Editing Juan de la Cierva (section)

==The gyroplane (autogyro)==
De la Cierva started building aircraft in 1912. In 1914, he designed and built a tri-motor aeroplane which was accepted by the Spanish government.<ref name ="Queensland Times"/> In 1919 he started to consider the use of a [[Helicopter rotor|rotor]] to generate lift at low airspeed, and eliminate the risk of [[Stall (fluid dynamics)|stall]].

[[File:Pitcairn Autogiro NASA GPN-2000-001990.jpg|thumb|right|[[Pitcairn PCA-2]] autogyro, built in the US under Cierva license, 1961.]]

In order to achieve this, he used the ability of a lifting rotor to [[Autorotation (helicopter)|autorotate]], whereby at a suitable pitch setting, a rotor will continue to rotate without mechanical drive, sustained by the torque equilibrium of the lift and drag forces acting on the blades.  With De la Cierva's autogyro, the rotor was drawn through the air by means of a conventional [[Propeller (aircraft)|propeller]], with the result that the rotor generated sufficient lift to sustain level flight, climb and descent.

Before this could be satisfactorily achieved, De la Cierva experienced several failures primarily associated with the unbalanced rolling movement generated when attempting take-off, due to [[dissymmetry of lift]] between the advancing and retreating blades. This major difficulty was resolved by the introduction of the flapping hinge. In 1923, De la Cierva's first successful autogyro was flown at Getafe aerodrome in Spain by Lt. Gomez Spencer.<ref name ="Queensland Times"/>

This pioneering work was carried out in De la Cierva's native Spain. In 1925, he brought his [[Cierva C.6|C.6]] to Britain and demonstrated it to the [[Air Ministry]] at [[Farnborough, Hampshire]]. This machine had a four blade rotor with flapping hinges but relied upon conventional airplane controls for [[Pitching moment|pitch]], roll and [[Yaw (rotation)|yaw]]. It was based upon an [[Avro 504K]] fuselage, initial rotation of the rotor was achieved by the rapid uncoiling of a rope passed around stops on the undersides of the blades.

The Farnborough demonstration was a great success, and resulted in an invitation to continue the work in the UK. As a direct result, and with the assistance of the Scottish industrialist [[James George Weir]], the Cierva Autogiro Company, Ltd., was formed the following year. From the outset De la Cierva concentrated upon the design and the manufacture of rotor systems, relying on other established aircraft manufacturers to produce the airframes, predominantly the [[Avro|A.V. Roe Company]].

The Avro built [[Cierva C.8|C.8]] was a refinement of the C.6, with the more powerful [[Armstrong Siddeley Lynx|180hp Lynx]] radial engine, and several C.8s were built. The C.8R incorporated drag hinges, due to blade flapping motion causing high blade root stresses in the rotor plane of rotation; this modification resulted in other problems such as ground resonance for which drag hinge dampers were fitted.

The resolution of these fundamental rotor problems opened the way to progress, confidence built up rapidly, and after several cross-country flights a C.8L4 was entered for the 1928 [[King's Cup Race|Kings Cup Air Race]]. Although forced to withdraw, the C.8L4 subsequently completed a {{convert|4800|km|mi|abbr=on}} tour of the British Isles. Later that year it flew from [[London]] to [[Paris]] thus becoming the first rotating wing aircraft to cross the [[English Channel]]. The tour was subsequently extended to include [[Berlin]], [[Brussels]] and [[Amsterdam]].

A predominant problem with the autogyro was driving the rotor prior to takeoff. Several methods were attempted in addition to the coiled rope system, which could take the rotor speed to 50% of that required, at which point movement along the ground to reach flying speed was necessary, while tilting the rotor to establish autorotation.

Another approach was to tilt the tail stabiliser to deflect engine slipstream up through the rotor. The most acceptable solution was finally achieved with the [[Cierva C.19|C.19 Mk.4]], which was produced in some quantities; a direct drive from the engine to the rotor was fitted, through which the rotor could be accelerated up to speed. The system was then declutched prior to executing the take-off run.

As De la Cierva's autogyros achieved success and acceptance, others began to follow and with them came further innovation. Most important was the development of direct rotor control through cyclic pitch variation, achieved initially by tilting the rotor hub and subsequently by [[Raoul Hafner]] by the application of a spider mechanism that acted directly on each rotor blade. The first production direct control autogyro was the [[Cierva C.30|C.30]], produced in quantity by Avro, [[Liore et Olivier]], and [[Focke-Wulf]]. This machine allowed for change of motion in any direction – upwards, downwards or sideways – by the tilting of the horizontal rotors and also effected a minimising of some of controls used in more conventional aircraft of the period.<ref>{{cite news |url=http://nla.gov.au/nla.news-article61735640 |title=New Autogiro  |newspaper=[[Townsville Daily Bulletin]] |volume=LV |issue=190 |location=Queensland, Australia |date=10 August 1933 |access-date=12 November 2021 |page=7}}</ref> Development of cyclic pitch variation was also influenced by the Dutch helicopter pioneer [[Albert Gillis von Baumhauer]], who adopted [[swashplate]] principle in his designs and probably influenced Cierva in their meeting in 1928.<ref name="Voogt">{{citation|doi=10.1179/1758120612Z.00000000022|url=https://www.academia.edu/2543089|title=The Transmission of Helicopter Technology, 1920–1939: Exchanges with von Baumhauer|journal=The International Journal for the History of Engineering & Technology|volume=83|pages=119–140|year=2013|last1=Voogt|first1=Alex de|s2cid=109718326}}</ref>

The introduction of jump take-off was another major improvement in capability. The rotor was accelerated in no-lift pitch until the rotor speed required for flight was achieved, and then declutched. The loss of torque caused the blades to swing forward on angled drag hinges with a resultant increase in collective pitch, causing the aircraft to leap into the air. With all the engine power now applied to the forward thrusting propeller, it was now possible to continue in forward flight with the rotor in autorotation.

The [[Cierva C.40|C.40]] was the first production jump takeoff autogyro.

Autogyros were built in many countries under De la Cierva licences, including France, Germany, Japan, Russia and the United States.

De la Cierva's motivation was to produce an aircraft that would not stall but near the end of his life he accepted the advantages offered by the helicopter and began the initial work towards that end. In 1936, the Cierva Autogiro Company, Ltd. responded to a British Air Ministry specification for a Royal Navy helicopter with the [[gyrodyne]].