Atlas Technical Info

Technical Information

Technical Information: Atlas Helicopter

The crucial rotor design of the Atlas human-powered helicopter was completed by the end of April 2012, and construction began with the full student team in May. The initial configuration study resulted in the selection of a quad-rotor design similar to that of the Yuri I and the Gamera. This was based on a lower predicted power requirement, the stability of the configuration, and the ease of construction based on many parts with production-line repeatability.

The rotor optimization was carried out using the in-house computational model outlined below. Further design on the helicopter components and overall structure was done using in-house finite element analysis programs and further computational optimization, as well as empirical design-test processes.

Further flight testing will likely generate changes with the final design, and this overview will be updated at the conclusion of Atlas’ flights. The overall specifications on the helicopter are:

Rotor Radius: 10.2m (33.5ft)

Maximum Dimension: 46.4m (154ft)

Height: 3.7m (12.1ft)

Overall Weight: 55Kg (121.4lb)


Computational Modeling and Design Optimization

The computational model involves a medium-fidelity aerodynamic model, combined with a finite-element structural analysis. Given a set of roughly 30 design variables, including rotor geometry, lift coefficient, spar diameter, and tube thickness the program computes the total mass of the aircraft, the required flight power and the stresses in all the various components. A gradient-based computational optimizer is then used to determine the design that minimizes the required power. Success of this design strategy depends on the accuracy of the aerodynamic model and structural predictions.

Several low and medium fidelity aerodynamic models have been implemented, including a simple momentum theory model, a blade-element model and a discrete vortex-ring model. The more advance vortex-ring model has the capability of computing the airflow pattern through the rotor in close proximity to the ground. Modeling this “ground-effect” is essential to the design of a helicopter that operates at such low altitude. The animation below shows the induced flow pattern as computed by the vortex-ring method. The graph shows how the induced power is reduced in proximity to the ground, where h/R is the fraction of the height to the rotor radius. The results of the vortex model are plotted along with empirically derived models given by several other authors.

Vortex Model

Vortex Model

Ground Effect plot

Ground Effect plot

The structural model is a linear finite-element model based on classical engineering beam theory. Composite analysis methods are used to generate accurate structural properties and failure characteristics of the carbon fibre tubes. During the course of the human-powered ornithopter project extensive structural testing was performed on representative tubular specimens in order to fine-tune the model. This gives us the capability of predicting structural deformation and failure to within 5% accuracy, which will result in a structure that is only just as heavy as it needs to be. The image below shows structural failure testing during the summer of 2009.

                             Structural failure testing


                           Structural failure testing

Finally, a gradient-based optimizer is used to navigate the design space and find a solution that truly results in minimum required power. The optimizer is able to evaluate the trade-off between the benefit of extra rotor diameter and the extra structural weight, or the benefit of wire bracing versus the extra aerodynamic drag, all while considering the aerodynamic efficiency and nearly a dozen different failure modes. The combined aero-structural model can evaluate a complete helicopter design in 0.1 to 15 seconds depending on the fidelity of the chosen model. This allows rapid design optimization that can be completed on the order of minutes instead of days.

Construction Techniques

The rotors were constructed in a similar fashion to those of the Gossamer Albatross, a human-powered aircraft that crossed the English Channel in 1979. The main spar is a carbon fiber tube, whose structural weight is reduced through the use of wire bracing to share the lift loads. The airfoils are constructed with expanded polystyrene foam with balsa wood cap strips on the top and bottom. The rotor is then covered with an incredibly thin sheet of Mylar plastic film, making the whole rotor transparent. The images below shows the structure of the Snowbird wing along side the even lighter wing of the Gossamer Albatross.

Power Plant

Plot showing power versus time for several world-class athletes.

Plot showing power versus time for several world-class athletes.

Todd Reichert is the pilot selected to fly the Atlas. Todd is a national-level speed skater and competitive athlete in the world of human-powered streamlined vehicles. His piloting background, as well as his experience flying the Snowbird human-powered ornithopter make him well suited for the job.

The average power required for a 1 minute Sikorsky Prize flight is currently estimated at 550 Watts for an 80 kg pilot like Todd. The figure below shows the power output of the average fit male, alongside that of cycling legend Eddy Mercks, and two recent laboratory ergometer tests from Todd Reichert. All of Todd’s is training is focused on efforts of 5 minutes or less, which is why his numbers exceed that of Merckx who was typically more of an endurance athlete. At 772 Watts for 1 minute, our pilot’s power output exceeds the power requirements of the helicopter by a safe margin.