US marketing name: Chrysalis
US Air Force designation: TG-11A

TYPE: Motor glider.

PROGRAMME: Prototype (D-KKST), with Glaser-Dirks DG500 wing, flown 6 July 1986; first flight of second prototype (D-KCHS) with definitive wing 2 June 1987; S10-VC surveillance and observation platform introduced in 1989; designed to JAR 22. Certified in Germany 31 December 1990, in UK 29 October 1991 and in USA, to FAR Pt 21, 8 July 1992. Production of S10 suspended March 1994; resumed late 1994 until 1997 with S10-V.

CURRENT VERSIONS: S10: Original version, with 69.4 kW (93 hp) Limbach L 2400 EB1.AD flat-four engine and retractable fixed-pitch propeller; 54 produced until March 1994, including prototypes.
S10-VC: Surveillance/observation conversion with underwing and small wingtip sensor pods for pollution control and resources investigation. One former S10 (D-KGCM/N600PL) used by Greenpeace since May 1994; one former S10-V (PH-1055) operated by Aerial Surveillance dem Hollander, Netherlands, since 1995.
S10-V: Variable-pitch propeller version; power plant as for S10. Demonstrator (D-KGCX) completed mid-1994 as conversion of S10 but written off in Tanzania 10 March 1995; certified September 1994; total of 29 built between late 1994 and 1997; further five, or more, conversion from S10; production completed. (S10-V has engineering designation S14.)
S10-VT: Current production version with turbocharged Rotax 914 engine and variable-pitch propeller. Prototype (D-KGCR) built 1997; LBA certification August 1997, FAA certification September 1997 and CAA certification May 1998; total of 78 produced by October 2002; of these 38 to USA.(S10-VT has engineering designation S11.) Set world soaring record (D-KMTE) of 1,330 n miles (2,463 km; 1,530 miles) on 26 November 2000, piloted by Klaus Ohlmann.
Following description applies to S10-VT, except where indicated.
S15: Launched at the 1996 Berlin Air Show; has a Rotax 914 engine and 20.00 m (65 ft 7½ in) wing span; two underwing hardpoints for sensor pods in law-enforcement or scientific research roles suitable for loads up to 65 kg (143 lb) each, including FLIR, night sun searchlights, video cameras, and environmental monitoring equipment being developed by Berlin Technical University's Geography Institute. Prototype (D-ESTE) registered 1996, but no record of completion. S15B, light surveillance version, based on S10-VT, was then due to enter service in 2002, followed by S15A advanced surveillance model in 2004; both sponsored by Deutsche Bundesstiftung Umwelt. First S10-VT (D-KGCR) shown at Berlin, June 2000 (and again in May 2002) as POC S15. Now superseded by S8-15 (which see).
S-UAV: Unpiloted surveillance conversion. One S10-V (N600V) used as testbed by Platforms International Corporation, Mojave, California.

CUSTOMERS: Owners in Australia, Austria, Belgium, Brazil, Canada, Czech Republic, Denmark, Finland, France, Germany, Italy, Mexico, Netherlands, New Zealand, South Africa, Spain, Switzerland, UK and USA. Two delivered in 1995 to 94th Air Training Squadron, USAF Academy, Colorado Springs, Colorado. By late 2002, when production temporarily paused, over 160 S10 variants (including prototypes) built.

COSTS: S10-VT €168,000 basic (2002).

DESIGN FEATURES: Three-part shoulder-wing, T-tail motor glider with mid-mounted engine and completely retractable nose-mounted propeller. Transition time between soaring and powered flight is 5 seconds. Winglets option introduced from 1997. Outer wings can be folded by one person for ground handling and hangarage; wing sections carried in gantries inside trailer so that one person can fit centre and outer sections straight from trailer to fuselage.
Wing section Horstmann & Quast laminar flow HQ41/14.35; dihedral 1°; no twist.

FLYING CONTROLS: Conventional and manual. Full-span, six-position (-10/-5/0/+5/+10/+16°) trailing-edge flaps, outer segments of which function also as ailerons. Flap/aileron linkage for manoeuvrability and docility at low airspeeds; Schempp-Hirth airbrakes in outer ends of wing centre-section.

STRUCTURE: CFRP wings in three sections detachable from fuselage; CFRP rear fuselage and tail mounted to steel tube centre frame carrying wing, engine and landing gear; cockpit section, of CFRP structure with Kevlar safety lining, mounted at front of centre frame. Engine fully accessible and horizontal firewall separates engine from wing and flying controls. Winglets optional. Airframe made in Poland by Wytwornia Konstrukcji Kompozytowych.

LANDING GEAR: Tailwheel type; electrically actuated, inward-retracting, narrow track mainwheels; non-retractable tailwheel, steered by rudder. Mainwheel tyres 5.00-5 or 6.00-5, with electrically actuated, mechanical standby disc brakes. Tailwheel: 210x65 tyre; fairing standard.

POWER PLANT: One 84.6 kW (113.4 hp) Rotax 914 F2/S1 turbocharged liquid/air-cooled flat-four engine mounted in the central fuselage steel tube frame aft of cockpit and driving a two-blade, variable-pitch retractable propeller via centrifugal clutch, a CFRP extension shaft and a reduction gear. Engine cooling by adjustable ram air intake. Nosecone is moved forward and spring-folded blades emerge through peripheral slot under centrifugal force.
Fuel in two 45 litre (11.9 US gallon; 9.9 Imp gallon) fuel tanks in outer ends of centre wing; 60 litre (15.8 US gallon; 13.2 Imp gallon) tanks optional. Total capacities 90 litres (23.8 US gallons; 19.8 Imp gallons) or 120 litres (31.7 US gallons; 26.4 Imp gallons).

ACCOMMODATION: Two pilots side by side; dual controls standard; seats adjustable for position and rake; one-piece canopy hinged at forward end and held open by gas struts.

SYSTEMS: 12 V electrical system; full night lighting, landing light and solar cells optional. Solar cells can be fitted behind cockpit to provide 12 V 37.5 W.

AVIONICS: Comms: Intercom, VHF radio and transponder optional, as is special cut-down panel for mountain soaring.