AUSTRALIA

Australian Centre for Field Robotics

The University of Sydney
The Rose Street Building J104
Sydney
New South Wales 2006
Tel: (+61 2) 93 51 71 26
Fax: (+61 2) 93 51 74 74
e-mail: info@acfr.usyd.edu.au
Web: http://www.acfr.usyd.edu.au

Products:
    UAVs

AeroSpace Technologies of Australia Pty Ltd (ASTA)

Private Box 226
Port Melbourne
Victoria 3207
Tel: (+61 3) 96 47 32 87
Fax: (+61 3) 96 46 22 53

Products:
    Aerial targets

Boeing Australia Ltd

363 Adelaide Street
Brisbane
Queensland 4000
Tel: (+61 2) 62 70 07 37
Fax: (+61 2) 62 70 07 47
Web: http://www.boeing.com.au

Products:
    UAVs  

ADI Jandu

Type    

Jet-powered experimental UAV.

Development           

Being developed, jointly with Global UAV Organisation (GUAVO) of Western Australia, under June 2005 technology demonstration contract from Australian Defence Science and Technology Organisation (DSTO). Engine and airframe by GUAVO. To be evaluated as potential high-speed surveillance UAV.

Description           

Airframe           

Torpedo-shaped fuselage, tapered at rear with engine pod mounted above; low-mounted, constant chord non-swept wings; twin fin and rudder tail unit. Composites construction.

Mission payloads           

EO/IR sensor probable.

Guidance and control           

Reportedly by a biomimetic (insect vision) system. Expected to include GPS waypoint navigation.

Launch           

Conventional wheeled take-off probable.

Recovery           

Conventional wheeled landing probable.

Specifications (provisional)           

Power plant

Dimensions

Weights

Performance

Status           

Under development for maiden flight in 2006.

Contractor           

ADI Limited

Mawson Lakes, South Australia.

BAE Systems Australia

Melbourne Office

677 Victoria Street
Abbotsford
Victoria 3067
Tel: (+61 3) 92 08 05 55
Fax: (+61 3) 92 08 05 08
e-mail: brad.yelland@baesystems.com
Web: http://www.baesystems.com

Products:
    UAVs

BAE Systems Kingfisher

Type  

UAV technology demonstrator.

Development           

BAE Systems Australia collaborated with the University of Sydney's Australian Centre for Field Robotics (ACFR) in 1999, in a three-year R & D programme known as ANSER (Autonomous Navigating and Sensing Experimental Research), to develop and demonstrate technologies to enhance network-centric warfare and autonomous UAV operations. Known as SLAM (Simultaneous Localisation and Map-building), these technologies were aimed at guidance of, and distributed data fusion from, multiple air vehicles.Potential applications include tactical and combat UAVs, reconnaissance, surveillance, avionics architecture and systems integration. The early air vehicle testbeds used in the programme were named Brumby; developed versions have the name Kingfisher.

Description           

Airframe           

Brumby Mk 3: Mid-mounted, clipped-delta wings with two-segment trailing-edge elevons; twin inset fins and rudders; pusher engine; fixed tricycle landing gear. Construction of composites and aluminium alloy. Rectangular canards.

Kingfisher Mk 1: Inherits fuselage (minus canards), power plant and landing gear of Brumby Mk 3, allied to new, constant chord, unswept, high-lift wing and conventional twin-boom tail assembly.

Kingfisher Mk 2: Combines wings,tail assembly and landing gear of Mk 1 with uprated engine and new box-section fuselage having solid nose and rectangular ventral cutout for sensor turret.

Mission payloads           

Modular, interchangeable payloads (any two from range of TV camera, laser range-finder or scanning MMW radar). Mounted in removable nose section of Brumby Mk 3/Kingfisher Mk 1; in ventral sensor turret on Kingfisher Mk 2.

Guidance and control           

BAE Systems GCS, incorporating ISR management system (latter co-developed with CDL Systems, Canada). Air vehicle is manually controlled during take-off and landing phases; fully autonomous with INS/GPS navigation, guidance and control during normal flight. UHF command datalink; S-band air-to-ground and air-to-air datalink; preprogrammed and in-flight navigation waypoint uplink. Electrical power supply from 250 W air vehicle generator or batteries. Fully decentralised, multiple-sensor, single- and multiple-platform, multiple-target tactical picture compilation (tracking); SLAM tactical picture compilation and navigation without GPS.

System composition           

Four air vehicles, each carrying up to four terrain and inertial sensors; mission planning and control station; air-to-ground and air-to-air communications links; ground support equipment.

Launch           

Conventional wheeled take-off.

Recovery           

Conventional wheeled landing.

Variants           

Brumby Mk 1           

Remotely piloted aircraft developed by students at the University of Sydney; first flight November 1997. Subsequently adopted as ANSER programme prototype and used for communications relay.

Brumby Mk 2           

Single-payload, intermediate airframe design, built by the ANSER team for sensor testing. First flight April 2000.

Brumby Mk 3           

Multipayload ANSER vehicle; bulged, transparent forward fuselage and rectangular, mid-mounted canard surfaces; autonomous flight control system. First flight early 2001. Developed as a research platform for operation in harsh environments, and to demonstrate low-cost rapid prototyping for UAV airframe design.

Kingfisher Mk 1           

Further refinement of Brumby Mk 3. Test-flown at Kingaroy, Queensland, in May 2005.

Kingfisher Mk 2           

Developed version, of different configuration. Substantial increases in payload and endurance capability.

Specifications           

(A: Brumby Mk 3, B: Kingfisher Mk 1, C: Kingfisher Mk 2)           

Power plant

Dimensions

Weights

Performance

Status           

In August 2002, successful completion was announced of a series of flight tests involving multiple UAVs (two Brumby Mk 3s) in the performance of fully decentralised picture compilation. They were remotely piloted over terrain at the Sydney University test range at Marulan, New South Wales, where they sensed a number of artificial ground features, processed the data on board and built up a real-time picture of ground activity without requiring to use a central processing facility. The ANSER team aimed to create a four-UAV testbed facility to develop and demonstrate decentralised data fusion technologies even further. Development of Kingfishers is continuing.

