Aeronautics and astronautics – Aircraft – heavier-than-air – Helicopter or auto-rotating wing sustained – i.e. – gyroplanes
Reexamination Certificate
2001-06-08
2002-08-06
Barefoot, Galen L. (Department: 3644)
Aeronautics and astronautics
Aircraft, heavier-than-air
Helicopter or auto-rotating wing sustained, i.e., gyroplanes
C244S1040LS, C244S108000
Reexamination Certificate
active
06427942
ABSTRACT:
BACKGROUND ART
1. Field of the Invention
The present invention relates generally to aircraft skid landing gear having a various directional stiffnesses. More specifically, the present invention relates to a skid landing gear assembly for a helicopter in which the vertical stiffniess is de-coupled from the longitudinal stiffniess.
2. Description of Related Art
Helicopter skid landing gear devices are well known in the art. For instance, most modern helicopters feature a skid landing gear having a pair of circular-section cross members attached to a pair of longitudinal skids. These circular-section cross members are designed to optimize the attenuation of the vertical energy of hard landings and to maximize fatigue life. However, with these circular-section cross members, the vertical stiffness is inherently coupled to the longitudinal stiffnesses, resulting in relatively high longitudinal stiffnesses. It is well known in the art that some of the rotor blade's rotational energy is transformed to oscillatory energy of the fuselage and of the rotor blade in the in-plane mode. This phenomenon is known as ground resonance. Ground resonance is destabilizing and requires adequate system damping in the fuselage and skids and in the rotor blade's lead-lag dampers. When the system damping is less than or equal to zero, there is a potential for instability. A high longitudinal stiffness generally has an adverse affect on shuffle mode ground resonance frequency placement, creating a direct conflict between energy attenuation and fatigue life requirements and ground resonance frequency placement. In order to resolve this conflict, prior-art skid landing gear designers have resorted to heavy and costly add-on devices, such as rocker beams, dampers, and skid springs.
For example, U.S. Pat. No. 4,270,711 to Cresap et al. discloses a helicopter skid landing gear with cross tube pivot. Cresap et al. employs a structural beam, or rocker beam, that allows central pivoting of the aft cross tube, creating a three-point support for reducing roll frequency. Cresap et al. has only an indirect affect on the longitudinal shuffle frequency. Thus, Cresap et al. is limited in its ability to tune the skid gear for both attenuating vertical landing energy, and avoiding ground resonance frequency. The Cresap et al. device is costly, complicated, and heavy. In addition, it is difficult-to design the centrally pivoted aft cross tube for adequate fatigue life.
Another example is U.S. Pat. No. 5,211,359 to Rene et al., which discloses a landing gear for aerodynes with cross pieces made of composite material. The Rene et al. device features a skid gear with laminated fiberglass cross members. Although it is generally believed that energy absorption cannot occur elastically, Rene et al. discloses an elastic energy absorption capacity that is superior to metallic devices. Although Rene et al. discloses the use of dampers to control ground resonance, there is no mention of how the dampers are tuned for ground resonance frequency placement. Rene et al. does not disclose the use of its laminated cross member section properties to obtain compliance to avoid ground resonance.
Another example of a helicopter skid landing gear is disclosed in U.S. Pat. No. 5,224,669 to Guimbal. The Guimbal device features laminated cross members made in the shape of an arch. Guimbal capitalizes upon the non-linear geometry of the arches and friction to obtain vertical energy absorption for light helicopters. Although Guimbal discloses the use of dampers to control the ground resonance, it makes no mention of how to tune the system properties for ground resonance stability.
Although these prior-art devices teach various methods of absorbing the vertical energy of landing, they do not adequately address the problem of helicopter ground resonance frequency placement. Despite these advances in the art, there continues to be a need for a helicopter skid landing gear that addresses not only vertical energy attenuation and fatigue life, but that also adequately addresses the problem of controlling the ground resonance frequency.
BRIEF SUMMARY OF THE INVENTION
There is a need for a helicopter having an improved skid landing gear in which the directional stiffnesses of the cross members are de-coupled so that the ground resonance frequency placement of the gear and its vertical energy attenuation and fatigue characteristics can be optimized independently.
It is an objective of the present invention to provide an improved helicopter including a skid landing gear assembly in which the vertical stiffness of at least one cross member is decoupled from the longitudinal stiffness, such that the longitudinal stiffness of that cross member may be optimized independently of the vertical stiffness.
It is another objective of the present invention to provide an improved helicopter including a skid landing gear assembly in which at least one cross member has a geometrical cross-section for which the moment of inertia about a vertical axis is not equal to the moment of inertia about a horizontal axis, thereby allowing optimization of the ground resonance frequency placement, while retaining optimum vertical stiffness characteristics for landing energy attenuation and long fatigue life.
It is another objective of the present invention to provide an improved helicopter having a skid landing gear in which at least one cross member has a geometrical cross-section for which the moment of inertia about a vertical axis is not equal to the movement of inertia about a horizontal axis, thereby inherently increasing the efficiency of the cross-section for vertical bending, and reducing fatigue stresses during normal helicopter operation.
It is another objective of the present invention to provide an improved helicopter having a skid landing gear in which at least one cross member has a geometrical cross-section having composite material that is distributed within the cross-section, such that the vertical stiffness is not equal to the horizontal stiffness, thereby allowing optimization of the ground resonance frequency placement, while retaining the optimum vertical stiffness characteristics for landing energy attenuation and long fatigue life.
It is another objective of the present invention to provide an improved helicopter including a skid landing gear assembly in which the skid landing gear optimizes the placement of ground resonance frequency without the use of rocker beams, dampers, or skid springs.
It is another objective of the present invention to provide an improved helicopter including a skid landing gear assembly having mounting devices for mounting cross members of the skid landing gear assembly to the helicopter, the mounting devices forming a selected angle with the helicopter, such that the directional stiffnesses of the cross members are de-coupled from each other.
It is another objective of the present invention to provide an improved helicopter including a skid landing gear assembly having mounting devices for mounting cross members of the skid landing gear to the helicopter, the mounting devices de-coupling the directional stiffnesses of the cross members from each other, thereby allowing the use of circular- or symmetric-section cross members.
It is another objective of the present invention to provide an improved helicopter including a skid landing gear assembly having an attachment means for attaching a cross member of the skid landing gear assembly to a skid member of the skid landing gear assembly, such that the directional stiffnesses of the cross member are de-coupled.
The above, as well as, additional objectives, features, and advantages of the present invention will become apparent in the following detailed description.
REFERENCES:
patent: 3716208 (1973-02-01), Fagan et al.
patent: 3888436 (1975-06-01), Sealey
patent: 4196878 (1980-04-01), Michel
patent: 4270711 (1981-06-01), Cresap et al.
patent: 4284255 (1981-08-01), Masclet et al.
patent: 4519559 (1985-05-01), Logan et al.
patent: 4558837 (1985-12-01), Mens et al.
patent: 464514
Howard John V.
Sareen Ashish K.
Smith Michael R.
Thiagarajan Ramesh
Barefoot Galen L.
Bell Helicopter Textron Inc.
Hill & Hunn LLP
Walton James E.
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