DAVID GERARD MATUSKA
Pilots at Winthrop Wood Rd, Huntington, CT

5636969, Jun 10, 1997

Mar 28, 1995

8/412175

David G. Matuska - Huntington CT
Edward W. Gronenthal - Shelton CT
W. Donald Jepson - Huntington CT

Sikorsky Aircraft Corporation - Stratford CT

B64C 1128

416 87

A torque tube/spar assembly (100) for transferring operational loads of a Variable Diameter Rotor blade assembly (16) to a rotor hub assembly (18) and includes a torque tube member (24), a spar member (30) and a bearing assembly (40a, 40b) for telescopically mounting the spar member (30) to the torque tube member (24) and furthermore defines an internal channel (62) for housing a retraction/extension mechanism (64) which mounts to an internally formed restraint surface (86) of the spar member (30) and is operative to vary the length of the rotor blade assembly (18). The torque tube member (30) has a substantially constant external geometry along the length of bearing assembly engagement and defines a root end region (102), a tip end region (106) and an intermediate transition region (104) disposed therebetween. The spar member (30) has a substantially constant internal geometry and defines a root end region (110), a first transition (112), an intermediate region (114), a second transition region (116), a restraint region (118) and a tip end region (120). Each of the various regions of the torque tube and spar members (24, 30) have a characteristic stiffness value wherein the characteristic values (104m, 106m) of the intermediate transition and tip end regions (104,106) of the torque tube member (24) are less than the characteristic stiffness value (102m) of the root end region (102) thereof, and wherein the characteristic stiffness value (118m) of the restraint region (118) of the spar member (30) is greater than said characteristic stiffness values (114m, 120m) of the intermediate and tip end regions (114, 120) thereof, and wherein the characteristic stiffness value (114m) of the intermediate region (114) is less than the characteristic stiffness values (110m, 112m, 116m, 118m) of the root end, first transition, second transition and restraint regions (110, 112, 116, 118).

7598888, Oct 6, 2009

Dec 8, 2006

11/608267

David G. Matuska - Huntington CT, US
Donald S. Anttila - Southbury CT, US

Sikorsky Aircraft Corporation - Stratford CT

G08B 21/00, G01S 13/00, G08G 5/04

340945, 340946, 340961, 340963, 340970, 342 29, 342 30, 342 36, 701 3, 701 9, 701 14, 701301

A safety enhancement warning system includes an avoidance system which communicates with a multiple of geographical positional systems. A geographic algorithm of the avoidance system utilizes a recursive algorithmic to determine if the aircraft will enter a sensitive area. If the aircraft distance to a sensitive area decreases below a predefined minimum threshold, then an audible and/or visual warning is issued. For certain sensitive areas, aircraft RF emissions are silenced or reduced in power when the predetermined minimum threshold breaches the sensitive area. The use of the avoidance system enables usage of relatively inexpensive UWB radar for the proximity sensor suite to assure avoidance of interference with particular delicate instruments and thereby meet regulations such as those propagated by the FCC.

5735670, Apr 7, 1998

Dec 11, 1995

8/569390

Robert C. Moffitt - Seymour CT
David G. Matuska - Huntington CT
Evan A. Fradenburgh - New London NH

Sikorsky Aircraft Corporation - Stratford CT

B64C 1128

416 87

A Variable Diameter Rotor (VDR) system (4) having telescoping odd and even blade assemblies (O. sub. b, E. sub. b) wherein the odd blade assemblies define a radial length R. sub. O and the even blade assemblies define a radial length R. sub. E. Each blade assembly (O. sub. b, E. sub. b) defines an internal chamber (64) for accepting a positioning means (70) operative to effect telescopic translation of the blade assemblies (O. sub. b, E. sub. b) such that the radial length R. sub. E of the even blade assemblies (E. sub. b) is equal to the radial length R. sub. O of the odd blade assemblies (O. sub. b) in a first operating mode, and such that the radial length R. sub. E is between about 70% to about 95% of the length R. sub. O in a second operating mode. The positioning means (70) includes a centrifugal restraint assembly (80) disposed within each internal chamber (64) of the rotor blade assemblies (O. sub. b, E. sub.

5642982, Jul 1, 1997

Dec 11, 1995

8/570579

David G. Matuska - Huntington CT
Edward W. Gronenthal - Shelton CT

Sikorsky Aircraft Corporation - Stratford CT

F04D 2918

416 87

A retraction/extension mechanism (70) for a Variable Diameter Rotor system (10), the Variable Diameter Rotor system (10) having a plurality of rotor blade assemblies (16) mounted to and rotating with a rotor hub assembly (18) about an axis of rotation (20), each rotor blade assembly (16) having inboard and outboard blade sections (24, 22) wherein the outboard blade section (22) telescopically mounts to the inboard blade section (24). The retraction/extension mechanism (70) includes a reeling assembly (80) disposed in combination with the outboard blade section (22) of each rotor blade assembly (16) and an epicyclic gear train (100) disposed in combination 7ith the rotor hub assembly (18) and the reeling assembly (80). The epicylic gea2 train is, furthermore, operative for driving the reeling assembly (80) so as to effect telescopic transition of the outboard blade sections (22) with respect to the inboard blade sections (24).

D418982, Dec 1, 1998

Dec 23, 1996

D/064119

Timothy F. Lauder - Oxford CT
David G. Matuska - Huntington CT

Sikorsky Aircraft Corporation - Stratford CT

1206

D12326

7751976, Jul 6, 2010

Aug 26, 2005

11/213110

David G. Matuska - Shelton CT, US
Vineet Sahasrabudhe - Hamden CT, US
Donald S. Anttila - Southbury CT, US

Sikorsky Aircraft Corporation - Stratford CT

G01C 5/00

701301, 701 9

A method of obstacle avoidance for a rotary wing aircraft includes detecting an obstacle proximate to the aircraft and commanding a servo to generate a force to an input control device in a direction that tends to preclude the aircraft from contacting the detected obstacle, the command having lesser authority than a pilot input command.