An aircraft, comprising: a fuselage; a wing coupled to the fuselage at a wing-fuselage joint, wherein the wing generates a lifting force when air passes over the wing; and a strut coupled to the fuselage at a strut-fuselage joint and coupled to the wing at a strut-wing joint, the strut-fuselage joint located below and at least partially aft of the wing-fuselage joint, wherein the strut comprises an A-frame structure having a strut front spar and a strut rear spar, each having a strut spar inboard end and a strut spar outboard end, wherein the strut spar outboard ends converge at the strut-wing joint; wherein: the lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint; the strut front spar and the strut rear spar are respectively configured to carry tension load and compression load in response to the vertical moment induced by the lifting force; the strut spar inboard ends are spaced apart from each other at the strut-fuselage joint, and are configured to transfer the tension load and the compression load into the fuselage at a strut front attach point and a strut rear attach point of the strut-fuselage joint; and at least one of the wing and the strut has a structural arrangement configured to counteract the vertical moment. a fuselage; a wing coupled to the fuselage at a wing-fuselage joint, wherein the wing generates a lifting force when air passes over the wing; and a strut coupled to the fuselage at a strut-fuselage joint and coupled to the wing at a strut-wing joint, the strut-fuselage joint located below and at least partially aft of the wing-fuselage joint, wherein the strut comprises an A-frame structure having a strut front spar and a strut rear spar, each having a strut spar inboard end and a strut spar outboard end, wherein the strut spar outboard ends converge at the strut-wing joint; wherein: the lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint; the strut front spar and the strut rear spar are respectively configured to carry tension load and compression load in response to the vertical moment induced by the lifting force; the strut spar inboard ends are spaced apart from each other at the strut-fuselage joint, and are configured to transfer the tension load and the compression load into the fuselage at a strut front attach point and a strut rear attach point of the strut-fuselage joint; and at least one of the wing and the strut has a structural arrangement configured to counteract the vertical moment. the lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint; the strut front spar and the strut rear spar are respectively configured to carry tension load and compression load in response to the vertical moment induced by the lifting force; the strut spar inboard ends are spaced apart from each other at the strut-fuselage joint, and are configured to transfer the tension load and the compression load into the fuselage at a strut front attach point and a strut rear attach point of the strut-fuselage joint; and at least one of the wing and the strut has a structural arrangement configured to counteract the vertical moment.