Aeronautics and astronautics – Aircraft structure – Load accommodation
Reexamination Certificate
1999-02-16
2001-06-05
Swiatek, Robert P. (Department: 3643)
Aeronautics and astronautics
Aircraft structure
Load accommodation
C089S037220
Reexamination Certificate
active
06241185
ABSTRACT:
CROSS-REFERENCE TO RELATED APPLICATIONS
This application discloses subject matter similar to that disclosed in U.S. Pat. Nos. 5,024,138 and 5,421,239 which are hereby incorporated by reference herein in their entireties.
BACKGROUND OF THE INVENTION
The present invention generally relates to aircraft armament apparatus and, in a preferred embodiment thereof, more particularly relates to a support plank-based aircraft armament mounting system incorporating thereon apparatus for supporting various aircraft cargo externally of the aircraft.
The external mounting on aircraft of weaponry such as machine guns, rocket launchers and the like, particularly in retrofit applications, has heretofore carried with it a variety of structural, operational and safety limitations and disadvantages. As but one example, the external mounting of machine guns on a helicopter has previously entailed securing an outwardly projecting metal support tube to the helicopter and then mounting the gun on the tube. While this seems to be a fairly straightforward approach, unavoidable limberness in the support tube often led to firing inaccuracies in the mounted gun due to wobbling of its firing axis relative to the aircraft.
To a great extent these problems have been eliminated by using the honeycombed metal support plank structure illustrated and described in U.S. Pat. No. 5,024,138 to Sanderson et al. This support plank structure includes a fixed length central longitudinal section which is transversely insertable through the cabin portion of the aircraft in a manner such that fixed opposite end portions of this plank section project outwardly from opposite sides of the body of the aircraft through cabin door openings therein. Pivotally secured to the outwardly projecting ends of this central plank section are outer tip portions of the overall plank structure. These outer tip portions are vertically pivotable, about plank structure hinge lines disposed exteriorly of the aircraft, between (1) lowered, fully extended operating positions in which they form outward extensions of the fixed, outwardly projecting opposite ends of the central plank section, and (2) upwardly and inwardly folded transport and storage positions in which the outer tip portions rest atop the outer end portions of the central plank section outboard of the opposite sides of the aircraft.
At the outer ends of these foldable tip portions are downwardly projecting outboard weaponry mounting structures which, using conventional bomb lug connector apparatus, are operative to removably support a pair of multiple tube rocket launchers at their bottom ends. Mounted on the undersides of the fixed position outwardly projecting central plank section end portions, inwardly of the hinge lines for the foldable plank tip portions, are a pair of inboard support structures operative to removably support a pair of machine guns such as 7.62 mm “mini guns”.
While the support plank-based aircraft armament system illustrated and described in U.S. Pat. No. 5,024,138 has proven to be structurally superior to metal tube-type weaponry support systems, the inboard portion of the central plank section, together with the ammunition magazines mounted on the top side thereof, occupies a considerable amount of space in the aircraft cabin area through which the plank extends. This, in turn, substantially reduces the amount of cargo that may be carried within the cabin area. To offset this reduction in the cargo-capacity of the aircraft cabin area, a modification was made to this support plank structure as illustrated and described in U.S. Pat. No. 5,421,239 to Sanderson.
In this modified support plank structure, front and rear sides of the outer end portions of the central plank section, which project outwardly beyond the opposite outer sides of the aircraft body, are fitted with removable front and rear auxiliary plank sections which may be pivoted, about horizontal axes parallel to the length of the plank structure, between (1) cargo support positions in which the two auxiliary plank sections on each outer central plank section end transversely extend horizontally from front and rear sides of the outwardly projecting central plank section end, and (2) a pivoted orientation in which one of the auxiliary plank sections is swung up onto the top side of its associated central plank section outer end portion.
While this modified plank structure advantageously provides, externally to its associated aircraft, additional cargo-carrying capacity its portions disposed externally to the aircraft also create an undesirable aerodynamic drag when not being used in a cargo-carrying capacity. It would thus be desirable to reduce such drag during flights of the aircraft in which the external cargo-carrying capabilities of the plank structure is not being utilized. It is to this goal that the present invention is directed.
SUMMARY OF THE INVENTION
In carrying out principles of the present invention, in accordance with a preferred embodiment thereof, improved support apparatus is provided for an aircraft, representatively a helicopter, and is useable to support, alone or in various combinations thereof, weaponry, cargo, and external fuel tanks. The aircraft has a cabin area with front and rear portions and opposite first and second outer side wall portions extending between the front and rear portions and having door openings therein. Illustratively, each of these opposite outer side wall portions of the aircraft representatively slopes forwardly and horizontally outwardly relative to the length of the aircraft.
In a preferred embodiment thereof, the support apparatus includes an elongated central support plank section having first and second opposite end portions with front and rear side edges. Securing apparatus is provided and is operative to horizontally secure the central support plank section to the aircraft, along a bottom side portion of the cabin area, in a manner such that the first and second opposite end portions of the central support plank section are respectively positioned inwardly adjacent the first and second outer side wall portions of the aircraft at the cabin area door openings therein.
The support apparatus also includes first and second auxiliary plank sections having inner ends and front and rear side edges. Cooperating mounting structures are associated with the first and second end portions of the central support plank section and the inner ends of the first and second auxiliary plank sections and are operative to respectively mount the first and second auxiliary plank sections on the first and second end portions of the central support plank section. The mounted first and second auxiliary plank sections are pivotal relative to the opposite central plank section ends, about generally horizontal first and second pivot axes extending through the cabin area of the aircraft and inset from the aforementioned first and second outer side wall portions thereof, between (1) first positions in which the first and second auxiliary plank sections are folded onto the end portions of the central support plank section and are disposed within the cabin area, and (2) second positions in which the first and second auxiliary plank sections are pivoted outwardly through the door openings and form longitudinal extensions of the central support plank section disposed exteriorly of the opposite sides of the aircraft.
According to one feature of the present invention, each of the generally horizontal first and second pivot axes on the central plank section ends are sloped relative to a horizontal reference axis transverse to the longitudinal axis of the central support plank section. Preferably, the first and second pivot axes, respectively, are oriented to be generally parallel to the forwardly and horizontally sloping first and second outer side wall portions of the aircraft when the central support plank section is operatively secured to the aircraft. Alternatively, if desired (for example when the first and second side wall portions of the aircraft are parallel to its longitudinal
Konneker & Smith P.C.
Swiatek Robert P.
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