Limbach l550E Engine
SKU: MD-P00788·Spare Parts & Components·Под заказ
Обзор
Limbach L550E is a four-cylinder, two-stroke, horizontally opposed engine, with excellent performance, outstanding reliability and excellent power-to-weight ratio, which has been used in many fixed-wing unmanned stages in France, South Africa, Thailand, Singapore and domestic Chinese Academy of Sciences and aerospace systems. In order to meet the demand for long endurance and high altitude, Limbach has launched the L550EF EFI engine, which has already been applied in many plateau-type unmanned aerial vehicles, and the L550E engine can be used in 200-450kg take-off weight taxiing, vertical take-off and landing fixed-wing unmanned aerial vehicles, as well as 100-160kg rotorcraft and helicopters. Limbach L550E is an air-cooled horizontally-opposed four-cylinder two-stroke petrol engine developing 37 kW (50 hp) at 7500 rpm which can drive a propeller either directly or geared. It employs a single magneto ignition, four carburettors, and is lubricated by oil mixture lubrication with a fuel to oil ratio of 25:1 for mineral oil or 50:1 for synthetic oil. Limbach L550E Specifications Type: Four cylinder, two stroke aircraft engine Displacement: 548 cc (33.4 cu in) Dry weight: 16 kg (35 lb) Fuel type: 90 RON octane unleaded petrol or 100 LL Avgas Oil system: oil mixture lubrication, 25:1 fuel to oil ratio for mineral oil, 50:1 for synthetic oil Power output: 37 kW (50 hp) Limbach L550E Mechanical Dimensions and Altitude and Power Figures Limbach l550E Engine Test Bench Test Instruction - Pre-Engine Test Installation 1、Preparation before engine installation First, place the Limbach L550E engine on a flat table and prepare the necessary accessories and tools for installation. 2、Engine installation on the test bench 2.1. Assemble 4 buffer spacers to the buffer pad mounting on the engine base respectively; install the engine mounting seat so that the rudder pull rod can pass through the mounting seat holes; tighten and connect the engine mounting seat with the buffer pad through the supporting bolts.
Технические характеристики
Specifications. Основные характеристики: Type Four cylinder, two stroke aircraft engine, Bore 66 mm (2.60 in), Stroke 40 mm (1.57 in), Displacement 548 cc (33.4 cu in), Length 300 mm (11.8 in), Width 410 mm (16.1 in), Height 301 mm (11.9 in), Dry weight 16 kg (35 lb), Fuel type 90 RON octane unleaded petrol or 100 LL Avgas, Oil system oil mixture lubrication, 25:1 fuel to oil ratio for mineral oil, 50:1 for synthetic oil, Cooling system air, Power output 37 kW (50 hp).
Технические характеристики — 1 groups
Основные характеристики: Type Four cylinder, two stroke aircraft engine, Bore 66 mm (2.60 in), Stroke 40 mm (1.57 in), Displacement 548 cc (33.4 cu in), Length 300 mm (11.8 in), Width 410 mm (16.1 in), Height 301 mm (11.9 in), Dry weight 16 kg (35 lb), Fuel type 90 RON octane unleaded petrol or 100 LL Avgas, Oil system oil mixture lubrication, 25:1 fuel to oil ratio for mineral oil, 50:1 for synthetic oil, Cooling system air, Power output 37 kW (50 hp).
Технические характеристики
Specifications
- Type
- Four cylinder, two stroke aircraft engine
- Bore
- 66 mm (2.60 in)
- Stroke
- 40 mm (1.57 in)
- Displacement
- 548 cc (33.4 cu in)
- Length
- 300 mm (11.8 in)
- Width
- 410 mm (16.1 in)
- Height
- 301 mm (11.9 in)
- Dry weight
- 16 kg (35 lb)
- Fuel type
- 90 RON octane unleaded petrol or 100 LL Avgas
- Oil system
- oil mixture lubrication, 25:1 fuel to oil ratio for mineral oil, 50:1 for synthetic oil
- Cooling system
- air
- Power output
- 37 kW (50 hp)
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