JOHN BURTON KALISZ
Pilots at Wayman St, Santa Clarita, CA

6422511, Jul 23, 2002

Jul 5, 2001

09/898840

John Kalisz - Newhall CA

Lockheed Martin Corporation - Palmdale CA

B64F 112

244114R, 244100 A

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.

5333817, Aug 2, 1994

Nov 22, 1993

8/155363

John B. Kalisz - Newhall CA
Mark H. Wexler - Studio City CA

Lockheed Corporation - Calabasas CA

B64B 162

244 97

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.

6293493, Sep 25, 2001

Dec 21, 1999

9/468457

David B. Eichstedt - Lancaster CA
John P. Morehead - Santa Clarita CA
John B. Kalisz - Newhall CA

Lockheed Martin Corporation - Palmdale CA

B64B 102

244 30

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.

6196498, Mar 6, 2001

Dec 21, 1999

9/467971

David B. Eichstedt - Lancaster CA
John P. Morehead - Santa Clarita CA
John B. Kalisz - Newhall CA

Lockheed Martin Corporation - Palmdale CA

B64B 120

244 5

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.

4600171, Jul 15, 1986

Oct 12, 1984

6/660174

John B. Kalisz - Newhall CA

Lockheed Corporation - Burbank CA

B64D 108, B64D 900

244137A

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.

6315242, Nov 13, 2001

Dec 21, 1999

9/467967

David B. Eichstedt - Lancaster CA
John P. Morehead - Santa Clarita CA
John B. Kalisz - Newhall CA

Lockheed Martin Corporation - Palmdale CA

B64B 102

244 30

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.

6164589, Dec 26, 2000

May 17, 1999

9/313309

John Kalisz - Newhall CA

Lockheed Martin Corporation - Palmdale CA

B64B 100

244 5

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.

5368256, Nov 29, 1994

Aug 19, 1993

8/108280

John B. Kalisz - Newhall CA
David E. Carlile - Lancaster CA

Lockheed Corporation - Calabasas CA

B65B 130, B65B 134

244 26

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.

6302357, Oct 16, 2001

Aug 28, 2000

9/648416

John B. Kalisz - Newhall CA

Lockheed Martin Corporation - Palmdale CA

B64B 114

244 30

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.