Patents by Inventor Ashish Bagai

Ashish Bagai has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 10676177
    Abstract: The present invention relates to robotic landing gear for a rotorcraft that is designed to allow for landing on sloped and irregular surfaces. The robotic landing gear consists of articulated legs with contact sensors. Once the contact sensor touches a landing surface, the articulated leg in which contact is detected retracts to maintain a certain amount of contact pressure with the surface. Each articulated leg does this independently until contact is detected on the sensors of all of the robotic legs, at which point the legs lock in position and the rotorcraft can safely land.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: June 9, 2020
    Inventors: Mark F. Costello, Michael Brian Ward, R Matthew Tallent, Ryan Hofmeister, Ashish Bagai
  • Publication number: 20160122011
    Abstract: A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, a tip region extending from a radial extent of the main region to a blade tip, and a trailing edge. A portion of one of the root region, the main region and the tip region has an airfoil profile section including a trailing edge reflex camber relative to a base airfoil shape of a remainder of the one of the root region, the main region, and the tip region to reduce pitching moment of the rotor blade while maintaining a positive aerodynamic characteristic of the base airfoil shape. The reflex camber extends 20% of a blade chord from the trailing edge.
    Type: Application
    Filed: November 30, 2015
    Publication date: May 5, 2016
    Inventor: Ashish Bagai
  • Patent number: 9284050
    Abstract: A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, and a tip region extending from a radial extent of the main region to a blade tip. At least a portion of one of the root region, the main region and the tip region includes an airfoil profile section defined by a scaled set of coordinates in which a set of y/c coordinates listed in Table I are scaled by a selected factor.
    Type: Grant
    Filed: December 9, 2011
    Date of Patent: March 15, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Ashish Bagai
  • Publication number: 20130149160
    Abstract: A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, and a tip region extending from a radial extent of the main region to a blade tip. At least a portion of one of the root region, the main region and the tip region includes an airfoil profile section defined by a scaled set of coordinates in which a set of y/c coordinates listed in Table I are scaled by a selected factor.
    Type: Application
    Filed: December 9, 2011
    Publication date: June 13, 2013
    Applicant: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Ashish Bagai
  • Patent number: 7600976
    Abstract: Main rotor blades of the dual, counter-rotating, rigid coaxial rotor system exhibit a unique unconventional combination of positive and negative twist gradients in which the rotor system rotor Figure of Merit (hover efficiency) is improved by providing a dissimilar twist distribution between the lower rotor blade and the upper rotor blades. This improvement is specifically a result of reduced profile drag of the lower rotor system, achieved by driving the effective operating condition of the lower rotor blades to be similar to the upper rotor blade such that the tip drag losses of the lower main rotor have been reduced considerably using a mathematically vigorous approach. While minimal induced power consumption resulted due to the dissimilar lower main rotor twist, a significant profile power benefit is realized, resulting in the improved hover efficiency with essentially no reduction in rotor forward flight performance.
    Type: Grant
    Filed: August 23, 2006
    Date of Patent: October 13, 2009
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Ashish Bagai, Lauren Kreuscher
  • Patent number: 7513750
    Abstract: A main rotor blade incorporating a rotor blade tip region having a tip chord and a tip taper such that the ratio of the main rotor blade chord to the tip chord is approximately 0.30. The tip taper ratio preferably providing an approximately 28% area of reduction in said outer 10% of said blade span. The tip region preferably further including a hover optimized high lift airfoil and a tip sweep that reaches a constant value of approximately 30 degrees along the quarter chord line.
    Type: Grant
    Filed: March 8, 2006
    Date of Patent: April 7, 2009
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Robert C. Moffitt, Thomas Alan Egolf, Robert D. Beatty, John K. Karpowich, Ashish Bagai
  • Publication number: 20070212223
    Abstract: A main rotor blade incorporating a rotor blade tip region having a tip chord and a tip taper such that the ratio of the main rotor blade chord to the tip chord is approximately 0.30. The tip taper ratio preferably providing an approximately 28% area of reduction in said outer 10% of said blade span. The tip region preferably further including a hover optimized high lift airfoil and a tip sweep that reaches a constant value of approximately 30 degrees along the quarter chord line.
    Type: Application
    Filed: March 8, 2006
    Publication date: September 13, 2007
    Inventors: Robert Moffitt, Thomas Egolf, Robert Beatty, John Karpowich, Ashish Bagai
  • Patent number: 7252479
    Abstract: A main rotor blade exhibiting a unique planform shape in which the blade chord increases from the root end of the blade inboard region to the outer main region of the blade, where the blade chord achieves a maximum chord at a spanwise location within the main region, then decreases toward a distal tip end. The leading edge preferably is generally straight while the trailing edge is contoured to define the chord. Another characteristic feature of the rotor blade design is the location of the blade-feathering axis in which the feathering axis is located at a mid chord position over some inboard length of the rotor blade then transitions to a quarter chord location. Another characteristic feature is an airfoil distribution along the blade span that transitions from a blunt trailing edge to a sharp trailing edge airfoil suited for mid-range Mach number operation. The tip region preferably utilizes a transonic flow airfoil.
