235:
rotational speed avoids this problem, but presents another. In the traditional method of the composition of velocity it is easy to understand that the velocity experienced by the retreating blade has a value that is produced by the vector composition of the velocity of blade rotation and the freestream velocity. In this condition it is evident that in presence of a sufficiently high advance ratio the velocity of air on the retreating blade is low. The flapping movement of the blade changes the angle of attack. It is then possible for the blade to reach the stall condition. In this case it is necessary that the stalling blade increases the pitch angle to keep some lift capability. This risk puts constraints on the design of the system. An accurate choice of the wing profile is necessary and careful dimensioning of the radius of the rotor for the specified speed range.
145:
it precisely. It had three flat surfaces and a rudder; the rear edge of one of surfaces could be bent, replacing the action of an elevator. Lift and thrust had to be created by paddle wheels consisting of 12 blades, established in pairs under a 120° angle. The blades of a concave shape were changing an angle of incidence by the means of eccentrics and springs. In a bottom of the craft 10 hp engine was arranged. Transmission was ensured by a belt. Empty weight was about 200 kg. "Samoljot" was constructed by the military engineer E.P. Sverchkov with the grants of the Main
Engineering Agency in St. Petersburg in 1909, was demonstrated at the Newest Inventions Exhibition and won a medal. Otherwise, it could not pass the preliminary tests without flying.
164:
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. There appears to be no evidence that this design was ever built, let alone flown. Based on Rohrbach's paddle-wheel research, however, Platt in the US designed by 1933 his own independent Cyclogyro. His paddle-wheel wing arrangement was awarded a US patent (which was only one of many similar patents on file), and underwent extensive wind-tunnel testing at MIT in 1927. Despite this, there is no evidence Platt's aircraft was ever built.
338:
rotational velocities makes it difficult to implement an actuator based mechanism, which calls for a fixed or variable shape track for pitch control, mounted parallel to blade trajectory, onto which are placed blade's followers such as rollers or airpads - the pitch control track shape reliably determines blade's pitch along the orbit regardless of the blade's RPM. While the pitching motions used in hover are not optimized for forward flight, in experimental evaluation they were found to provide efficient flight up to an advance ratio near one.
20:
211:
77:
114:
320:. This is attributed to utilizing unsteady lift and consistent blade aerodynamic conditions. The rotational component of velocity on propellers increases from root to tip and requires blade chord, twist, airfoil, etc., to be varied along the blade. Since the cyclorotor blade span is parallel to the axis of rotation, each spanwise blade section operates at similar velocities and the entire blade can be optimized.
239:
independent actuation of the blades which have been recently patented and successfully tested for naval use by use on hydraulic actuation system. The horizontal axis of rotation always provides an advancement of the upper blades, that produce always a positive lift by the full rotor. These characteristics could help overcome two issues of helicopters: their low
404:
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367:
547:
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171:. Its origins date to the decision of the Voith company to focus on the business of transmission gear assemblies for turbines. The famous Voight propeller was based on its fluid-dynamics know-how gained from previous turbine projects. It was invented by Ernst Schneider, and enhanced by Voith. It was launched with name of
252:
rotation around a point that rotating describes an ideal circumference. The combination of the advancement motion of the centre of rotation of the blade and the oscillation of the blade (it is a movement somehow similar to the pendulum), which continue to vary its pitch generate a complex set of aerodynamic phenomena:
384:
successfully commercially employed the propeller. This Voith-Schneider propeller was fitted to more than 100 ships prior to the outbreak of the Second World War. Today, the same company sells the same propeller for highly manoeuvrable watercraft. It is applied on offshore drilling ships, tugboats, and ferries.