Contractor           

BAE Systems Australia

Abbotsford, Victoria.

Codarra Advanced Systems

BAE Systems Building
Fernhill Park
Canberra Bruce
ACT 2627
Tel: (+61 2) 62 64 01 00
Fax: (+61 2) 62 64 01 99
e-mail: information@codarra.com.au
Web: http://www.codarra.com.au Products:
    UAVs

Codarra Avatar

Type           

Man-portable tactical surveillance UAV.

Development           

Developed originally as a private venture, at first under project designation CX-1 and based on existing foreign design; first flight in this form March 2000. Reflown after much redesign in 2002, funded by grant from Australian government. Intended as low-cost system for real-time imagery acquisition.

On 6 July 2004, an Avatar made the first fully autonomous flight, in restricted airspace, at the Australian Army Graytown Range, guided by an intelligent software program known as Jack, developed by Melbourne-based Agent Oriented Software. Given the option of two waypoints about 1 km apart, the Agent software selected the shorter of the two routes and directed the UAV's auilot to the nearer location.

Codarra has also developed an unmanned ground vehicle known as Silverback.

Description           

Airframe           

High-wing, T-tailed powered sailplane configuration; no landing gear. Composites (CFRP) construction. Expected life of about 100 flights.

Mission payloads           

Small CCD video camera originally, with selectable 2.434 or 2.411 GHz real-time imagery downlink. One or two switchable, high-resolution digital stills cameras now standard; zoom in/out, power on/off and shutter release can be operated either automatically, as waypoint events, or manually via GCS. Alternatively, imagery can be stored on board for downloading on completion of mission. Onboard cameras permit the use of seven CCTV focal lengths from 3.6 to 16 mm. Future payload options include radio relay, thermal imaging, target acquisition and laser rangefinding.

Guidance and control           

Flight path and altitude preprogrammed by entering up to 100 waypoints into a notebook computer. GPS-based navigation. Modem link (range 5.4 n miles; 10 km; 6.2 miles) permits in-flight reprogramming. Windows-based software warns operator if operating boundaries are exceeded. Electronic map option on computer. Downlinked imagery can be recorded on same computer or on an external video recorder. GCS is housed in a water-resistant container.

Transportation           

Portable by one person. Dismantles into two Pelican 1700 cases or standard Australian Army backpacks. Can be set up and launched in less than 10 minutes.

Launch           

Hand launch.

Recovery           

Manual (belly landing) or parachute recovery.

Specifications           

Power plant

Dimensions

Weights

Performance

Status           

Five prototypes acquired by Australian Army in 2001 for test and evaluation; further 13 production aircraft reportedly acquired later. Was used by ADF Special Forces in East Timor as part of UN force supporting transition to independence.

Customers           

Australian Defence Force (Army); Defence Science and Technology Organisation (DSTO); Queensland University of Technology.

Contractor           

Codarra Advanced Systems

Canberra.

V-TOL Aerospace i-CopterType           

Helicopter UAV.

Development           

This company was established in January 2005, although activities had begun some four months earlier and the first of two prototype unmanned helicopters was flown in late 2004. The i-Copter made its public debut at the Australian air show at Avalon in March 2005, the Seeker version being known at that time as the Series 2. A family of three versions was said to be planned, of which two have since emerged, the third being understood to be an enlarged variant of the Seeker with twin turboshaft engines. Plans were to certify the UAVs for use in controlled airspace, for a range of applications such as agricultural/farm patrol and police work.

Description           

Airframe           

Four-blade main and two-blade tail rotors. Lightweight metal and composites fuselage/tailboom. Metal twin-skid landing gear.

Mission payloads           

Day/night sensors such as CCD TV, IR or thermal imagers and laser rangefinder/designators can be mounted on a two- or three-axis, gyrostabilised gimbal in the nose or under the fuselage. Other types of payload can be carried on side-mounted pylon; or in belly-mounted tanks.

Guidance and control           

Autonomous or semi-autonomous, using secure radio or satcom, and data, links for real-time sensors. Typical GCS comprises power supply, link control and GPS modules; datalink antenna; remote video monitor; Ethernet hub; back-up batteries; and two personnel (air vehicle and payload operators).

Launch           

Conventional helicopter take-off.

Recovery           

Conventional helicopter landing.

Variants           

i-Copter Seeker           

Smallest member of family; first flight early March 2005.

i-Copter Phantom           

Larger and more versatile version; under development.

Specifications           

(A: Seeker, B: Phantom)           

Power plant

Dimensions

Weights

Performance

Status           

Seeker version believed developed and available; development of Phantom continuing.

Contractor           

V-TOL Aerospace Pty Ltd

Rocklea, Queensland.

Boeing Australia Ltd

363 Adelaide Street
Brisbane
Queensland 4000
Tel: (+61 2) 62 70 07 37
Fax: (+61 2) 62 70 07 47
Web: http://www.boeing.com.au

Products:
    UAVs

BRAZIL

Aeronaves e Motores SA

Avenida das Industrias 1210
90200-290 Porto Alegre
Rio Grande do Sul
Tel: (+55 51) 371 16 44
Fax: (+55 51) 371 16 55
e-mail: jjotz@aeromot.com.br
Web: http://www.aeromot.com.br

Products:
    Aerial targets

BULGARIA

Aviotechnica Ltd

Assenovgradsko shosse Street
PO Box 423
BG-4000 Plovdiv
Tel: (+359 32) 65 85 60
Fax: (+359 32) 68 25 40
e-mail:aviotechnica@abv.bg
Web: http://promo.abv.bg/new_sms.html

Products:
    UAVs
    Aerial targets

Aviotechnica Yastreb-2

Type           

Recoverable aerial target.

Development           

The Yastreb (Sparrowhawk) is a ground-launched aerial target system for anti-aircraft artillery, air-to-air missile and surface-to-air missile weapons training. After developing various earlier aerial drones (RUM-2MB, M-200 Siniger, UTRUM-2 and P-200) for the armies of former Warsaw Pact countries, Aviotechnica began development of the Yastreb in 1972. Series production began with the Yastreb-1 in 1981 and continued with the Yastreb-2 family from 1983. Until 1990, the majority of the 1,500 or so produced to date were for the former USSR.

