An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple the elevator rotational motion from the stabilizer translation motion for the higher order horizontal fr
An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple the elevator rotational motion from the stabilizer translation motion for the higher order horizontal frequencies having node lines in the proximity of the mass outboard counterbalance weights. The original tail section includes a rudder, and a horizontal stabilizer supporting an elevator mounted adjacent the rudder. The elevator includes a proximal end adjacent the rudder and a distal end that includes a counterbalance portion. The improvement includes replacement of an original mass counterbalance weight from within the counterbalance portion with a new mass counterbalance weight of less mass, and the inclusion of additional mass counterbalance weights disposed within the elevator and interposed between the proximal end and the counterbalance portion.
대표청구항▼
1. In an aircraft, an improvement comprising, a tail section providing a horizontal stabilizer secured to a rudder of said aircraft and supporting an elevator, said elevator included at least a proximal end adjacent said rudder and a mass counterbalance weight confined completely within and distribu
1. In an aircraft, an improvement comprising, a tail section providing a horizontal stabilizer secured to a rudder of said aircraft and supporting an elevator, said elevator included at least a proximal end adjacent said rudder and a mass counterbalance weight confined completely within and distributed in contact adjacency along a leading edge of said elevator, in which a weight of and distribution of said mass counterbalance weight along said leading edge of the elevator uncouples a rotational motion of said elevator from translation motions of said stabilizer, thereby mitigating a predictive occurrence of a flutter event, wherein said mass counterbalance weight includes at least a plurality of non-contacting mass counterbalance weights disposed between the rudder and a counterbalance portion. 2. The aircraft of claim 1, in which an original tail section comprising the rudder, and the horizontal stabilizer supporting the elevator mounted adjacent said rudder, wherein said elevator comprises the proximal end adjacent said rudder and a distal end that provides an original mass counterbalance weight within the counterbalance portion, and in which the improvement further comprising replacement of the original mass counterbalance weight with said mass counterbalance weight, wherein said mass counterbalance weight has a mass greater than a mass of said original mass counterbalance weight. 3. The aircraft of claim 1, in which said improvement further comprising a mass increase of said elevator and its associated mass counterbalance weight for inclusion on said tail section. 4. The aircraft of claim 1, in which said elevator comprises the proximal end adjacent said rudder and a distal end providing the counterbalance portion, and in which the improvement further comprising said mass counterbalance weight disposed within said elevator and interposed between said proximal end and said counterbalance portion of said elevator. 5. The aircraft of claim 1, in which an original tail section comprising the rudder, the horizontal stabilizer comprising the leading edge, a trailing edge and is mounted adjacent said rudder, and the elevator comprising an upstream edge and a downstream edge wherein said elevator is secured to said horizontal stabilizer at a hinge point thereby providing an axis of rotation for said elevator relative to said horizontal stabilizer, wherein said elevator further comprising: a distal end providing the counterbalance portion adjacent said horizontal stabilizer;a first portion disposed between said axis of rotation and said downstream edge; anda second portion disposed between said axis of rotation and said upstream edge, in which the improvement further comprising the mass counterbalance weight disposed within said second portion and interposed between said proximal end and said counterbalance portion of said elevator. 6. The aircraft of claim 1, in which an original tail section comprising the rudder, and the horizontal stabilizer supporting the elevator mounted adjacent said rudder, wherein said elevator comprises the proximal end adjacent said rudder and a distal end providing the counterbalance portion with an original mass counterbalance weight contained therein, and in which the improvement further comprising removal of said original mass counterbalance weight and placement of a first portion of said mass counterbalance weight disposed within the counterbalance portion, wherein said first portion of said mass counterbalance weight has a mass less than a mass of said original mass counterbalance weight, and wherein said original mass counterbalance weight has been removed from said aircraft. 7. The aircraft of claim 6, in which the improvement further comprising adding additional portions of said mass counterbalance weight, wherein a total mass of said mass counterbalance weight is greater than a total mass of the original mass counterbalance weight. 8. The aircraft of claim 7, in which said distal end of said elevator comprising the counterbalance portion, and in which the improvement further comprising said additional portions of said mass counterbalance weight disposed within said elevator and interposed between said proximal end and said counterbalance portion of said elevator. 9. The aircraft of claim 8, in which said horizontal stabilizer comprising a leading edge and a trailing edge, and said elevator comprising an upstream edge and a downstream edge, wherein said elevator is attached to said horizontal stabilizer at a hinge point thereby providing an axis of rotation for said elevator relative to said horizontal stabilizer, and wherein said elevator further comprising: a first portion disposed between said axis of rotation and said downstream edge; anda second portion disposed between said axis of rotation and said upstream edge, wherein the improvement further comprising said additional portions of said mass counterbalance weight disposed within said second portion and interposed between said proximal end and said counterbalance portion of said elevator.
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이 특허에 인용된 특허 (7)
Hassan, Ahmed A.; Hamilton, Brian K.; Ngo, Hieu T., Gust alleviation/flutter suppression device.
Evans Hugh G. (W. 214 6th Ave. Spokane WA 99204) Speer Stephen (S. 358 Couer d\Alene ; Apt. #6 Spokane WA 99204) Christy James S. (E. 10918 26th Spokane WA 99204), Vibration-insulating stability improving torque force device.
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