In order to reduce wing root bending moment of high aspect ratio unmanned vehicle, bi-fuselage and stay bar methods were used. The bending moment and deflection along the wings were calculated and analyzed. The results show that the two methods can greatly reduce the wing’s bending moment as well as deflection. Bi-fuselage’s reduction of moment can reach 24% of the original mono-fuselage and stay bar can reduce to 20%. The deflection reductions are significant too. The instability characteristics of the compressed wings with stay bars were analyzed and the result shows that the wings will not lose stability under the assuming parameter.