A low-disturbance dual-gimbal flywheel for spacecraft attitude control, comprising a spatial parallel mechanism, one single wheel body, one single high-speed motor, a bearing, and a housing, wherein the wheel body, the high-speed motor and the bearing together form a rotor assembly; and wherein the spatial parallel mechanism comprises n drive branch chains, a static base and a movable platform having at least two rotational degrees of freedom; wherein the bearing is mounted at a center of the wheel body, a rotor of the high-speed motor is mounted on the bearing; the bearing and a stator of the high-speed motor are together mounted on the movable platform, and the wheel body, the stator and rotor of the high-speed motor, and the bearing are coaxially mounted; the spatial parallel mechanism, the wheel body, the high-speed motor and bearing are mounted inside the housing by means of a port of the static base; a lug outside the housing is connectable to an outer spacecraft deck; the housing encloses a maximum moving range of the wheel body; wherein the spatial parallel mechanism controls movement of the movable platform through movement of the n drive branch chains, wherein n is a positive integer equal to or larger than 3; wherein the static base comprises a platform and n legs, and the platform is supported by the n legs evenly distributed in a circumferential direction of the platform at a bottom of the platform; wherein the low-disturbance dual-gimbal flywheel is configured to achieve continuous angular maneuvering of the rotor assembly angular momentum vector in a local area through continuous rotation of the movable platform in the local area, wherein a direction of the rotor assembly angular momentum vector is changed and a gyroscopic moment is output, and to change the magnitude of the angular momentum vector through a speed change of the high-speed motor, wherein a reaction moment is output; wherein the gyroscopic moment and the reaction moment can be used separately or together as an attitude control moment of the spacecraft. a spatial parallel mechanism, one single wheel body, one single high-speed motor, a bearing, and a housing, wherein the wheel body, the high-speed motor and the bearing together form a rotor assembly; and wherein the spatial parallel mechanism comprises n drive branch chains, a static base and a movable platform having at least two rotational degrees of freedom; wherein the bearing is mounted at a center of the wheel body, a rotor of the high-speed motor is mounted on the bearing; the bearing and a stator of the high-speed motor are together mounted on the movable platform, and the wheel body, the stator and rotor of the high-speed motor, and the bearing are coaxially mounted; the spatial parallel mechanism, the wheel body, the high-speed motor and bearing are mounted inside the housing by means of a port of the static base; a lug outside the housing is connectable to an outer spacecraft deck; the housing encloses a maximum moving range of the wheel body; wherein the spatial parallel mechanism controls movement of the movable platform through movement of the n drive branch chains, wherein n is a positive integer equal to or larger than 3; wherein the static base comprises a platform and n legs, and the platform is supported by the n legs evenly distributed in a circumferential direction of the platform at a bottom of the platform; wherein the low-disturbance dual-gimbal flywheel is configured to achieve continuous angular maneuvering of the rotor assembly angular momentum vector in a local area through continuous rotation of the movable platform in the local area, wherein a direction of the rotor assembly angular momentum vector is changed and a gyroscopic moment is output, and to change the magnitude of the angular momentum vector through a speed change of the high-speed motor, wherein a reaction moment is output; wherein the gyroscopic moment and the reaction moment can be used separately or together as an attitude control moment of the spacecraft.