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So the rotor possesses three degrees of rotational freedom and its axis possesses two. The rotor responds to a force applied to the input axis by a reaction force to the output axis. A gyroscope flywheel will roll or resist about the output axis depending upon whether the output gimbals are of a free or fixed configuration.
Rotordynamics (or rotor dynamics) is a specialized branch of applied mechanics concerned with the behavior and diagnosis of rotating structures. It is commonly used to analyze the behavior of structures ranging from jet engines and steam turbines to auto engines and computer disk storage .
Power can be supplied by a variety of engines. McCulloch drone engines, Rotax marine engines, Subaru automobile engines, and other designs have been used in Bensen-type designs. [citation needed] The rotor is mounted atop the vertical mast. The rotor system of all Bensen-type autogyros is of a two-blade teetering design.
Upper rotor and drive propeller powered by separate engines; B-8MJ Gyro-Copter - B-8M modified for "jump" take off by a small second engine providing power to rotor head with anti-torque provided by rudder correction under power. [3] X-25A 68-10770 in flight; B-8MW Hydro Copter - float-equipped B-8M; X-25A - B-8M evaluated by USAF.
A control moment gyroscope (CMG) is an attitude control device generally used in spacecraft attitude control systems. A CMG consists of a spinning rotor and one or more motorized gimbals that tilt the rotor’s angular momentum. As the rotor tilts, the changing angular momentum causes a gyroscopic torque that rotates the spacecraft. [1] [2]
A Focke-Achgelis Fa 330 rotor kite. A rotor kite or gyrokite is an unpowered, rotary-wing aircraft. Like an autogyro or helicopter, it relies on lift created by one or more sets of rotors in order to fly. Unlike a helicopter, gyrokites and rotor kites do not have an engine powering their rotors, but while an autogyro has an engine providing ...
The Calidus features a single main rotor, a two-seats in tandem enclosed cockpit with a complete aerodynamic cockpit fairing, tricycle landing gear with wheel pants and a four-cylinder, air and liquid-cooled, four-stroke, dual-ignition 100 hp (75 kW) Rotax 912 engine or turbocharged 115 hp (86 kW) Rotax 914 engine in pusher configuration.
The Hawk 4 had a steel rotor mast and engine mountings but was mostly aluminium elsewhere, including the rotor, rotor head and propeller. The fuselage was an aluminium semi-monocoque . Some components, such as the nosecone, engine cowling and cabin door were formed from composite materials .