Merlin 200

Development of Merlin 200, a fixed wing UAV, was originally intended as a low-cost research test bed. As such, the Merlin 200 features a large payload bay located in the fuselage of the aircraft and operates on a pusher propeller so that the nose of the aircraft is free for the mounting of any forward looking sensors. The large payload area in the fuselage in conjunction with the large maximum payload weight simplifies the mounting of vibration isolated avionics and minimizes the space and weight considerations that often plague flight platforms intended for rapid prototyping. However, in spite of the research origins of the Merlin 200, the tactical capabilities of this aircraft have also been taken into consideration during the preliminary design process.
 
The aircraft’s major parts were processed in several different molds using composite materials such as carbon fiber, Kevlar, and fiberglass. Therefore, upon the customer’s request, the configuration of the aircraft, such as different internal structures, parts, or equipment, can be easily tailored to meet mission requirements. For example, a 200 cc. 19 hp. two cycle engine is installed for the research version of the testbed. However, there are a variety of engine selections (19hp~40hp) that can be chosen from for the different applications of the aircraft. The Merlin 200 wing span is 16ft, and has over a 65 lb. payload capacity with one of the largest payload spaces in its class. The first flight of the Merlin 200 was performed on February 17th, 2006 in the state of Georgia successfully.

 

Brief Information:
 
Use(s):
Reconnaissance, Observation, Target acquisition, Surveillance, and Research Test bed.
 
Power plant:
Engine Type: 2 Cycle, Air Cooled, Twin Horizontal Opposed Piston Engine
Displacement: 200CC.
Engine Output: 19hp (40hp. max)
 
Dimension:
Wing Span: 16 ft (4.88m)
Length: 11 ft (3.35m)
Height: 3.5 ft (1.07m)
 
Weight:
Empty Weight: 96 lb. ( 43.5 Kg)
Gross Weight: *161 lb. (73 Kg)
Payload Weight: *65 lb. (30 Kg)
  
Performance:
Speed: Approx. 115 mph (Approx.).
Endurance: 3.5 hr. with standard internal Fuel Tank (3 Gal)
Service Ceiling: *12,000ft

 * Payload weight and gross weight are from the initial flight test result. Service Ceiling is estimated. More accurate information will be available after further flight test program.