A design method of grid rudder missile for reducing pressure center variation

Abstract

The invention discloses a design method applied to a guided missile with grid fins and used for reducing the pressure center variation. The design method comprises the following steps that step1, the general parameters, general indexes and design constraints of the guided missile are determined; step2, the shape of the grid fin surfaces of the guided missile is determined; step3, strake wings are additionally arranged at the positions, on the front sides of the grid fins, of the body of the guided missile, and the geometric parameters of the strake wings are determined; step4, on the premise that the geometric parameters of the strake wings are invariable, the distance d between the strake wings and the folded grid fin surfaces is determined. According to the design method, the strake wings are additionally arranged on the front sides of the grid fins, and meanwhile design is performed according to the geometric parameters of the strake wings, the positions of the strake wings on the body of the guided missile and the maximum expansion length of the strake wings, so that the pressure center variation is well reduced in the actual use of the guided missile with the grid fins, and the problem that from the folded state to the unfolded state of the grid fin surfaces of the guided missile with the grid fins, the pressure center variation of the whole guided missile is too large, and consequently controllability and stability are difficult to coordinate is solved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a design method for a missile with a grid rudder for reducing the amount of pressure center variation. Background technique [0002] The grid rudder rudder surface in the missile is a multi-lift surface system formed by many thin grid walls embedded in the frame. It has better lift performance in a given space, is easy to fold, and has a small hinge moment. Therefore, a lot of research has been carried out on the application of grid rudders at home and abroad. In the existing technology, such as figure 1 , 2 , as shown in 3, figure 1 It is a schematic diagram of the grid rudder rudder surface in the folded state on the missile with grid rudder in the prior art, figure 2 It is a schematic diagram of the positional relationship between the grid rudder and the outer envelope geometric limit of the missile body when the grid rudder surface of the missile with grid rudder is fol...

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a design method for missiles with grid rudders used to reduce the amount of pressure center variation; The position of the fins on the missile body and the design of the maximum length of the fins allow the missile with grid rudders to obtain a good effect of reducing the pressure center change in actual use, and solve the problem of the center grid of the missile with grid rudders. When the grid rudder surface changes from the folded state to the unfolded state, the center of pressure of the missile's full bomb changes too much, which brings about the problem that the control and stability characteristics are difficult to coordinate

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