443:
A large exposed area makes airships susceptible to gusts and difficult to takeoff, land, or moor in windy conditions. Propelling airships with cyclorotors could enable flight in more severe atmospheric conditions by compensating for gusts with rapid thrust vectoring. Following this idea, the US Navy
383:
fitted a pair of cyclorotors to a 32 ft boat in
Washington, which eliminated the need for a rudder and provided extreme manoeuvrability. While the idea floundered in the United States after the Kirsten-Boeing Propeller Company lost a US Navy research grant, the Voith-Schneider propeller company
238:
Slow speed cyclorotors bypass this problem through a horizontal axis of rotation and operating at a comparatively low blade tip speed. For higher speeds, which may become necessary for industrial applications, it seems necessary to adopt more sophisticated strategies and solutions. A solution is the
234:
and sonic blade tip constraints. As helicopters fly forward, the tip of the advancing blade experiences a wind velocity that is the sum of the helicopter forward speed and rotor rotational speed. This value cannot exceed the speed of sound if the rotor is to be efficient and quiet. Slowing the rotor
206:
resist rotation. For many practical applications (helicopters, airplanes, ships) this requires rotating the entire vessel. In contrast, cyclorotors need only to vary the blade pitch motions. Since there is little inertia associated with blade pitch change, thrust vectoring in the plane perpendicular
163:
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
144:
The origin of the rotocycloid propeller are
Russian and relates to the aeronautic domain. Sverchkov's "Samoljot" (St. Petersburg, 1909) or "wheel orthopter" was the first vehicle expressly thought to have used this type of propulsion. Its scheme came near to cyclogiro, but it's difficult to classify
328:
Cyclorotor blades require support structure for their positioning parallel to the rotor axis of rotation. This structure, sometimes referred to as "spokes," adds to the parasite drag and weight of the rotor. Cyclorotor blades are also centrifugally loaded in bending (as opposed to the axial loading
267:
The two effects are evidently correlated with a general increase of the thrust produced. If compared to a helicopter or any other propeller, it is evident that the same blade section in a rotocycloid produces much more thrust at the same
Reynolds number. This effect can be explained by considering
175:
Propeller (VSP) for commercial vessels. This new marine drive could significantly improve the manoeuvrability of a ship as demonstrated in the successful sea trials on the test boat
Torqueo, in 1937. The first Voith Schneider Propellers were put into operation in the narrow canals of Venice, Italy.
287:
makes cyclorotors more efficient at small scales, low velocities, and high altitudes than traditional propellers. It is otherwise evident that many living beings, such as birds, and some insects, are still much more efficient, because they can change not only the pitch but also the shape of their
337:
Cyclorotors require continuously actuated blade pitch. The relative flow angle experienced by the blades as they rotate about the rotor varies substantially with advance ratio and rotor thrust. To operate most efficiently a blade pitch mechanism should adjust for these diverse flow angles. High
275:
and laminar flow conditions can be reached. Considering a traditional wing profile it is evident that those conditions minimize the speed differences between upper and lower face of the wing. It is then evident that both lift and stall speed are reduced. A consequence is a reduction of angle of
251:
The advancement of the blades and oscillations are the two dynamic actions which are produced by a cyclorotor. It is evident that the wing-blades of a cyclorotor operates in different way than a traditional aircraft wing or a traditional helicopter wing. The blades of a cyclorotor oscillates by
419:
for lift and often also for propulsion and control. Advances in cyclorotor aerodynamics made the first untethered model cyclogyro flight possible in 2011 at the
Northwestern Polytechnic Institute in China. Since then, universities and companies have successfully flown small-scale cyclogyros in
455:
crashed while transiting a squall line on 3 September 1925 before any possible installation and testing. No large scale tests have been attempted since, but a 20 m (66 ft) cyclorotor airship demonstrated improved performance over a traditional airship configuration in a test.
427:
can stay aloft for only minutes. Cyclorotor MAVs (very small scale cyclogyros) could utilize unsteady lift to extend endurance. The smallest cyclogyro flown to date weighs only 29 grams and was developed by the advanced vertical flight laboratory at Texas A&M university.
295:
Some research tries to acquire the same level of efficiency of the natural examples of wings or surfaces. One direction is to introduce morphing wing concepts. Another relates to the introduction of boundary layer control mechanisms, such as dielectric barrier discharge.
1317:
Benedict, Moble; Jarugumilli, Tejaswi; Lakshminarayan, Vinod & Chopra, Inderjit (April 2012). "Experimental and
Computational Studies to Understand the Role of Flow Curvature Effects on the Aerodynamic Performance of a MAV-Scale Cycloidal Rotor in Forward Flight".
