ENGINEERING AND CONSTRUCTION


Final wing assembly
Completed wings
Wing manufacture
Vertical stabilizer - LAMBADA

CONSTRUCTION TECHNIQUES USED IN THE SAMBA AND LAMBADA

Previous generations of Ultra-Light aircraft employed meta, tube and/or fabric. These aircraft designs were slow, inefficient and noisy.

That has all changed, and happily those days are gone...

The construction technique chosen for the SAMBA and the LAMBADA is driven by the need for a light, efficient and cost-effective aircraft. In order to achieve a design with a minimal empty weight, a shell construction method is used, resulting in optimal use of material, giving maximum strength. Using finely polished moulds allows for a perfect finish, greatly affecting the aerodynamic characteristics of the aircraft.

The fuselage is designed as a pure monocoque shell with several partitions. Non load-bearing parts and surfaces are reduced to a minimum to save weight and even the seat formers are an integral part of the fuselage.

Cockpit - SAMBA XXL
Fuselage mould - LAMBADA
Tail boom - SAMBA XXL
Engine mount - SAMBA XXL


The wing design is similar to most modern high-performance composite sailplanes. The spar is a fibreglass I-beam. It is capped with carbon-fibre for extreme tensile strength. This spar is laminated onto a fibreglass sandwich structural wing skin. On the LAMBADA, automatic hook-up of aileron or flaperon drives, flaps, spoilers and the elevator allow safe, easy and quick rigging and de-rigging. The wing spar stubs carry through the fuselage and interlock on assembly. A wingpin secures the spars in place.

Wing manufacture
Wing sandwich prior to lay-up
Interior showing carbon spar capping
Wing spar stubs
Cockpit - SAMBA XXL
Wing spar construction
Spar pin inter-lock
Flap pre-cut markup


The laminar flow wing (Profile SM 701) demonstrates high performance in all modes of flight. The wing complies with the specifications for JAR-22 and JAR-VLA categories, and AULA category in Canada.

ENGINEERING

The original designs of the composite shells were done on the basis of manual calculations. Detailed models of the wing and the fuselage have been created using MSC/NASTRAN.


Strength calculations were performed at Vanessa Air s.r.o. by Eng. Miroslav Kábrt and Eng. Petr Kábrt. Aerodynamic calculations were also completed by Vanessa Air s.r.o. The calculations are based on the most advanced computer methods. The strength calculations - performed originally on the basis of finite element modelling - were finally checked by load tests at the Technical University of Brno, where the wing loading (break) test was successfully completed. After demanding operational tests all over the world, the SAMBA XXL, SAMBA and LAMBADA were successfully certified in the Czech Republic, Germany, France, and South Africa.

TESTS ON THE LAMBADA  - UFM-11

Wing test rig - University of Brno
Cockpit crash / drop test
Lambada cockpit (1300 kg) and engine mount (560) kg loading
Lambada tail - 270 kg vertical
and 100 kg lateral loading

WING BENDING MOMENT TEST ON UFM-11 at the University of Brno AND FLOW TEST VIDEOS

All wing test videos have been abridged and are presented at 32x normal speed.
NegativeBending Moment - 44%
Negative Bending Moment -100%
Positve Bending Moment and Torque -44%

Positve Bending Moment and Torque -100%
Positve Bending Moment and Torque - To failure
Flow test - flaps

COCKPIT CRASH / DROP TEST



© - Advanced Composite Aircraft Inc. 2008
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