Lockheed Martin Corporation

Kellstrom Defense Aerospace, Inc.

Lockheed Corporation

John Burton Kalisz

Joshua Ryan Werner

John P Morehead

David B Eichstedt

Mark H Wexler

David E Carlile

A wing skin, which was secured to a wing structure by a plurality of fasteners extending through the wing skin, is removed from the wing and aligned with a template. Template holes are drilled through the template corresponding to each of the fastener holes of the wing skin. The template is then aligned with a new wing skin, and pilot holes are drilled through the new wing skin corresponding to each of the template holes. The new wing skin is then aligned with the wing structure such that the pilot holes permit access to corresponding fastener holes of the wing structure. A mill bit is then positioned through each pilot hole and aligned with the center of the corresponding consumable bushing in the fastener hole of the wing sub-structure, and the skin pilot holes are milled to form fastener holes in the new wing skin aligned with existing sub-structure.

Aircraft wing repair methods

Consumable bushing for use with aircraft wing repair systems and methods

Aircraft wing repair systems and methods

The invention is a system for supporting a vertical take off and landing aircraft during hover tests about the ground, the aircraft having a longitudinal, vertical, and lateral axis, a nose landing gear and a main landing gear positioned rear therefrom on either side of the longitudinal axis. In detail, the system includes a bearing assembly, preferably and air bearing assembly positionable under the nose and each main landing gear. An air cushion assembly mounted to each of the air bearings with the air cushion assembly detachably coupled to each landing gear. Preferably, the air cushion assemblies are coupled to the landing wheel axles. Thus the bearing assemblies allow horizontal motion above the ground and the air cushion provides for vertical movement of the aircraft above the ground.

Support system for ground testing an aircraft

A propulsion system for a non-rigid and at least semi-buoyant vehicle, the vehicle including a pressure stabilized gasbag having a gondola mounted on the bottom thereof. The gasbag further includes catenary curtains extending from the top of gasbag to the bottom of the gasbag and attached thereto. In detail, the propulsion system includes a first pair of tubular members attached, preferably pivotally attached, by one of their ends to the gondola and which extend through the air bag and exit out the top thereof and having propulsion units, preferably turbo-prop engines, attached to their opposite ends. A second pair of tubular members is attached by one of their ends to the gondola, preferably pivotally attached, and extends into the gasbag and having their opposite ends terminating therewithin. A horizontal tubular member extends through the gasbag and has its ends extending out of the sides thereof and is attached to the opposite ends of the second pair of tubular members in the middle thereof. The ends of the second pair of tubular members also have propulsion units attached thereto.

Propulsion system for a semi-buoyant vehicle with an aerodynamic

This invention relates to a pressure stabilized inflated air transport vehicle having means for limiting crack propagation in the hull envelope whereby leakage of the gas in the haul due to the crack will not exceed the gas pressure maintaining means.

Pressure stabilized inflated air transport vehicle

A non-ridged semi-buoyant vehicle includes a pressure stabilized gasbag having a longitudinal, vertical and horizontal axis, top, bottom and side surfaces and front and rear ends and an aerodynamic shape capable of producing lift. Within the gasbag are first and second vertical catenary curtains attached to the top and bottom surfaces between the sides of the gasbag. These first and second catenary curtains are positioned on either side of the longitudinal axis extending from the front end along a first portion of the gasbag. A pair of first and second Y shaped catenary curtains are coupled to the first and second vertical catenary curtains and extend along a second portion of the gasbag. The arms of each of the Y shaped curtains are attached to the top surface and the legs are attached to the bottom surface of the gasbag. First and second pairs of vertical catenary curtains are coupled to the first and second pairs of Y shaped catenary curtains, respectively, and extend to the rear end of said gasbag. The first and second pairs of vertical catenary curtains are attached at their top and bottom ends to the top and bottom surfaces of the gasbag. Secondary vertical catenary curtains are positioned on either side of the first and second pairs of vertical catenary curtains and extend from the rear end of the gasbag a portion of length of the first and second pairs of catenary curtains. These secondary vertical catenary curtains are attached at their top and bottom ends to the top and bottom surfaces of the gasbag.

