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Multi-mode unmanned aerial vehicle

  • US 10,293,932 B2
  • Filed: 12/08/2016
  • Issued: 05/21/2019
  • Est. Priority Date: 06/28/2016
  • Status: Active Grant
First Claim
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1. A multi-mode unmanned aerial vehicle, comprising:

  • an elongated fuselage having a front end, a rear end with a curved guide slot, a right side, a left side, and a wing-in-ground (WIG) effect bottom;

    a right-fixed wing extending from the right side of the elongated fuselage;

    a right tilt wing attached at a first side to a free end of the right fixed wing, the right tilt wing being rotatable in a range of 0-135 degrees about a lateral axis of the multi-mode unmanned aerial vehicle;

    a right duct attached to a second side of the right tilt wing;

    a right winglet attached to the right duct opposite to the right tilt wing;

    a left-fixed wing extending from the left side of the elongated fuselage;

    a left tilt wing attached at a first side to a free end of the left fixed wing, the left tilt wing being rotatable in a range of 0-135 degrees about the lateral axis of the multi-mode unmanned aerial vehicle;

    a left duct attached to a second side of the left tilt wing;

    a left winglet attached to the left duct opposite to the left tilt wing;

    a tilt tail located within the curved guide slot at the rear end of the elongated fuselage, the tilt tail being rotatable in a range of 0-90 degrees about the lateral axis of the multi-mode unmanned aerial vehicle and within the curved guide slot, wherein the tilt tail includes a vertical stabilizer, a right horizontal stabilizer, and a left horizontal stabilizer;

    a rear duct attached to the tilt tail;

    a tilting mechanism includinga first set of servo actuators connected via a bevel gear group to a right and left set of horizontally-oriented shafts integrated with the right tilt wing and the left tilt wing, respectively,a set of pulleys connected to the right and left set of horizontally-oriented shafts, anda second set of servo actuators connected to a rear shaft integrated with the tilt tail; and

    an integrated autonomous flight control system including processing circuitry configured to control flight and navigation of the multi-mode unmanned aerial vehicle and to control the tilting mechanism.

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