US 12,240,633 B2
Rotary wing vehicle
Paul E. Arlton, West Lafayette, IN (US); and David J. Arlton, Lafayette, IN (US)
Filed by Paul E. Arlton, West Lafayette, IN (US); and David J. Arlton, Lafayette, IN (US)
Filed on Mar. 23, 2023, as Appl. No. 18/125,300.
Application 13/270,872 is a division of application No. 12/872,622, filed on Aug. 31, 2010, granted, now 8,042,763, issued on Oct. 25, 2011.
Application 12/872,622 is a division of application No. 11/105,746, filed on Apr. 14, 2005, granted, now 7,789,341, issued on Sep. 7, 2010.
Application 18/125,300 is a continuation of application No. 17/007,647, filed on Aug. 31, 2020, granted, now 11,649,051.
Application 17/007,647 is a continuation of application No. 15/995,419, filed on Jun. 1, 2018, granted, now 10,814,969, issued on Oct. 27, 2020.
Application 15/995,419 is a continuation of application No. 15/175,161, filed on Jun. 7, 2016, abandoned.
Application 15/175,161 is a continuation of application No. 13/899,252, filed on May 21, 2013, granted, now 9,434,471, issued on Sep. 6, 2016.
Application 13/899,252 is a continuation in part of application No. 13/270,872, filed on Oct. 11, 2011, granted, now 8,469,307, issued on Jun. 25, 2013.
Claims priority of provisional application 61/799,878, filed on Mar. 15, 2013.
Claims priority of provisional application 61/649,741, filed on May 21, 2012.
Claims priority of provisional application 60/562,081, filed on Apr. 14, 2004.
Prior Publication US 2023/0294828 A1, Sep. 21, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. B64U 10/13 (2023.01); B64C 7/00 (2006.01); B64C 27/605 (2006.01); B64U 10/17 (2023.01); B64U 20/30 (2023.01); B64U 20/80 (2023.01); B64U 30/24 (2023.01); B64U 30/293 (2023.01); B64U 40/10 (2023.01); B64U 50/19 (2023.01); B64U 50/23 (2023.01); B64U 70/20 (2023.01); B64U 80/70 (2023.01); B64U 80/82 (2023.01); B64C 27/82 (2006.01); B64U 30/12 (2023.01)
CPC B64U 10/13 (2023.01) [B64C 7/00 (2013.01); B64C 27/605 (2013.01); B64U 10/17 (2023.01); B64U 20/30 (2023.01); B64U 20/80 (2023.01); B64U 30/24 (2023.01); B64U 30/293 (2023.01); B64U 40/10 (2023.01); B64U 50/19 (2023.01); B64U 50/23 (2023.01); B64U 80/70 (2023.01); B64U 80/82 (2023.01); B64C 2027/8236 (2013.01); B64C 2027/8281 (2013.01); B64U 30/12 (2023.01); B64U 70/20 (2023.01); B64U 2201/10 (2023.01); B64U 2201/20 (2023.01)] 24 Claims
OG exemplary drawing
 
1. A rotary wing aircraft comprising
a non-rotating structural airframe extending along a rotor axis of rotation and formed to include a hollow channel arranged to lie in parallel relation to the rotor axis of rotation,
a first variable pitch rotor blade supported for rotation about the rotor axis of rotation in a first rotor plane of rotation by the non-rotating structural airframe,
a second variable pitch rotor blade supported for rotation about the rotor axis of rotation by the non-rotating structural airframe in a second rotor plane of rotation and the second rotor plane of rotation is spaced apart from the first rotor plane of rotation along the rotor axis of rotation,
a control module coupled to the non-rotating structural airframe to control the flight of the rotary wing aircraft,
a first servo actuator coupled to the non-rotating structural airframe to vary the pitch of either the first variable pitch rotor blade or the second variable pitch rotor blade, and
a payload module coupled to the non-rotating structural airframe and containing a mission-specific payload,
wherein the control module and the first servo actuator communicate by way of electrical wiring running through the hollow channel in the non-rotating structural airframe to control the flight of the rotary wing aircraft and deliver the payload module accurately to a desired location.