    Type: Grant
    Filed: May 31, 2005
    Date of Patent: August 7, 2007
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Ashish Bagai, Robert C. Moffitt, Robert H. Blackwell, Jr., Timothy A. Krauss
  • Publication number: 20070110582
    Abstract: Main rotor blades of the dual, counter-rotating, rigid coaxial rotor system exhibit a unique unconventional combination of positive and negative twist gradients in which the rotor system rotor Figure of Merit (hover efficiency) is improved by providing a dissimilar twist distribution between the lower rotor blade and the upper rotor blades. This improvement is specifically a result of reduced profile drag of the lower rotor system, achieved by driving the effective operating condition of the lower rotor blades to be similar to the upper rotor blade such that the tip drag losses of the lower main rotor have been reduced considerably using a mathematically vigorous approach. While minimal induced power consumption resulted due to the dissimilar lower main rotor twist, a significant profile power benefit is realized, resulting in the improved hover efficiency with essentially no reduction in rotor forward flight performance.
    Type: Application
    Filed: August 23, 2006
    Publication date: May 17, 2007
    Inventors: Ashish Bagai, Lauren Kreuscher
  • Publication number: 20060269418
    Abstract: A main rotor blade exhibiting a unique planform shape in which the blade chord increases from the root end of the blade inboard region to the outer main region of the blade, where the blade chord achieves a maximum chord at a spanwise location within the main region, then decreases toward a distal tip end. The leading edge preferably is generally straight while the trailing edge is contoured to define the chord. Another characteristic feature of the rotor blade design is the location of the blade-feathering axis in which the feathering axis is located at a mid chord position over some inboard length of the rotor blade then transitions to a quarter chord location. Another characteristic feature is an airfoil distribution along the blade span that transitions from a blunt trailing edge to a sharp trailing edge airfoil suited for mid-range Mach number operation. The tip region preferably utilizes a transonic flow airfoil.
    Type: Application
    Filed: May 31, 2005
    Publication date: November 30, 2006
    Inventors: Ashish Bagai, Robert Moffitt, Robert Blackwell, Timothy Krauss
  • Patent number: 6984109
    Abstract: A rotor blade assembly provides a pitch control assembly to pitch the rotor blade about a rotor blade pitch axis. The pitch control assembly includes a trailing edge flap and a trailing edge servo flap that extend from the trailing edge of the rotor blade. The trailing edge flap is offset in the span wise direction relative to the trailing edge flap. The trailing edge servo flap is located upon a trailing edge servo flap arm linked to the trailing edge flap. To pitch the rotor blade, the trailing edge servo flap is pitched in a direction opposite the desired pitch direction of the trailing edge flap.
    Type: Grant
    Filed: December 4, 2003
    Date of Patent: January 10, 2006
    Assignee: Sikorsky Aircraft Corporation
    Inventor: Ashish Bagai
  • Patent number: 6932569
    Abstract: A multi-element rotor blade includes an individually controllable main element and fixed aerodynamic surface in an aerodynamically efficient location relative to the main element. The main element is controlled to locate the fixed aerodynamic surface in a position to increase lift and/or reduce drag upon the main element at various azimuthal positions during rotation.
    Type: Grant
    Filed: December 27, 2002
    Date of Patent: August 23, 2005
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Michael S. Torok, Robert C. Moffitt, Ashish Bagai
  • Publication number: 20050123400
    Abstract: A rotor blade assembly provides a pitch control assembly to pitch the rotor blade about a rotor blade pitch axis. The pitch control assembly includes a trailing edge flap and a trailing edge servo flap that extend from the trailing edge of the rotor blade. The trailing edge flap is offset in the span wise direction relative to the trailing edge flap. The trailing edge servo flap is located upon a trailing edge servo flap arm linked to the trailing edge flap. To pitch the rotor blade, the trailing edge servo flap is pitched in a direction opposite the desired pitch direction of the trailing edge flap.
    Type: Application
    Filed: December 4, 2003
    Publication date: June 9, 2005
    Inventor: Ashish Bagai
  • Publication number: 20050042091
    Abstract: A multi-element rotor blade includes an individually controllable main element and fixed aerodynamic surface in an aerodynamically efficient location relative to the main element. The main element is controlled to locate the fixed aerodynamic surface in a position to increase lift and/or reduce drag upon the main element at various azimuthal positions during rotation.
    Type: Application
    Filed: December 27, 2002
    Publication date: February 24, 2005
    Inventors: Michael Torok, Robert Moffitt, Ashish Bagai