The baggage compartment of
40 l (0,15 ft3) is behind removable
seatback. Composite cabin hood with polycarbonate windshield
of 2 mm thickness opens to the side. It is lockable. The
NACA inlet for ventilation is on the side of cabin hood.
Two part wing uses GA 37U-A315
airfoil. It consists of composite main spar with carbon caps
on which are glued ribs made of extruded polystyrene. It is
covered with 1 mm plywood. Wingtips are made of extruded
polystyrene with fibreglass layup or premolded are vacuum
bagged sandwich. The weight of painted wing half is 12 kg
(27 lbs). Connection of wings to fuselage is made thru two
main and two auxiliary pins. Disassembly of wings takes 5
and assembly 10 minutes. The connection of flaperons to
controls is performed by simple inserting of control pin
The all movable horizontal tail
(HT) has anti-servo tab and is statically balanced. Tails
are of similar construction as wings- on composite spar are
attached polystyrene ribs and plywood skin. Spring trimming
is under pilot seat. Disassembly of HT is made thru
disconnection of control and tab rods and pulling out of
pin. The fin has main composite spar with carbon caps and HT
The legs of main gears
are made of fiberglass rods. The wheels of 12x4
size are braked using mechanical drum brakes. Tail wheel of
100 mm (4") diameter is controlled via ruder and is attached
to the fiberglass spring.
The horizontal tail and
flaperons are controlled via pushrods and bellcranks. Rudder
is controlled via ropes.
The prototype of airplane is
driven by Trabant auto conversion with 120x70 (48"x27.5")
propeller fitted directly on the crankshaft. The Trabant
engine is good choice for SD-1 due to its robustness, high
reliability, low consumption and cost.
airplanes are till now driven by Hirth F-33 AS, F-23 AS and
B&S Vanguard 22 HP engines. It is
possible to use any engine of 22-50 HP power range up to 40
kg (89 lbs) weight. This criterion fulfil e.g. Hirth 2702,
Simonini Victor 1, 2SI 460 F, 1/2 VW etc.
The integral tank of 28
l (7.4 US gal.) capacity is placed behind fuselage firewall.
It is made of fiberglass-PVC foam sandwich. The Mikuni pump
is connected to crankcase. The auxiliary electric pump is
placed on the firewall.
The bus is
juiced by battery and is charged by alternator integrated in
electronic ignition. It is possible to place 12 V outlet
under instrument panel for GPS etc.
The airplane is fitted with
basic flying instruments-speedometer, altimeter, compass and
vario. The RPM?s, total hours, head and exhaust gas
temperatures are checked on the engine. There is place for
COM transceiver with installing diameter of 57 mm in the
instrument panel. The COM antenna is built in the airframe.
The transponder could be placed to the socket on the cockpit
The prototype airplane is
equipped with rescue system GRS 4/270. The container
of system is attached on fuselage bulkhead behind pilot?s
back. The front ropes are attached on upper engine
mount hinges. The auxiliary rope is attached to fuselage
It is possible to use also other systems in serial
version. If is used light engine is possible to mount rescue
system on the firewall. It is possible to built airplane
without rescue system.