Basic Helicopter Aerodynamics

Seddon, John M.; Newman, S.J.

doi:10.1002/9781119994114

Cited by 166 publications

(157 citation statements)

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“…Momentum theory can be used to provide models for the Normal and Windmill Brake state [83]. However, momentum theory fails in the Vortex Ring and Turbulent Wake states.…”

Section: Effect Of Vertical Descentmentioning

confidence: 99%

Energetics in robotic flight at small scales

Karydis

Kumar

2017

Interface Focus.

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Recent advances in design, sensing and control have led to aerial robots that offer great promise in a range of real-world applications. However, one critical open question centres on how to improve the energetic efficiency of aerial robots so that they can be useful in practical situations. This review paper provides a survey on small-scale aerial robots (i.e. less than 1 m 2 area foot print, and less than 3 kg weight) from the point of view of energetics. The paper discusses methods to improve the efficiency of aerial vehicles, and reports on recent findings by the authors and other groups on modelling the impact of aerodynamics for the purpose of building energy-aware motion planners and controllers.

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“…Momentum theory can be used to provide models for the Normal and Windmill Brake state [83]. However, momentum theory fails in the Vortex Ring and Turbulent Wake states.…”

Section: Effect Of Vertical Descentmentioning

confidence: 99%

Energetics in robotic flight at small scales

Karydis

Kumar

2017

Interface Focus.

View full text Add to dashboard Cite

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“…Una relación entre el empuje producido y la velocidad comunicada al aire se puede obtener por la aplicación de la mecánica de Newton por medio de las leyes de conservación de la masa, cantidad de movimiento -energía, y la energía del proceso global. Este enfoque se conoce comúnmente como la teoría de impulso para helicópteros, la relación entre el empuje y la velocidad es (Seddon, 1990):…”

Section: Teoría De Cantidad De Movimientounclassified

“…En vuelo axial ascendente existe una velocidad relativa entre la hélice y el aire (Seddon, 1990) lo que implica que ≠ 0. Se considera una velocidad máxima de ascenso de 6 m/s por lo cual la potencia requerida para este tipo de maniobra es igual a 254.46 W. Se puede observar que en vuelo a descenso se obtiene una potencia nula para velocidades de 15,4 m/s, además la potencia requerida es la misma para un descenso de hasta 13 m/s, por seguridad se tomará como velocidad máxima de descenso un valor de 6 m/s.…”

Section: Potencia En Vuelo Axial Ascendente Y Descendenteunclassified

Análisis Y Diseño De Una Aeronave No Tripulada Para Uso Agrícola

Chávez

Sampedro

Reyes

et al. 2017

ESJ

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The present research proposes to diversify the use of unmanned aerial vehicles (UAV) with rotating wings for applications in the agricultural sector. For this we have analyzed and designed an unmanned aircraft. In first instance the applications of this type of aircraft in this sector were reviewed to determine possible design conditions that would aid in the sizing and design of the aircraft. Once the requirements had been determined, aerodynamic analysis was carried out to size up and launch the required power output for the craft. This in order to optimize the weight and autonomous fight time to finally design an aircraft prototype built in carbon fiber with the aid of fault theories as applied to composite materials. At the end of the research, an unmanned aircraft of 6 rotors, each with an installed power supply of 700W was designed. The aircraft has an autonomous flight time of 40 minutes without a payload, 20 minutes with a payload of 3Kg, and 8 minutes with a payload of 5Kg. The commercial application of these aircraft are the monitoring of land and fumigation in inaccessible areas.

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“…This is a significant simplification of the problem and quantitative determination of finite wing aerodynamics calls for a more accurate model [15]. Thus, we find it necessary to further develop the approach by setting the circulation strength along the wing to an elliptic distribution which from lifting line theory is known to produce a constant downwash velocity distribution [15,16]. Since lift and hence bound circulation falls to zero at the inboard edge of the wing and there is no carryover of lift to the opposite wing [9,17,18] [19].…”

Section: Lettermentioning

confidence: 99%