Aeronautics and astronautics – Aircraft – heavier-than-air – Helicopter or auto-rotating wing sustained – i.e. – gyroplanes
Patent
1986-07-09
1987-12-01
Nase, Jeffrey V.
Aeronautics and astronautics
Aircraft, heavier-than-air
Helicopter or auto-rotating wing sustained, i.e., gyroplanes
244139, B64D 1742
Patent
active
047098813
ABSTRACT:
A parachute-type safety lowering or descent system (10) for helicopters or other types of hovering aircraft includes a rotor hub assembly (12) to which is secured to the top thereof a parachute housing (14), for containing the safety lowering parachute, through means of a dual set of vertically spaced ball bearings (52, 58) for rotationally isolating the parachute housing (14) from the induced rotation effects of the hub rotor assembly (12) under normal aircraft operating conditions. In an emergency, however, such as, for example, in the case of a rotor, rotor blade, rotor hub assembly, or rotor drive engine failure, malfunction, fracture, or separation, the safety lowering parachute will be deployed whereupon the entire weight load of the aircraft will be borne by the safety parachute. Under such conditions, and load factors, the ball bearings (58) will be subjected to substantial impact or impulse forces as to freeze, jam, or become otherwise damaged whereby induced rotational effects will be transferred from the rotor hub assembly (12) to the parachute housing (14) and the parachute deployed therefrom. Such rotational effects can cause twisting, tangling, or other fouling of the parachute shroud lines connected to the housing rungs (70) whereby collapse of the parachute can occur with consequent loss of support by the parachute for the disabled aircraft. In order to prevent or counteract such induced rotational forces, pivotably deployed air brakes (84) in the form of arcuately shaped wings or vanes are moved in an arcuate manner away from their stowed position against the outer peripheral surface of the parachute housing so as to form with the housing peripheral surface air pockets (86) within which captured air causes substantial rotational resistance which counteracts the induced rotation of the housing (14) from the rotor hub assembly (12) and thereby terminates such rotational movement so as to permit complete and proper deployment of the safety parachute without risking collapse of the same and loss of support of the aircraft.
REFERENCES:
patent: 1023233 (1912-04-01), Williams
patent: 1084806 (1914-01-01), Lister
patent: 1541534 (1925-06-01), Souder
patent: 1705489 (1929-03-01), Mladinich
patent: 2673051 (1954-03-01), Frost
patent: 3138348 (1964-06-01), Stahmer
patent: 3246864 (1966-04-01), Mack et al.
Rafikian Faraz
Rafikian, deceased Manoucher
Corl Rodney
Nase Jeffrey V.
Rafikian Faraz
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