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Revision as of 14:49, 27 December 2016
 | This article includes a list of general references, but it lacks sufficient corresponding inline citations. (December 2012) |
| G 103 Twin Astir | |
|---|---|
| |
| A G 103 Twin Astir landing | |
| Role | Sailplane |
| National origin | Germany |
| Manufacturer | Grob Aircraft |
| First flight | 31 December Template:Avyear |
| Number built | 291 |
The Grob G 103 Twin Astir is a glass-reinforced plastic two-seat sailplane that was developed in Germany in the 1970s by Grob Aircraft AG as a counterpart to the single-seat G 102 Astir then in production. Construction throughout is similar, although to preserve the centre of gravity of the design, the wings were given a slight forward sweep. While many two-seat derivatives of single-seat sailplanes have fixed undercarriage, due to the added space restrictions created by the second seat, Grob devised a novel retraction system for the Twin Astir. The single wheel was designed to rotate 90° sideways before retracting "flat" under the rear seat, resulting in a rather unusual seating position. This was only incorporated in early examples, later on, the wheel was fixed. Factory options offered to customers included whether the front seat should be equipped with flight instruments, and whether water ballast capacity should be installed.
Production continued until around 1980, when it was replaced in production by the Twin II, a new and not directly related design originally designated G 118 but later redesignated the G 103a. The G 103a was in turn replaced by the Twin III in production in 1989.
The Twin was one of the first two-seat sailplanes built from fibreglass and has higher glide performance than most similar sailplanes of the time (e.g. Schleicher ASK 21, Scheibe SF 34 and SZD-50 Puchacz). However, all rudders require very high forces and it is less agile.[citation needed]
Operators
- Italian Air Force operated 9 Grob G103 Twin Astir from 1975 until 1999[1]
Specifications
General characteristics
- Crew: one
- Capacity: one passenger
- Aspect ratio: 17.1
Performance
- Maximum glide ratio: 38
See also
References
- Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 441.
- Hardy, Michael (1982). Gliders and Sailplanes of the World. Shepperton: Ian Allan. p. 49.
- Coates, Andrew (1978). Jane's World Sailplanes and Motor Gliders. London: MacDonald and Jane's. p. 61.