The Dornier 228: D-CALM

The ARSF deploys a highly-capable Dornier 228-101 research aircraft purchased from Deutsches Zentrum fuer Luft-und Raumfahrt (DLR).

The Do 228 is a twin turbo-prop powered, non-pressurised, shoulder-wing monoplane with rectangular-section fuselage and a double passenger/cargo door. The aircraft is used in the fields of optical remote sensing, oceanography, atmospheric and earth science research. A range of sensors may be installed, for example metric cameras, multi- and hyperspectral scanners, optoelectronic and infrared line scanners, microwave radiometers, synthetic aperture and side-looking airborne radar, scatterometers, LIDAR, etc.

In ARSF service, the aircraft is configured with a core remote sensing instrument suite which comprises:

• AISA Eagle & Hawk hyperspectral instruments (Specim)
• Leica ALS50-II LiDAR
• Leica RCD105 39 megapixel digital camera

In addition to this the facility can operate an Aircraft Integrated Meteorological Measurement System (AIMMS).

The Dornier's size and flexibility make it an excellent test and development platform. D-CALM has a number of hard points on the exterior available for mounting instruments, as well as a forward roof opening which can accommodate the whole air sampling 'snorkel'. For the majority of the flying season, the cabin contains the core remote sensing instrumentation, although the Dornier’s sizeable cabin enables the housing of additional instrumentation in standard 19" racks.

The aircraft's excellent range/payload characteristics enable support of marine remote sensing application in continental shelf environments.

Technical Data

General

Engines	Garrett TPE 331 - 5A - 252 D with 533 kW (715 SHP) TO power
Minimum Crew	IFR: 2 Pilots
Electrical power for Experiments	DC: 28V / max. 220 A/ 6.3kW; AC via inverter: 220V / 50Hz (2000 VA)
Pressure-Cabin / Cabin-volume	None / approx. 14 m3

Weights

max. Take-Off weight	5980 kg	13184 lbs.
max. Landing-weight	5700 kg	12566 lbs.
max. Zero-fuel weight	5540 kg	12214 lbs.
max. fuel	1885 kg	4156 lbs.
Crew & payload @ max fuel	499 kg	1100 lbs.

Performance

Altitude [ft]	5 000	10 000	15 000
max. Distance [NM]	1270	1440	1610
max. Endurance [h]	05.90	07.00	08.00
max. Speed	190 KTAS	200 KTAS	206 KTAS
max. Speed for science	160 KTAS	160 KTAS	160 KTAS

Max. Ceiling for science		15 000 ft
Service ceiling	8230 m	25 000 ft
Take-Off distance, MTOW, ISA, MSL	625 m	2050 ft

Special Configurations:

One 2060 mm x 515 mm (frame 20 to 25) and one approx. 425mm diam (frame 25 to 27) opening in the cabin floor that can be opened/closed during flight.

Covered openings in the cabin roof:

• 400 mm diam (between frame 23 and 24)
• 150 mm diam (frame 12/13)
• 150 mm diam (frame 22/23)

Bubble-window with operator position and floor-opening for navigation-sight at the right forward side of the cabin.

Six hardpoints below the cockpit-area for external loads up to 200 Kg.

Each fuselage side (cockpit area) has three hardpoint-pairs to carry a load of 50 Kg (e.g. SLAR-antennae).

On both wings (outside of propwash) two wing-stations for external loads up to 100kg.

From the wing-stations to the cabin there are tubes for cables (power and data lines), suitable for Particle Measurement Systems (PMS).

Inlet for atmospheric chemistry sampling installed on the roof.

Mounting rails on the cabin roof (frame 14/15 and 19/20) for racking.

Oxygen system for two pilots (demand-system) and three operators (constant-flow), which allows flights up to 25 000 ft (5 hours max).

Special avionics:

• Global Navigation System GNS-X flight management system, Collins HF 9000 with Selcal, Weather-radar WXR270, Radar-Altimeter, Garmin GPS 160, CMC - Pilot View EFB.