64:. A unique aspect is that it can change the magnitude and direction of thrust without the need of tilting any aircraft structures. The patented application, used on ships with particular actuation mechanisms both mechanical or hydraulic, is named after German company
279:
In this regime, conventional propellers and rotors must use larger blade area and rotate faster to achieve the same propulsive forces and lose more energy to blade drag. It is then evident that a cyclorotor is much more energy efficient than any other propeller.
378:
The most widespread application of cyclorotors is for ship propulsion and control. In ships the cyclorotor is mounted with the axis of rotation vertical so that thrust can quickly be vectored in any direction parallel to the plane of the water surface. In 1922,
47:
into the acceleration of a fluid using a rotating axis perpendicular to the direction of fluid motion. It uses several blades with a spanwise axis parallel to the axis of rotation and perpendicular to the direction of fluid motion. These blades are cyclically
176:
During the 1937 World Fair in Paris, Voith was awarded the grand prize – three times – for its exhibition of Voith
Schneider Propellers and Voith turbo-transmissions. A year later, two of Paris' fire-fighting boats started operating with the new VSP system.
201:
produce thrust only along their axis of rotation and require rotation of the entire device to alter the thrust direction. This rotation requires large forces and comparatively long time scales since the propeller inertia is considerable, and the rotor
329:
on propellers), which requires blades with an extremely high strength to weight ratio or intermediate blade support spokes. Early 20th century cyclorotors featured short blade spans, or additional support structure to circumvent this problem.
60:) in any direction normal to the axis of rotation. Cyclorotors are used for propulsion, lift, and control on air and water vehicles. An aircraft using cyclorotors as the primary source of lift, propulsion, and control is known as a
1248:
Hwang, Seong; Min, Seung Yong; Jeong, In Oh; Lee, Yun Han & Kim, Seung Jo (5 April 2006). Matsuzaki, Yuji (ed.). "Efficiency Improvements of a New Vertical Axis Wind Turbine by Individual Active Control of Blade Motion".
1615:
Nozaki, Hirohito; Sekiguchi, Yuya; Matsuuchi, Kazuo; Onda, Masahiko; Murakami, Yutaka; Sano, Masaaki; Akinaga, Wakoto & Fujita, Kazuhiro (4 May 2009). "Research and Development on Cycloidal Propellers for Airships".
88:
over time. The joint action of the advancement produced by the orbital motion and pitch angle variation generates a higher thrust at low speed than any other propeller. In hover, the blades are actuated to a positive
93:(outward from the centre of the rotor) on the upper half of their revolution and a negative pitch (inward towards the axis of rotation) over the lower half inducing a net upward aerodynamic force and opposite fluid
1100:
Gagnon, Louis; Wills, David; Xisto, Carlos; Schwaiger, Meinhard; Masarati, Pierangelo; Xisto, Carlos M.; Pascoa, Jose; Castillo, Mike & Ab Sa, Mehdi (2014). "PECyT - Plasma Enhanced Cycloidal Thruster".
526:, Josef Hochleitner & Harald Gross, "Device for controlling a cycloid propeller for watercraft", issued 21 June 1988, assigned to Siemens AG and J. M. Voith GmbH
304:
During experimental evaluation, cyclorotors produced little aerodynamic noise. This is likely due to the lower blade tip speeds, which produce lower intensity turbulence following the blades.
808:
Benedict, Moble; Ramasamy, Manikandan & Chopra, Inderjit (July–August 2010). "Improving the Aerodynamic Performance of Micro-Air-Vehicle-Scale Cycloidal Rotor: An Experimental Approach".
283:
Actual cyclorotors bypass this problem by quickly increasing and then decreasing blade angle of attack, which temporarily delays stall and achieves a high lift coefficient. This
872:
Marchetti, Karen; Price, Trevor & Richman, Adam (September 1995). "Correlates of wing morphology with foraging behaviour and migration distance in the genus Phylloscopus".
1487:
Benedict, Moble; Shrestha, Elena; Hrishikeshavan, Vikram & Chopra, Inderjit (2014). "Development of a 200 gram Twin-Rotor Micro Cyclocopter Capable of Autonomous Hover".
358:, with large benefits with respect to traditional VAWTs. This kind of turbine is stated to overcome most of the traditional limitations of traditional Darrieus VAWTs.
