One embodiment of the invention discloses a low-orbit satellite double-shaft solar wing control and energy balance coupling calculation method. The method comprises the steps of obtaining solar wing theoretical output power Ps, a beta angle, satellite average power consumption P (flat), satellite illumination area total time Tg, satellite orbit period total time T sum and solar wing shielding area S, wherein the angle beta periodically changes in a range of [-90 degrees, 90 degrees], traversing the angle beta in the range of [-90 degrees, 90 degrees], calculating to obtain an optimal solution of the energy margin, obtaining a control angle a of the solar wing under the condition, combining the a with a coordinate system definition of the solar wing, and proposing a control strategy corresponding to the solar wing under the condition of different angles beta. The average power consumption of the satellite is calculated in a segmented mode in an orbit period, the on-orbit energy balance condition of the satellite is accurately calculated through a program in combination with an on-orbit control strategy of the solar wing, and an accurate basis is provided for design of the solar wing and a storage battery.