Description           

Airframe           

Tapered mid-wing monoplane with circular-section fuselage, V tail and two rectangular ventral fins. NACA 64A series wing aerofoil section. Steel tube fuselage frame with duralumin and composites skin; wings and tail surfaces have metal spars. Ailerons located at approximately mid-span of wings; fixed tab on each outer wing trailing-edge; tail surfaces have inset ruddervators. No landing gear, but underfuselage reinforced to absorb landing impact.

Mission payloads           

A variety of internal devices can be installed in the fuselage, including miss-distance indicators, flares and radar reflectors. There are external attachments for towed target bodies or banner targets. A single infra-red source can be mounted under the port wing.

Guidance and control           

Three-channel auilot controls engine throttle, ailerons and ruddervators and stabilises air vehicle airspeed, height and course. Flight control can be by direct remote piloting from the ground, or automatic via the auilot with provision for overriding by the ground controller. Telemetry downlink data are displayed in analogue and digital form on a ground station TV monitor. Preprogrammed control provides third option in Yastreb-2MA.

System composition           

System comprises air vehicle(s) (designation AL.06. Ya2); launcher (SCT.06); GCS (SP.1B); air vehicle support equipment (SP.1K); and air vehicle functional systems (FTs.1). Set-up time, by four ground crew, is 1 hour (30 minutes for system assembly, 25 minutes preflight preparation and 5 minutes prelaunch preparation).

Launch           

By small booster rocket motor from truck-mounted zero-length launcher.

Recovery           

Parachute recovery to landing on underfuselage airbags. Deployment of parachute is automatic in the event of a control link failure.

Variants           

Yastreb-2           

Initial production version; 7.2 kW (9.6 hp) DB-150SHE single-cylinder two-stroke engine.

Yastreb-2MA           

Improved version, developed from 1990. Principal differences are greater range, third (preprogrammed) method of control and ability to carry larger payloads.

Yastreb-2MB           

Similar to -2MA but with 12.3 kW (16.5 hp) DB-250 engine, increasing maximum speed to more than 129 kt (240 km/h; 149 mph) and permitting wider range of possible missions. Modified navigation and control systems.

Yastreb-2S           

Electronic warfare version; described separately.

Yastreb-2MV           

Similar to -2MB but with 16.4 kW (22 hp) Limbach L 275 E engine, increasing maximum speed to more than 129 kt (240 km/h; 149 mph) and permitting wider range of possible missions. Modified navigation and control systems. Description applies mainly to this version except where indicated

Specifications           

Power plant

Dimensions

Weights

Performance

Status           

The company has confirmed that, as of September 2005, this system was still in service in Bulgaria.

Customers           

Earlier targets (1969-78) produced for Bulgaria; former East Germany; India; Iraq; and former USSR. Yastreb series produced for Bulgaria; and (until 1990, when suspended due to lack of payment) former USSR. Total Yastreb family production exceeds 1,500.

Contractor           

Aviotechnica Ltd

Plovdiv.

CANADA

Bombardier CL-327 Guardian

Type

Multirole VTOL surveillance UAV.

Development

Utilises the development and operating experience of Bombardier's earlier CL-227 Sentinel to offer extended range and enhanced capabilities. Improvements include increased rotor diameter, upgraded transmission and larger payload bay. Specifically designed to operate from any small naval platform or from all-terrain land vehicles with only minimal manning. Bombardier announced in September 1996 that it had entered the CL-327 into production as a company-funded venture. In mid-1997, it was stated that six air vehicles, plus a rotor system test module, were under construction; first flight was made on 30 November 1997.

Variants

    CL-327 Guardian: Enhanced production version of CL-227. Description applies to this version except where indicated.
    CL-427: Alternative projected version, based on airframe of Puma submission in 1996 TUAV competition but subsequently abandoned.

Airframe

The air vehicle comprises an upper power module, a central propeller/rotor module (with two contrarotating three-blade rotors) and a lower payload module. It has an aluminium and composites outer shell and all-composites rotor blades to minimise radar signature, and the six blades and four landing legs are easily installed and removed in the field. The power module accommodates the turboshaft engine, fuel tank, gearbox, fuel control unit and starter/alternator. Special emphasis has been placed on survivability through low thermal, visual, audible and radar signatures, and construction is modular to facilitate field repair. Airframe is EMI shielded and, in maritime configuration, is treated against saltwater corrosion.

Mission payloads

Interchangeable, modular payloads can include combined E-O/IR, communications relay, SAR or active ESM. IAI Tamam MOSP appeared to be preferred sensor in early 2002.

Guidance and control

MIAG (which see) digital flight control system, including GPS and inertial navigation (255 waypoints). Automated flight, flight patterns, target tracking and reversionary modes. Radio command uplink and real-time video downlink (both G/H-band).

System composition

Baseline system consists of four air vehicles, two payloads, a downsized GCS, a digital datalink, a training package and a spares package; customised maritime package also available. Crew of two to set up and operate.

Transportation

Complete system transportable on two HMMWVs and a two-wheeled trailer.

Launch

Conventional VTO and transition between horizontal and hovering flight. The land-based system uses a small trailer platform for take-off. The ship-based variant is launched from a specially designed four-wheel deck traverser, used to transport the air vehicle from the storage area or hangar. The traverser also contains all necessary equipment for air vehicle power and start-up.

Recovery

The land-based system does not require a landing platform, as touchdown can be made on any relatively flat area of ground. Shipboard landings are performed onto a small grid, which captures probes installed in the air vehicle's feet. These components are designed by Indal Technologies Inc and are compatible with standard RAST track. Compatible with Sierra Nevada UCARS system.

