URBAN AIR s.r.o.
516 61 Libchavy 83 Czech Republic
TEL./FAX +420 465 582153

UFM - 13 Lambada
UFM - 10 Samba

Czech version...

Fotogalerie

Welcome to URBAN AIR and to our family of Lambada aircraft.
UFM-13 Lambada and UFM-10 Samba are a two-seat, fully-composite microlight aeroplane, designed for economical touring, pilot training and sport flying. UFM_13W is pure glider.

The Lambada family represents a new generation of outstandingly beautiful and aerodynamically efficient light aircraft, which offer exceptional quality, performance, and value for money. The aircraft´s advanced structure and design puts it at the forefront of this rapidly developing field of aviation.

In May 1996, the prototype UFM-13 was submitted to a rigorous program of flight tests and load tests, which included testing the wing to destruction (up to + 12 "G") at the Aeronautical Engineering faculty of Brno University.

All of the composite components are built in high quality moulds, thus ensuring a much higher standart of accuracy and finish than is obtainable with any other method of construction. The materials used (imported glass and carbon fibre epoxy laminate of aircraft manufacturing grade) guarantee uniform qualities of strengh and lightness.

Tests the aeroplane successfully passed the wing loading test carried out at the Aeronautical Engineering faculty of Brno University.

The wing-flaps, ailerons or flaperons and the elevator all feature automatic self-aligning connectors, which greatly facilitate quick assembly and de-rigging of the wings and tailplane. The wing spars are reinforced with carbon fibre and reguire no struts. They locate into each other and into the fuselage with great precision and are locked in place with just one steel pin. The whole operation is designed to be extremely simple and performed in a few minutes without tools. Once dismanted UFM aircraft can be easily transported on a special trailer, with the wings supported alongside the fuselage. The laminar wing profile SM 701 gives high performance in all phases of flight

A monocuque shell structure has been adopted to provide maximum strength-to-weight ratio and a streamlined form of exceptional smoothness and high-gloss finish, which accounts for the very low drag of this plane. The fuselage is largely tubular in section with several annular bulkheads, and the wings are a combination of a sandwich shell and a beam. The number of parts not contributing directly to the structural strength has been minimised e.g. even the seats form an integral part of the fuselage.

The load test program was based on the Czech UL-2 regulations, howeveer, due to the aircrafts high performance, several tests were carried out to the more demanding standards of JAR-22 and JAR VLA. Specifically wing gust loading and undercarriage load tests, among others, were proved at hte higher standard. The initial arrangement of composite lay-up was calculated manually. Then a three-dimensional computer model of the wing and fuselage was created and used for the finite element analysis of static strength using the computer program MSC/NASTRAN.

The basic design and detailed structure were the responsibility of Pavel Urban and his colleagues Karel Faltus and Milos Mladek. The aerodynamic design and calculations were the responsibility of Mirko Musil, who unfortunately died at the end of his work. We are very grateful for his help and would honour his memory.
Stress calculations were carried out by

Mr. Kabrt and his brother, from Vanessa Air Ltd.,

who also completed some of the aerodynamic calculations. Some of the most modern computer methods of finite element analysis were employed in the successful load testing program at Brno University.