US 12,434,828 B2
Air vehicle and method of operation of air vehicle
Ehud Baharav, Ramat Gan (IL); and Avner Volovick, Petach Tikva (IL)
Assigned to ISRAEL AEROSPACE INDUSTRIES LTD., Lod (IL)
Filed by ISRAEL AEROSPACE INDUSTRIES LTD., Lod (IL)
Filed on Feb. 13, 2024, as Appl. No. 18/440,535.
Application 18/440,535 is a continuation of application No. 17/296,427, granted, now 11,932,386, previously published as PCT/IL2019/051267, filed on Nov. 20, 2019.
Claims priority of application No. 263301 (IL), filed on Nov. 25, 2018.
Prior Publication US 2024/0217655 A1, Jul. 4, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. B64C 29/00 (2006.01); B64C 39/04 (2006.01); B64D 27/34 (2024.01); B64D 31/16 (2024.01)
CPC B64C 29/0033 (2013.01) [B64C 29/0025 (2013.01); B64C 39/04 (2013.01); B64D 27/34 (2024.01); B64D 31/16 (2024.01)] 21 Claims
OG exemplary drawing
 
1. An air vehicle configured for being operated in vectored flight mode and in powered aerodynamic flight mode, the air vehicle having a longitudinal axis and center of gravity, and comprising:
an airframe comprising aerodynamic lift-generating fixed wings for enabling operation of said air vehicle in said powered aerodynamic flight mode;
a propulsion system, configured for providing propulsion to said air vehicle in said powered aerodynamic flight mode and said vectored flight mode, and for providing stability and control to said air vehicle in said vectored flight mode, and comprising a set of first propulsion units and a set of second propulsion units, wherein:
said set of first propulsion units comprising at least three said first propulsion units, said first propulsion units being arranged in polygonal arrangement with respect to the airframe, said polygonal arrangement enclosing the center of gravity when the air vehicle is viewed in plan view;
said first propulsion units being non-pivotably attached with respect to said airframe to provide a fixed vertical thrust vector with respect thereto,
said set of first propulsion units configured to provide an aggregate vertical thrust sufficient for providing said vectored flight mode;
said set of second propulsion units comprising at least three said second propulsion units, each said second propulsion unit being arranged in spaced relationship with respect to the center of gravity when viewed in plan view such that said set of second propulsion units comprises one or more forward mounted said second propulsion units and correspondingly one or more aft mounted said second propulsion units, said set of second propulsion units being further configured to provide vectored control moments to the air vehicle in three rotational degrees of freedom;
said second propulsion units each being pivotably attached with respect to said airframe to enable angular displacement of a respective thrust vector at least between a respective vertical position and a respective horizontal position with respect thereto,
said set of second propulsion units configured to provide at least an aggregate horizontal thrust sufficient for providing said powered aerodynamic flight mode;
wherein the air vehicle is further configured for enabling the one or more forward mounted second propulsion units to be pivoted independently of the correspondingly one or more aft mounted second propulsion units;
wherein the air vehicle is further configured for operating in transition mode when transitioning between said vectored flight mode and said powered aerodynamic flight mode; and
wherein the air vehicle is configured to operate in said transition mode, wherein the aft mounted second propulsion units are operated to provide control moments, and the forward mounted second propulsion units are operated to provide horizontal thrust vectors; and
wherein the air vehicle is configured to operate in said transition mode, wherein for at least a portion of said transition mode, the aft mounted second propulsion units are pivoted to respective vertical positions and operated thereat to provide control moments, and wherein the forward mounted second propulsion units are partially pivoted towards the respective horizontal positions and operated thereat to provide respective horizontal thrust components for forward propulsion.