152:
addressed the Russian government with the project of the cyclogiro-like aircraft, his scheme was similar to Sverchkov's "Samoljot". The project was not carried out.
601:
Jarugumilli, Tejaswi; Benedict, Moble & Chopra, Inderjit (4 January 2011). "Experimental Optimization and Performance Analysis of a MAV Scale Cycloidal Rotor".
84:
Cyclorotors produce thrust by combined action of a rotation of a fixed point of the blades around a centre and the oscillation of the blades that changes their
750:, Herbert Perfahl, "Cycloidal propeller, especially for ship propulsion", issued 27 March 2002, assigned to Voith Hydro Holding GmbH and Co KG
720:
Benedict, Moble; Jarugumilli, Tejaswi & Chopra, Inderjit (2013). "Effect of Rotor Geometry and Blade Kinematics on Cycloidal Rotor Hover Performance".
545:, Prof Dr Rainer, "Voith-Schneider perpendicular propeller with blades which can be orientated in the longitudinal direction of the ship"
423:
The performance of traditional rotors is severely deteriorated at low Reynolds Numbers by low angle-of-attack blade stall. Current hover-capable
781:
Mayo, David B.; Leishman, Gordon (1 April 2010). "Comparison of the Hovering Efficiency of Rotating Wing and Flapping Wing Micro Air Vehicles".
507:, Wolfgang Baer, "Rotary blade propeller with protection against overload", issued 22 March 1966, assigned to J. M. Voith GmbH
1633:
1531:
1335:
1118:
1042:
1009:
647:
618:
1418:
Kirke, Brian; Lazauskas, Leo (March 2011). "Limitations of fixed pitch Darrieus hydrokinetic turbines and the challenge of variable pitch".
1153:
1066:
1462:
1602:
Technical Report, National Advisory Committee for Aeronautics Translation from Zeitschrift fĂĽr Flugtechnik und Motorluftschiffahrt
1187:"Design, Development, and Flight Test of a Small-Scale Cyclogyro UAV Utilizing a Novel Cam-Based Passive Blade Pitching Mechanism"
664:
227:, which, in theory, would enable a cyclogyro aircraft to fly at subsonic speeds well exceeding those of single rotor helicopters.
952:
97:. By varying the phase of this pitch motion the force can be shifted to any perpendicular angle or even downward. Before blade
911:
1351:
Jarugumilli, Tejaswi (2012). "Experimental Investigation of the Forward Flight Performance of a MAV-Scale Cycloidal Rotor".
1394:
1079:
845:
Leger Monteiro, Jakson Augusto; Páscoa, José C. & Xisto, Carlos M. (2016). "Aerodynamic optimization of cyclorotors".
1514:
Runco, Carl C.; Coleman, David; Benedict, Moble (4 January 2016). "Design and Development of a Meso-Scale Cyclocopter".
355:
240:
483:
371:
1548:
874:
432:
190:
1398:
1266:
1166:
817:
231:
1681:
445:
1366:
Lazauskas, Leo (January 1992). "Three pitch control systems for vertical axis wind turbines compared".
1258:
909:
Monkkonen, Mikko (September 1995). "Do migrant birds have more pointed wings?: a comparative study".
679:
1403:
1271:
1691:
1686:
1447:
822:
284:
1654:
1284:
1251:
Proceedings of SPIE, Smart Structures and Materials 2006: Smart Structures and Integrated Systems
928:
891:
663:
Benedict, Moble; Mattaboni, Mattia; Chopra, Inderjit & Masarati, Pierangelo (November 2011).
80:
A cyclorotor generates thrust by altering the pitch of the blade as it transits around the rotor.
1029:[Aeroelasticity of Aeronautical Systems Immersed in Subsonic Flows – A New Methodology]
1027:"Aeroelasticidad de Sistemas Aeronáuticos Inmersos en Flujos SubsĂłnicos – Una Nueva MetodologĂa"
19:
1629:
1527:
1331:
1114:
1038:
1005:
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643:
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424:
380:
149:
98:
580:
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1496:
1427:
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Controle da variação do arqueamento de um aerofólio utilizando atuadores de memória de forma
961:
920:
883:
854:
827:
790:
729:
687:
639:
606:
477:
194:
1445:
Levinson, M. (1991). "Illegal Immigrant Extraordinary: The Aeronautical Years, 1920-1938".
