Летающий комбайн

Группа Арей Состояние темы в мире

VTOL cycloidal rotors, cyclogyro, Cyclocopter, cycloidal-rotor aircraft, Разработка авиационных транспортных средств вертикального взлета и посадки на основе крыльчатых воздушных движителей. //  arey-group.ru

 

Новый импульс развитию темы КД в США придали усилия соискателя ученой степени Мобле Бенедикта, который, под руководством профессора Индержита Чопра, к 2010 году проделал огромную работу, обобщая мировой опыт, конструируя движители и тестовое оборудование, исследуя и экспериментируя

 

USA-BenMob.jpg @ arey-group.ru [кеш]

Quad-cyclocopter.jpg @ arey-group.ru [кеш]

Группа АРЕЙ история

Разработка авиационных транспортных средств вертикального взлета и посадки на основе крыльчатых воздушных движителей. //  arey-group.ru

 

72.jpg @ arey-group.ru [кеш]

Cyclogyro - Wikipedia

The cyclogyro, or cyclocopter, is an aircraft configuration that uses a horizontal-axis cyclorotor as a rotor wing to provide lift and sometimes also propulsion and control. In principle, the cyclogyro is capable of vertical take off and landing and hovering performance like a helicopter, while potentially benefiting from some of the advantages of a fixed-wing aircraft. The cyclogyro is distinct from the Flettner airplane which uses a cylindrical wing rotor to harness the Magnus effect. The cyclogyro wing resembles a paddle wheel, with airfoil blades replacing the paddles. //  Дальше — en.wikipedia.org

 

Cyclogyro-Mechanics.gif @ upload.wikimedia.org [кеш]

Rohrbach Cyclogyro

ROHRBACH CYCLOGYRO (1933)      By Rob Arndt In 1933, experiments in Germany by Adolf Rohrbach resulted in a paddle-wheel wing arrangement. Oscillating winglets went from positive to negative angles of attack during each revolution to create lift, and their eccentric mounting would, in theory, produce nearly any combination of horizontal and vertical forces.     The DVL evaluated Rohrbach’s design, but the foreign aviation journals of the time cast doubt on the soundness of the design which meant that funding for the project could not be raised, even with a latter proposal as a Luftwaffe transport aircraft. //  Дальше — discaircraft.greyfalcon.us

 

The Cyclogyros

Douglas Self, cyclogyro, cyclogyre, cyclogiro, Rohrbach //  web.archive.org

 

The Cyclogyros

Douglas Self, cyclogyro, cyclogyre, cyclogiro, Rohrbach //  www.douglas-self.com

 

Review of Historic and Modern Cyclogyro Design | Joint Propulsion Conferences

Search for more papers by this author Search for more papers by this author //  arc.aiaa.org

 

Aerodynamics of the Cyclogyro

Session EN - Aerodynamics. ORAL session, Monday morning, November 19 Manchester 1, Marriott Hotel and Marina San Diego The Cyclogiro is the name given by NASA researchers in the '30s to an aerodynamic configuration of several large aspect ratio rectangular airfoils with horizontal span, placed on the circumference of a vertical circle of radius of the order of the airfoil chord, and rotating around the circle center at high speed, with periodically changing angle of attack. This configuration produces aerodynamic forces that can be applied to lift and thrust, depending on the phase angle between the instantaneous position and angle of attack. //  Дальше — flux.aps.org

 

Aerodynamics of the Cyclogyro
Gil Iosilevski, Yuval Levy, Daniel Weihs (Faculty of Aerospace Engineering, Technion,Haifa 32000,Israel)

The Cyclogiro is the name given by NASA researchers in the '30s to an aerodynamic configuration of several large aspect ratio rectangular airfoils with horizontal span, placed on the circumference of a vertical circle of radius of the order of the airfoil chord, and rotating around the circle center at high speed, with periodically changing angle of attack. This configuration produces aerodynamic forces that can be applied to lift and thrust, depending on the phase angle between the instantaneous position and angle of attack. The original approach was to install such rotors instead of an aircraft wing, and thus combine the lift amp; thrust producing functions. As a result of the state of knowledge of unsteady aerodynamics at the time disparities between predictions and measured forces remained unexplained. This, combined with low efficiency resulted in the concept being abandoned. In the present study the concept is revisited, as a possible propulsor/lift generator for a hover-capable micro-UAV. Preliminary analysis showed that scaling down to rotor airfoil sizes of 10-15 cm span and 2 cm chord will reduce the centrifugal forces to manageable proportions while the aerodynamic forces would be comparable to those obtained by conventional rotors. A series of experiments was performed, showing disparities of up to 30theory. Visualization showed that this difference resulted mainly from interactions between single foil wakes with the following foils, and a numerical study confirmed the magnitude of the effects, in good agreement with the experiments.