Pressure stabilized gasbag for a partially buoyant vehicle

The invention is a non-ridged, semi-buoyant vehicle. In detail, the invention includes a pressure stabilized gasbag having front and rear ends and an aerodynamic shape capable of producing lift, and longitudinal, vertical and horizontal axis, the tail end of the gasbag extending outward along the horizontal axis from each side of the longitudinal axis toward said front end at an acute angle to the horizontal axis. A horizontal tail surface is mounted outboard of the rear end of the gasbag, having a trailing edge extending outward along the horizontal axis from each side of the longitudinal axis toward the front end at the acute angle to the horizontal axis. A horizontal ridged beam is mounted outboard of the rear end of the gasbag that extends outward along the horizontal axis from each side of the longitudinal axis toward the front end at the acute angle to the horizontal axis with the horizontal tail surface mounted to the beam. The preferred acute angle is approximately 20 degrees. The gasbag further includes a plurality of vertical catenary curtains attached between the top and bottom surfaces of the gasbag. A vertical extending flexible bean is attached to each of catenary curtains. These straps have top and bottom ends extending out of the top and bottom surfaces, respectively, of said gasbag. Top and bottom attachment fittings are mounted by a first end to the top and bottom ends, respectively, of the ridged beam and by their second ends to the top and bottom ends, respectively, of the flexible straps.

Semi-buoyant vehicle with aerodynamic lift capability

A partially buoyant aircraft capable of transporting very large cargo payloads comprises a lifting body with an exterior airfoil configuration that includes internal structural support members for an exterior skin, the skin defining an internal volume for storing the cargo, propulsion apparatus, flight stabilization apparatus on a portion of the lifting body, lift assisting apparatus carried within the lifting body, and landing gear arranged in close proximity to the longitudinal centerline of the lifting body. Each landing gear comprises a wheel supported by a cylinder set including upper and lower telescoping cylinders, the upper cylinders of the wheels being ported together to operate as a single element.

Centerline landing gear for aerocraft

The invention is a propulsion system for a lighter-than-air vehicle. In detail the propulsion system includes a pylon having a longitudinal axis and first and second ends, the first end of the pylon rotatably mounted to the vehicle and the second end extending outward from the vehicle. The pylon is rotatable about the first end in a plane perpendicular to the longitudinal axis of the vehicle. A thrust producing assembly is mounted on the second end of the pylon and is rotatable about an axis of rotation in a plane perpendicular to the longitudinal axis of the pylon. A powerplant assembly is coupled to the thrust producing assemblies to provide power thereto. An actuation system is provided for rotating the assembly about the axis of rotation. A second actuation system is provided for rotating the pylon about the first end.

Propulsion system for a lighter-than-air vehicle

The invention is a ballonet system for a lighter-than-air-vehicle, the vehicle having a lift producing gasbag and a longitudinal, vertical and lateral axis. In detail, the ballonet system includes a plurality of ballonets located within the gasbag positioned along the longitudinal axis and on each side of the vertical axis of the vehicle. Each of the ballonets include a flexible sheet joined at its periphery thereof to a portion of the wall of the gasbag. A ballonet pressurization system is coupled to each ballonet for pressurizing them with air that includes the portion of the wall of the gasbag forming the ballonet having a plurality of holes therethrough. A manifold having an inlet port is joined to the wall covering the holes therein and is adapted to diffuse the pressurized air entering therein. Also included is at least one fan having an inlet port coupled to ambient atmosphere and an outlet port coupled to the inlet port of the manifold for providing pressurized air to the interior thereof. A check valve located in the outlet port of the fan is provided for preventing air from flowing from the interior of the manifold out the inlet port of the fan. A ballonet venting system is included for venting the interior of the ballonet to ambient atmosphere.

Ballonet system for a lighter-than-air vehicle

The invention is an aircraft stores extension and retraction system 10 for raising and lowering stores mounted to a stores support assembly 69 along a substantially vertical path 94' of a specified length. The system 10 comprises first and second translating links 40A and 40B, each having first 42A, 42B, second 44A, 44B, and third 46A, 46B pivot supports, forming the corners of a right triangle. The second pivot supports 44A, 44B, are pivotally attached to stores support assembly 69. At least one connecting link 50 is pivotally attached at its first and second ends to the third pivot supports 46A, 46B of the first and second translating links 40A, 40B, respectively. First and second positioning links 30A, 30B are provided, each having first ends 32A, 32B and second ends 35A, 35B. The first ends 32A, 32B of the positioning links are pivotally attached to the structure 33 of the aircraft and the second ends 35A 35B are pivotally attached to the first pivot supports 42A, 42B of the first and second translating links 40A, 40B, respectively. At least one control link 60 is provided having first and second ends 62A 64A. The first end 64A of the at least one control link 60A is pivotally attached to the structure 33 of the aircraft and the second end 62A is pivotally attached to the third pivot support 46A of the first translating link 40A. Actuators 82 are coupled to the structure and the first and second positioning links 30A, 30B and are adapted to cause the positioning links 30A, 30B to pivot about their first ends. Thus, as the first and second positioning links 30A, 30B pivot, the second pivot supports 44A, 44B translate substantially along a vertical path 94.

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Newhall, CA, United States of America

John Burton Kalisz