Dennis E Ruzicka from Saint Louis, MO

Automated Director Light System For Aerial Refueling Operations
view source
US Patent:

59047291, May 18, 1999
Filed:

Mar 4, 1997
Appl. No.:

8/810417
Inventors:

Dennis E. Ruzicka - Enumclaw WA
Assignee:

The Boeing Company - Seattle WA
International Classification:

B64D39/00
US Classification:

701300
Abstract:

A method and apparatus for generating visual information for an operator in a first aircraft and a pilot in a second aircraft regarding the second aircraft's position relative to a first aircraft. A 3-D camera system (72) generates a real time 3-D video image of the second aircraft. A selecting device (82) provides selection of a stored geometric model based on the second aircraft type. A display monitor (83) displays the generated real time 3-D video image and the selected geometric model. A matching device (84) matches the displayed geometric model to the displayed real time 3-D video image. A processor (84) determines the position of the second aircraft relative to stored zone information according to the matched geometric model and generates control signals according to the determined second aircraft position. Director lights (88) mounted on the outside of the first aircraft display position information visible to the pilot of the second aircraft according to the generated control signals. The monitor also displays the position of the second aircraft relative to a boom.

Internal Weapon Carriage System For Wide Body Aircraft
view source
US Patent:

57638110, Jun 9, 1998
Filed:

Apr 4, 1997
Appl. No.:

8/833301
Inventors:

Dennis E. Ruzicka - Enumclaw WA
Assignee:

The Boeing Company - Seattle WA
International Classification:

B64D 104
B64C 122
US Classification:

89 151
Abstract:

A weapons launching system (20) is located in an internal weapons storage compartment of an airplane, preferably a widebody aircraft. The system includes a monorail assembly (22) supported by a rail frame (24), and a number of carriage trucks (26) movably engaged with the monorail assembly (22). The carriage trucks (26) deliver weapons (27) via the monorail assembly (22) to a launch bay (28) located near one end of the storage compartment. The carriage trucks (26) include handling-release units (30) for picking up and moving weapons (27) within the storage compartment and for releasing the weapons (27) out the launch bay (28). A portion of the weapons are initially held by the handling-release units (30), while the remaining weapons are supported on stationary support units (34) located in the rail frame (24). An automatic launching control system (36) causes translation of the carriage trucks (26) along the monorail assembly (22) and activation of the handling-release units (30) and stationary support units (34). The carriage trucks (26) are used to quickly deliver weapons (27) to the launch bay (28) in an orderly, sequential manner.

Fighter Aircraft
view source
US Patent:

56368135, Jun 10, 1997
Filed:

Jun 5, 1995
Appl. No.:

8/465076
Inventors:

Richard Hardy - Seattle WA
Frank D. Neumann - Bellevue WA
Dennis E. Ruzicka - Enumclaw WA
Assignee:

The Boeing Company - Seattle WA
International Classification:

B64D 106
US Classification:

2441181
Abstract:

A fighter aircraft achieves low aerodynamic drag and radar signature without sacrificing flight performance through a unique arrangement of the air inlets, the weapons bays, and the main landing gear. Separate main and auxiliary weapons bays permit a narrower fuselage than could be obtained with a single common bay. Also, the auxiliary weapons bays and the landing gear can be aligned outboard of the main weapons bay without needing to increase the length or width of the aircraft. The air intake ducts extend aft from each intake and curve upwardly and inwardly over the main weapons bay. The result of the design configuration is an aircraft of minimum fuselage width for optimal performance and which has a forward aspect reduced to the minimum necessary to accommodate the components that need forward visibilities, which translates to minimum aerodynamic drag and radar signature.

Fighter Aircraft Having Low Aerodynamic Drag And Low Radar Signature Configuration
view source
US Patent:

55225667, Jun 4, 1996
Filed:

Aug 10, 1994
Appl. No.:

8/288637
Inventors:

Richard Hardy - Seattle WA
Frank D. Neumann - Bellevue WA
Dennis E. Ruzicka - Enumclaw WA
Assignee:

The Boeing Company - Seattle WA
International Classification:

B64D 102
US Classification:

2441371
Abstract:

A fighter aircraft achieves low aerodynamic drag and radar signature without sacrificing flight performance through a unique arrangement of the main weapons bay, the auxiliary weapons bays, and the main landing gear. Separate main and auxiliary weapons bays permit a narrower fuselage than could be obtained with a single common bay. Also, the auxiliary weapons bays and the landing gear can be aligned outboard of the main weapons bay without needing to increase the length or width of the aircraft. The air intake ducts extend aft from the intake and curve upwardly and inwardly over the main weapons bay. The result of the design configuration is an aircraft which has a forward aspect reduced to the minimum necessary to accommodate the components that need forward visibilities, which translates to minimum aerodynamic drag and radar signature.

Aircraft Autonomous Reconfigurable Internal Weapons Bay For Loading, Carrying And Launching Different Weapons Therefrom
view source
US Patent:

46977643, Oct 6, 1987
Filed:

Feb 18, 1986
Appl. No.:

6/830007
Inventors:

Richard Hardy - Seattle WA
Frank D. Neumann - Bellevue WA
Dennis E. Ruzicka - Enumclaw WA
Assignee:

The Boeing Company - Seattle WA
International Classification:

B64D 106
B64D 708
US Classification:

2441374
Abstract:

An aircraft autonomous, reconfigurable internal weapons bay for launching different types of weapons such as air-to-air and air-to-ground missiles with folding or fixed fins. The weapons bay is characterized by having internally folding doors which provide separate shallow compartments. The individual compartments are adaptable for carrying a multitude of different types and sizes of missiles internally or semi-submerged.

Actuated Roll Axis Aerial Refueling Boom
view source
US Patent:

57852766, Jul 28, 1998
Filed:

Dec 22, 1995
Appl. No.:

8/577034
Inventors:

Dennis E. Ruzicka - Enumclaw WA
Assignee:

The Boeing Company - Seattle WA
International Classification:

B64D 3900
US Classification:

244135A
Abstract:

An improvement in an airplane mounted aerial refueling boom wherein the boom assembly mounting permits motion about three axes. A first pivot attached to the fuselage of the airplane provides for radial or azimuth motion of the boom about a vertical or yaw axis of rotation essentially normal to the air stream. The second axis of motion, the pitch axis, is located below the airplane fuselage and perpendicular to the yaw axis so that the pitch axis rotates with any yaw motion of the boom and allows vertical displacement of the boom. Vertical and yaw displacement takes place in a conventional fashion. The third axis of motion, the roll axis, is located in-plane with and perpendicular to the pitch axis. This roll axis is coincident with the longitudinal centerline of the boom structural tube and a helical rotary actuator that produces a commanded roll motion as a function of pitch and yaw motion of the boom assembly. Rolling motion of the boom assembly serves to align the cross-sectional vertical chord axis of the boom and boom mounted aerodynamic surfaces with the local free stream air flow about the tanker airplane to minimize drag and optimize control authority.