The Lambert Mission 212 is a conventionally laid out low-wing, fixed undercarriage, single-engine, four-seat kit built aircraft designed in the UK by a Belgian college student. Kits are manufactured in Belgium.[1]
The M212 has had an unusually long gestation time. It was designed in 1992 by Filip Lambert, then a student at the College of Aeronautics, Cranfield, and was selected as one of three winners of the Royal Aeronautical Society Light Aircraft Competition in 1995. Construction of the M212-100 prototype began in 1996. This aircraft was registered in the UK in 2000 and was displayed, complete apart from some engine and fuel supply systems, at the Popular Flying Association (PFA) Rally held at Cranfield in June 2002. The first flight, delayed by another two years, took place on 13 April 2004 at Cranfield with Roger Bailey as pilot.[2]
The fuselage is a monocoque construction, tapering strongly to the rear. The cockpit seats four in two rows with dual controls in front, covered by a forward-hinged, single-piece canopy. There are two side windows for the rear seat passengers. The M212 has a fixed tricycle undercarriage, the mainwheels mounted on forward-leaning cantilever legs in narrow chordfairings, attached to the fuselage. The mainwheels have brakes and the nosewheel is steerable.[2]
The first M212 is powered by a 112 kW (150 hp) Lycoming O-320-ED flat-four engine driving a three-bladed propeller. Other engines have been considered, including the 134 kW (180 hp) Superior X-360, a flat-four related to the Lycoming O-360, and the 134-149 kW (180-200 hp) DeltaHawk DH180A4 liquid-cooled, four-cylinder, two-strokeDiesels.[2][3][4]
The M212 was initially intended to feature a Zoche aero-diesel ZO 01A,[5][6] a radical single-row "cross-4" engine of 2,660 cc (162 cu in), producing up to 150 hp (112 kW) @ 2500 rpm. This engine was to be compact, lightweight (84 kg/185 lb),and economical, consuming some 21 litres per hour @ 75% power. As the Zoche company showed no signs of nearing production, Lambert had to settle for a more conventional, but readily available, option.
Operational historyedit
In the mid-2000s Lambert were concentrating on the Mission 106 and Mission 212 kits were not produced until late 2006. In May 2010 the first kit-built example and second M212, registered in the Netherlands, was flown.[2] It attempted an around-the-world flight which was ended by an engine fire and an emergency landing in the Philippines.[7]
Variantsedit
Data from Jane's All the World's Aircraft 2011/12[2]
M212-100
First prototype, proof-of-principle, one example only.
M212-200
Production base level four-seater, flyaway or kit. Certification to JAR/FAR 23 planned.[4]
M212-300
Proposed two-seat aerobatic trainer, now abandoned.
M212-400
Four seat version with increased baggage and range (1,850 km or 1,000 mi. Maximum takeoff weight 1,000 kg (2,425 lb); optional retractable undercarriage.
M216
Proposed version with retractable gear.
Specifications (provisional)edit
Data from Jane's All the World's Aircraft 2011/12[2]
General characteristics
Crew: one
Capacity: three
Length: 7.40 m (24 ft 3 in)
Wingspan: 9.80 m (32 ft 2 in)
Height: 2.90 m (9 ft 6 in)
Wing area: 12.00 m2 (129.2 sq ft)
Aspect ratio: 8.0
Empty weight: 722 kg (1,592 lb)
Max takeoff weight: 1,150 kg (2,535 lb)
Fuel capacity: 160 L (42.3 US gal; 35.2 Imp gal) in production aircraft
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The Lambert Mission 212 is a conventionally laid out low wing fixed undercarriage single engine four seat kit built aircraft designed in the UK by a Belgian college student Kits are manufactured in Belgium 1 Mission 212Role Four seat kit builtManufacturer Lambert Aircraft Engineering BVBA WevelgemFirst flight 13 July 2004Number built 2 Contents 1 Design and development 2 Operational history 3 Variants 4 Specifications provisional 5 ReferencesDesign and development editThe M212 has had an unusually long gestation time It was designed in 1992 by Filip Lambert then a student at the College of Aeronautics Cranfield and was selected as one of three winners of the Royal Aeronautical Society Light Aircraft Competition in 1995 Construction of the M212 100 prototype began in 1996 This aircraft was registered in the UK in 2000 and was displayed complete apart from some engine and fuel supply systems at the