An Energy Method for Prediction of Helicopter Maneuverability

Wood, T.; Livingston, C L

doi:10.21236/ada021266

Cited by 4 publications

(8 citation statements)

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“…Assuming a symmetric shape aerodynamic lift is neglected. (1) If we consider the helicopter energy model defined by Wood [3] and Zuang [4], the energy state of a helicopter during flight is given by equation (1): (2) By taking the partial derivative with respect to time of equation 1, the energy rate is expressed as: (3) In which it can be assumed that the angular acceleration is negligible against other terms. Equation (3) reduces to the following: (3')…”

Section: Control Propulsion and Energy Assessment Of A Spherical Uasmentioning

confidence: 99%

Control, Propulsion and Energy Assessment of a Spherical UAS for Low Speed Operations

Bandycki

Trancossi

Páscoa

2017

SAE Technical Paper Series

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This paper presents a comparison between different hypotheses of propulsion of a spherical UAS. Different architectures have been analyzed assessing their specific aerodynamic, energetic, and flight mechanics features. The comparison has been performed assuming the robustness of flight control in different wind conditions, defining for each the specific operative ranges, mission profiles, and energy assessment. An effective energy assessment and comparison against a commercial UAS has been produced. Even if the paper considers a preliminary simplified configuration, it demonstrates clearly to be competitive against traditional quadcopters in a predefined reference mission.

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Section: Control Propulsion and Energy Assessment Of A Spherical Uasmentioning

confidence: 99%

Control, Propulsion and Energy Assessment of a Spherical UAS for Low Speed Operations

Bandycki

Trancossi

Páscoa

2017

SAE Technical Paper Series

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“…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.…”

Section: Hp Req Total = η Hp Req Rotormentioning

confidence: 99%

“…It is possible to produce an effective definition of a realistic even if simplified energy model that allow weighting the energy needs for different operations, which are necessary for power dimensioning of different flight conditions. According to Wood [1] and Zuang [6] the energy model of a helicopter during flight is given by equation…”

Section: Energy Balancementioning

confidence: 99%

“…According to Figure 1, it is possible to describe different flight conditions (Appendix 1). Wood [1] and Zuang [47] have developed helicopters energetic flight models of a helicopter. A measure of the energy state of a helicopter at any altitude airspeed-RPM combination can be expressed as: 1…”

Section: Energy Model Of An Helicoptermentioning

confidence: 99%

“…With the development of aviation technology, helicopter has coupled effective performances and flexibility [1][2][3] with lower energy efficiency than any other vehicle [4]. This paper takes the moves from the optimization of the energy balance of a helicopter in flight and by optimizing this model arrives to the definition of a new vehicle concept, which can do anything that a helicopter can do with mayor energetic benefits.…”

Section: Introductionmentioning

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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An Integrated System of Airborne and Ground-Based Instrumentation for Flying Qualities Research with the X-22A Airplane

Beilman

1973

j am helicopter soc

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An Energy Method for Prediction of Helicopter Maneuverability

Cited by 4 publications

References 0 publications

Control, Propulsion and Energy Assessment of a Spherical UAS for Low Speed Operations

Control, Propulsion and Energy Assessment of a Spherical UAS for Low Speed Operations

A New Propelled Wing Aircraft Configuration

An Integrated System of Airborne and Ground-Based Instrumentation for Flying Qualities Research with the X-22A Airplane

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