Lockheed AH-56 Cheyenne

Lockheed AH-56 Cheyenne
Maa	Yhdysvallat
Rooli	Hyökkäyshelikopteri
Ensimmäinen lento	21. syyskuuta 1967
Rakennettu	10

Nniiden Lockheed AH-56 Cheyenne oli Lockheedin Yhdysvaltain armeijalle kehittämä hyökkäyshelikopteri. Se nousi armeijan Advanced Aerial Fire Support System (AAFSS) -ohjelmasta palvelun ensimmäiseen omistettuun hyökkäyshelikopteriin. Lockheed suunnitteli Cheyennen käyttämällä nelilapaista jäykkäroottorijärjestelmää ja konfiguroi lentokoneen yhdistelmähelikopteriksi, jossa oli matalalle asennetut siivet ja pyrstöön asennettu työntöpotkuri, jota ohjaa General Electric T64 -turboakselimoottori. Cheyennellä oli oltava nopea viivakyky tarjota aseistettu saattaja armeijan kuljetushelikoptereille, kuten Bell UH-1 Iroquois.

Lähde: Lockheed AH-56 Cheyenne Wikipediassa

AH-56 Cheyenne Walk Around
Valokuvaaja	Mikko Fortin
Lokalisointi	Ei tietää
Valokuvat	22

AH-56 Cheyenne 1

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AH-56 Cheyenne 8

AH-56 Cheyenne 9

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General Characteristics and Role

The Lockheed AH-56 Cheyenne was an advanced attack helicopter developed for the United States Army as part of the Advanced Aerial Fire Support System (AAFSS) program during the Vietnam War era. It featured a revolutionary design, combining the agility of a helicopter with the high speed of a fixed-wing aircraft. The Cheyenne utilized a rigid rotor system and a pusher propeller to achieve speeds far greater than conventional helicopters of the time. The aircraft incorporated a sophisticated stabilized gun turret and a separate crew station for the gunner, with the commander/pilot located behind. Though highly innovative and setting several speed records, the program was ultimately canceled in 1972 due to political infighting, high costs, and technical complexity, paving the way for the eventual development of the AH-64 Apache.

Property	Typical Value (AH-56A)
Rooli	Attack and Reconnaissance Helicopter
National Origin	Yhdysvallat
Valmistaja	Lockheed Corporation
First Flight	21. syyskuuta 1967
Luotu numero	10 Prototypes
miehistö	2 (Pilot/Commander, Gunner)
Length (Fuselage)	16.66 m (54 ft 8 in)
Rotor Diameter	15.62 m (51 ft 3 in)
korkeus	4.19 m (13 ft 9 in)
Empty Weight	5,800 kg (12,780 lb)
Max Takeoff Weight	13,380 kg (29,500 lb)

Powerplant and Performance

Engine: One General Electric T64-GE-16 turboshaft engine.
Power Output: 2,927 kW (3,925 hp).
Propulsion System: Combined main rotor, anti-torque tail rotor, and a 3-bladed auxiliary pusher propeller (providing forward thrust at high speeds).
Maximum Speed: 393 km/h (244 mph; 212 kn) (Self-imposed limit; capable of higher speeds).
Range: 1,955 km (1,215 mi; 1,055 nmi).
Unique Feature: Employed a Lockheed rigid rotor system which allowed it to transition smoothly between helicopter and autogyro flight modes, greatly enhancing high-speed stability.

Armament and Fire Control

Armament System: Featured a chin-mounted turret with a 30 mm M129 grenade launcher or 40 mm XM140 grenade launcher, and a belly-mounted 30 mm XM52 cannon turret (operated by the gunner).
Weapon Stations: 6 underwing hardpoints for rockets and missiles. Typical load included:
- Hydra 70 rockets.
- TOW anti-tank guided missiles.
Fire Control: Incorporated an advanced, stabilized gunner’s station, allowing the gunner to rotate 360 degrees and aim independently of the helicopter’s direction of flight. The gunner’s seat rotated with the turret.
Fate: Despite its advanced capabilities, the AH-56 was deemed too complex and expensive, leading to the cancellation of its production contract in 1972.

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