Operational status

Two aircraft demonstrated to US Navy at Yuma Proving Grounds, Arizona, between 12 March and 6 June 1998; made more than 40 flights, including one of more than 4 hours. Other 1998 activity included five flights in civilian airspace at Montreal International Airport, operating under normal ATC procedures.
    Successful shipboard automatic landing 22 November 1999 on US Coast Guard cutter Thetis, using UCARS and Joint Service Tactical Control System (TCS); Guardian landed within 15 cm (6 in) of planned touchdown point. However, CL-327 withdrawn from US Navy VTUAV Competition (bids for which closed on 1 November 1999) due to concerns regarding ability to meet USN speed, payload and endurance criteria. Demonstrations to various agencies since that time, including Canadian Army in early 2002.
    Marketing of the CL-327 is understood to have ceased in 2003.

Customers

One Guardian system went on short-term lease to the Australian MoD for use by the Australian Army in land warfare exercises in Northern Australia during 1999. Leased to Canadian Army for trials in early 2002.

Specifications

Power plant

One 93.2 kW (125 shp) Williams WTS117-5 heavy-fuel turboshaft, flat rated at 74.6 kW (100 shp). Fuel capacity 180 litres (47.5 US gallons; 39.6 Imp gallons), with 130 litres (34.3 US gallons; 28.6 Imp gallons) in upper tank and 50 litres (13.2 US gallons; 11.0 Imp gallons) in lower tank.

Dimensions

Weights

Performance

Prime contractor

Bombardier Defence Services
Mirabel, Québec.

Meggitt Defence Systems Canada

3-1735 Brier Park Road NW
Medicine Hat
Alberta T1C 1V5
Tel: (+1 403) 528 87 82
Fax: (+1 403) 529 26 29
e-mail: palmer@schreinercanada.com
Web: http://www.schreinercanada.com

Products:
    Aerial targets
    Control/communications
    Launch/recovery systems

Meggitt Vindicator II

Type           

Recoverable aerial target.

Development           

The Vindicator II was designed by Bristol Aerospace as a basic training target for the evaluation and testing of anti-aircraft 20 and 40 mm gunnery and low-speed missile systems, and for training personnel in the use of such weapon systems. It has been used as a target for Blowpipe, Javelin, ADATS, Vertically Launched Sea Sparrow, Vulcan (with PIVADS) and Avenger surface-to-air missiles, and for Bofors 40 mm, Oto Melara 76 mm, Skyguard 35 mm and FAADS 20 mm gun systems. It can be used for shipboard and land-based operations, and precise flight profiles can be repeated or varied to meet the exact requirements of individual weapons, sensors and/or tracking systems. In July 1999 the system was acquired from Bristol by Schreiner Target Services, which in turn became part of Meggitt in late 2004.

During AEGIS ship trials with the US Navy at Point Mugu, California, in June 2000, Vindicator was used to replicate a UAV on one mission and a helicopter on a later sortie, in the latter case utilising a Boeing Helicopter Radar Signature System (HRSS). Developed for the Canadian Navy, this is believed to have been a 'first' for aerial target operations. The HRSS provides a radar return for a full-size helicopter and can be configured to represent various rotary-wing threats.

Description           

Airframe           

Bullet-shaped fuselage; low-mounted, low-aspect ratio tapered wings with endplate fins; ventral landing skid. All-composites (glass fibre and epoxy) construction. All major components can be easily removed from the fuselage. Initial batch of 20 built under subcontract by Tasuma (UK) Ltd; subsequent manufacture in Canada.

Mission payloads           

Modular construction combined with extensive use of quick-release fittings enables Vindicator to carry a wide range of payloads in nose, mid- and rear-fuselage bays. These can include active radar augmentation (three 63.5 mm; 2.5 in Luneberg lenses and one 190.5 mm; 7.5 in lens in nose bay, plus two 7.5 in lenses in fuselage); radar transponder; Boeing HRSS (see above); radar altimeter; flare pack (maximum 12 flares); visual augmentation (smoke generator and/or continuous or strobe light); Racal Doppler radar or Air Target Sweden acoustic miss-distance indicator; corner reflectors; autostabiliser with height lock; height- and range-tracking systems. The Vindicator incorporates programmable target signatures in E-Prom, and can store up to four different fixed- or rotary-wing signatures, various frequency bands, CW signal-type pulses, time domain data, and skin scintillation.

Guidance and control           

Standard control station is the Meggitt Universal Target Control Station (UTCS), used when the Vindicator is equipped with auilot avionics. The UTCS receives and records vehicle telemetry, can be used to fly waypoint navigation using GPS, controls payloads, and allows night operation. Vehicle position is shown on a moving map display. Radio-controlled air vehicles do not require the UTCS and instead are flown visually by the pilot, using a hand-held encoder and transmitter.

Fully programmable digital auilot, which continuously monitors command datalink quality, has 16 analogue input channels with 14-bit resolution, eight servo outputs, and eight discrete bits that can be configured as inputs or outputs. Asynchronous serial communications are used for the command and telemetry links (auilot has a universal asynchronous receiver/transmitter). Standard airframe incorporates GPS tracking; optional radar tracking allows for flights beyond visual range. Target aircraft's heading and altitude can be controlled manually or by an automated waypoint navigation system. Telemetry information is downlinked in real time.

Typical flight profiles include low-altitude attack and crossing patterns, low-altitude attack with a pop-up manoeuvre, continuously varying altitude, jinking, or any combination of these. With active radar augmentation fitted, Vindicator can simulate the signature of an attack helicopter, including blade/hub Doppler and blade flash.

Launch           

From simple, low-maintenance pneumatic mobile launcher (4.57 m; 15 ft launch stroke).

Recovery           

Conventional skid landing or parachute recovery can be commanded either manually or automatically. Fail-safe system automatically shuts down engine and deploys parachute in the event of auilot or sensor failure, and initiates automatic recovery if the command link is lost. After recovery, Vindicator can be readied for a new flight within 30 minutes.

Specifications           

Power plant

Dimensions

Weights

Performance

Status           

In production and service.

Customers           

Canadian Forces (initial batch of 20 built in UK; subsequent production in Canada); used in Operation 'Iraqi Freedom'. Royal Saudi Navy (15).

Contractor           

Schreiner Target Services Canada Ltd

Medicine Hat, Alberta.

