FanWing UAV

*FANWING*

prototype UAV airframes

(Other images and details of the most recent short-take-off prototypes can be seen on the News Page and on video links elsewhere.)

UAV airframe 2008/9

Dry Weight 6 kg

MTOW 12 kg

Rotor Span 1.6 m

Flight Speed 8 m/sec 28 km/h

Engine electric 1.2 kW

Construction composite

Autonomy 80 minutes

Payload 2 kg

Flight video from ParcAberporth 2008

FanWing CargoLift UAS

Preliminary Specifications:

MTOW	12,000 + lbs
Empty weight	6,000 lbs
Fuel load	1,000 lbs 6 hours flight @ full load
Payload	5,000+ lbs
Take – off / Landing distance	200 ft / 50 ft
Cruise speed	70 KIAS (140 Kt @ 18,000 ft)
Minimum Speed at full load @ 90% power	20 KIAS sea level
Ceiling	20,000 ft
Engine	RR 250 C30R/3 650 shp (485 kW)
Rotor Span ( 4 sections )	54 ft
Total span including winglets	70 ft
Length	64 ft
Height to tip of Vertical tail	22 ft
Cargo space	5 x 5 x 20 ft (8 x 8 x 28 ft optional)
Cargo volume	500 ft3
Construction	Composite
Cargo Delivery @ 75 nm / 24 hours	8 Trips , 3 hour cycles, 2.5 flying, 0.5 turn around = 40,000 Lbs at FOB

Design sketch

Smart - Murch prototype modified with a 35 cc Honda engine 2007


See specifications of this prototype below	Slightly reduced lift on this test but lower sound

35 cc 4 cycle gasoline engine confirming fuel consumption @ 500g per hour Video clips 8.5 mb

Short video clips from same flight (5 mb)

FanWing UAV Prototype (with pilot Raffaele Moreschini)

Test flight with suspended lead payload (10kg)

FanWing UAV Prototype Development

The Murch/SMART UK government co-funded UAV model is now flying under RC control and engaged in ongoing weight tests, still open ended but with present payload now at 12kg.

It is clear that the new FanWing technology lift efficiency improves with upscaling. The company are keen to exploit the possibilities with a larger prototype which will not only act as a high-lift commercial UAV airframe but also provide essential research data for the future manned ultralight.

Achieved and Projected Milestones

First (SMART) Phase (completed end of 2003): production of a viable long-endurance (> 8 hours) slow-flying manoeuvrable surveillance airframe.

Second Phase: ongoing payload flight tests with onboard surveillance equipment

Projected Third Phase: construction of a new prototype airframe to carry 60 kg of useful payload, with a flight duration of 12 hours controlled by an autonomous flight-control computer.

Specifications of First/Second Phase UAV Prototype

Empty weight

MTOW

Rotor span

Engine

Flight speed

Take off distance @ 18 Kg

Autonomy*

8 kg

20 kg

2.2 m

11.5 cc glow engine

7-15 m/sec

20 m

To be determined*

*A new engine will be installed shortly which will use approximately 500 g. of fuel per hour providing 8 hours of autonomy with 4 kg in fuel, leaving 6 kg for electronic payload.

Early UAV Prototype Flight Clips (October 2003) with first experiments in surveillance