1155:
Fundamental Understanding of the Cycloidal-Rotor Concept for Micro Air Vehicle Applications
210:
1553:
260:
172:
85:
1262:
1025:
Roccia, Bruno; Preidikman, Sergio; GĂłmez, Cynthia & Ceballos, Luis (November 2014).
683:
76:
1185:
Adams, Zachary; Benedict, Moble; Hrishikeshavan, Vikram; Chopra, Inderjit (June 2013).
695:
156:
1026:
113:
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474: – Aircraft configuration that uses a horizontal-axis cyclorotor as a rotor wing
313:
224:
1288:
932:
947:
747:
351:
317:
160:
57:
1134:
Boschma, J.; McNabb, M. (1998). "Cycloidal Propulsion for UAV VTOL Applications".
1431:
1387:
Development and evaluation of passive variable-pitch vertical axis wind turbines
1253:. Smart Structures and Materials 2006: Smart Structures and Integrated Systems.
444:
seriously considered fitting of six primitive Kirsten-Boeing cyclorotors to the
90:
65:
49:
214:
Cyclorotors can quickly vector thrust by altering the pattern of blade pitching
1203:
1186:
858:
416:
272:
198:
44:
561:
542:
1001:
665:"Aeroelastic analysis of a micro-air-vehicle-scale cycloidal rotor in hover"
471:
412:
398:
289:
203:
61:
975:
794:
523:
504:
101:, increasing the amplitude of the pitching kinematics will magnify thrust.
230:
Single rotor helicopters are limited in forward speed by a combination of
948:"The hydrodynamic function of shark skin and two biomimetic applications"
94:
1625:
1523:
1327:
1110:
354:
are a potential application of cyclorotors. They are named in this case
966:
924:
895:
610:
465:
1500:
1280:
733:
691:
403:
366:
288:
wings, or they can change the property of the boundary layer such as
53:
887:
831:
415:
is a vertical takeoff and landing aircraft using a cyclorotor as a
1233:
Strandgren, C. (1933). "The Theory of the Strandgren Cyclogyiro".
402:
365:
209:
168:
75:
18:
1075:
1218:
Wheatley, J. (1935). "Wind-Tunnel Tests of a Cyclogiro Rotor".
998:
Flow Phenomena in Nature: Inspiration, learning and application
1390:
1162:
108:
1575:
1302:
Clark, Robert (24 July 2006). "VTOL to Transonic Aircraft".
189:
Cyclorotors provide a high degree of control. Traditional
1035:
III Congreso Argentino de IngenierĂa Aeronáutica (Caia 3)
259:
an increase of the maximum blade lift coefficient at low
1618:
18th AIAA Lighter-Than-Air Systems Technology Conference
167:
The first operative cycloid propulsion was developed at
766:
Eastman, Fred (1945). "The Full-Feathering Cyclogiro".
585:
Disc Aircraft of the Third Reich (1922-1945 and Beyond)
435:
are being developed by D-Daelus and Pitch Aeronautics.
125:
23:
Cyclorotor before installation on small-scale cyclogyro
1655:"Non-tilting cyclorotor drone boasts unique abilities"
316:
than comparable scale traditional rotors at the same
312:
In small-scale tests, cyclorotors achieved a higher
1103:
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference
468: – Curve traced by a point on a rolling circle
1320:American Institute of Aeronautics and Astronautics
1147:
1145:
223:Cyclorotors can produce lift and thrust at high
1600:Sachse, H. (1926). "Kirsten-Boeing Propeller".
636:The Helicopter: Thinking Forward, Looking Back
276:attack at which stall conditions are reached.
946:Oeffner, Johannes; Lauder, George V. (2012).
847:Aircraft Engineering and Aerospace Technology
43:, is a fluid propulsion device that converts
8:
1180:
1178:
1176:
486: – Proprietary marine propulsion system
219:High advance ratio thrust and symmetric lift
1235:National Advisory Committee for Aeronautics
1220:National Advisory Committee for Aeronautics
1191:International Journal of Micro Air Vehicles
16:Perpendicular axis marine propulsion system
1353:Journal of the American Helicopter Society
1136:Naval Air Warfare Center-Aircraft Division
783:Journal of the American Helicopter Society
596:
594:
356:variable-pitch vertical-axis wind turbines
1402:
1270:
1202:
965:
821:
768:University of Washington Technical Report
268:the traditional behavior of a propeller.
