The beginning and concept:

At the end of 2009 SSVOBB Lambach Aircraft decided to freeze the Impuls-project. The rest of that academic year was used by the team to analyse what actually went wrong with the project. Valuable lessons were learned and gathered.  During the summer of 2010 the society decided that it still would like to chase its dream of designing and building its own aircraft.

One of the first aspects of the S-Vision concept is that it is based on the principles learned from the Impuls project. One of those principles, which can be recognised within the design of the S-Vision, is that the society tries to keep its design as simple as possible. This is shown by the fact that the S-Vision is a conventional 2-seater, certified under the Dutch “Regeling amateurbouwluchtvaartuigen”. This means that the CS-VLA (Very Light Aeroplanes) regulations are used next to the Dutch regulations. A second important aspect of the S-Vision concept is that it tries to be innovative by trying to be as efficient as possible. This in turn translates to a higher cruise speed than most aircraft in its class.


The name:

svision1The idea behind the aircraft was immediately clear to the society, but another issue would take a bit longer to resolve: the name. The fact that it was so hard to find a name can be seen in the fact that within the society the aircraft was initially called “NoName I”. After half a year of development, it was decided to name the project “LA-I” or “Lambach Aircraft I” until a better name was found: “the S-Vision”.


Conceptual Design:

In the first year of the project, the mission analysis, which specifies what the aircraft needs to be capable of and the conceptual design were completed. This means that the configuration and size of the aircraft and it components were determined.


Preliminary design:

svision2From the summer of 2011 until the summer of 2013 work has progressed on the preliminary design. Work has been performed on the aerodynamics, the structure and all the systems. The layout of the systems were determined, as well as the final sizes of the aircraft. At the end of this stage the design was frozen. This means that all outer dimensions are known and will not be changed anymore.


Detailed design:

From 2013 onwards the team is working on the detailed design of the S-Vision. This means that everything will be designed up to the position of the last rivet. Specifically work is being performed on the composite structure of the tailboom, the control stick and the rudder pedals.

Work planned for the near future consists of the design of the horizontal tail, the wings including flaps and ailerons and the fuselage frame.



Technical details:

svision3The S-Vision is a two-seater with a side-by-side configuration powered by a ULPower UL350iS which produces 130 horsepower (97 kW). A single slotted flap mechanism will allow the plane to reach a high lift coefficient. This ensures the stall speed to be well below the 83 km/h (45 kts) stall limited dictated by the CS-VLA.

Different construction techniques will be used in the construction of the S-Vision. This includes regular sheet-metal forming but also the use of composites to produce the more difficult shapes of the aircraft. The S-Vision will be equipped with two 10 inch glass cockpit panels. Which provide the pilots with a lot of information such as: a detailed GPS map, synthetic vision, flight parameters, engine parameters, air traffic information and more.

A full aircraft ballistic parachute will be installed to increases the safety of the aircraft. Combined with two payload bays integrated on the bottom side of the aircraft, and the option to install wingtip modifications or wingpods, makes the S-Vision a great platform for flight tests.


Wing span: 9.45 meter
Length: 7.99 meter
Height: 2.30 meter
Empty weight: 3765 N (384 kg)
Payload: 2727 N (278kg)
Maximum take-off weight: 6492 N (661 kg)
Stall speed (Clean): 48 KIAS (88 km/h)
Stall speed (Flapped): 40 KIAS (74 km/h)
Cruise speed (VA): 146 KIAS (270 km/h)
Maximum speed (VNE): 195 KIAS (360 km/h)
Maximum G-load: -1.9 / +3.8
Minimum take-off distance: 350 meter
Minimum landing distance: 260 meter
Range: >1000 km
Fuel capacity: 100 L
Endurance: 4 h (270 km/h)
Delft University of Technology