Mist Mobility Integrated Systems Technolgy Inc

Unit 14B
190 Colonnade Road South
Nepean
Ontario K2E 7J5
Tel: (+1 613) 723 04 03
Fax: (+1 613) 723 89 25
e-mail: mccann@mmist.ca
Web: http://www.mmist.ca

Products:
    UAVs

MMIST CQ-10A SnowGoose

Type           

Cargo, communications and ISR UAV.

Development           

US Special Operations Command (USSOCOM)launched a programme intended to acquire a Wind Supported Aerial Delivery System (WSADS) for the aerial delivery of leaflets. The air-launched WSADS offers precise delivery of leaflets and reduced risk to aircrew and transport aircraft. MMIST's SnowGoose, a version of the company's Sherpa guided parafoil system, was chosen after initial trials, and was subsequently formally designated CQ-10A SnowGoose. In conjunction with the US Army Unmanned Aerial Vehicle Systems (UAVS) office, an ACTD programme called Air Launched Extended Range Transporter (ALERT) was established. Its goal was to upgrade and demonstrate the basic WSADS with multiple, existing, non-developmental payloads such as E-O/IR cameras, communications relays, meteorological sensors and dropsondes. ALERT is part of the Expendable UAV (XUAV) ACTD managed by US Naval Air Systems Command (NAVAIR) for USSOCOM.

  In addition to payload demonstrations, ALERT included upgrades to the basic air vehicle such as the introduction of a satcom datalink for command and control of the air vehicle and its payloads; an IFF transponder; navigation lights; and a feed into Blue Force Tracking (BFT). A multipurpose payload interface unit was also added to the basic air vehicle configuration to allow up to 1 kW of vehicle electrical power to be shared with various payloads. All ALERT upgrades are now part of the CQ-10A SnowGoose full-rate production baseline.

  A Military Utility Assessment (MUA) was conducted at the 2004 Quartermasters' Liquid Logistics Exercise (QLLEX) at Fort Hunter Liggett. A reserve unit from the 383rd Quartermasters Battalion operated the SnowGoose after a three-week operator's course. From a tactical operations centre, multiple missions per day were flown, including night-time recoveries. Mission highlights included a multimission demonstration in which communications relay functions were performed, while simultaneously using an E-O/IR camera to identify simulated pipeline saboteurs, after which spare parts were delivered within 50 m (165 ft) of intended recipients on the ground, all within a single sortie. The SnowGoose received a high satisfaction rating from the Battalion, and was given the highest possible rating for combat service support (CSS) in the areas of communications relay, resupply and ISR.

  Soldier teams have used the SnowGoose in demonstrations and training exercises for autonomous delivery of vaxipacks, trauma kits, water, fuel and fragile payloads such as blood. Post-delivery testing confirmed that blood products were delivered undamaged. Other applications of interest to the US Army include use of the SnowGoose as an emplacement vehicle for ISR unattended ground sensors (UGSs). NATO allies have also shown strong interest in the SnowGoose as a communications relay platform.

Description           

Airframe           

Central fuselage module containing fuel, payload, propulsion system and guidance unit; air or ground launch parafoil; foldable landing skids.

Mission payloads           

Six cargo bays (three each side) can be used to carry modular fuel bins, cargo bins or fixed electronic payloads, permitting easy trade-off between payload capacity and endurance over the full flight envelope. Each standard cargo bin is suitable for dispensing up to 45.4 kg (100 lb) of medical supplies, food, water, leaflets, ammunition, fuel, tools or spare/replacement parts. High-Altitude Low-Opening (HALO) parachutes provide low-observability delivery of 100 lb bundles with autonomous precision.

  As of May 2005, payloads flown had included an E-O/IR camera; an LOS communications relay; a meteorological sensing unit; a wind sonde dispenser; and a security loudspeaker. Others due to be flown during the remainder of 2005 included a high-capacity (2 Mbps) satcom link, FM broadcast and TV broadcast.

Guidance and control           

The SnowGoose features a fully autonomous guidance, navigation and control system based on the Sherpa parachute control unit. System autonomy includes waypoint navigation, avoidance areas, air launch, landing and cargo delivery executed, based upon in-flight, real-time wind measurements. The airborne guidance unit (AGU) performs all navigation and control functions. Flight plan is programmed on an industry-standard lap computer with map underlay and uploaded into the AGU before launch or via the satcom datalink. A remote manual override is available, using a LOS RF datalink, allowing the operator to interrupt an autonomous mission to fly and land the system, or to deploy the cargo manually.

Launch           

SnowGoose can be air-launched from a C-130, C-141 or C-17 transport aircraft, or ground-launched from a HMMWV or logistics trailer. Four air vehicles can be deployed in-flight from a single C-130.

Recovery           

SnowGoose performs fully autonomous landings over a wide variety of unprepared surfaces. A four-person recovery team can retrieve the air vehicle with an unmodified HMMWV..

Specifications           

Power plant

Dimensions

Weights

Performance

Status           

The CQ-10A reached a Milestone C LRIP decision in June 2003, followed by an FRP contract awarded to MMIST in August 2004 for up to 200 air vehicles over five years.

The first production operational set was fielded to the 3rd Psychological Operations Battalion, 4th Group, US Army, in February 2005. At that time, production and fielding were continuing at a minimum rate of two air vehicles per month.

Customers           

US Army Special Operations Command (up to 200 air vehicles).

Contractor           

Mist Mobility Integrated Systems Technology Inc

Nepean, Ontario.

Pan Atlantic Aerospace Corporation

PO Box 599, Station B
Ottawa
Ontario K1P 5P7
Tel: (+1 613) 776 13 51
Fax: (+1 613) 776 23 70
e-mail: ltadrone@aol.com

Products:
    UAVs

CHILE

Industrias Electricas RMS Ltda

Avenida Industrial No 1920
Quilpué
Tel: (+56 32) 91 14 46
Fax: (+56 32) 91 33 01
e-mail: rmsltd@entelchile.net

Products:
    Aerial targets

RMS Trauco III

Type

Basic training target.