271:At low Reynolds numbers there is little
148:In 1914, Russian inventor and scientist
496:
52:twice per revolution to produce force (
1549:"How D-Dalus Flies Like Nothing Else"
7:
1065:de Faria, Cássio Thomé (July 2010).
603:49th AIAA Aerospace Sciences Meeting
1547:Miller, Kaitlin (27 January 2012).
1304:SBIR A02.07: Final Technical Report
155:In 1933, experiments in Germany by
1385:Pawsey, N. C. K. (November 2002).
243:and the advance ratio limitation.
207:to the axis of rotation is rapid.
14:
374:with thrust plate on a tug's hull
1152:Moble, Benedict (January 2010).
180:Design advantages and challenges
112:
1463:"Voith Schneider Propeller VSP"
953:Journal of Experimental Biology
439:Airship propulsion and control
407:Concept drawing of a cyclogyro
1:
1576:"Industrial Inspection Drone"
1395:University of New South Wales
256:the delay of the blade stall;
1432:10.1016/j.renene.2010.08.027
634:Leishman, J. Gordon (2007).
543:US Withdrawn DE3214015A1
581:"Rohrbach Cyclogyro (1933)"
362:Ship propulsion and control
1708:
1080:SĂŁo Paulo State University
996:Liebe, R. J., ed. (2006).
748:EP Expired EP0785129B1
480: – Aircraft component
396:
333:Blade pitch considerations
308:Hovering thrust efficiency
1653:Blain, Loz (2022-06-06).
1204:10.1260/1756-8293.5.2.145
859:10.1108/AEAT-02-2015-0051
562:"History of the Rotoplan"
524:US Expired US4752258A
505:US Expired US3241618A
484:Voith Schneider Propeller
372:Voith Schneider propeller
324:Structural considerations
875:Journal of Avian Biology
420:several configurations.
62:cyclogyro or cyclocopter
1167:University of Maryland
795:10.4050/JAHS.55.025001
642:: College Park Press.
408:
375:
232:retreating blade stall
215:
185:Rapid thrust vectoring
81:
24:
431:Commercial cyclogyro
406:
369:
247:Unsteady aerodynamics
213:
79:
22:
912:Evolutionary Ecology
1626:10.2514/6.2009-2850
1524:10.2514/6.2016-1255
1489:Journal of Aircraft
1467:Voith GmbH & Co
1448:Journal of the West
1328:10.2514/6.2012-1629
1263:2006SPIE.6173..316H
1111:10.2514/6.2014-3854
1078:) (in Portuguese).
810:Journal of Aircraft
722:Journal of Aircraft
684:2011AIAAJ..49.2430B
72:Operating principle
37:cycloidal propeller
967:10.1242/jeb.063040
925:10.1007/BF01237833
611:10.2514/6.2011-821
409:
376:
216:
124:. You can help by
82:
25:
1635:978-1-62410-158-8
1580:Pitch Aeronautics
1533:978-1-62410-388-9
1501:10.2514/1.C032218
1337:978-1-60086-937-2
1281:10.1117/12.658935
1120:978-1-62410-303-2
1044:978-950-34-1152-0
1011:978-1-84564-095-8
734:10.2514/1.C031461
701:on 7 January 2017
692:10.2514/1.J050756
678:(11): 2430–2443.
649:978-0-96695-531-6
620:978-1-60086-950-1
381:Frederick Kirsten
241:energy efficiency
204:gyroscopic forces
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728:(5): 1340–1352.
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694:. Archived from
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1676:Categories
1664:2022-06-06
1257:: 617311.
491:References
453:Shenandoah
448:Shenandoah
417:rotor wing
393:Cyclogyros
273:turbulence
191:propellers
133:March 2016
29:cyclorotor
1659:New Atlas
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472:Cyclogyro
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566:Rotoplan
460:See also
388:Aircraft
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105:History
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300:Noise
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425:MAVs
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