest electronic technology' and ‘advanced digital processingtechniques' for control and measurement. System features include:• altitude and heading reference correction (using a strap‐down IMUwith GPS and 3‐axis magnetometer feedback)• onboard flight data recording• stabilisation and control of the host vehicle's angular movements• an automatic navigation capability• independent angular measurement on all three axes• measurement of both static and dynamic pressure• the ability to change pre‐programmed flight plans at ‘any stage in theflight'• automatic take‐off and landing facilities (with the latter making use ofGPS and an optional laser altimeter)• an automatic recovery function• fail‐safe functionality in case of uplink interruption• fault identification• automatic guidance to a pre‐set landing point in case of emergency• sensor thermal compensation• use of an eCAN bus configuration to facilitate interfacing with servos, atransceiver unit, a laser altimeter and ‘other peripherals'• a 3‐axis magnetometer interface• the availability of two RS‐232 serial ports• control of up to 16 payloads.

Specifications

Dimensions

Length......................................................................................... 200 mm (7.87 in)Width........................................................................................... 110 mm (4.33 in)Depth............................................................................................ 50 mm (1.97 in)

Weights

Unit................................................................................................. 0.9 kg (1.98 lb)Performance

Angular speed........................................................................±150°/s (maximum)Acceleration................................................................................. ±2 g (maximum)Power supply................................9‐18 V (300 mA with over voltage and polarity

protection)Operating temperature.................................................................–20°C to +70°C

Status: Over time, ADCOM‐3D has continued to be promoted.Contractor: Adcom Systems

Abu Dhabi.

Adcom ADNAV GCSType: UAV GCS.Development: Jane's Unmanned Aerial Vehicles and Targets first became

aware of the Adcom ADNAV GCS during July 2009.Description: Manned (in baseline form) by two operators, the Adcom

ADNAV GCS tracks, commands, controls and communicates with AVsand their payloads. As such, a single ADNAV GCS is able tosimultaneously control up to seven AVs and an integral ‘enhanced mission

A general view of the OPATS electronic unit (left) and the system'stripod‐mounted sensor (RUAG) 1329021

A close‐up of the OPATS system's retro‐reflectors mounted in thenose of a UAV (RUAG) 1329019

Air Target Sweden Marque and Mini Marque – Adcom ADNAV GCS < Switzerland – United Arab Emirates < Control and communications 401

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