Development

The Trauco III is essentially a Chilean-manufactured version of the Northrop/RDAE BTT (which see), initiated in 1980 following a US embargo on the sale of military equipment to that country. RMS has also supplied components for this target to RDAE in the USA.

Airframe

As described for BTT.

Mission payloads

Similar to those described for BTT.

Guidance and control

Generally as described for BTT. GPS navigation standard.

Launch

As for BTT.

Recovery

As for BTT.

Operational status

In service; production status not known.

Customers

Chilean Navy.

Specifications

Power plant
As for BTT

Dimensions
As for BTT

Weights

Performance

Prime contractor

Industrias Eléctricas RMS Ltda
Quilpué.

EGYPT

AOI Kader Factory for Developed Industries

2 El Tayaran Street
PO Box 287
Heliopolis
Nasr City, Cairo
Tel: (+20 2) 402 43 19
Fax: (+20 2) 260 87 18

Products:
    Aerial targets

Kader TN-1

Type

Subscale recoverable aerial target.

Development

Designed as a simple, low-cost target for the training of anti-aircraft artillery crews.

Variants

    TN-1A: Initial version; smaller wing and less powerful engine than TN-1B.
    TN-1B: Principal production version, with better performance and manoeuvrability than TN-1A.

Airframe

High-wing monoplane with tapered wings and long dorsal fin; narrow, flat-sided `two-dimensional' fuselage and tail surfaces. Fuselage in side elevation broadly resembles MiG-23 fighter/attack aircraft. Construction probably mainly of composites. Non-retractable tricycle landing gear.

Mission payloads

Underwing pylons can carry smoke canisters or infra-red tracking flares.

Guidance and control

Control is line of sight using a form of model aircraft radio command uplink.

Launch

Conventional wheeled take-off.

Recovery

Conventional wheeled landing.

Operational status

No recent information.

Customers

Egyptian Air Force.

Specifications

Power plant

One 1.34 kW (1.8 hp) two-stroke engine in TN-1A; 2.24 kW (3 hp) two-stroke in TN-1B. Two-blade propeller.

Dimensions

Weights

Performance

Prime contractor

AOI Kader Factory for Developed Industries
Cairo.

FRANCE

Association

Unmanned Vehicle Systems International

(UVS International)
(ex-European Unmanned Vehicle Systems Association)
86, rue Michel Ange, Paris, F-75016, France
Tel: (+33 1) 46 51 88 65
Fax: (+33 1) 46 51 05 22
e-mail: info@uvs-international.org
    www.uvs-info.com
Web: www.uvs-international.org

President: Peter van Blyenburgh

Products/Services
  RPVs, target (including unmanned target aircraft)
  Unmanned air vehicles (UAVs)

Activities/Services

·         Organisation founded for the international promotion of unmanned vehicles.

Aviation Design

ZI le Chenet
F-91490 Milly La Foret
Tel: (+33 1) 64 98 93 93
Fax: (+33 1) 64 98 93 88
e-mail: aviation.design@wanadoo.fr
Web: http://www.adjets.com

Products:
    Aerial targets

Aviation Design Carine

Type

Jet-powered recoverable target.

Development

Aviation Design specialises in the design and manufacture of jet-powered unmanned vehicles. The Carine (Cible Autonome Rapide Infrarouge pour tirs Nocturnes avec Evasives: autonomous high-speed infra-red drone for evasive nocturnal firing) was developed in collaboration with the French Army for training with surface-to-air missiles in a nocturnal environment. Development began in November 1998; it was unveiled at the Paris Air Show in June 1999.
    The company also produces small turbojet engines in the 5 to 100 daN (112 to 2,248 lb st) power range, and undertakes prototyping on behalf of other customers such as Dassault Aviation and SAGEM.

Airframe

CAD design having low-mounted, sweptback wings with centrally mounted ailerons and pod at each tip; cigar-shaped fuselage. V tail surfaces (included angle approximately 120º) with arrowhead finlet at each tip; underslung jet engine. Fully moulded carbon fibre, glass fibre and epoxy construction.

Mission payloads

Infra-red signature provided throughout flight by a novel system (patent applied for) which uses hot air from the jet engine to heat the target, rendering the carriage of IR flares unnecessary.

Guidance and control

Carine is fitted with an auilot (electronic computer and gyroscope). Flight track is followed by ground station by means of GPS. Speed, altitude and other flight parameters are relayed to GCS via telemetry downlink.

Launch

By catapult, or from prepared runway.

Recovery

Parachute recovery system, deployed by either auilot or GCS; or runway landing.

Operational status

In production and service. Company literature states that "hundreds" of its jet-powered unmanned vehicles are produced per year, with exports to more than 30 countries worldwide.

Customers

Include French Army and Navy; other customers not identified.

Specifications

Power plant

One 0.29 kN (66 lb st) JPX miniature turbojet.

Dimensions

Weights

Performance

Prime contractor

Aviation Design
Milly La Foret.

CAC Systèmes SA

Aérodrome du Blois-Le Breuil
F-41330 La Chapelle-Vendomoise
Tel: (+33 2) 54 52 65 65
Fax: (+33 2) 54 52 65 75
e-mail: cacsystemes.dg@wanadoo.fr
Web: http://www.cacsystemes.fr

Products:
    UAVs
    Aerial targets

CAC Systèmes Fox TX

Type
Electronic warfare UAV.

Development
Developed between 1987 and 1992 as one of the basic members of the Fox family (see Fox AT in this section and Fox TS in Aerial Targets section). Currently configured for four basic EW roles: radar interception, identification and location; radar and radio communications jamming; anti-radar; and communications ESM.

Airframe
As described for Fox AT.

Mission payloads
Currently offered with five alternative Thomson-CSF EW payloads including Phalanger (E to J band radar emission interception, localisation and identification); a high-power, multithreat SHF band radar jammer; a Pari E to J band passive RF seeker for anti-radar attack; an interceptor for all types of radio communications; and a Barrage VHF/UHF radio communications jammer.

