Roto-Cycloid Propelled Airship Dimensioning and Energetic Equilibrium

Trancossi, Michele; Dumas, Antonio; Xisto, Carlos; Páscoa, José; Andrisani, Andrea

doi:10.4271/2014-01-2107

Cited by 9 publications

(8 citation statements)

References 17 publications

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“…To this end, data for a cyclogyro of similar dimensions as the wind turbine, operating in propulsion mode (V wind = 0), is used. This configuration, here denominated IAT21-L3 rotor, was analysed as a part of a major European ongoing project, which aims to develop the cyclogyro technology as a mean of propulsion for small and medium size aircraft [12,[15][16][17][18][19]. It is obvious that the results obtained for the IAT21-L3 rotor does not faithfully represent the features of a VAWT, since in propulsion mode energy is being provided and not extracted from the flow.…”

Section: Numerical Methods and Validationmentioning

confidence: 99%

Numerical Analysis of Design Parameters With Strong Influence on the Aerodynamic Efficiency of a Small-Scale Self-Pitch VAWT

Xisto

Páscoa

Trancossi³

2015

Volume 1: Advances in Aerospace Technology

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Section: Numerical Methods and Validationmentioning

confidence: 99%

Numerical Analysis of Design Parameters With Strong Influence on the Aerodynamic Efficiency of a Small-Scale Self-Pitch VAWT

Xisto

Páscoa

Trancossi³

2015

Volume 1: Advances in Aerospace Technology

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“…The possibilities disclosed by cyclorotors seem allowing novel VTOL aircraft architectures. If the design attention is focused on performance, it allows definition of novel air vehicle concepts, which can reach high subsonic speeds and higher energy efficiency than helicopters [17]. Despite their recent improvements, cyclorotors present actual limits in term of affordability at high rotation speed and of induced vibration, which is due to both aerodynamic forces and change in inertia moment.…”

Section: Cyclorotorsmentioning

confidence: 99%

“…Similar weights can be easily assumed by carbon fibres components, which could allow higher resistance but has higher costs. Energy balance is produced by considering equation (16) and (17). A reference profile mission is defined in Figure 32.…”

Section: Energy Balancementioning

confidence: 99%

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A New Propelled Wing Aircraft Configuration

Trancossi

Stewart

Páscoa

2016

Volume 1: Advances in Aerospace Technology

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This paper investigates by an energetic approach possible new configurations of aircrafts, which can rival in low speed operations against helicopters. It starts from an effective energy balance of helicopters during fundamental operations: takeoff, horizontal flight, hovering, and landing. The energy state of a helicopter can be written as: E = ½ mV2 + mgh + ½ I ω2 (1) where m is mass of helicopter, I is total rotor inertia, ω is rotor rotational speed. By taking the partial derivative with respect to time of equation 1, the power is expressed as dE/dt = ΔP = mV dV/dt + mg dh/dt (2) By optimizing the energy balance of the helicopter a new aircraft configuration has been obtained that allow a very high lift even at very low speed, but drastically reducing the energy consumption during horizontal flight. The total power required is obtained by rotor power and overall efficiency factor (η) and HPreq total = η HPreq rotor. By equations (1) and (2) it has been produced a preliminary optimization in different operative conditions considering a speed range from 0.5 (hovering conditions) to 50 m/s. By an accurate balance of the results, it has been identified that the most disadvantageous situation for a helicopter is forward flight. A new powered wing architecture has been specifically studied for replicating the behaviour of helicopters. Preliminary it has been defined by starting from the energy equations the main characteristics of the propelled wing. From those numerical results it has been defined a new configuration of propelled wing and the new aircraft configuration which allow adequate performance against helicopter. Those wings take a large advantage of two not common features: symmetry with respect to a vertical axis and possibility of optimizing the shape for specific missions. It has been designed and optimized in different configurations by CFD. In particular, an accurate analysis of fluiddynamic of the system allows quantifying the different effects that allows realizing an extraordinary ratio between lift and thrust producing an effective vehicle that can rival against helicopter also at very low speeds with a morphing configuration that will be presented in the final paper because of patenting reasons. Results show that the proposed innovative aircraft configuration allows hovering and very low speed flight. In particular, the conditions and the design for this kind of operation are presented even if still in initial design stage. The presented aircraft architecture can also allow inverting the direction of motion just by inverting the direction of the thrust. In this case, it will allow overcoming completely the performances of helicopters. The energetic balance of flight has been evaluated and the advantages with respect to helicopters have been finally expressed with surprising results.

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“…Such system was never accepted in the aeronautical industry due to the lack of technology and due to the fact that old days analytical tools were unable to analyse the complex flow that was associated with the interaction between the pitching rotating blades. New advancements in technology are now opening the possibility of introducing the cyclorotor concept in the aeronautical market as a propulsion system for airships 5,6,7 and into disruptive aircrafts, see Fig. 1-b).…”

Section: Introductionmentioning

confidence: 97%

PECyT - Plasma Enhanced Cycloidal Thruster

Xisto¹,

Páscoa²,

Abdollahzadeh³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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In the following paper we introduce PECyT system for enhancing the aerodynamic efficiency of cycloidal rotors. For that purpose the incorporation of Dielectric Barrier Discharge plasma actuators for active flow control on a pitching airfoil, under deep-stall conditions, will be assessed using a numerical tool. Two different arrangements of DBD actuators will be analysed, namely single- and multi-DBDs configurations. For the single- DBD plasma actuator the effect of different modes of actuation on the lift coefficient will also be studied. We will show that the multi-DBD actuator, in a steady-actuation mode, could delay stall and allows for a faster reattachment of the flow. However during the downstroke phase of the pitching cycle the unsteady operation of a single-DBD gives us the best results in terms of lift coefficient

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Roto-Cycloid Propelled Airship Dimensioning and Energetic Equilibrium

Cited by 9 publications

References 17 publications

Numerical Analysis of Design Parameters With Strong Influence on the Aerodynamic Efficiency of a Small-Scale Self-Pitch VAWT

Numerical Analysis of Design Parameters With Strong Influence on the Aerodynamic Efficiency of a Small-Scale Self-Pitch VAWT

A New Propelled Wing Aircraft Configuration

PECyT - Plasma Enhanced Cycloidal Thruster

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