The invention is applicable to the technical field of rocket control, and provides an omni-directional launch control method and device for a carrier rocket as well as computer equipment and a storagemedium. The method comprises the following steps that an initial attitude angle is acquired, moreover, an initial quaternion is calculated, wherein the initial attitude angle comprises an initial rolling angle; a real-time angle increment of the current control period is acquired, and the real-time quaternion is calculated; a standard quaternion is calculated according to the initial rolling angle; an attitude angle deviation is calculated on the basis of the real-time quaternion and the standard quaternion, and a target attitude control signal is obtained according to the attitude angle deviation and is output to an execution mechanism. The initial quaternion is calculated through the initial attitude angle to obtain the standard quaternion and the real-time quaternion, the attitude angle deviation is obtained through calculation and is resolved to obtain the target attitude control signal for controlling the rocket, omni-directional launch control of the rocket is realized without rotating an indexing mechanism, the indexing mechanism is omitted, so that the cost is saved, the time for rotating the rocket for alignment is shortened, and the rapid response capability and the automatic level of the rocket are improved.