Guidance and control
GCS contains workstations for flight preprogramming management and localisation system with digital GPS navigation (maximum of 98 waypoints); piloting control station; datalink and tracking system; setting and control station; and telemetry storage and display system. Ground pilot can interchange between programmed flight plan and remote-control mode. Real-time operation and transmission of data to end-user. Power supply 900 VA from GPU and Ni/Cd batteries. Ground crew of three.

System composition
Four air vehicles (in transportation container mounted on launch catapult trailer); truck-mounted GCS shelter.

Launch
Automatic day or night launch by trailer-mounted pneumatic catapult, or by booster rocket from zero-length launcher.

Recovery
By commanded or automatically deployed Aerazur parachute system. Recovered air vehicle can be readied for another flight within 30 minutes.

Operational status
Available.

Customers
None known.

Specifications
Power plant

One 16.4 kW (22 hp) Limbach L 275E flat-twin engine; two-blade pusher propeller.

Dimensions: As for Fox AT

Weights

Performance

* Extendable

Prime contractor
CAC Systèmes
La Chapelle-Vendomoise.

EADS Defence and Communications Systems SA

6 rue Dewoitine
F-78140 Vélizy-Villacoublay
Tel: (+33 1) 34 60 71 70
Fax: (+33 1) 34 60 81 12
e-mail: brigitte.faure@eads.com
Web: http://www.eads.com

Products:
    UAVs
    Aerial targets

EADS DCS Fox TS1

Type

Recoverable aerial target.

Development

Known until 1991 as Aspic, this aircraft appeared in 1988, development having been started by CAC Systèmes in 1986 in co-operation with 10 other French aerospace companies to meet the requirements of the French Army and potential export customers. More than 800 have been built for civil and military applications. Used by French armed forces in presentations for 40 to 127 mm anti-aircraft gun training and Mistral, Sadral, AATCP, Simbad, Crotale, Stinger and Roland missiles.

Variants

    Fox AT: Close-range reconnaissance/surveillance version; described separately.
    Fox TS1: Original aerial target version. Description and specifications apply to this model.
    Fox TS3: Higher-speed target version (more than 214 kt; 396 km/h; 246 mph); described separately.
    Fox TX: Electronic warfare (EW) version of Fox AT.
    Mini Fox: Very low-cost target for small anti-aircraft arms. Has also been sold as small civil reconnaissance UAV.

Airframe

High-wing monoplane with pod and boom fuselage, pusher engine and T tail. Constructed of duralumin, glass fibre, carbon fibre and styrofoam; wing and tail surfaces attached by single bolts.

Mission payloads

Various combinations of infra-red or smoke flares (up to 14), hot nose, Luneberg lenses, chaff dispensers, radio altimeter (for 5 m; 15 ft low-altitude or sea-skimming flights), acoustic or Doppler miss-distance indicator, radar or IFF transponder, corner reflector, towed targets, heading sensor or other equipment. Provision for some stores to be mounted under wings or fuselage.

Guidance and control

Fixed or mobile GCS. Digital flight computer controls pitch, roll, height, safety and recovery; eight- to 10-channel GPS receiver and/or VHF telemetry system optional. Ni/Cd batteries for onboard power supply. Two or three Fox targets can be piloted simultaneously.

System composition

Standard system comprises up to eight air vehicles plus mobile launching catapult, transportation container (optionally trailer-mounted), omnidirectional datalinks, piloting control station and setting mini-station. Options include pneumatic launcher, mapping and location system, telemetry storage and display system, mini radar station and MDI receiving station.

Launch

Automatic day or night launch by mobile bungee catapult is standard; hydraulic launcher optional.

Recovery

By commanded or automatically deployed Aerazur parachute system, or belly landing in any flat area. Recovered air vehicle can be readied for another flight within 30 minutes.

Operational status

Fox TS1 in production and service; at least 800 ordered, of which about 20 per cent for export. Mini Fox also in production as aerial target.

Customers

French Army; four known export customers, including Romania and two in Middle East (one of which is reportedly Qatar). Romanian TS1s in service since 1996 at Capu Midia AFB.

Specifications

Power plant

One 16.4 kW (22 hp) Limbach L 275E flat-twin engine; two-blade pusher propeller.

Dimensions

Weights

Performance

Prime contractor

EADS Defence and Communications Systems
Vélizy-Villacoublay.

MBDA

20-22 rue Grange Dame Rose
F-78141 Vélizy Villacoublay Cedex
Tel: (+33 1) 34 88 14 96
Fax: (+33 1) 34 88 14 94
e-mail: pierre.bayle@mbda.fr
Web: http://www.mbda.fr

Products:
    Aerial targets

MBDA Dragon

Type

Concept validation testbed for battlefield EW (tactical radio/radar jamming) UAV.

Development

Initiated by Matra Défense in 1991 under a contract valued at approximately FFr50 million from the Délégation Générale pour l'Armement, and intended as proof-of-concept demonstrator for eventual Franco-German Busard EW programme. TTL (Meggitt) Spectre (which see) chosen as basic air vehicle, modified to Dragon configuration by TTL France. First flight took place in January 1995 at the Centre d'Essais des Landes; public debut at Eurosatory exhibition in June 1996, at which time Dragon had made 12 flights.
    Matra proposal for Busard requirement was based on the German Brevel/KZO airframe; this would have 3.40 m (11 ft 1.9 in) wing span, 2.30 m (7 ft 6.6 in) length, 54 n mile (100 km; 62 mile) range and 8-hour endurance.

Airframe

Generally as described for Spectre, but with longer and thicker nose section, sweptback fins (starboard one with rudder) at wingtips, and twin jammer antennas along port side of fuselage (retracted for launch and recovery phases, deployed during horizontal flight).

Mission payloads

Thales Bacarat system for airborne jamming of hostile radio communications. The two antennas deploy when the UAV begins to implement the different flight phases of the trajectory in the target area.
    Requirement for Busard is for VHF/UHF communications jammer able to jam military communications, some radio-telephony, citizen bands, police security networks, and some FM radio stations.