Popular Flying Association PFA Rally held at Cranfield in June 2002 The first flight delayed by another two years took place on 13 April 2004 at Cranfield with Roger Bailey as pilot 2 The M212 is an all composite aircraft with 95 of its weight in pre pregs The wing has two main spars plus an auxiliary one all formed from glass and carbon fibre in epoxy resin In plan the wing is gently straight tapered with most sweep on the trailing edge and with turned up wingtips It has 5 of dihedral and 2 of washout Electrically actuated single slot flaps are fitted Fin and rudder are swept with a small dorsal fin the rudder is horn balanced The tailplane is rectangular and set a little above the fuselage carrying inset elevators 2 The fuselage is a monocoque construction tapering strongly to the rear The cockpit seats four in two rows with dual controls in front covered by a forward hinged single piece canopy There are two side windows for the rear seat passengers The M212 has a fixed tricycle undercarriage the mainwheels mounted on forward leaning cantilever legs in narrow chord fairings attached to the fuselage The mainwheels have brakes and the nosewheel is steerable 2 The first M212 is powered by a 112 kW 150 hp Lycoming O 320 ED flat four engine driving a three bladed propeller Other engines have been considered including the 134 kW 180 hp Superior X 360 a flat four related to the Lycoming O 360 and the 134 149 kW 180 200 hp DeltaHawk DH180A4 liquid cooled four cylinder two stroke Diesels 2 3 4 The M212 was initially intended to feature a Zoche aero diesel ZO 01A 5 6 a radical single row cross 4 engine of 2 660 cc 162 cu in producing up to 150 hp 112 kW 2500 rpm This engine was to be compact lightweight 84 kg 185 lb and economical consuming some 21 litres per hour 75 power As the Zoche company showed no signs of nearing production Lambert had to settle for a more conventional but readily available option Operational history editIn the mid 2000s Lambert were concentrating on the Mission 106 and Mission 212 kits were not produced until late 2006 In May 2010 the first kit built example and second M212 registered in the Netherlands was flown 2 It attempted an around the world flight which was ended by an engine fire and an emergency landing in the Philippines 7 Variants editData from Jane s All the World s Aircraft 2011 12 2 M212 100 First prototype proof of principle one example only M212 200 Production base level four seater flyaway or kit Certification to JAR FAR 23 planned 4 M212 300 Proposed two seat aerobatic trainer now abandoned M212 400 Four seat version with increased baggage and range 1 850 km or 1 000 mi Maximum takeoff weight 1 000 kg 2 425 lb optional retractable undercarriage M216 Proposed version with retractable gear Specifications provisional editData from Jane s All the World s Aircraft 2011 12 2 General characteristicsCrew one Capacity three Length 7 40 m 24 ft 3 in Wingspan 9 80 m 32 ft 2 in Height 2 90 m 9 ft 6 in Wing area 12 00 m2 129 2 sq ft Aspect ratio 8 0 Empty weight 722 kg 1 592 lb Max takeoff weight 1 150 kg 2 535 lb Fuel capacity 160 L 42 3 US gal 35 2 Imp gal in production aircraft Powerplant 1 Superior XP 360 flat four 134 kW 180 hp Propellers 3 bladedPerformance Maximum speed 259 km h 161 mph 140 kn Cruise speed 233 km h 145 mph 126 kn at 60 power Stall speed 99 km h 62 mph 53 kn flaps down Never exceed speed 338 km h 210 mph 183 kn Range 1 018 km 633 mi 550 nmi maximum fuel 60 power Rate of climb 4 6 m s 910 ft min maximum at sea level Take off run 280 m 920 ft References edit Mission M212 200 Lambert Pilotfriend com Retrieved 2012 10 04 a b c d e f g Jackson Paul 2011 Jane s All the World s Aircraft 2011 12 Coulsdon Surrey IHS Jane s p 28 ISBN 978 0 7106 2955 5 Bayerl Robby Martin Berkemeier et al World Directory of Leisure Aviation 2011 12 page 106 WDLA UK Lancaster UK 2011 ISSN 1368 485X a b Tacke Willi Marino Boric et al World Directory of Light Aviation 2015 16 page 113 Flying Pages Europe SARL 2015 ISSN 1368 485X Michael Zoche Antriebstechnik April 2007 Zoche Aero Diesels zoche de retrieved 4 October 2012 zoche aero diesels testbench video Zoche de Retrieved 2012 10 04 Janes Update Retrieved 2 January 2012 Retrieved from https en wikipedia org w index php title Lambert Mission 212 amp oldid 993816155, wikipedia, wiki, book, books, library,
