Take off when you want.
No longer wait for a tow-plane if you have one the powerful retractable Solo engine installed. Once you have retracted the engine after taking off, the low extra weight of the engine unit and its optimized integration will make you forget that you're flying a self-launching sailplane.
The engine is rigidly coupled with the pivoting propeller tower and gets swiveled with it when the propeller gets extracted, so both engine and exhaust system remain in the engine box. The modern ILEC control unit allows automated operation, avoids operational errors and makes engine use a pleasure.
Fault Tolerance by Redundancy.
In order to assure a save mode of operation, a redundancy system has been developed, which can be manually activated if the normal engine control fails, e.g. due to a faulty sensor. It consists of a simple ECU, which contains a characteristic diagram. This diagram (fuel supply over engine speed) controls two additional injection valves. The fuel is guided through two hoses into the manifolds. The engine speed and the fixed ignition timing are detected by an additional inductive sensor. The ECU has two ignition controllers which control the two ignition coils, which are also used for the normal engine operation.
The redundancy system has no correction for air pressure and temperature. The engine operational data and limitations are unchanged if the engine is operated using this system.
Simple to Engage.
Engine start-up is straightforward and easy thanks to the newly designed automatic. To engage the engine, the pilot only needs to switch on the ignition and press the start button once the engine has been fully extracted. The engine’s start setup is always optimized by a microprocessor to match the current environment.
Simple to Stop.
Disengaging the engine is just as easy. After switching off the ignition on the Ilec engine control unit, the control unit automatically stops and fixes propeller in the correct upright position and the engine gets retracted.
The Engines.
SOLO has specifically designed the two-stroke engines of our self-launching models for retractable engine systems. The Ventus-2cxM uses the single-carburator engine SOLO 2625-01 with a performance of 52 hp (38 kW), while the Arcus M and Quintus M are equipped with the stronger injection engine SOLO 2625-02i with electronic double ignition and a performance of 68 hp (50 kW).
Both engines are characterized by low weight, compact measurements, double-ignition, high reliability and a long life-time.
Gallery
Engine Specifications
Engine displacement | 625 ccm |
Compression rartio | 9.5 : 1 |
Ignition unit | Dual electronic high-voltage ignition (Ducati Energia) or ISKRA |
Ignition plugs | BOSCH W5 AC, Gap at electrodes 0.5 mm |
Carburetor | MIKUNI diaphragm carburetor Typ BN 38 |
Direction of rotation | Clockwise, seen in direction of flight |
Fuel | 2-Stroke-mixture, AVGAS 100LL, premium gas min. 95 ROZ |
Mixture | Mixture ratio 1:50, 2-stroke Castrol mineral oil or synthetic oil, or other oils with specification according to JASO FC or FD |
Dry weight | 23 kg |
Generator | 12 V / 150 W |
Coolant | Engine coolant (Glysantin BASF G48), tab water (0-20° dh) in a mixture of 40:60 (27 °C) |
Take-off-speed, -power | 6250 rpm with a power of 39 kW (53 hp) |
Max. cont. speed, -power | 6250 rpm with a power of 39 kW (53 hp) |
Max. rpm | 7000 rpm |
Idle rpm approx. | 2300 rpm |
Max. temp. cooling liquid | 115 °C (240 °F) measured in the cylinder head |
Fuel consumption | Max. continous power 5.94 US gal./hr. (22.5 l/h) |
Engine displacement | 625 ccm |
Compression rartio | 9.5 : 1 |
Ignition unit | Dual electronic high-voltage ignition, mapped |
Ignition plugs | BOSCH W5 AC, Gap at electrodes 0.5 mm |
Fuel injection | Electronic, two butterfly shutters, mapped |
Direction of rotation | Clockwise, seen in direction of flight |
Fuel | 2-Stroke-mixture, AVGAS 100LL, premium gas min. 95 ROZ |
Mixture | Mixture ratio 1:50, 2-stroke Castrol mineral oil or synthetic oil, or other oils with specification according to JASO FC or FD |
Dry weight | 24 kg without exhaust (according to airframe manufacturer) |
Generator | 12 V / 500 W |
Coolant | Engine coolant (Glysantin BASF G48), tab water (0-20° dh) in a mixture of 40:60 (27 °C) |
Take-off-speed, -power | 6600 rpm at a power of 50 kW (68 hp) |
Max. cont. speed, -power | 6600 rpm at a power of 50 kW (68 hp) |
Max. rpm | 6700 rpm |
Cut off speed by CPU | 6700 rpm |
Idle rpm approx. | 2300 rpm |
Max. temp. cooling liquid | 115 °C (240 °F) measured in the cylinder head |
Fuel consumption | Max. continous power 6.47 US gal./hr. (24.5 l/h) |