US 12,420,907 B2
Fixed-wing control mechanism
Fahrettin Ozturk, Kahramankazan/Ankara (TR); and Mustafa Murat, Kahramankazan/Ankara (TR)
Assigned to TUSAS—TURK HAVACILIK VE UZAY SANAYII ANONIM SIRKETI, Kahramankazan/Ankara (TR)
Appl. No. 18/694,337
Filed by TUSAS—TURK HAVACILIK VE UZAY SANAYII ANONIM SIRKETI, Kahramankazan/Ankara (TR)
PCT Filed Jun. 28, 2022, PCT No. PCT/TR2022/050673
§ 371(c)(1), (2) Date Mar. 21, 2024,
PCT Pub. No. WO2023/055319, PCT Pub. Date Apr. 6, 2023.
Claims priority of application No. 2021/015233 (TR), filed on Sep. 29, 2021.
Prior Publication US 2024/0400189 A1, Dec. 5, 2024
Int. Cl. B64C 3/38 (2006.01)
CPC B64C 3/385 (2013.01) 12 Claims
OG exemplary drawing
 
1. An air and/or space vehicle comprising:
at least one fuselage (2) located in an air and/or space vehicle;
at least one structural part (3) in the fuselage (2) which supports an inner surface of the fuselage (2) in terms of strength;
a plurality of beams (5) which are located in wings (4) to provide rigidity to the wings (4);
a plurality of openings (6) located on the fuselage (2) facing each other which allow the plurality of beams (5) to extend into the fuselage (2);
at least one actuator (7) located in the fuselage (2) for actuating the plurality of beams (5), a fixed-wing control mechanism (1), which comprises;
a plurality of carrier elements (8) located on the fuselage (2) facing each other, in a same axis with the plurality of beams (5), so that the plurality of beams (5) are mounted thereon, wherein when the plurality of carrier elements (8) are triggered by the actuator (7), one of the wings (4) is moved at an angle predetermined by a user and to be brought to an incidence angle of that one wing (4), thereby changing lift and drag forces;
a first wing (401) and a second wing (402) among the wings (4) extending outwardly from the fuselage (2) and coaxial with each other;
a first beam (501) among the plurality of beams (5) located in the first wing (401) and a second beam (502) among the plurality of beams (5) located in the the second wing (402), the first beam (501) and the second beam (502) extending towards each other to have at least partially a distance therebetween, and detachably mounted on one of the plurality of carrier elements (8);
at least one sealing element (18) which is located on the fuselage (2), form-fitting with one of the plurality of openings (6), thus substantially preventing a flow of liquid which may leak into the fuselage (2) through the plurality of beams (5);
the fixed-wing control mechanism (1), which comprises at least one bearing element (9) located on the structural part (3) facing the opening (6), and allowing rotational movement of the structural part (3); and
a first carrier element (801) and a second carrier element (802) located in the fuselage (2) facing each other, on which the plurality of beams (5) are mounted, a plurality of adapters (10) located in the fuselage (2) facing each other, which are mounted detachably on the plurality of carrier elements (8) so as to remain between the bearing element (9) and the first carrier element (801) and the second carrier element (802), wherein the plurality of adapters (10), when triggered by the actuator (7), allow the first carrier element (801) and the second carrier element (802) are moved simultaneously.