Helicopter stowable horizontal stabilizer

An airfoil is provided for an aircraft such as a helicopter, wherein the airfoil can be folded to a stowed position and unfolded to an operational position, without requiring an adjustment of the control rod assembly which lies within the airfoil. The control rod assembly (50, FIG. 2) includes inboa...

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Bibliographic Details
Main Author HEIN; JEFF M
Format Patent
LanguageEnglish
Published 08.07.1997
Edition6
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Summary:An airfoil is provided for an aircraft such as a helicopter, wherein the airfoil can be folded to a stowed position and unfolded to an operational position, without requiring an adjustment of the control rod assembly which lies within the airfoil. The control rod assembly (50, FIG. 2) includes inboard and outboard control rods (60, 62) with adjacent ends lying below the main axis (86) about which the foldable airfoil parts pivot, with a linkage (64) connecting the control rods. The linkage includes a long first link (90, FIG. 5) pivotally connected at a first axis (92) to an end of the inboard control rod and a second link (96) pivotally connected at a second axis (102) to the first link and at a third axis (106) to the outboard control rod. The links are constructed so they overlap in the operational position of the horizontal stabilizer, with the first, second, and third axes lying substantially along a force line (70). A spring (130) urges the first link to pivot upwardly about the first axis to keep the three axes close to the force line in the flight position.
Bibliography:Application Number: US19940297394