Guidance and control

Satan flight control system. Operator plots the trajectory required on a map displayed on the screen, using a mouse. System automatically checks flight, feasibility, estimates its duration and calculates fuel consumption. During flight, the onboard system navigates using standard instruments, updating itself periodically by means of GPS. The trajectory is remotely loaded via a two-way radio link. During the flight, the same link can be used to load a new flight plan or to take over remote control of the air vehicle.
    Busard generally as for KZO; requirement for latter to be able to control four air vehicles in flight simultaneously.

Launch

From cradle-type ramp by two jettisonable solid-propellant booster rockets. Set-up/turnround target time of 45 minutes for Busard.

Recovery

By engine shutdown and deployment of recovery parachute; landing impact absorbed by inflatable underfuselage pad.

Transportation

Busard to be air-transportable by Lockheed Martin C-130 or Transall C.160.

Operational status

Dragon operationally tested and market-ready. No recent information on Busard, which was originally planned for service entry in 2010.

Customers

Busard intended for French and German armies.

Specifications

Power plant

One 28.3 kW (38 hp) UEL AR 731 rotary engine; two-blade pusher propeller.

Dimensions

Weights

Performance

Prime contractor

MBDA
Vélizy-Villacoublay.

SAGEM SA

Division Défense et Securité
Le Ponant de Paris
27 rue Leblanc
F-75512 Paris Cedex 15
Tel: (+33 1) 40 70 63 54
Fax: (+33 1) 40 70 64 54
Web: http://www.sagem.com
Products:
    UAVs
    Sensor payloads
    Control/communications

SAGEM Crecerelle

Type           

Surveillance and target acquisition UAV.

Development           

Crecerelle (Kestrel) was developed under a 1993 contract from the French DGA's missiles and space directorate. The SAGEM Group was selected by the French Army to supply two systems for evaluation. Crecerelle is derived directly from the interoperable ATAOS (autonomous tactical attack and observation systems) developed by SAGEM for observation, reconnaissance and neutralisation missions. The Meggitt Spectre is the air vehicle basis for the Crecerelle system.

Description           

Airframe           

Delta-wing monoplane, with elevons; mainly cylindrical fuselage; sweptback fin and rudder; pusher engine. Composites construction. No landing gear.

Mission payloads           

Crecerelle is a standard platform for a SAGEM orientable LOS payload with TV and FLIR, or a Cyclope 2000 IRLS with both daylight and IR. Each payload provides high-resolution, full real-time image data transmission, and target localisation with a level of accuracy ensuring first-round strike. The LOS payload provides all-over pinpoint observation and moving target tracking in both the visible and IR spectra. The IRLS offers continuous coverage also in the visible and IR spectra; a typical mission patrols more than 1,000 km² (386 sq miles) of terrain. Crecerelle's direct LOS range for real-time return of visible or IR imagery is 32 to 49 n miles (60 to 90 km; 37 to 56 miles). Image signals are transmitted simultaneously to the operations and management centre and to the ground station.

EW version equipped with Thales Communications 12.5 kg (27.6 lb) Bred V/UHF tactical communications jammer.

Other payloads can include meteorological and atmospheric sounding sensors.

Guidance and control           

Single remote-control uplink; separate downlinks for navigation data and sensor payload signals. The SAGEM operations centre is shelter-mounted on a standard army vehicle. It provides the Crecerelle crew with all elements needed for mission planning, tracking and monitoring, as well as for image reception and analysis. Only three operators, working at individual state-of-the-art workstations, are needed to handle mission planning, piloting and interpreting.

The mission planning (navigator) station offers the user a complete mapping database, including digital maps at scales from 1 : 250,000 to 1 : 50,000; digital terrain elevation data; and catalogues of reconnaissance images (from Spot satellites, reconnaissance flights, previous Crecerelle flights, and so on). All data are stored on optical disks, guaranteeing wide flexibility and high reliability. Mission planning operations are, to a large extent, automated, which makes the system very fast (typical mission planning time of 20 minutes), as well as reliable and easy to use. Following the planning phase, flight plan data are transferred to the UAV's computer which then provides independent guidance along the preset trajectory. Using DGPS, the ground station can track the UAV's position to within 10 m (33 ft).

The pilot station groups the mission tracking and monitoring functions. Images from the UAV are shown to the operator, who then selects which ones to interpret, as well as the parameters that enable checking that the mission is proceeding as planned. The operator can change the UAV's flight plan during the mission - for example, to return to a zone that seemed interesting during the first overflight. At any given moment the operator at the pilot station can take over manual control of the UAV by sending high-level orders (altitude, route) via the uplink.

The operations station contains the hardware needed to analyse and interpret the selected images. Various computer tools enable processing of the images to enhance their aspect (for example higher contrast), or using zooms, or overlaying images on maps to locate objects to within several tens of metres. Processed images, retaining their full resolution, are then stored on digital disks. The Crecerelle ground segment can also include remote, portable stations that enable front-line units to receive images directly from the UAV.

System composition           

Six air vehicles and payloads, one GCS (mounted on an all-terrain truck), one launcher (on a single-axle trailer), one UAV storage/recovery/recycling all-terrain truck, and one towed power generation set, plus GCS crew of four (tactical command officer and three NCOs). Entire system air-transportable by two C-130 Hercules or C.160 Transalls.

Launch           

Pneumatic catapult from trailer-mounted ramp.

Recovery           

Autonomous parachute recovery with discard device for safe landing in windy conditions.

Specifications           

Power plant

Dimensions

Weights

Performance

Status           

Two Crecerelle systems ordered for French Army March 1993. Initial flight tests conducted 26/27 May 1994; delivered May 1995 and April 1996; first system deployed to Bosnia November/December 1995. Further deployments to Bosnia and Macedonia from November 1998 until July 1999; three air vehicles lost during NATO Allied Force operations over Kosovo (March to June 1999).

New DGA contract, announced in June 1999, for a platoon of three electronic warfare Crecerelles, delivery of which was made during December 2001.

Customers           

French Army (7th Artillery Regiment initially), but from 1 July 1999 were reallocated, together with CL-289 Pivers, to 61st Artillery Regiment at Chaumont (Haute-Marne).

Contractor           

SAGEM SA, Defence and Security

Paris.