Landing gear mechanism including bypass valve assembly for reducing damping loads during taxiing
AssigneePneumo Corporation
InventorLouis C. Hrusch
Life of this patent
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AssigneePneumo Corporation
InventorLouis C. Hrusch
Estimating the term…
Landing gear mechanism includes a restrictor assembly containing a main orifice for controlling the rate of instroke of the landing gear mechanism during landing and a taxi instroke bypass valve which provides for increased flow of hydraulic fluid within the landing gear mechanism whenever the landing gear mechanism engages a bump during taxiing to reduce the damping loads that would otherwise occur if all of the hydraulic fluid were required to flow through the main orifice. The taxi instroke bypass valve assembly includes a slide member axially movable relative to the restrictor assembly for opening and closing one or more bypass orifices in the restrictor assembly. The slide member is held in the closed position whenever the landing gear mechanism is in a specified stroke range from fully extended by a secondary piston which is acted upon by the pressure in a precharged secondary chamber urging the secondary piston into engagement with a probe connected to the slide member. At some point in the strut stroke, the pressure within the upper piston chamber of the landing gear mechanism will rise to that of the precharged secondary chamber, whereby the secondary piston will be stroked along with the main strut piston and the slide member will move to the open position allowing fluid to bypass the main orifice, thereby reducing the damping loads as the landing gear mechanism negotiates bumps during taxiing.
A landing gear mechanism for high performance aircraft comprising a main cylinder, a main strut piston axially movable within said main cylinder, a restrictor member contained within said cylinder and defining with said cylinder and piston upper and lower chambers, said restrictor member having orifice means therethrough for controlling the rate of flow of hydraulic fluid from said lower chamber to said upper chamber during landing, and bypass valve means providing for increased flow of hydraulic fluid from said lower chamber to said upper chamber whenever said landing gear mechanism engages a bump during taxiing to reduce the damping loads that would otherwise occur if all of such hydraulic fluid were required to flow through said orifice means, said bypass valve means comprising bypass passage means around said orifice means, a slide member mounted for axial movement relative to said restrictor member between open and closed positions for respectively opening and closing said bypass passage means, and means for keeping said slide member in the closed position until after landing has taken place and the pressure in said upper chamber has risen to a predetermined level, said means for keeping said slide member in the closed position until after landing has taken place comprising a secondary piston having a first surface area which is continually acted upon by a secondary pressure source of a predetermined magnitude urging said secondary piston toward said slide member.
Dependencies are inferred from the claim text.